NASA Student Launch Critical Design Review Report Summary

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Critical Design Review Report
NASA Student Launch
Mini-MAV Competition
2014-15
1000 W. Foothill Blvd.
Glendora, CA 91741
Project Λscension
Jan 15, 2015

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Contents
General Information........................................................................................................................ 8
School Information ..................................................................................................................... 8
Adult Educators........................................................................................................................... 8
Safety Officer.............................................................................................................................. 8
Student Team Leader .................................................................................................................. 8
Team Members and Proposed Duties ......................................................................................... 8
NAR/ TRA Sections ................................................................................................................... 9
I. Summary of CDR Report .......................................................................................................... 10
Team Summary......................................................................................................................... 10
Launch Vehicle Summary......................................................................................................... 10
AGSE/ Payload Summary......................................................................................................... 10
II. Changes made since PDR......................................................................................................... 11
Changes to Vehicle Criteria ...................................................................................................... 11
Changes to AGSE/ Payload Criteria ......................................................................................... 11
Changes to Project Plan ............................................................................................................ 11
PDR Feedback........................................................................................................................... 11
III. Vehicle Criteria....................................................................................................................... 13
Design and Verification of Launch Vehicle ............................................................................. 13
Flight Reliability and Confidence............................................................................................. 13
Mission Statement................................................................................................................. 13
Requirements and Mission Success Criteria......................................................................... 13
Major Milestone Schedule .................................................................................................... 14
Design Review ...................................................................................................................... 15
System Level Functional Requirements ............................................................................... 25
Workmanship as it Relates to Mission Success.................................................................... 32
Additional Planned Component, Functional, and Static Testing .......................................... 33
Manufacturing/ Assembly Status and Plans ......................................................................... 34
Design Integrity..................................................................................................................... 37
Safety and Failure Analysis .................................................................................................. 41
Subscale Flight Results ............................................................................................................. 43
Flight Data............................................................................................................................. 43

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Predicted and Actual Flight Data Discussion ....................................................................... 44
Impacts on Full-Scale Launch Vehicle ................................................................................. 46
Recovery Subsystem................................................................................................................. 46
Parachute, Harnesses, Bulkheads, and Attachment Hardware.............................................. 47
Electrical Components .......................................................................................................... 49
Drawings, Sketches, Block Diagrams, and Electrical Schematics ....................................... 49
Kinetic Energy at Significant Phases of the Mission............................................................ 50
Test Results........................................................................................................................... 50
Safety and Failure Analysis .................................................................................................. 51
Mission Performance Predictions ............................................................................................. 52
Mission Performance Criteria ............................................................................................... 52
Flight Profile Simulations ..................................................................................................... 52
Scale Modeling Results......................................................................................................... 55
Stability Margin .................................................................................................................... 55
AGSE/ Payload Integration....................................................................................................... 56
Ease of Integration.................................................................................................................... 58
Integration Plan..................................................................................................................... 58
Compatibility of Elements .................................................................................................... 60
Simplicity of Integration Procedure...................................................................................... 62
Changes to AGSE/ Payload .................................................................................................. 63
Launch Concerns and Operation Procedures............................................................................ 63
Final Assembly and Launch Procedures............................................................................... 63
Safety and Environment (Vehicle and AGSE/ Payload) .......................................................... 71
Updated Preliminary Analysis of Failure Modes.................................................................. 71
Updated Listing of Personnel Hazards ................................................................................. 75
Environmental Concerns....................................................................................................... 78
IV. AGSE/ Payload Criteria.......................................................................................................... 80
Testing and Design of AGSE/ Payload Equipment .................................................................. 80
Design Review ...................................................................................................................... 80
Planned Component, Functional, and Static Testing .......................................................... 139
Manufacturing/ Assembly Status and Plans ....................................................................... 142
Integration Plan................................................................................................................... 145

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Precision of Instrumentation and Repeatability of Measurement ....................................... 149
AGSE/ Payload electronics................................................................................................. 150
Safety and Failure Analysis ................................................................................................ 158
AGSE/ Payload Concept Features and Definition .................................................................. 159
Creativity and Originality ................................................................................................... 159
Uniqueness or Significance................................................................................................. 159
Suitable Level of Challenge................................................................................................ 159
Science Value.......................................................................................................................... 159
AGSE/ Payload Objectives and Success Criteria ............................................................... 159
V. Project Plan ............................................................................................................................ 161
Status of Activities and Schedule ........................................................................................... 161
Budget Plan......................................................................................................................... 161
Funding Plan....................................................................................................................... 164
Timeline .............................................................................................................................. 165
Educational Engagement..................................................................................................... 167
VI. Conclusion............................................................................................................................ 170
Appendix A: Citrus College Profile........................................................................................... 171
Figure 1: Organizational flow chart................................................................................................ 9
Figure 2: Rocket exploded view ................................................................................................... 15
Figure 3: Side and bottom view of the rocket............................................................................... 16
Figure 4: Rocket booster section................................................................................................... 17
Figure 5: Rocket middle section ................................................................................................... 18
Figure 6: Main parachute piston ................................................................................................... 19
Figure 7: Payload containment bay and nose cone exploded view .............................................. 20
Figure 8: Rendering of the payload containment device .............................................................. 21
Figure 9: Description of nose cone and payload containment system.......................................... 22
Figure 10: Piston Ejection Ground Test....................................................................................... 23
Figure 11: Aerotech K1275R Thrust Curve................................................................................. 25
Figure 12: AeroPack Retainer....................................................................................................... 40
Figure 13: RockSim Design of the 2/3 Subscale Vehicle ............................................................ 43
Figure 14: The Rocket Owls with the Subscale Launch Vehicle ................................................ 45
Figure 15: The Subscale Altimeter Bay with Redundant RRC2+ Altimeters ............................. 45
Figure 16: The Subscale Vehicle under Two Parachutes ............................................................ 46
Figure 17: Recovery Deployment................................................................................................ 47
Figure 18: Electrical schematics for the main recovery system. .................................................. 49
Figure 19: Electrical schematics for the payload recovery system. .............................................. 50

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Figure 20: Simulated Drag, Velocity, and Altitude ..................................................................... 52
Figure 21: Flight profile simulations ............................................................................................ 53
Figure 22: Stability Diagram ....................................................................................................... 55
Figure 23: Description of payload containment and nose cone section........................................ 56
Figure 24: Rendering of the Payload Containment Device .......................................................... 57
Figure 25: Dimensional drawing of the payload containment device. ......................................... 58
Figure 26: The integration of the payload containment device into the launch vehicle. .............. 60
Figure 27: Side view and section view of the payload containment device. ................................ 62
Figure 28: AGSE Isometric System Overview............................................................................. 82
Figure 29: AGSE Exploded System Overview............................................................................. 83
Figure 30: AGSE System Master Switches .................................................................................. 84
Figure 31: Body Overview............................................................................................................ 88
Figure 32: Chassis Dimensions..................................................................................................... 89
Figure 33: Chassis Design ............................................................................................................ 90
Figure 34: Chassis Dimensions..................................................................................................... 91
Figure 35: Chassis Lid Design...................................................................................................... 92
Figure 36: Chassis Lid Dimensions .............................................................................................. 93
Figure 37: Rocker Bogie Overview .............................................................................................. 94
Figure 38: Center Bogie Design ................................................................................................... 95
Figure 39: Front Bogie Design ..................................................................................................... 96
Figure 40: Front Bogie Dimensions.............................................................................................. 97
Figure 41: Rear Bogie Dimensions............................................................................................... 98
Figure 42: Rear Bogie Design....................................................................................................... 99
Figure 43: Camera Mount Shaft Design ..................................................................................... 100
Figure 44: Camera Mount Shaft Dimensions ............................................................................. 101
Figure 45: Camera Mount Shaft Base Design ............................................................................ 102
Figure 46: Camera Mount Shaft Base Dimensions..................................................................... 103
Figure 47: Wheel Assembly Design Overview .......................................................................... 104
Figure 48: Servo Bracket Design................................................................................................ 105
Figure 49: Servo Bracket Dimensions ........................................................................................ 106
Figure 50: Servo Pivot Bracket Design ...................................................................................... 107
Figure 51: Servo Pivot Bracket Dimensions............................................................................... 108
Figure 52: Motor Mount Design................................................................................................. 109
Figure 53: Motor Mount Dimensions ......................................................................................... 110
Figure 54: Pivot Shaft Washer Dimensions................................................................................ 111
Figure 55: Pivot Shaft Washer Dimensions................................................................................ 112
Figure 56: Wheel Spindle Design............................................................................................... 113
Figure 57: Wheel Spindle Dimensions ....................................................................................... 114
Figure 58: Wheel Hub Designs................................................................................................... 115
Figure 59: Wheel Hub Dimensions............................................................................................. 116
Figure 60: Wheel Design ............................................................................................................ 117
Figure 61: Wheel Dimensions .................................................................................................... 118
Figure 62: Mouth of Chassis Prototype ...................................................................................... 123

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Figure 63: Fully assembled AL5D robotic arm .......................................................................... 124
Figure 64: Elbow Servo (Left) and Base Servo (Right) Bracket Mounting ............................... 124
Figure 65: HS-422 Gripper (left) and Wrist Servo (right).......................................................... 125
Figure 66: Rocker Bogie Failure................................................................................................. 127
Figure 67: Pan/ Tilt servo test schematic.................................................................................... 129
Figure 68: Wiring Setup for Pan-Tilt Servo Test........................................................................ 130
Figure 69: PixyMon Calibration and Testing ............................................................................. 131
Figure 70: Overall AGSE Electrical Schematic.......................................................................... 150
Figure 71: AGSE Overall Block Diagram.................................................................................. 151
Figure 72: Pixy Camera Block Diagram..................................................................................... 152
Figure 73: Robotic Arm Block Diagram .................................................................................... 152
Figure 74: Allpower Power Bank ............................................................................................... 153
Figure 75: Single 4.2 Volt Battery Testing ................................................................................. 154
Figure 76: Series Circuit Using Both Batteries........................................................................... 155
Figure 77: Master and Pause Switch Locations.......................................................................... 156
Figure 78: Planned Budget Distribution ..................................................................................... 163
Figure 79: NASA Student Launch Timeline .............................................................................. 165
Figure 80: AGSE and Rocket Construction Timeline ................................................................ 166
Figure 81: Outreach Timeline..................................................................................................... 166
Table 1: Team Member Duties ...................................................................................................... 8
Table 2: Major Milestone Schedule............................................................................................. 14
Table 3: Piston Ejection Test Results ........................................................................................... 24
Table 4: Final Motor Selection ..................................................................................................... 24
Table 5: Launch Vehicle Requirements and Verification............................................................ 26
Table 6: Recovery Requirements and Verification...................................................................... 30
Table 7: Remaining Manufacturing and Assembly Schedule....................................................... 34
Table 8: Vehicle Subsystem Parts and Manufacturing Processes ............................................... 35
Table 9: Vehicle Subsystem Parts and Manufacturing Processes ............................................... 38
Table 10: Vehicle Weight, Altitude, and Rail Velocity............................................................... 41
Table 11: Vehicle Failure Modes.................................................................................................. 41
Table 12: Propulsion Failure Modes............................................................................................. 42
Table 13: Recovery Subsystem Components .............................................................................. 47
Table 14: Kinetic Energy of each Rocket Section ....................................................................... 50
Table 15: Recovery Failure Modes............................................................................................... 51
Table 16: Drift from Launch Pad (all sections) ........................................................................... 55
Table 17: Internal Interfaces ......................................................................................................... 61
Table 18: Vehicle Failure Modes.................................................................................................. 71
Table 19: AGSE Failure Analysis................................................................................................. 72
Table 20: Propulsion Failure Modes............................................................................................. 73
Table 21: Recovery Failure Modes............................................................................................... 74
Table 22: Tripoli minimum distance table .................................................................................... 75
Table 23: Tool Safety.................................................................................................................... 76

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Table 24: Environmental Hazards................................................................................................. 78
Table 25: Project Risk Quantitative Assessment .......................................................................... 79
Table 26: Project Risk Qualitative Assessment ............................................................................ 79
Table 27: AGSE Subsystem Overview......................................................................................... 81
Table 28: Body Subsystem Component Overview....................................................................... 85
Table 29: Camera Subsystem Component Overview ................................................................. 119
Table 30: Payload Retrieval Subsystem Component Overview ................................................. 121
Table 31: Structural Capacity Summary for the Body Subsystem ............................................. 126
Table 32: Test Summary for Body Components ........................................................................ 127
Table 33: Test Summary for Camera Subsystem Components .................................................. 128
Table 34: AGSE Requirement Verifications .............................................................................. 133
Table 35: AGSE Requirements................................................................................................... 136
Table 36: Test Summary for Body Components ........................................................................ 139
Table 37: Test Summary for Camera Subsystem Components .................................................. 140
Table 38: Test Summary for Payload Retrieval Subsystem Components .................................. 141
Table 39: Component Level Integration..................................................................................... 147
Table 40: Camera Subsystem Instrumentation Performance ...................................................... 149
Table 41: Payload Retrieval subsystem Instrumentation Performance ...................................... 149
Table 42: Testing Plans for Safety Related AGSE Electronics .................................................. 157
Table 43: AGSE Failure Analysis............................................................................................... 158
Table 44: Scientific Objectives & Success Criteria .................................................................... 159
Table 45: Budget......................................................................................................................... 161
Table 46: Funding Plan............................................................................................................... 164

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GeneralInformation
School Information
More information on Citrus College can be found in Appendix A
Adult Educators
Lucia Riderer Rick Maschek
Physics Faculty/ Team Advisor Director, Sugar Shot to Space/ Team Mentor
lriderer@citruscollege.edu rickmaschek@rocketmail.com
(626) 643-0014 (760) 953-0011
Safety Officer
Alex
Kemnitz714@gmail.com
(626) 643-0014
Student Team Leader
Aaron
Aaronbunch713@gmail.com
(509) 592-3328
Team Members and Proposed Duties
The 2014-15 Citrus College NASA Student Launch team, the ‘Rocket Owls’, consists of five
students, one faculty team advisor, and a team mentor. The student members’ proposed duties
are listed in Table 1 below.
Table 1: Team Member Duties
Team Member Title Proposed Duties
Aaron Team Leader
Oversight, coordination, and planning
Assistance with all team member duties
Lead rocket design and construction
Alex Safety Officer Implementation of Safety Plan
Brian Robotics Specialist Lead AGSE design and construction
John Payload Specialist
Oversight and coordination of payload
acquisition, retention, and ejection systems
Joseph Outreach Officer
Educational Engagement
Social Media, Website maintenance

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Figure 1: Organizational flow chart
NAR/ TRA Sections
For launch assistance, mentoring, and review, the Rocket Owls will associate with the Rocketry
Organization of California (ROC) (NAR Section #538, Tripoli Prefecture #48) and the Mojave
Desert Advanced Rocket Society (MDARS) (Tripoli Prefecture #37).

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I. Summary of CDR Report
Team Summary
Citrus College Rocket Owls
Mailing address: Team Mentor:
Lucia Riderer Rick Maschek
Physics Department TRA #11388, Cert. Level 2
Citrus College
1000 W. Foothill Blvd.
Glendora, CA 91741
Launch Vehicle Summary
 Length: 112.5 in
 Diameter: 6 in
 Mass (without motor): 8.9 kg
 Weight (without motor): 87.2 N/19.6 lb
 Motor: AeroTech K1275R
 Recovery system: Redundant Missile Works RRC2+ altimeters will deploy a 30”
elliptical drogue parachute at apogee, and a 72” elliptical main parachute at 800 ft (AGL).
A separate pair of RRC2+ altimeters will eject the nosecone and attached payload bay at
1000 ft (AGL), which will descend untethered under its own 42” elliptical parachute.
 The milestone review flysheet is a separate document
AGSE/ Payload Summary
Title: Project scension
A six-wheeled rover with rocker-bogie suspension will autonomously:
 identify and navigate as needed to a payload lying on the ground
 pick up the payload with a robotic arm
 identify and navigate as needed to the horizontally positioned rocket
 insert the payload into the rocket
The team or other personnel will manually:
 move the rocket to a vertical launch position
 install the igniter
 launch the rocket

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II. Changes made since PDR
Changes to Vehicle Criteria
Three changes have been made to the vehicle criteria since the PDR:
1. The motor has been upgraded to the AeroTech K1275R, after the subscale test flight indicated
that RockSim likely overestimates the altitude achievable by the K1100T.
2. Missile Works RRC2+ altimeters will be used instead of the RRC3 model. The extra features
of the RRC3 (e.g. the third deployment output) are not needed.
3. The main altimeter bay will be separated into two compartments by a central bulkhead
covered with aluminum foil. The deployment altimeters on one side will be shielded from the
GPS transmitter on the other side.
Changes to AGSE/ Payload Criteria
1. The laser ranging system has been removed and the Pixy Camera will operate on its own.
2. The Arduino Uno has been replaced with BeagleBone which is coded in python.
3. The center bogies have been redesigned to be adjustable in the placement on the body of the
AGSE.
4. The wheel has been redesigned to be a triacontagon (30 sided polygon).
5. The position of the robotic arm has been changed from the top to the front mouth of the body.
Changes to Project Plan
1. The budget plan and funding plan have been updated to more accurately represent the
monetary status of the team.
PDR Feedback
1. The power plant idea is very creative!
Thanks!
2. Can the team explain why it chose a 6’ rail? The motor provided is very aggressive, but
the forward rail button does not have much room on the rail.
The team has adjusted the rail size to 8’ in order to give the forward rail button a greater distance
before leaving the rail.
3. What is the location of the GPS transmitter in regards to the recovery electronics? What
kind of EMI shielding will be used?
The GPS transmitter for both sections will be in a separate compartment from the recovery
altimeters. The TeleGPS will be in a compartment directly below the altimeters, but there will be

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an aluminum plate between them to shield the altimeters from electromagnetic waves. The EM-
506 GPS will be separated by a much greater distance and will still be in a separate
compartment.
4. The review team noticed that the eye-bolts being used are open. Will the team weld these
shut, or consider forged eye-bolts/u-bolts? Open eye-bolts have a lower failure stress.
The eye-bolts have been replaced with u-bolts.
5. Is there anything preventing the piston from moving backwards?
A piece of coupler will be epoxied in the body tube. The piston will be resting on this coupler
during flight and a black powder charge from the opposite side will not be able to push it
backwards
6. Traditionally, pistons will push the parachute out, but this design has the piston pulling
the chute out. Can the team explain why this configuration is chosen?
This configuration was chosen to keep the main parachute and the payload parachute separate.
There is less chance for the two parachutes to tangle in some way. The system has been tested in
the subscale and shows proof of concept for this setup.
7. How is the camera imaging system interacting with the laser ranging system?
The laser ranging system has been removed and the camera imaging system will act on its own.
The AGSE will use the angle of the camera and the position of the object in the image to
determine how far it is. More details can be found in the design review for the AGSE.
8. Is there anything hardcoded as to where the rocket is, or will the AGSE have to find
everything?
The AGSE will have to figure things out on its own. The coding will allow the AGSE to
determine what adjustments must be made to perform its operations, but positions of objects will
not be hardcoded into the AGSE. It is entirely responsive to its environment.

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III. Vehicle Criteria
Designand Verification of Launch Vehicle
Flight Reliability and Confidence
MissionStatement
Project Λscension will use autonomous ground support equipment (AGSE) to retrieve a 4 oz.
payload from the ground and secure it within a launch vehicle. The launch vehicle will carry the
payload to an altitude of 3000 ft AGL. Upon descending to 1000 ft AGL, the payload bay will
be ejected from the launch vehicle, and descend under its own parachute to the ground to be
recovered.
Requirements and MissionSuccess Criteria
In addition to meeting all NASA mission requirements (addressed below), mission success
requires that the AGSE:
 identify the payload on the ground
 retrieve the payload
 insert the payload into the launch vehicle
The launch vehicle must:
 be aerodynamically stable
 reach apogee as close as possible to 3000 ft AGL
 deploy the drogue parachute at apogee
 eject the payload bay at 1000 ft AGL
 deploy the main parachute at 800 ft AGL
 land safely and undamaged
 transmit its location so that it can be retrieved
The payload bay must:
 secure the payload
 deploy its parachute when it is ejected at 1000 ft AGL
 land safely and undamaged
 transmit its location so that it can be retrieved

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Major Milestone Schedule
The following table presents the schedule of major milestones for the launch vehicle design,
construction, testing, operations, and reviews.
Table 2: Major Milestone Schedule
Major Milestone Date Status
Proposal Submission 10/6/ 2014 Complete
Notification of Selection 10/17/2014 Complete
Web Presence Established 10/31/2014 Complete
PDR Report, Presentation, Flysheet Submitted 11/5/2014 Complete
PDR Presentation 11/14/2014 Complete
Subscale Launch Vehicle Completed 12/18/2014 Complete
Subscale Ground Testing 12/19/2014 Complete
Subscale Test Flight 12/20/2014 Complete
Piston Parachute Deployment Testing 1/9/2015 Complete
CDR Report, Presentation, Flysheet Submitted 1/15/2015 Complete
CDR Presentation 1/26/2015 In Progress
Full Scale Launch Vehicle Completed 1/30/2015 In Progress
Parachute Deployment Ground Testing 2/2/2015 Pending
Payload Retaining System Ground Testing 2/3/2015 Pending
Full Scale Test Flight 2/7/2015 Pending
Back-up Test Flight Date 2/15/2015 If necessary
2nd Back-up Test Flight Date 2/22/2015 If necessary
3rd Back-up Test Flight Date 2/28/2015 If necessary
FRR Report, Presentation, Flysheet Due 3/16/2015 Pending
FRR Presentation TBD Pending
LRR 4/7/2015 Pending
Launch Day 4/10/2015 Pending
PLAR Due 4/29/2015 Pending

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DesignReview
Final Drawings and Specifications
Figure 2: Rocket exploded view

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Figure 3: Side and bottom view of the rocket

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Figure 4: Rocket booster section

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Figure 5: Rocket middle section

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Figure 6: Main parachute piston

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Figure 7: Payload containment bay and nose cone exploded view

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Figure 8: Rendering of the payload containment device

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Figure 9: Description of nose cone and payload containment system

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Final Analysis and Model Results
Final analysis and model results are detailed below in Subscale Flight Results.
Test Results
1. Subscale Test Flight
The subscale test flight is detailed below in Subscale Flight Results.
2. Piston Ejection Mechanism for the Main Parachute
Test Description: The piston ejection mechanism was ground-tested using the middle section of
the 2/3-subscale rocket. Video of the tests is posted on the team web site:
http://amiwa/rocketowls/. The avionics bay rested on the ground, and the attached body tube
(containing the parachute and the piston) was propped up on a cardboard stand as shown in the
following diagram. The ejection charge was detonated with a J-tek electric match connected to a
6-volt lantern battery with 15 ft. of copper wire.
Figure 10: Piston Ejection Ground Test
Design Concerns:
1. Will the piston eject cleanly from the body tube past the sheared nylon pins that held the
ejected payload bay and nosecone?
2. Will the relatively lightweight piston have sufficient momentum to pull the parachute out of
the body tube?
3. Will the parachute be damaged by the ejection charge?

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Test Results:
The test results are summarized in the following table:
Table 3: Piston Ejection Test Results
Trial
Amount of
Black
Powder (g)
Piston Ejected
Cleanly?
Parachute Pulled
from Body Tube?
Parachute
Damaged by
Ejection Charge?
1 1.0 Yes No No
2 1.5 Yes Yes No
Discussion of Test Results:
1. In both trials, the piston ejected cleanly from the body tube. The remains of the two sheared
nylon pins near the opening were no significant obstruction.
2. In the second trial, 1.5 g of black powder gave the piston sufficient momentum to fully and
forcefully deploy the parachute. In the first trial, 1.0 g of black powder ejected the piston, but
the parachute was not pulled from the body tube.
3. In both trials, the parachute and shock cord were undamaged by the ejection charge. A 12-
inch-square Nomex blanket provided sufficient protection from the hot gases.
Conclusions:
The test results show that the proposed piston ejection mechanism can effectively deploy the
main parachute. Further testing will determine the size of the ejection charge required for the
full-scale vehicle.
Final Motor Selection
The following motor has been selected:
Table 4: Final Motor Selection
Make Code Diameter Length Weight
Burn
Time
Total
Impulse
Max
Thrust
AeroTech K1275R 54 mm
569 mm
22.4 in
2061 g
4.54 lbs
1.9 s
2132 N-s
480 lb-s
1558 N
350 lbs
Justification of motor selection:
Rail Exit Velocity: The AeroTech K1275R is an aggressive motor (see the thrust curve below)
that will accelerate the vehicle quickly off the launch pad. RockSim estimates an 8-ft rail exit
velocity between 73 – 83 ft/s, depending on the final mass of the vehicle.
Mass Increase: The K1275R permits up to a 25% mass increase between the CDR and the
competition launch, as explained in the Mass Statement below.

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Altitude: At the present estimated vehicle weight (19.63 lbs), RockSim predicts an altitude of
4300 ft. AGL with this motor. But the subscale test flight (detailed below) leads us to believe
that this overestimates the altitude by 600 ft. or more. Moreover, any mass increase between the
CDR and the competition launch will lower the altitude of the vehicle. If full-scale test flights
significantly over-shoot the 3000 ft. target, ballast can be added to the vehicle.
Figure 11: Aerotech K1275R Thrust Curve
(http://www.rocketreviews.com/k1275-5081.html)
System Level Functional Requirements
The launch vehicle meets all requirements of the Student Launch Statement of Work. The
following tables list each requirement, the design feature that satisfies the requirement, and the
means of verification.

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Table 5: Launch Vehicle Requirements and Verification
Requirement Design Feature Verification
1.1 The vehicle shall deliver
the payload to, but not
exceeding, an apogee altitude
of 3,000 feet above ground
level (AGL).
With an expected vehicle mass
increase of 10 – 20%, the selected
AeroTech K1275R will reach
3000 ft AGL.
Full-scale test
flights
1.2. The vehicle shall carry
one commercially available,
barometric altimeter for
recording the official altitude
used in the competition
scoring.
One of the Missile Works RRC2+
altimeters will record the official
altitude.
Functional Testing
1.2.1. The official scoring
altimeter shall report the
official competition altitude
via a series of beeps to be
checked after the competition
flight.
The Missile Works RRC2+
altimeter reports the altitude via a
series of beeps.
Functional Testing
1.2.2.3. At the launch field,
to aid in determination of the
vehicle’s apogee, all audible
electronics, except for the
official altitude-determining
altimeter shall be capable of
being turned off.
All audible electronics, except for
official scoring altimeter, will be
capable of being turned off.
Functional Testing
1.3. The launch vehicle shall
be designed to be recoverable
and reusable.
Current simulations predict that all
rocket components will be
recovered within 2300 ft. of the
launch pad, and all components
are designed to be reusable.
By inspection, and
functional testing
have a maximum of four (4)
independent sections.
The launch vehicle has three (3)
independent sections.
By inspection
be limited to a single stage.
The launch vehicle has only one
stage.
By inspection

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be capable of being prepared
for flight at the launch site
within 2 hours, from the time
the Federal Aviation
Administration flight waiver
opens.
Flight preparation will be
completed in less than 2 hours. A
checklist will be used to ensure
that flight preparation is efficient
and thorough. The team will have
practiced these operations during
test flights.
Functional testing
be capable of remaining in
launch-ready configuration at
the pad for a minimum of 1
hour without losing the
functionality of any critical
on-board component.
All onboard electronics draw very
little power, and can remain in
launch-ready configuration for
several hours.
Functional testing
be capable of being launched
by a standard 12-volt direct
current firing system.
The AeroTech K1275R is a
commercial, ammonium
perchlorate motor that will ignite
with 12-volt direct current.
Functional testing
use a commercially available
solid motor propulsion
system using ammonium
perchlorate composite
propellant (APCP) which is
approved and certified by the
National Association of
Rocketry (NAR), Tripoli
Rocketry Association (TRA),
and/or the Canadian
Association of Rocketry
(CAR).
The launch vehicle will use a TRA
certified AeroTech K1275R
motor.
By inspection
1.10. The total impulse
provided by a launch vehicle
shall not exceed 5,120
Newton-seconds (L-class).
The launch vehicle will use a K-
class motor, which does not
exceed 5,120 N-s total impulse.
By inspection

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1.13. All teams shall
successfully launch and
recover a subscale model of
their full-scale rocket prior to
CDR. The subscale model
should resemble and perform
as similarly as possible to the
full-scale model, however,
the full-scale shall not be
used as the subscale model.
The team has launched and
recovered a 2/3-scale (4”
diameter) model of the full-scale
rocket prior to CDR. See the
Subscale Test Flight section of the
CDR.
By inspection
1.14. All teams shall
successfully launch and
recover their full-scale rocket
prior to FRR in its final flight
configuration. The rocket
flown at FRR must be the
same rocket to be flown on
launch day.
The team will successfully launch
and recover the full-scale (6”
diameter) rocket prior to FRR in
its final flight configuration. See
the timeline for anticipated dates.
By inspection
1.14.2.1. If the payload is not
flown, mass simulators shall
be used to simulate the
payload mass.
The team plans to fly the payload
in the full-scale demonstration
flight.
By inspection
1.14.2.3. If the payload
changes the external surfaces
of the rocket (such as with
camera housings or external
probes) or manages the total
energy of the vehicle, those
systems shall be active
during the full-scale
demonstration flight.
All payloads will be active during
the full-scale demonstration flight.
By inspection
1.14.4. The vehicle shall be
flown in its fully ballasted
configuration during the full-
scale test flight.
The vehicle will be flown in its
fully ballasted configuration
during the full-scale test flight.
By inspection

29
1.14.5. After successfully
completing the full-scale
demonstration flight, the
launch vehicle or any of its
components shall not be
modified without the
concurrence of the NASA
Range Safety Officer (RSO).
The launch vehicle will not be
modified after the full-scale
demonstration flight without the
concurrence of the NASA RSO.
By inspection
1.15. Each team will have a
maximum budget they may
spend on the rocket and the
Autonomous Ground Support
Equipment (AGSE). Teams
who are participating in the
Maxi-MAV competition are
limited to a $10,000 budget
while teams participating in
Mini-MAV are limited to
$5,000. The cost is for the
competition rocket and
AGSE as it sits on the pad,
including all purchased
components.
The team has budgeted $1500 for
the competition rocket, and $3500
for the AGSE. Throughout
development and construction of
the rocket and AGSE, the team
will be looking for ways to cut
costs and stay within the $5000
total budget.
By inspection
1.16.1. The launch vehicle
shall not utilize forward
canards.
The launch vehicle does not use
forward canards.
By inspection
shall not utilize forward
firing motors.
forward firing motors.
By inspection
shall not utilize motors that
expel titanium sponges.
motors that expel titanium
sponges.
By inspection
shall not utilize hybrid
motors.
The launch vehicle uses
commercially available solid
APCP motors.
By inspection
shall not utilize a cluster of
motors.
The launch vehicle uses only a
single motor.
By inspection

30
Table 6: Recovery Requirements and Verification
Requirement Design Feature Verification
stage the deployment of its
recovery devices, where a
drogue parachute is deployed
at apogee and a main
parachute is deployed at a
much lower altitude.
Redundant Missile Works RRC2+
altimeters will eject a drogue
parachute at apogee, the payload
bay at 1000 ft, and a main
parachute at 800 ft.
By inspection
2.2. Teams must perform a
successful ground ejection
test for both the drogue and
main parachutes. This must
be done prior to the initial
subscale and full scale
launches.
Successful ground ejection tests
will be performed prior to initial
subscale and full scale launches.
By inspection
2.3. At landing, each
independent section of the
launch vehicle shall have a
maximum kinetic energy of
75 ft-lbf.
Current simulations predict that all
vehicle sections will land with less
than 75 ft-lbf of kinetic energy.
The team will use
simulation results to
calculate the kinetic
energy of each
vehicle section at
landing.
2.4. The recovery system
electrical circuits shall be
completely independent of
any payload electrical
circuits.
There are no payload electrical
circuits.
By inspection
2.5. The recovery system
shall contain redundant,
commercially available
altimeters. The term
“altimeters” includes both
simple altimeters and more
sophisticated flight
computers. One of these
altimeters may be chosen as
the competition altimeter.
The recovery system will contain
redundant Missile Works RRC2+
altimeters to deploy the
parachutes. One of the RRC2+
altimeters will be used as the
competition altimeter.
By inspection

31
2.6. A dedicated arming
switch shall arm each
altimeter, which is accessible
from the exterior of the
rocket airframe when the
rocket is in the launch
configuration on the launch
pad.
Both RRC2+ altimeters will have
separate external arming switches
accessible when the rocket is in
launch position.
By inspection
2.7. Each altimeter shall have
a dedicated power supply.
Each altimeter will have a
dedicated 9V power supply.
By inspection
2.8. Each arming switch shall
be capable of being locked in
the ON position for launch.
The arming switches will require a
straight-edged screwdriver to lock
them in the ON position.
By inspection
2.9. Removable shear pins
shall be used for both the
main parachute compartment
and the drogue parachute
compartment.
All parachute compartments are
attached with #2 nylon shear pins.
By inspection
2.10. An electronic tracking
device shall be installed in
the launch vehicle and shall
transmit the position of the
tethered vehicle or any
independent section to a
ground receiver.
An Altus Metrum TeleGPS
tracking device will be installed in
the launch vehicle.
By inspection
2.10.1. Any rocket section, or
payload component, which
lands untethered to the
launch vehicle shall also
carry an active electronic
tracking device.
The untethered payload
compartment will have its own
GPS tracking device.
By inspection
2.10.2. The electronic
tracking device shall be fully
functional during the official
flight at the competition
launch site.
The GPS tracking devices will be
fully functional at the competition
launch site.
Functional testing

32
2.11.1. The recovery system
altimeters shall be physically
located in a separate
compartment within the
vehicle from any other radio
frequency transmitting
device and/or magnetic wave
producing device.
The recovery system altimeters
will be separated from the GPS
transmitters by plywood bulkheads
covered with aluminum foil.
By inspection
electronics shall be shielded
from all onboard transmitting
devices, to avoid inadvertent
excitation of the recovery
system electronics.
The recovery system electronics
will be shielded from the GPS
transmitters by plywood bulkheads
covered with aluminum foil.
By inspection
from all onboard devices
which may generate
magnetic waves (such as
generators, solenoid valves,
and Tesla coils) to avoid
inadvertent excitation of the
recovery system.
from any other onboard
devices which may adversely
affect the proper operation of
the recovery system
electronics.
Workmanship as it Relates to MissionSuccess
Careful attention to workmanship is critical to mission success, especially with regard to:
 Structural integrity of the launch vehicle
 Proper functioning of the recovery electronics
Structural integrity requires proper bonding of structural elements. This will be accomplished by
the following practices:

33
 Epoxy resin and hardener will be carefully measured to attain the proper ratio (1:1 by
volume)
 Surfaces to be bonded will be cleaned with alcohol and lightly sanded
 Joints will be immobilized until the epoxy has set
 All bonds will be inspected by a second team member
Proper functioning of the recovery electronics requires that electronics and wiring be properly
and securely mounted. This will be accomplished by the following practices:
 Electronics will be handled carefully by the edges and stored in ESD bags to avoid
damage from static discharge
 Altimeters and GPS units will be securely mounted to electronics sleds with nylon
standoffs
 Wiring connections will be secured by soldering, or with screw terminals, or with snap-
together quick-connectors
 Quick-connectors will be taped prior to flight
 Soldering will be inspected for ‘cold joints’
 Batteries will be secured with bubble-wrap and quick-ties
 Wiring will be bundled and routed in such a way that it does not flop around excessively
during flight
 Continuity of circuits will be tested with a multi-meter
All electronics and wiring will be inspected by a second team member
Additional Planned Component, Functional, and Static Testing
Full-scale ground testing of the payload containment system. With the launch vehicle in a
horizontal position, the payload will be inserted through the payload bay doors just below the
nosecone. Then the launch vehicle will be raised to a vertical position. The test should
determine by inspection whether the payload bay reliably receives the payload, and whether the
payload reliably slides into a slot that secures it for launch when the rocket is raised to a vertical
position.
Full-scale ground testing of the drogue parachute deployment. The entire full-scale vehicle will
be configured for launch and propped against a cardboard stand as in the subscale piston ejection
test (see Figure 10 above). The test will determine the amount of black powder required to
separate the booster section from the upper sections and deploy the drogue parachute.
Full-scale ground testing of the payload ejection system. The upper sections of the launch
vehicle including the nosecone and payload bay will be configured as in the subscale piston
ejection test (see Figure 10 above). The test will determine the amount of black powder required
to separate the nosecone and attached payload bay from the upper section of the vehicle.
Full-scale ground testing of the piston ejection mechanism for the main parachute. The
altimeter bay and middle section of the launch vehicle will be configured as in the subscale
piston ejection test (see Figure 10 above). The nosecone and payload bay will already have been
ejected, and the remains of the shear pins will still be lodged in the body tube near the forward,

34
open end. The test will determine the amount of black powder required for the piston to deploy
the main parachute reliably.
Full-scale test flights. One or more full-scale test flights will be performed to determine whether
all systems function as expected.
Manufacturing/ Assembly Status and Plans
The following table details the remaining manufacturing and assembly schedule for the full-scale
launch vehicle.
Table 7: Remaining Manufacturing and Assembly Schedule
Action To be completed by:
Laser cut fins 1/23/2015
Laser cut parts for the payload containment system 1/23/2015
Laser cut parts for the altimeter bay 1/23/2015
Cut body tubes and motor mounts to size with chop saw 1/23/2015
Build 2 booster sections (one is a back-up) 1/26/2015
Build piston parachute ejection system 1/26/2015
Assemble payload containment system 1/26/2015
Assemble altimeter bay 1/26/2015
Mount and wire the electronics and switches 1/28/2015
Launch vehicle complete, ready for ground testing 1/30/2015
Paint the launch vehicle after flight tests are completed 3/22/2015

35
The next table details the parts and manufacturing processes for each launch vehicle subsystem.
Table 8: Vehicle Subsystem Parts and Manufacturing Processes
Subsystem Parts Manufacturing Process
Booster section
 Pre-slotted
BlueTube body tube
 BlueTube motor
mount
 Pre-cut plywood
centering rings and
bulkheads
 Plywood fins
 AeroPack motor
retainer
 The body tube and
motor mount are cut to
size with a chop saw.
 The body tubes are pre-
slotted by the
manufacturer for
through-the-wall fin
mounting.
 The fins are laser cut by
the team.
 All parts are attached
with 30-minute epoxy.
Altimeter Bay
 BlueTube coupler
tube
 Pre-cut plywood
bulkheads
 ¼” all-thread rods
 ¼” brass tubing
 Plywood electronics
sled
 Wiring supplies
 Rotary switches
 ½” PVC caps to hold
ejection charges
 U-bolts
 The electronics sled is
laser cut by the team.
 The brass tubing is cut
to length with a
hacksaw and epoxied to
the underside of the
sled.
 The sled with tubing
slides onto the all-
thread rods.
 The PVC caps are
bolted and epoxied to
the bulkheads.
 Wiring and electronics
are mounted with
screws and bolts.

36
Main Parachute Piston
Ejection System
 BlueTube
coupler tube
 Pre-cut plywood
bulkhead
 U-bolt and
forged eye-bolt
 The coupler tube is cut
to length with a chop
saw.
 The pre-cut bulkhead is
epoxied into the coupler
tube.
 The U-bolt and eye-bolt
are mounted on
opposite sides of the
bulkhead.
 A ring of coupler tube
is epoxied into the body
tube below the piston to
prevent the piston from
sliding backward and
compressing the
parachute.
Payload Containment Bay
 BlueTube body
tube and coupler
tube
 Pre-cut plywood
bulkheads
 U-bolt
 ¼” all-thread
rods
 Aluminum
flanges
 Aluminum
payload bay
doors
 Plywood
 Spring-loaded
hinges
 Fiberglass nose
cone
coupler tube are cut to
length with a chop saw.
 The bulkheads are
attached to the body
and coupler tubes with
epoxy, screws or
removable rivets.
 The payload
containment system is
constructed from
plywood parts laser cut
by the team and
epoxied together.
 The aluminum flanges
are attached with
screws.
 The payload bay doors
will be milled by the
team from sheet metal.
 The spring-loaded
hinges will be riveted to
the body tube.
 The nosecone is
attached to the payload
containment bay with
removable plastic
rivets.

37
DesignIntegrity
Suitability of shape and fin style
The primary advantage of the selected trapezoidal fin shape is the forward sweep of the trailing
edge. This makes it very unlikely that the booster section will land on a fin tip and break it. The
aft end of the body tube will most likely hit the ground first.
These fins are not as aerodynamic or lightweight as other fins. But the selected motor has plenty
of thrust, and weight and drag are not serious issues for this mission.
Materials in fins, bulkheads, and structural elements
The airframe consists of three sections of 6” diameter BlueTube 2.0. BlueTube 2.0 is a
proprietary material manufactured by Always Ready Rocketry. According to the manufacturer,
BlueTube requires no reinforcement for subsonic speeds.
The fins, bulkheads, and centering rings are made of plywood. The three fins are made from
3/16” 10-ply aircraft plywood. The ½” bulkheads and centering rings are made from two sheets
of ¼” 5-ply birch plywood glued together.
The ogive nosecone is made of fiberglass.
Assembly procedures, attachment and alignment of elements, connection points, and load paths
The three sections of the launch vehicle fit together with 12” sections of BlueTube coupler tube.
The coupler and airframe overlap by 6” (1 airframe diameter) at the joints to ensure that the
airframe remains straight and rigid during flight.
Where the airframe should separate to deploy parachutes, the sections are secured by two #2
nylon shear pins. Where the airframe should not separate during flight, the sections are secured
by four removable plastic rivets.
The following table details the parts and manufacturing processes for each launch vehicle
subsystem.

38
Table 9: Vehicle Subsystem Parts and Manufacturing Processes
Subsystem Parts Manufacturing Process
Booster section
 BlueTube body tube
 BlueTube motor
mount
 Pre-cut plywood
centering rings and
bulkheads
 Plywood fins
 AeroPack motor
retainer
motor mount are
cut to size with a
chop saw.
 Fin slots will be
marked and cut by
hand with a rotary
tool for through-
the-wall fin
mounting.
 The fins are laser
cut by the team.
 All parts are
attached with 30-
minute epoxy.
Altimeter Bay
tube
 Pre-cut plywood
bulkheads
 ¼” brass tubing
 Plywood electronics
sled
 Wiring supplies
 Rotary switches
 ½” PVC caps to hold
ejection charges
 U-bolts
 The electronics sled
is laser cut by the
team.
 Brass tubing is cut
to length with a
hacksaw and
epoxied to the
underside of the
sled.
 The sled with tubing
slides onto the all-
thread rods.
 The PVC caps are
bolted and epoxied
to the bulkheads.
 Wiring and
electronics are
mounted with
screws and bolts.

39
Main Parachute Piston
Ejection System
tube
 Pre-cut plywood
bulkhead
 U-bolt and forged
eye-bolt
 Coupler tube is cut to
 The pre-cut bulkhead is
epoxied into the coupler
tube.
 The U-bolt and eye-bolt
are mounted on
opposite sides of the
bulkhead.
 A ring of coupler tube is
epoxied into the body
tube below the piston to
prevent the piston from
sliding backward and
compressing the
parachute.
Payload Containment
Bay
 BlueTube body tube
and coupler tube
 Pre-cut plywood
bulkheads
 U-bolt
 Aluminum flanges
 Aluminum payload
bay doors
 Plywood
 Spring-loaded hinges
 Fiberglass nose cone
coupler tube are cut to
 The bulkheads are
attached to the body
and coupler tubes with
epoxy, screws or
removable rivets.
 The payload
containment systemis
constructed from
plywood parts laser cut
by the team and epoxied
together.
 The aluminum flanges
are attached with
screws.
 The payload bay doors
will be milled by the
team from sheet metal.
 The spring-loaded
hinges will be riveted to
the body tube.
 The nosecone is
attached to the payload
containment bay with
removable plastic rivets.

40
Motor mounting and retention
The motor mount is a 54 mm diameter, 23” length of BlueTube. It is epoxied to three ½”
plywood centering rings, and to the three fin tabs inserted through the airframe. The centering
rings and fins are epoxied to the airframe. These connection points provide many secure paths to
distribute the thrust from the motor to the airframe.
The motor is retained in the motor mount by an AeroPack retainer, pictured below. The two
parts are threaded. The part on the right is epoxied to the aft end of the motor mount. After the
motor casing is inserted into the motor mount, the left part screws on by hand, and secures the
motor in the motor mount.
Figure 12: AeroPack Retainer
Status of verification
The status of verification is found in Table 5: Launch Vehicle Requirements and Verification
above.
Drawings of the launch vehicle, subsystems, and major components
See the drawings of the launch vehicle, subsystems, and major components at the beginning of
the Design Review section above.
Mass Statement
The current mass estimate is based on RockSim and SolidWorks models, and on component spec
sheets. The estimate is preliminary and likely to increase. The Aerotech K1275R can
accommodate mass increases of up to 25%, and still reach the 3000 ft. target altitude. Although
simulations predict an altitude of 3090 ft. with a 33% mass increase, the subscale test flight
indicates that this may be a significant overestimate.

41
Table 10: Vehicle Weight, Altitude, and Rail Velocity
vehicle weight
w/out motor (lbs)
motor
simulated altitude
(ft.)
8 ft. rail exit velocity
(ft./s)
19.63
Aerotech
K1275R
4280 83
+25%
Aerotech
K1275R
3355 75
+33%
Aerotech
K1275R
3090 73
Safety and Failure Analysis
Table 11 below shows the possible failure modes of the vehicle and the mitigations for those
failures.
Table 11: Vehicle Failure Modes
Risk Consequence
Pre-
RAC
Mitigation
Post-
RAC
Center of
gravity is too
far aft
Unstable flight
2B-
12
Add mass to the nose cone 2B-9
Piston
functionality
failure
Main chute not deployed,
damage to overall vehicle
1C-
15
Rigorous testing to will be
done to confirm the efficiency
of the design
1C-
12
Electronic
triggering of
black powder
Piston not ejected, parachute
not deployed, damage to
overall vehicle, payload not
ejected on descent
2B-
12
Rigorous testing will be done
to confirm the efficiency of
the design, wires will be
checked multiple times to
ensure functionality
2B-
9
Center of
pressure is too
far forward
Unstable flight
2B-
12
Increase the size of the fins to
lower the center of pressure
2B-9
Fin failure
Unstable flight, further
damage to the rocket
1C-
12
Careful construction to ensure
proper fin attachment
1C-8
Shearing of Loss of rocket 1C- A material with high shearing 1C-8

42
airframe 12 strength will be used
Premature
rocket
separation
Failure to reach target altitude,
failure of recovery system
3A-8
Check the shear pins before
launch, test the timers in test
launches, calculate the
required mass for black
powder charges
3A-6
Centering ring
failure
Loss of rocket
1A-
15
Check construction of
centering rings for a good fit,
check for damage to centering
rings pre-launch and post
recovery.
2B-6
Bulkhead
failure
Damage to payload, avionics,
failure of recovery
2C-5
Proper construction, extensive
ground testing of removable
bulkheads
2C-4
Nose cone
failure
Flight instability, damage to
payload bay, unable to re-
launch rocket
2C-5
Strong nose cone constructed
from fiberglass
2C-4
Table 12 shows the propulsion failure modes and the mitigations for those failure modes.
Table 12: Propulsion Failure Modes
Risk Consequence
Pre-
RAC
Mitigation
Post-
RAC
Motor ignition
failure
Failure to launch 3B-9
Check continuity, replace
igniter if necessary
3B-3
Motor CATO Loss of rocket
1B-
15
Assembly of motors by
certified members only
2B-10
Motor mount
failure
Motor launches into the
body of the rocket, damage
to payloads, loss of rocket
1C-
12
Proper construction of the
motor mount
2C-4
Improper
transportation
or mishandling
Unusable motor, failure to
launch
1C-6
Motors to be handled by
certified members only,
motors to be stored
properly
2C-3

43
Subscale Flight Results
Flight Data
Video of the subscale test flight is available on the team web site: http://amiwa/rocketowls/
2/3 Subscale Vehicle Summary
 Length: 72 in
 Diameter: 4 in
 Stability: 3.2 caliber
 Mass (without motor): 2.95 kg
 Weight (without motor): 28.9 N/6.5 lbs.
 Motor: AeroTech J350W
 Recovery system: Redundant Missile Works RRC2+ altimeters deploy a 24” elliptical
drogue parachute at apogee, and a 48” elliptical main parachute at 800 ft (AGL).
Figure 13 shows a RockSim design of the subscale launch vehicle.
Figure 13: RockSim Design of the 2/3 Subscale Vehicle

44
Comparison with the Full-scale Design
The chief differences between the 2/3 subscale and the full-scale design are:
 The subscale payload bay is empty.
 The subscale payload bay is tethered to the other sections of the rocket.
 The subscale payload bay pulls out the main parachute; there is no piston deployment.
Despite the empty payload bay, the stability margin of the subscale vehicle (3.2 caliber) is not far
from the estimated stability margin of the full-scale design (3.6 caliber).
Flight Results
Launch conditions:
Date: 12/20/2014
Location: Friends of Amateur Rocketry site, Mojave Desert
Weather: dry, overcast
Temp: 45 F
Wind: calm (3 – 5 mph)
Launch angle: 5 degrees
Flight Data:
The RRC2+ altimeters record only the peak altitude. No other flight data was collected.
Altitude estimated by RockSim: 3314 ft. AGL
Altitude reported by the RRC2+ altimeter: 2726 ft. AGL
Predicted and Actual Flight Data Discussion
All systems functioned as designed. The flight of the vehicle was straight and stable. Because
the winds were calm, it could not be determined if weather-cocking will be an issue under
windier conditions. Both parachutes deployed as expected, and the vehicle was recovered
undamaged only a few hundred feet from the launch pad.
The most significant result of the test flight is the fact that RockSim overestimated the peak
altitude by 600 ft. The error is not due to inaccurate vehicle weight, because the vehicle weight
was taken from the fully constructed and equipped subscale vehicle. The error could be due to
several other factors (see Karbon, “The Top 5 Reasons Why Your Altimeter and Computer
Simulation Don’t Agree”, Peak of Flight Newsletter, Issue 380):
 The vehicle’s coefficient of drag is underestimated.
 The vehicle’s trajectory was slightly non-vertical.
 The low temperature (45 F) reduced the total impulse of the motor.
 The total impulse of the motor is lower than advertised due to random variations in
manufacturing.
 The motor thrust curve used by RockSim is inaccurate.

45
We suspect that the first factor (underestimating the Cd) is the most significant, and that
RockSim systematically underestimates the Cd (see Van Milligan, “Maximum Simulation
Accuracy for RockSim”, Peak of Flight Newsletter, Issues 45, 46).
Subscale photos:
Figure 14: The Rocket Owls with the Subscale Launch Vehicle
Figure 15: The Subscale Altimeter Bay with Redundant RRC2+ Altimeters

46
Figure 16: The Subscale Vehicle under Two Parachutes
Impacts on Full-Scale Launch Vehicle
The results lead us to reconsider our motor choice. The simulated altitude with the AeroTech
K1100T (from the PDR) is 3011 ft. AGL. We now suspect that the actual altitude with this
motor could be closer to 2400 ft. So we have switched to the more powerful K1275R, with a
simulated peak altitude of 4300 ft. AGL. We expect the actual altitude with this motor to be
closer to 3700 ft. AGL. This leaves room for a 10 – 20% mass increase between the CDR and
the competition launch. If the altitude is significantly higher than 3000 ft. in the full-scale test
flights, ballast can be added to lower the altitude accordingly.
Recovery Subsystem
The recovery subsystem consists of parachute deployment electronics and mechanisms, three
parachutes and their attachment hardware, and two GPS tracking devices. This system must
 accurately detect apogee, 1000 ft AGL, and 800 ft AGL
 reliably deploy parachutes at these altitudes
 reduce the kinetic energy of each vehicle section to less than 75 ft-lbf at landing
 transmit the location of each section to a ground station

47
The recovery system components are summarized in the following table:
Table 13: Recovery Subsystem Components
section
descent weight
of section (lb)
drogue
parachute
main
parachute
attachment
scheme
deployment
process
untethered
payload
4.9
30"
elliptical
42" elliptical
5/8" tubular
nylon harness,
sewn loops,
attached to 1/4”
U-bolts with
3/16” quick-
links.
U-bolts are
mounted to
1/2"plywood
bulkheads.
Redundant
Missile Works
RRC2+
altimeters fire
black powder
charges.
middle 7.2
72" elliptical
booster 8.8
Order of Deployment
1. The booster section separates at apogee to deploy the drogue chute.
2. The nosecone and attached payload capsule are ejected at 1000 ft., and descend under
their own parachute.
3. The main parachute is deployed at 800 ft. out the forward end of the middle section.
Figure 17: Recovery Deployment
Parachute, Harnesses, Bulkheads, and Attachment Hardware
Main Parachute Deployment
A piston deploys the main parachute. This is necessary because the main parachute deploys out
the forward end of the rocket after the nosecone/payload bay has been ejected. The main chute
cannot reliably be blown out of the airframe by an ejection charge; the hot gases simply go

48
around the parachute. Therefore, the parachute is attached to a piston inside the airframe. The
piston is pushed out by the ejection charge, and pulls the main chute out with it. Figures 5 and 6
above show the design of the piston and its location in the middle section of the rocket.
Drogue Parachute
Fruity Chute 30” elliptical parachute. Materials: 1.1 oz. rip-stop nylon, 330 lb braided nylon
shroud lines, 3/8” nylon bridle, 1000 lb swivel. RockSim estimates a descent rate of 50 ft/s
under this parachute.
Main Parachute
Fruity Chute 72” elliptical parachute. Materials: 550 lb nylon, 11/16” nylon bridle, 3000 lb
swivel. According to Fruity Chutes, 17 lb. will descend at 20 ft/s under this parachute. Our
tethered booster and middle sections weigh 16 lb.
Payload Parachute
Fruity Chute 42” elliptical parachute. Materials: 1.1 oz. rip-stop nylon, 400 lb braided nylon
shroud lines, 5/8” nylon bridle, 1500 lb. swivel. According to Fruity Chutes, 6 lb. will descend
at 20 ft/s under this parachute. The nosecone and attached payload bay weigh approximately 4.9
lb., so we expect a descent rate somewhat less than 20 ft/s.
Harnesses, Attachment Hardware, and Bulkheads
The drogue and main parachute swivels will be attached with 3/16” stainless steel quick links to
a sewn loop in 9 ft long, 5/8” tubular nylon shock cords. Sewn loops at the ends of the shock
cords will be attached with quick links to 1/4” steel U-bolts mounted on 1/2” thick plywood
bulkheads. The bulkheads will be epoxied into the airframe.
The nosecone and attached payload bay are untethered to the other sections of the rocket. The
payload parachute swivel will be attached with a 1/8” stainless steel quick link to the sewn loop
of a 3 ft, 3/8” tubular nylon shock cord. The other end of the shock cord will be attached with a
quick-link to a 1/4” U-bolt mounted on a 1/2” plywood bulkhead. The bulkhead will be epoxied
into the payload bay airframe.
All recovery subsystem materials and hardware are in accord with the recommendations of the
parachute manufacturer (Fruity Chutes). For rockets up to 30 lbs., Fruity Chutes recommends:
 5/8” tubular nylon shock cord
 3/16” stainless steel quick links
For the 5 lb., untethered payload section, smaller hardware is permitted:
 3/8” tubular nylon shock cord
 1/8” quick links
1/4” steel U-bolts mounted on 1/2” thick bulkheads epoxied into the airframe should be
sufficient to withstand the forces of parachute deployment.

49
Electrical Components
Deployment Altimeters
Missile Works RRC2+ altimeters have the requisite functionality, are reliable, easy to use, and
inexpensive. The RRC2+ is a barometric altimeter with two outputs to initiate two separate
flight events, such as deploying parachutes. After each flight, the peak altitude is reported by a
series of beeps. A standard 9V battery powers each altimeter.
Recovery System Electrical Schematics
Electrical schematics for the recovery system are shown below. The main vehicle has a recovery
subsystem consisting of a main and drogue parachute, and has two sets of e-matches in order to
deploy either one. The payload containment device has a similar setup, however, it contains only
one parachute and needs only one set of e-matches.
Drawings, Sketches, Block Diagrams, and Electrical Schematics
Figure 18: Electrical schematics for the main recovery system. The altimeters will be connected
to a power source, switches, and E-matches for the drogue and main parachute.

50
Figure 19: Electrical schematics for the payload recovery system. The altimeters will be
connected to a power source, switches, and E-matches for the parachute.
Kinetic Energy at Significant Phases of the Mission
The following table summarizes the kinetic energy of each independent and tethered section of
the launch vehicle. The kinetic energy of each section is well below the maximum 75 ft-lb at
landing.
Table 14: Kinetic Energy of each Rocket Section
section
descent weight
of section (lb)
speed
under
drogue
(ft/s)
kinetic energy
under drogue
(ft-lb)
speed at
landing (ft/s)
kinetic energy
at landing (ft-
lb)
untethered
payload
4.9 50 190 <20 <31
middle 7.2 50 280 <20 <45
booster 8.8 50 342 <20 <55
Test Results
Ground Testing
Black powder charges will eject the nosecone and attached payload bay, and deploy the drogue
and main parachutes. The team mentor will assist with ground testing these ejection charges to

51
determine the required amount of black powder, and to ensure that deployment mechanisms are
functioning properly. Only the team mentor will handle the black powder.
Safety and Failure Analysis
Table 15 shows the failure modes for the recovery system and the mitigations for these failures
Table 15: Recovery Failure Modes
Risk Consequence
Pre-
RAC
Mitigation
Post-
RAC
Rapid Descent
Damage to airframe and
payloads, loss of rocket
1B-
16
Redundant altimeters,
verification testing of the
recovery system, simulation
to determine appropriate
parachute size
1C-
12
Parachute
deployment
failure
Loss of rocket, extreme
damage to rocket and all
components
1B-
16
Ground test of parachute
deployment
1C-
12
Parachute
separation
Loss of parachute, loss of
rocket, extreme damage to
rocket and all components
2A-
15
Strong retention system, load
testing
2B-
12
Parachute tear
Damage to rocket, loss of
parachute, rapid descent
resulting in an increased
kinetic energy
2B-
12
Safety check the parachute for
damage, clear parachute bays
of any possible defects,
properly pack the parachutes
2C-
4
Parachute melt
Damage to rocket, loss of
parachute, rapid descent
resulting in an increased
kinetic energy
1C-
10
Proper protection from
ejection charges, ground
testing of recovery system
2C-5
Slow Descent
Rocket drifts out of intended
landing zone, loss of rocket
2B-9
Verification testing of
recovery system, simulation
to determine appropriate
parachute size
2C-5

52
MissionPerformance Predictions
MissionPerformance Criteria
The primary mission performance criteria for the launch vehicle are:
 stable flight
 3000 ft. AGL apogee
 payload ejection at 1000 ft. AGL
 kinetic energy at landing for each section <75 ft.-lbf
Flight Profile Simulations
The following graph created with RockSim shows the simulated velocity, drag, and altitude of
the vehicle from lift-off to apogee.
Figure 20: Simulated Drag, Velocity, and Altitude

53
Figure 21: Flight profile simulations
Altitude
Although the simulated altitude of the vehicle is 4300 ft., the subscale test flight indicates that
this overestimates the altitude by as much as 600 ft. Moreover, the team expects a vehicle mass
increase of 10 – 20% between the CDR and the competition launch, which would lower the
expected altitude several hundred feet more. The combination of these factors leads the team to

54
expect an altitude at the competition launch close to 3000 ft. If full-scale test flights are
significantly higher than 3000 ft., ballast can be added to the vehicle.
Payload Ejection
Redundant Missile Works RRC2+ altimeters will eject the payload bay at 1000 ft. AGL.
Kinetic Energy
Table 14 summarizes the kinetic energy of each independent and tethered section of the launch
vehicle. The kinetic energy of each section is well below the maximum 75 ft-lb at landing.
Drift from Launch Pad
Only rough estimates of the vehicle’s drift from the launch pad are possible at this time. The
RockSim flight simulations assume that
1. the rocket is launched at a 5-degree angle
2. all parts of the rocket descend and drift together under the drogue parachute
3. all parts of the rocket descend and drift together under the main parachute
4. the vehicle is not buoyed by a thermal column
The third and fourth points introduce some error into the estimates. At 1000 ft AGL, the payload
bay is ejected, and it descends untethered under its own parachute. The tethered sections of the
rocket descend under a main parachute that is deployed at 800 ft AGL. These facts are not
accounted for in the simulation. However, this error should not be very great, since the distance
to the ground is small (<1000 ft), and both parts of the rocket should descend at roughly equal
speeds (even under separate parachutes).
Thermal columns of air at low altitudes can buoy a vehicle under parachute and extend its drift.
In simulations that included random thermal columns, drift was increased by up to 1000 ft.
Because thermal columns are random and infrequent, they are not accounted for here. The
following table gives rough baseline drift estimates, which assume vehicle drift is not affected by
thermal columns.

55
Table 16: Drift from Launch Pad (all sections)
wind speed
(mph)
drift at 1000 ft
AGL (ft.)
total drift at
landing (ft.)
0 525 525
5 662 878
10 760 1132
15 970 1560
20 1070 2287
Scale Modeling Results
The scale modeling results can be found in the Subscale Flight Results section.
Stability Margin
The subscale test flight demonstrates the stability of the design. See the Subscale Flight Results
section above. With the motor installed, RockSim gives the following estimates for the full-scale
vehicle:
Center of Gravity (measured from nose): 67.9 in
Center of Pressure (measured from nose): 89.7 in
Stability Margin (caliber): 3.6
Figure 22: Stability Diagram

56
AGSE/ Payload Integration
The payload will be captured by the AGSE and will be transferred to the payload containment
system. The AGSE will have the task of retrieving the payload and safely returning it to the
launch vehicle and the payload containment system will have the task of safely transporting the
payload throughout the flight of the vehicle. The payload containment has been designed to be
compatible with the current AGSE design. The following section describes how the containment
system will work alongside the AGSE in order to capture and contain the payload safely
throughout the flight and recovery phase.
Figure 23: Description of payload containment and nose cone section

57
Figure 24: Rendering of the Payload Containment Device

58
Ease of Integration
Integration Plan
Figure 25: Dimensional drawing of the payload containment device.
The payload will be integrated into the vehicle through the payload containment bay shown in
Figure 25. The payload will fall into the payload containment area when it is inserted into the
rocket. The opening that the payload falls into will be chamfered on the long sides to ensure that
the payload falls into place correctly. However, the payload is not secured until the vehicle is
lifted upright. When the vehicle is lifted upright, gravity causes the payload to fall into the

59
payload slot, which will hold the payload through the flight. The payload slot can be seen to the
left of the payload containment area in Figure 25. This containment bay will be secured to a
wood sled that slides onto all-thread rods via four all-thread attachment blocks, which are
pointed out in the dimensional drawing in Figure 25. This assembly will be between two
bulkheads that will prevent it from sliding around on the all-threads during flight. The tracking
device will be located on an electronics sled that will be above the payload containment area. It
is shown to the right of the payload containment area in Figure 25. Most of the assembly will be
constructed using birch plywood, although some aluminum will be used. The components are all
rated to withstand the stresses that will be present during boost. Preliminary analysis indicates
that with the payload, 30 lbs of stress is added to the bulkhead. This bulkhead is currently
planned at 0.5” thick and will withstand this force. The walls of the payload containment area are
reinforced with aluminum, so they will be able to withstand the stress exerted on them by the
payload. The figure also shows the dimensions for the components that comprise the payload
containment device. These dimensions have been set to fit the current design of the vehicle
between the payload containment bay and the nosecone.
The payload containment device will be made to fit into the payload section (forward section) of
the vehicle. The containment device will be made to slide into the payload section from the fore
end. The bottom bulkhead of the containment device will have a section flattened so that it can
slide past the spring-loaded doors in the airframe. The payload containment area must line up
with the doors or the payload cannot be inserted. The doors are spring-loaded so that no
electronics are necessary to operate it. The payload will be pushed through the door by the
AGSE in order to contain it since the doors will not open under the weight of the payload by
itself. Once the payload containment device has been slid into place, the assembly will be
secured to the airframe of the vehicle through a series of locking bolts. These locking bolts will
slide through the airframe of the payload section and into the bulkheads of the payload
containment device. The locking bolts can be seen in Figure 26 below and above the payload
doors. Once the assembly is locked inside the vehicle, the nosecone can slide into the body of the
vehicle. The nosecone will also be locked with bolts that extend through the airframe so that it
does not come off at any point during the flight. The bottom of the payload section will be
attached to a parachute and the recovery electronics will ensure that the sections separate and the
parachute deploys at the proper times.

60
Compatibility of Elements
Figure 26: The integration of the payload containment device into the launch vehicle.
Aside from the recovery elements within this section of the rocket, all elements in the
containment section of the vehicle are mechanical and are compatible. All components have been
designed around each other with the single purpose of capturing the payload and returning it
safely. The AGSE interfaces with the payload containment system mechanically and will be able
to apply enough force to open the doors. The payload containment device is fully compatible
with the current launch vehicle design and will integrate into the launch vehicle as shown in
figure 26.

61
The interfaces that will be present our internal as well as from vehicle to the ground station. The
internal interfaces are outlined in the table below.
Table 17: Internal Interfaces
Components Interface
Booster and middle section
These components connect through the shock
cord that attaches to the drogue parachute.
The shock cord will be attached to a
bulkhead from each section so that the
sections cannot separate in flight.
Avionics and middle section
The avionics will connect to the middle
section through an electronics sled. This sled
will be placed in its own bay at the bottom of
the middle section and will rest between two
bulkheads.
Recovery electronics and parachutes
The recovery electronics will interface with
the recovery parachutes through black
powder charges. E-matches will be
connected to the recovery electronics and
these will ignite the black powder charges
that separate the sections and eject the
parachutes.
Middle section and main parachute piston
The main parachute will not be connected to
the forward section. It will be connected to a
piston in the middle section through a shock
cord. Ejecting the piston will cause the
parachute to eject.
Payload recovery electronics and payload
section
The payload recovery electronics will be
placed on the backside of the payload
containment area. The electronics will be
secured to a wood piece as shown in Figure
25.
Payload recovery electronics and
parachute
The payload recovery electronics will be
connected to an E-match. This E-match will
be connected to a black powder charge. This
charge will cause the complete separation of
the payload section with the rest of the main
vehicle and will cause the parachute to
deploy.

62
The vehicle to ground station interfaces are wireless communication interfaces. Both the
TeleGPS and the EM-506 GPS will interface with separate ground stations in order to help track
the different components during the recovery phase. Both components will have the means to
wirelessly communicate with the ground station.
Simplicity of Integration Procedure
Figure 27: Side view and section view of the payload containment device.
The AGSE and containment have been designed to minimize the integration procedures required
on launch day. The containment device will be assembled as shown in Figure 25 prior to launch
day. The payload doors will be attached to the airframe of the rocket using spring loaded hinges
which eliminates the need for any electronic elements associated with the doors. On the
containment device, mounts will be in place for both recovery altimeters and a recovery GPS.
All wiring will be done prior to launch day. Switches will be placed in the airframe of the vehicle
and wire connectors will allow the recovery altimeters to interface with the switches in a simple
and easily removable manner. The containment device will slide in using a rail system that will
ensure the proper orientation inside the body of the launch vehicle. Locking bolts will be placed
to ensure the bottom bulkhead is secure. Since the GPS will be placed above the top bulkhead on
the electronics sled, the switch for this component will be placed in the nose cone. The switch
will interface with the electronics using a wire connector which is easy to install and remove.
The section view in Figure 27 shows where the RRC2+ altimeters will be mounted. The left side

63
is the electronics sled that the GPS will be mounted to although all of this will be complete prior
to launch day. In summary, the integration procedure on launch day consists of plugging in the
electronics, sliding the payload containment device into the body tube, sliding the nose cone into
the body tube and securing the entire assembly with locking bolts. The components have been
designed to easily fit together and reduce the amount of work needed to perform during launch
day.
The full checklist of launch day integration procedures can be found in the Launch Concerns and
Operation Procedures section.
Changes to AGSE/ Payload
Components pertaining to AGSE and payload containment were not tested with the subscale and
therefore, no changes to either the AGSE or payload containment system pertain to it, although
the payload containment system hasn’t been changed. Changes made to the AGSE can be found
in the prior section dealing with changes to criteria.
Launch Concerns and Operation Procedures
Final Assembly and Launch Procedures
The following section describes the procedures that will be required to prepare the vehicle during
launch. Prior preparation has been optimized in order to reduce the launch preparations as much
as possible. A checklist has been prepared that will be printed out and used at all full scale
launches. This checklist has the same material as listed here but requires signing off of each step
in order to reduce the risk of system failure.
Avionics Bay
Prior to launch day, the recovery system electronics and batteries will be mounted in the avionics
bay and all wiring will be completed. The electronics sled will be connected to the bottom
bulkhead previously as well. The following procedures are required for preparation of the
avionics bay on launch day.
1. Check and verify voltage of batteries
2. Plug in batteries for both altimeters and GPS
3. Connect the wire connectors for switches together
4. Slide the electronics sled into the avionics bay
5. Connect the wire connectors for the drogue and main ejection charge together
6. Connect the bulkheads at both ends
7. Temporarily bridge the terminals for each ejection charge, turn switches to on position and
verify continuity and battery voltage
8. Return switches to off position

64
Nose Cone/ Payload Containment
Prior to launch day, the recovery electronics for this section will be mounted and the wiring will
be completed. The payload containment device will be preassembled as well. The following
procedures are required for preparation of the nose cone and payload containment on launch day.
2. Plug in batteries for GPS and both altimeters
3. Connect the wire connectors for both altimeter switches and ejection charges together
4. Slide payload containment section into the body tube of the forward section
5. Secure bottom bulkhead with locking bolts
6. Connect the wire connectors for the GPS switch together
7. Slide the nose cone into the body tube
8. Secure the nosecone and top bulkhead with locking bolts
9. Temporarily bridge the terminals for each ejection charge, turn the switches for the altimeters
on, and verify continuity and battery voltage
10. Turn the switches on for GPS and verify functionality
Recovery Systems
The recovery electronics have already been prepared so this section focuses on the ejection
charges and parachutes. No prior preparation of ejection charges or parachutes will be
completed.
1. Measure out the proper amounts of black powder for drogue ejection charge
2. Install two e-matches into each set of terminals and place ends into the black powder
3. Load black powder for drogue into the cap
4. Cover black powder with cotton wadding and tape off
5. Repeat step 1-4 for the main and containment ejection charges
6. Fold drogue parachute and attach harness to shock cord
7. Wrap the Nomex blanket around the parachute
8. Connect the harnesses on both ends of the shock cord to the U-bolts in drogue bay and on the
lower side of the avionics bay ensuring that the shorter side is connected to the avionics bay
9. Fold main parachute and attach harness to shock cord

65
11. Connect the harnesses on both ends of the shock cord to the U-bolts in the main bay and on
the lower side of the piston ensuring that the shorter side is connected to the piston
12. Fold the payload parachute and attach harness to shock cord
14. Connect the harness on the end of the shock cord to the U-bolt on the bottom of the payload
containment section
Motor
No prior preparation will be completed prior to launch day. The motor will be completely
disassembled and reload kits will be opened only at the launch field. The instructions for
assembling the motor will be on hand and only team members that have previously assembled
the motor successfully will be allowed to prepare the motor on launch day.
1. Prepare motor as described by the AeroTech user manual
2. Verify motor assembly with team mentor
3. Load motor into launch vehicle
4. Install motor retention
Setup on Launcher
While performing the procedures of this section, extra care must be taken. Installing igniters into
motors and activating electronics connected to energetics pose a hazard. All precautions must be
taken to minimize the risk of injury to personnel.
1. Slide vehicle onto launch rail
2. Allow AGSE to perform its operations
3. Lift launch rail upright
4. Turn on electronics one at a time and listen for response from electronics where applicable
5. Install igniter, ensure that the igniter is at the top of the motor and place tape over bottom to
hold the igniter in place
6. Attach igniter to the ignition system
Troubleshooting
Although testing will be performed to ensure that all components are operating properly prior to
launch day, errors may occur that cause certain systems to malfunction. This section addresses
certain issues that arise and how to fix those issues.

66
Issues with continuity in the altimeters can be determined based on the beeps that come from the
component. If continuity is the issue, the wiring of that altimeter will be inspected, a multimeter
will be used to determine the position of the discontinuity, and the e-matches will be replaced.
Issues with the igniter will be determined when the motor fails to ignite. If this happens, a few
minutes will be allowed to pass and the igniter will be inspected and replaced if needed.
If either GPS fails to transmit the data, the electronics will have to be inspected and the ground
stations will be troubleshooted. First the wiring and the functionality of the GPS component will
be analyzed. If everything is in place, the programs on the ground station responsible for the GPS
that is not transmitting data will be inspected to determine if the ground station is responsible for
the error.
Post-Flight Inspection
The post-flight inspection will be conducted to determine what happened during the flight. The
post-flight inspection consist of analyzing the components of the vehicle and listening to the
altimeters for the altitude.
First, the altimeters will be removed and the altitude will be determined through a series of
beeps. The parachutes will be inspected for any holes or tears. The body tubes will be inspected
for any deficiencies that may have been caused by the flight. Finally, the payload will be
inspected to determine whether any damage has occurred.
The following pages are the official checklist that are to be printed out and used on launch day.

67
Rocket Owl’s Launch Procedure Checklist
All of the following steps must be completed prior to launch. Each step must be signed off
by at least two team members that witnessed its completion. Following this procedure will
reduce the risk of any system malfunction during flight. After the checklist is complete, the
team leader and safety officer should inspect the launch vehicle and verify flight readiness.
Avionics Bay
2. Plug in batteries for both altimeters and
GPS
3. Connect the wire connectors for switches
together
4. Slide the electronics sled into the avionics
bay
5. Connect the wire connectors for the
drogue and main ejection charge together
6. Attach bulkheads at both ends
7. Temporarily bridge the terminals for each
ejection charge, turn switches to on position
and verify continuity and battery voltage
Nose Cone/ Payload Containment
2. Plug in batteries for GPS and both
altimeters
3. Connect the wire connectors for both
altimeter switches and ejection charges
together
4. Slide payload containment section into
the body tube of the forward section
5. Secure bottom bulkhead with locking
bolts
Initial Initial
1. __________ __________
2. __________ __________
3. __________ __________
4. __________ __________
5. __________ __________
6. __________ __________
7. __________ __________
8. __________ __________
1. __________ __________
2. __________ __________
3. __________ __________
4. __________ __________
5. __________ __________

68
6. Connect the wire connectors for the GPS
switch together
7. Slide the nose cone into the body tube
8. Secure the nosecone and top bulkhead
with locking bolts
9. Temporarily bridge the terminals for each
ejection charge, turn the switches for the
altimeters on, and verify continuity and
battery voltage
10. Turn the switches on for GPS and verify
functionality
Recovery Systems
1. Measure out the proper amounts of black
powder for drogue ejection charge
2. Install two e-matches into each set of
terminals and place ends into the black
powder
3. Load black powder for drogue into the
cap
4. Cover black powder with cotton wadding
and tape off
5. Repeat step 1-4 for the main and
containment ejection charges
6. Fold drogue parachute and attach harness
to shock cord
7. Wrap the Nomex blanket around the
parachute
8. Connect the harnesses on both ends of the
shock cord to the U-bolts in drogue bay and
on the lower side of the avionics bay
ensuring that the shorter side is connected to
the avionics bay
9. Fold main parachute and attach harness to
shock cord
6. __________ __________
7. __________ __________
8. __________ __________
9. __________ __________
10.__________ __________
11.__________ __________
1. __________ __________
2. __________ __________
3. __________ __________
4. __________ __________
5. __________ __________
6. __________ __________
7. __________ __________
8. __________ __________
9. __________ __________

NASA Student Launch Critical Design Review Report Summary

NASA Student Launch Critical Design Review Report Summary

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