Detailed System Baseline Review for the Rocky CUBESAT project by the integrated product team at the University of Alabama in Huntsville (UAH)

1. Detailed System Baseline Review
ROCKY
TEAM CD

2. ROCKY
Goal: Design and Develop a 3U CubeSat
➢ Measures lift, drag, magnetic fields, radiation, and GPS
Performance in LEO
➢ Actively controls descent into the atmosphere to maximize
duration in LEO
Customer: U.S. Army Space and Missile Defense Command
Process: Agile SE processes
2

3. Team CD
Luis
Aaron
Hugo
Team Lead
Christian
Kenneth
= UAH Engineering
= CofC Science
= Tuskegee Engineering
= UTEP Engineering
= ESTACA Engineering
Tech Editor
Robin
Computer Sci
Megan
Political Sci
Morgan
Astro Ph
Michel
Astro Ph
Haven
PCE
Nathan
Sandlin
Geo
David
AE
Ricardo
AE
Qioa
Environment
Austin
Sci Ops
Jeremiah
SCE
Justin
Smith
Thermal
Andrew
Tuskegee
Khiante’
Structure
Hagen
UTEP
Daniel
LSE
Janelle
Williams
Team Lead
Calin
Emeric
Antoine
Emilie
Yohann
PM
Eric
Powell
PI
Wendell
Tech Editor
Sarah
3

4. Team Responsibilities
➢ UAH, Engineering:
➢ Overall project guidance, lead the project; staff the payload and spacecraft teams
to design and develop ROCKY
➢ UTEP, Engineering:
➢ Design and develop electrical power, communications, and command and data
handling subsystems in accordance with project terms set forth by UAH for ROCKY
➢ ESTACA, Engineering:
➢ Design and develop a model and perform a simulation of ROCKY in LEO during
deorbit from various attitudes and assist with uncertainty analysis of payload
measurements
➢ CofC, Science:
➢ Develop a science enhancement object (SEO) for the primary mission of ROCKY
➢ TU, Engineering:
➢ Design and develop the ADACS control system
4

5. Agenda
➢ Detailed description of the payload
➢ All instrumentation identified
➢ How it meets the requirements
➢ Detailed subsystem component data outlining interfaces
with other components
➢ Identify key risks
➢ Technical and programmatic
➢ 5x5 matrix
➢ Update proposed budget for hardware only
5

6. ➢ Altitude of 350 km circular orbit at 28.5°
➢ Abide by all requirements in the CubeSat Design Specification, REV. 13
➢ The ROCKY shall survive the environment outlined in NASA TM 82478,
Space and Planetary Environment Criteria Guidelines for Use in Space
Vehicle Development, 1982 Revision, Volume 1
➢ Incorporate available technology (technology readiness level ≥6)
➢ If non-space qualified hardware is chosen, survivability shall be
demonstrated.
Verification of Requirements
6

7. Impact of Requirements
Impact of Requirements: How did each Requirement shape the design of the CubeSat?
Requirement Primary Impact(s)
All components must be TRL-6 or greater Trade Study Compliance: Components selected must have had
flight heritage or extensive testing in simulated operational
environment
Mass must be less that 10 Kg Mass budgeting: Components such as the VACCO & MAI-400 units
took up 15% of mass budget.
Volume must be 3U sized(10x10x30 cm) Volume budgeting: Components selected had limited outer
dimension of 10x10cm in order to fit in CubeSat. Drove the
selections of antenna & propulsion system selections heavily
Measurements(Lift,Drag,Radiation,GPS) Budget: The accuracy of the components drove the cost increasing
with accuracy.
Increase lifetime by 10% Material compliance: Propulsion system selected had to utilize non
volatile propellants
Science Enhancement Option: Measure LEO Magnetic field Structural: Magnetometers had be placed away from other
components to provide accurate data
No space debris after 25 years Analysis: Show proof that CubeSat would deorbit within 25 years
7

8. Cubesat Solution
Last Review Model Final Model
8

9. Concept of OperationsConcept of Operations 9

10. Concept of Operations
• ConOps is expanded over cycle of 1 orbit
• Experiment will collect continuously
• Communication with ground stations
will range from 2-7 mins
Priority of Operations
1. Communication with Ground Stations
2. Health Ping
3. Perform Experiment
4. Detect CubeSat Orientation
5. Make Orientation Adjustments
10

11. Profile overview
• Profiles show activity over 90 minute Orbital Period
• Profiles Included
-Communications & Data Profile: Radio activities for
communications including data generation & transmittal
-Power profile: Power requirements for experiment, radios, general
operations
11

12. Communications
Data Collection Rate: 8 kB/min
Transmit Rate: 72 kb/min
• Communications occur between 2
ground stations: UAH & UTEP
• Data communications rate is 9.6
kbps
• Communications occur over 2-7
minute period, best case scenario
is shown
• All data is transmitted to UTEP
ground station
• Commands are received from UAH
ground station
12

13. Power Profile
● Single orbit averages 90 minutes
-Eclipse Period: 35 minutes
-Sunlight Exposure: 55 mins
● P110 Solar cells generate 15 W for a total of
13.75 W-hr per orbit
● Power draw is a total of 12.226 W-hr per orbit
for a worst case scenario
● BM-1 Battery pack is depleted less that 10%
for a typical orbit
Assumptions:
-Battery levels assumed to be at full capacity(40 W-
hr)
-Direct sunlight outside of eclipse
13

14. Mass Budget
Total Mass: 4.944 Kg With estimates and creep margin: 5.14 Kg
Mission Requirement: 10 Kg
Actual: 5.14 kg
Difference: 4.86 kg
This difference allows for
additional payload
opportunities.
14

15. Patran/Nastran Analysis
● Cubesat Structure made of Aluminum 7075
● Ultimate Strength of 572 MPa
● Yielding Strength of 503 MPa
15

16. Cubesat Components
● Section 1: Thruster (VACCO AFRL)
● Section 2: ADACS (MAI 400)
● Section 3: Dosimeter, Magnetometer, GPS, Antenna, Radio, Battery, SD Card, and
Microcontroller
16

17. -
Command and Data Handling 17

18. Command and Data Handling
-
18

19. Propulsion VACCO AFRL
Function:
Provide propulsion to prolong mission life
Driving Features:
High Impulse yield COT thruster
➢ Self-contained integral controller,
propellant storage, propellant feed
system, heaters and sensors
➢ Over 200,000 thruster firings in a
simulated space environment
➢ Total altitude change…..3631 meters
➢ Total Impulse.....................1808 N/sec
➢ Standby Power…...……...0.055 Watts
➢ Peak Power.......................<15 Watts
➢ Dry Mass............................ 568 grams
➢ Propellant Mass ……....... 495 grams
➢ Total Mass .........................1,063 grams
618 N-sec/Liter Performance Density
19

20. Power
-
20

21. Power
-
21

22. Structure
Function:
➢ Housing and
protection from any debris,
radiation, and temperatures while
in LEO
Temperature Range: -170°C to 123°C
Mass: 255 grams
Volume: 340.5mm X 100mm X 100mm
Key Features:
➢ Frame: Aluminum 7075
anodized, hardcoat, and
Alodine 1200.
22

23. Communications
-
23

24. Communications
-
24

25. Thermal
-
25

26. ADACS
Maryland Aerospace MAI-400
Function: Stabilize & Point Rocky
Driving Requirements:
Plug and Play stand alone attitude control
system with superior flight heritage
Key components:
- Reaction Wheel
- Magnetorquer
- Star Tracker
- Horizon Sensor
➢ Mass: 694 grams
➢ Estimated Power :
Steady State/ Typical W: 3.17
(0.63amps @ 5V)
➢ Peak Wattage: 7.23 (145 amps
@ 5V)
➢ Volume: 10x 10 x 5.9cm
➢ Partners: Tuskegee University
26

27. ADACS cont… MAI-400 A La Carte
Attitude control
Reaction Wheels…………… 3 single axis
1108 mNms Momentum Storage @ 1000 rpm
Magnetorquer Rods………. 3 single axis
0.15/0.6/0.3 Am2 Moment @ 72% duty cycle
Integrated ,PCB board driven
27

28. ADACS cont… MAI-400 A La Carte
Positioning
Static Earth Horizon Sensor…1/60 arcminute accuracy
Star Tracker ……………...…..0.013/54 arcsec accuracy
28

29. GNSS
Novatel OEM628 Triple-Frequency + L-Band GNSS Receiver
Highly accurate, Environmental tested
Compliant with MIL-STD 810G
- Accuracy: Time…………………… 20 ns RMS
Positional (TerraStar-C).............. 4 cm
- Initialization reliability……………… >99.9%
- Time to first fix: hot start ................. 35 s
cold start ................. 50 s
- Weight……………………………...... 37 g
- Power………………………………... 1.3 W
- Maximum Data Rate……………....100 Hz
29

30. Honeywell HMC2003 Magnetometer
Honeywell Magnetometer -Records magnetic
field fluctuations for science objective.
- Field Range: ±2 Gauss = ± 200 μT
- Sensitivity: 40 μG = ± 0.004 μT
- Power Requirements: 20 mA
Years of Comparable Earth Based Data Already
archived by NOAA.
30

31. Teledyne UDOS007-K Dosimeter
Teledyne UDOS007 - Measure Radiation Exposure
as part of science objective requirements.
Energy Range:
- Min: 1 MeV
- Max: 15 MeV
Sensitivity Range:
- Min: 12 µRads/step
- Max: 16 µRads/step
Power Requirements:
- 0.02 Watts

32. Measure Lift / Drag
Since space does not act as a
Newtonian Fluid, the drag force is due
to the collision between the spacecraft
and present particles. Therefore, the
drag of the spacecraft will be found by
multiplying the deceleration of the
Cubesat in the tangential direction by
the mass.
32

33. Science Enhancement Objective
(SEO)
Wendell Roberson1, Morgan Godfrey4, David McWhorter2, Haven Kerley1, Michel
Cuvillier2, Megan Landau3, Dr. Cassandra Runyon2, and Dr. Jon Hakkila1
1Department of Physics and Astronomy, 2Department of Geology and Environmental
Geosciences, 3Department of Computer Science, 4Department of Political Science

34. HOW WILL AN EXPERIMENTAL KP VALUE IN
LOW EARTH ORBIT DIFFER FROM THE
PLANETARY KP-INDEX AND CONTRIBUTE TO
FINDING A LAG TIME?

35. Ionizing Radiation
▶ Direct Ionizing Radiation:
Charged Particles
▶ Repel and attract
▶ Knock loose electrons
▶ Indirect Ionizing Radiation:
Photons
▶ Eject electrons from atoms
through photoelectric effect
and Compton scattering
Source: Biology Forums

36. Solarwinds and Geomagnetic Storms
▶ Solar Winds
▶ Continuous flow of
charged particles with
solar origin
▶ Geomagnetic Storms
▶ Magnetic response to
influxes of charged
particles are classified as
Geomagnetic Storms
▶ Metricized by the Kp-
Index
Source: Astronomy GCSE

37. Adverse Effects of Geomagnetic Storms
Our technology-based infrastructure
can be adversely affected by rapid
magnetic-field variations. This is
especially true during “magnetic
storms."
▶ Long-range radio communication
disrupted
▶ Increase in satellite drag
▶ Makes orbit difficult to control
▶ Satellite electronics can be damaged
▶ Hipparcos, solar panel degradation
▶ Astronauts/high-altitude pilots subjected
to increased levels of radiation.
▶ Magnetic-field variations can cause
blackouts
Source: Montana Space Grant Consortium

38. The Kp-Index
▶ A geomagnetic storm index (Kp-
index)
▶ Averaged magnetometer
readings
▶ 0-9 integer
▶ 1 = calm
▶ > 4 Geomagnetic Storm
▶ Now-cast, not forecast
LOCATION SPECIFIC!
Source: NOAA

39. Calculating the Planetary K-Index
▶ Average of 13 Location Specific
Data Values
▶ Accuracy an issue due to
enormous amount of location
specific factors.
▶ Location
▶ Season
▶ Magnetic Field Strength
▶ The global KP value system uses
formulas derived in the 1930’s,
before satellite observation was
even possible! (Outdated!)
Source: National Institute of Geology and Volcanology

40. Scientific Mission Goal:
▶ Develop experimental
“Kp-value” and compare
to the the Earth derived
index.
▶ LEO vs. Ground
▶ IS THERE A LAG?
▶ Magnetometer readings
(nT) converted to a Kp-
index
Conversion chart
for Boulder, CO Source: NOAA

41. Determining a Lag-time
Space-based
Ground-based
Fabricated graph of what we hope to find

42. Conclusions
1. Ionizing Radiation is harmful to spacecraft and subsystems.
2. IR is transported in Solarwinds that cause Geomagnetic Storms.
3. A Kp-Index is published characterizing Geomagnetic Storms.
4. Our project aims to compare an Experimental “Kp value” to the Kp-index.
5. Magnetometer readings and data transmission are important to mission.
6. Our project contributes to space weather forecasting.
7. This data will help develop prevention methods to avoid catastrophes associated
with Geomagnetic Storms.

43. Test Matrix
Structural:
Thermal Vacuum Testing:
-Standard: MIL_STD1540 B
-Min Range: -14 to 71 C
-Cycles: 8
Dwell Time: 1 hour min @ extreme temp after thermal stabilization
-Transition : <5C/minute
-Vacuum = 1x10-4 Torr
Random Vibration Testing
- Standard: Max Predicted vibration + 6 dB for 3 minutes, each of
3 axis
Sinusoidal Vibration
-Standard: Max Predicted vibration + 6 dB. Testing shall be
performed for content that isn’t covered by random vibration test
Shock Testing
-Shock: Max Predicted vibration + 6 dB, 3 times in both directions
axes
Software:
Software Validation Testing(Process)
1. Unit testing
1-2 inputs with 1 output. Smallest form of testing
to test low level functions independent of other code
1. Software integration and Verification
Subsystem Level testing. Used to expose
defects in interfacing/interactions between integrated
systems
1. Software Validation
Verifies that integrated system meets specified
requirements. Usually performed by independent
tester
43

44. Test Matrix
Power Characterization and Testing
Power Generation:
Measure voltage levels of P100 solar panels to confirm power
budget available matches Datasheet values
-Solar panels mounted on 3u CubeSat frame
-Panels in parallel wiring scheme
Battery Storage & Charging:
Verify BM-1 battery pack charges and maintains 7.4V level as stated
in data sheet
-Document time for charge/discharge
-Document power required for full charge
Power levels:
Verify voltage levels on power rails and subsystem inputs via
voltmeter
-Document power levels for various operations(Communications,
General Operations,etc)
Thermal Regulation
Temperature Sensing
Perform measurements with thermistors to ensure correct
values are read in mounted positions. Validate against
calibrated temperature source
Thermal System Logic
Validate Software logic w/temperature sensing data to ensure
thermal subsystem keeps spacecraft in operational limits.
ADACs Validation
Stabilization
Verify MAI-400 can overcome moments of inertia and stablize
CubeSat.
-Testing can be performed 1 dimensionally with on air bearing
table
-3 dimensional testing can be performed aboard Nasa’s Zero
Gravity aircraft, the Vomit Comet
Slew rates
Measure the slew rate of the CubeSat cause by MAI-400
-Data will be used to refine time limits in Concept of Operations
44

45. Risk Consequence Definitions
45

46. Risk Probability Definitions
46

47. Risk Matrix
47

48. 3U CubeSat Component Cost: $ 283,000
Programmatics
48

49. Program Schedule
49

50. Summary
- Goal: Measure lift/drag, magnetic fields,
radiation, record GPS, and actively
control descent into Earth’s atmosphere
- 2 Semester Duration
- Used Agile and sprint systems in order to
break a large project into several small
tasks
50

51. Back Up
51

52. Radiation Profile
Radiation Profile from AGILE Spacecraft
• Radiation will be strongest
over South Atlantic Anomaly
52

53. Time of Eclipse Calculations
Radius of Earth = 6378 km
Altitude = 350 Km
Inclination = 28.5 degrees
Beta Value = .3239 Radians
=18.56 Degrees
Alpha Value =.371 radians
=21.23 degrees
% Sunlight = 61.8%
% Eclipse =38.2%
T_eclipse =34.9 mins
T_sunlight = 55.1 mins
53

54. Initial Draft
Top ViewFront View Side View
54

55. -
Command and Data Handling 55

56. Command and Data Handling
-
56

57. Current Data Protocols
➢ UART
➢ I2C
➢ SPI
➢ Analog
Command and Data Handling 57

58. Propulsion VACCO AFRL
Function:
Provide propulsion to prolong mission life
Driving Features:
High Impulse yield COT thruster
➢ Self-contained integral controller,
propellant storage, propellant feed
system, heaters and sensors
➢ Over 200,000 thruster firings in a
simulated space environment
➢ Total altitude change…..3631 meters
➢ Total Impulse.....................1808 N/sec
➢ Standby Power…...……...0.055 Watts
➢ Peak Power.......................<15 Watts
➢ Dry Mass............................ 568 grams
➢ Propellant Mass ……....... 495 grams
➢ Total Mass .........................1,063 grams
618 N-sec/Liter Performance Density
58

59. Power
-
59

60. Power
-
60

61. Structure
Function:
➢ Housing and
protection from any debris,
radiation, and temperatures while
in LEO
Temperature Range: -170°C to 123°C
Mass: 255 grams
Volume: 340.5mm X 100mm X 100mm
Key Features:
➢ Frame: Aluminum 7075
anodized, hardcoat, and
Alodine 1200.
61

62. Communications
-
62

63. Communications
-
63

64. Thermal
-
64

65. ADACS
Maryland Aerospace MAI-400
Function: Stabilize & Point Rocky
Driving Requirements:
Plug and Play stand alone attitude control
system with superior flight heritage
Key components:
- Reaction Wheel
- Magnetorquer
- Star Tracker
- Horizon Sensor
➢ Mass: 694 grams
➢ Estimated Power :
Steady State/ Typical W: 3.17
(0.63amps @ 5V)
➢ Peak Wattage: 7.23 (145 amps
@ 5V)
➢ Volume: 10x 10 x 5.9cm
➢ Partners: Tuskegee University
65

66. ADACS cont… MAI-400 A La Carte
Attitude control
Reaction Wheels…………… 3 single axis
1108 mNms Momentum Storage @ 1000 rpm
Magnetorquer Rods………. 3 single axis
0.15/0.6/0.3 Am2 Moment @ 72% duty cycle
Integrated ,PCB board driven
66

67. ADACS cont… MAI-400 A La Carte
Positioning
Static Earth Horizon Sensor…1/60 arcminute accuracy
Star Tracker ……………...…..0.013/54 arcsec accuracy
67

68. GPS
Novatel OEM628 Triple-Frequency + L-Band GNSS Receiver
Highly accurate, Environmental tested
Compliant with MIL-STD 810G
- Accuracy: Time…………………… 20 ns RMS
Positional (TerraStar-C).............. 4 cm
- Initialization reliability……………… >99.9%
- Time to first fix: hot start ................. 35 s
cold start ................. 50 s
- Weight……………………………...... 37 g
- Power………………………………... 1.3 W
- Maximum Data Rate……………....100 Hz
68

69. Honeywell HMC2003 Magnetometer
Honeywell Magnetometer -Records magnetic
field fluctuations for science objective.
- Field Range: ±2 Gauss = ± 200 μT
- Sensitivity: 40 μG = ± 0.004 μT
- Power Requirements: 20 mA
Years of Comparable Earth Based Data Already
archived by NOAA.
69

70. Teledyne UDOS007-K Dosimeter
Teledyne UDOS007 - Measure Radiation Exposure
as part of science objective requirements.
Energy Range:
- Min: 1 MeV
- Max: 15 MeV
Sensitivity Range:
- Min: 12 µRads/step
- Max: 16 µRads/step
Power Requirements:
- 0.02 Watts

71. System Risks, Analysis, & Mitigation
71

72. System Risks, Analysis, & Mitigation
72

73. System Risks, Analysis, & Mitigation
73

74. System Risks, Analysis, & Mitigation
74