CanSat2015_2701_CDR_V01

Team Logo
Here
CanSat 2015 CDR: Team (2701 and KEYA INTERNATIONAL) 1
CanSat 2015
Critical Design Review (CDR)
Team # 2701
TEAM: KEYA INTERNATIONAL
VIT UNIVERSITY

Team Logo
Here
(If You Want)
Presentation Outline
Introduction
 Team Keya International
 Team organization
 Acronyms
System Overview
 System requirements
 System level cansat configuration trade and selection
 System concepts of operation
 Context diagram
 Physical layout-cansat
 Physical layout-Science vechicle
 Launch vehicle compatibility
Presenter: Ketan Gupta

Team Logo
Here
(If You Want)
Sensor Subsystem Design
 Science vehicle sensor subsystem overview
 Sensor subsystem requirement
 Science vehicle altitude sensor trade and selection
 Science vehicle impact force sensor trade and selection
Descent Control Design
 Descent control overview
 Descent control requirements
 Descent rate control strategy selection and trade
 Mechanism selection
 Metal selection
 Shape selection
 Descent rate calculations
 Assumptions

Team Logo
Here
(If You Want)
Mechanical Subsystem Design
 Mechanical subsystems overview
 Mechanical subsystems requirements
 Science vechicle egg protection trade and selection
 Mechanical layout of components
 Material selection
 Re-entry container science vechicle interface
 Structure survivability trades
 FEA for structural survivability
 Mass budget
 Tests performed
Communication And Data Handling Subsystem Design
 CDH overview
 CDH requirements
 Processor and memory trade and selection
 Science vechicle antenna trade and selection
 Radio configuration
 Science vechicle telemetry formats
 Activation of telemetry transmissions
 Locator device trade and selection

Team Logo
Here
(If You Want)
Electrical Power Subsystem
 EPS overview
 EPS requirements for Science vechicle
 Lander electrical block diagram
 Power budget
 External power control mechanism
 Power source trade and selection
 Battery voltage measurement
Flight Software Design
 FSW overview
 FSW requirements
 Re-entry container FSW overview
 Science vehicle FSW overview
 Software development plan

Team Logo
Here
(If You Want)
Ground Control System Design
 GCS overview
 GCS requirements
 GCS antenna trade and selection
 GCS software description
Cansat Integration And Test
 CIT overview
 Cansat integration
 Test performed
 Tests to be performed
Mission Operation And Analysis
 MOA overview
 MOA manual development plan
• Cansat integration
• Launch preparation
• Launch procedure
• Lemoval procedure
 Cansat location recovery

Team Logo
Here
(If You Want)
Management
 Cansat budget
 Sponsorship plans
 Program schedule
 Conclusions

Team Logo
Here
(If You Want)
Team Organization
NO. NAME YEAR OF
STUDY
POSITION CONTACT DETAILS
1. KETAN GUPTA 2nd year Team leader ketan.gupta2013@vit.ac.in
2. YASHVARDHAN 2nd year Alternate team leader yashvardhan2013@vit.ac.in
3. AMARENDRA ROUT 2nd year Member amarendra.rout2013@vit.ac.in
4. SAUMIK NANDI 2nd year Member saumik.nandi2013@vit.ac.in
5. SIDDHESH GOSAVI 2nd year Member siddhesh.gosavi2013@vit.ac.in
6. VEDANT KUMAR 4nd year Member vedant.kumar2011@vit.ac.in
7. VAIBHAV KUMAR SINGH 2nd year Member vaibhavcreed@gmail.com
8. M.KIRAN SAI REDDY 2nd year Member munnangikiran.sai2013@vit.ac.in
9. MANMEET SINGH BEHL 2nd year Member Manmeet.singh2013@vit.ac.in
10. JOE JACOB THOMAS 2nd year Member Joejacob.thomas2013@vit.ac.in

Team Logo
Here
(If You Want)
CanSat 2015 CDR: Team (2701 and KEYA
INTERNATIONAL)
9
MENTOR
Beth Timmons
TEAM ADVISOR
Dr. Jagannath Mohan
TEAM LEADER
Ketan Gupta
ALTERNATE TEAM
LEADER
Yashvardhan
Electronics design
team
Lead:Vedant kumar
Members
Amarendra rout
Saumik Nandi
M.Kiran Sai Reddy
Vaibhav kumar singh
Mechanical design
team
Lead: Siddhesh
gosavi
Members
Joe jacob thomas
Manmeet Singh

Team Logo
Here
(If You Want)
Acronyms
• SR- System requirement
• SS-System Subsystem
• DCS-Descent control system
• MS-Mechecnical Subsystem
• CDH-Communication and data handling
• VM- Verification Method
• A-Analysis
• I-Inspect
• T-Test
• D-Demonstration
• EP- Electric Power
• FSC-Flight Software of Container
• FSSV-Flight Software of Science Vehicle
• GCS-Ground Control System
Presenter: Yashvardhan

Team Logo
Here
Systems Overview
Ketan Gupta

Team Logo
Here
(If You Want)
Mission Summary
The Main Objective:
→The main purpose of Cansat is to provide egg safety from launch while sampling the atmospheric
composition during descent.
Other Objectives:
→ To carry the hen’s egg intact for the entire duration from launch to landing.
→ To control the descent of the Cansat container and maintaining the descend speed of 4-10 m/s.
→ The Container should hold the Science vehicle till deployment and after the container reaches certain
height after deployment, it should deploy the science vehicle containing the egg.
→ To control the descent of the science vehicle after its deployment from the container at the descend
speed of 4-10 m/s rotating blades are used(auto gyro recovery).
→ To predict the landing position of the science vehicle based on the sensor data.
→ To send the telemetry data to a central ground station.
→ To record the video from the camera attached to the science vehicle in nadir direction.
Bonus Objectives:
→ Use a three-axis accelerometer to measure the stability and angle of descent of the Science
Vehicle during descent. Sample at appropriate rate and store data for later retrieval.

Team Logo
Here
(If You Want) System Requirement Summary
CanSat 2015 CDR: Team (2701 and KEYA INTERNATIONAL) 13Presenter: Ketan Gupta
ID Requirements Rationale Priority Parent Children VM
A I T D
SR-1 Total mass of the CanSat should
be 600gms (excluding the egg).
Competition
requirement
High MS01,DCS2
x
SR-2 The science vehicle shall hold on
one raw hen’s egg which shall
survive launch, deployment and
landing.
Competition
requirement
High SS4
SR-3 The CanSat shall fit in the
envelope of 125mmx310mm
including the container.
Competition
requirement
High MS02,DCS1,
DCS2,DCS3 x
SR-4 The CanSat shall not have any
sharp edges and must be of
florescent color, pink or orange.
Competition
requirement
High MS03,MS05
x
SR-5 The CanSat shall deploy from the
rocket payload section.
Competition
requirement
High DCS1
x x
SR-6 All descent control devices shall
survive 50Gs of shock.
Competition
requirement
High DCS4,MS06
x
SR-7 Use of helicopter recovery
system with no fabric or material
between the blades.
Competition
requirement
High DCS3,MS04
x x x
SR-8 Mechanisms shall not use
pyrotechnics or chemicals
causing risk of setting vegetation
on fire.
Competition
requirement
High MS05, DCS4

Team Logo
Here
(If You Want) System Requirement Summary
ID Requirements Rationale Priority Parent Children VM
A I T D
SR-9 XBEE radios shall be used for
telemetry.
Competition
requirement
High SS8,FSSV01,
FSSV02,CDH10,
GC S02
x
SR-10 The science vehicle shall
transmit telemetry at 1Hz rate.
Competition
requirement
High GC S02, FSSV01
x
SR-11 The science vehicle shall have a
video camera installed and
recording the complete journey.
Competition
requirement
High SS7
SR-12 The descent rate of science
vehicle shall be less than 10m/s
and greater than 4m/s.
Competition
requirement
High DCS3
x
SR-13 All telemetry shall be displayed in
engineering units(meters,
meters/sec, Celsius etc).
Competition
requirement
High
x
SR-14 The science vehicle shall include
an easily accessible switch not
requiring removal from the
container.
Competition
requirement
High
x
SR-15 Cost of the CanSat shall be
under $1000.(excluding
ground support and analysis
tools)
Competition
requirement
High
SR-16 The CanSat and associated
operation shall comply with
the field safety regulations.
Competition
requirement
High DCS4,MS05

Team Logo
Here
(If You Want)
System Level CanSat Configuration
1.Choice of aluminium over steel: aluminium was chosen
over steel keeping in mind the mass constraints.
2.Science vehicle’s blades do not rotate until the vehicle is
out of the container: as during the testing we found that if we
switch on the blades inside the container then it strike the
interior of the container causing damage to the system.
3.Earlier the egg container had polythene as shock
absorber for egg: but due to unavailability and failure of
polythene bags in protecting egg during experiment,
polyurethane foam is used instead of polythene bags

Team Logo
Here
(If You Want)
This was the cansat system which we
considered but was rejected due to the
below mentioned reason:
The board we was using earlier was rectangle in
shape and we were bound to place in the shown
manner(green) yielding to its wear and tear
around the corner and edges but now we are
using round board. Even the overall structure
was unstable because the above part contained
blades and board which were less in weight
hence it resulted in vehicle falling upside down.

Team Logo
Here
(If You Want)
CanSat 2015 CDR: Team (2701 and KEYA INTERNATIONAL)
System Concept of Operations
Pre-Launch
Launch
CanSat
Post-
Launch
Pre-flight Briefing
Coming
Competition Area
Last Electronics
Controls
Locate CanSat
Sending and
Collecting Data
Open Umbrella
On CanSat
Launch Flight
Presentation PFR
Prepare PFR
Analyzing Data
Saving Data
Pre-flight
Operations
Last Mechanic
Controls
17

Team Logo
Here
(If You Want) System Concept of Operations
On CanSat
Leaving
CanSat from
Rocket
Launch
Rocket
Put CanSat
on Rocket
Off CanSat
Locate
CanSat
Calculate
collusion
force
Measuring
Height of
CanSat
Separate
Container
and Sc.
vehicle
Control of
descent
speed
Collecting
data by
ground
station

Team Logo
Here
(If You Want)

Team Logo
Here
(If You Want) Physical layout
Egg compartment
Sensor Board
Blades
Battery placement plate
20 cm
9.5 cm
22
cm
8cm
INTERNATIONAL)
23

Team Logo
Here
INTERNATIONAL)
24
22 cm
9.5 cm
2cm
8 cm
4 cm
3 cm
7 cm

Team Logo
Here
INTERNATIONAL)
25
Hook for attaching
parachute
container
29.5 cm
1.5 cm

Team Logo
Here
INTERNATIONAL)
26
Container

Team Logo
Here
(If You Want)
Launch Vehicle Compatibility
• Cansat structure is designed strictly keeping in
mind the size and weight restrictions.
• Maximum diameter of the Cansat re-entry container
is 12.5cm .
• Height of the CanSat is 31cm which will be
including the Container passive descent control
system.
• No electronic/mechanical control is employed to
push the cansat out of payload and is assumed that
once the rocket dismantles it will automatically slip
out of the payload bay.

Team Logo
Here
INTERNATIONAL)
28
Sensor Subsystem Design
Vedant Kumar
Ketan Gupta

Team Logo
Here
(If You Want)
INTERNATIONAL)
29
Sensor Subsystem Overview
Science payload Sub-System Overview
Presenter: Vedant Kumar
Battery Voltage Data
Microcontroller
(Atmega2560)
Pressure sensors
(BMP085)
Non-GPS altitude
Temperature
sensor
GPS sensors
(Global technology)
Accelerometer
(MPU9150)
Pressure sensor
Non GPS Altitude
External & internal
Temperature
sensor

Team Logo
Here
(If You Want)
INTERNATIONAL)
30
Sensor Subsystem Overview
Re-entry container Sub-System Overview
Servo motor
(Avionics)
Microcontroller
(Arduino pro mini)

Team Logo
Here
(If You Want) Sensor Changes Since PDR
GPS sensor
PDR choice- Robokits india GPS Sensor
Due to unavailability of GPS sensor from Robokits india, we changed the
GPS Sensor.
New GPS Sensor from Global top technology(g.top019)
Rationale-
- easy available
- simple coding
- high accuracy
INTERNATIONAL)
31

Team Logo
Here
Camera-
PDR choice-link sprite JPEG color camera
It doesn’t record video but only capture photo.
CDR choice-Super Mini high definition camera is selected as onboard camera.
Ratinale-
• High quality video at 640 x 480 VGA
• Small size 27x26x26mm
• Less weight(11g)
INTERNATIONAL)
32

Team Logo
Here
Servo motor:
We have included servo motor(Avionics AV9A) for separation of science payload &
re-entry container instead of electronic clippers.
Rationale-
• Easier than previous method.
• Less power consumption.
INTERNATIONAL)
33

Team Logo
Here
Altitude Sensor:
PDR Choice-Motorola(MPX6115A)
In CDR we are using same Bosch(BMP085) sensor to calculate the altitude.It can
calculate altitude, temperature,pressure through simple conversion equations.
Rationale-
• Power consumption is less.
• High accuracy
• Low cost
INTERNATIONAL)
34

Team Logo
Here
(If You Want)
INTERNATIONAL)
35
Sensor Subsystem Requirements
ID Requirements Guide
reference
Rationale Priority Parent(s) Child(ren) V M
A I T D
SS1 Measurement of barometric
altitude
21 It is required for telemetry HIGH CDH02 X X
SS2 Measurement of air
temperature(inside/outside)
21 Air condition of launch
location
MEDIUM CDH03 X
SS3 Measurement of battery voltage 21 Arduino microcontroller
operates at 3.3 V
HIGH CDH04
CDH08
CDH14
X
SS4 3-axis Acceleration sensor 21 To measure the stability
and angle of descent of
science vechile during
descent
HIGH SR-2 X
SS5 Audio beacon derived For recovery after
landing
MEDIUM
SS6 GPS location data derived To obtain the closest
position
HIGH CH01
SS7 Camera must have atleast VGA
resolution
27 For recording complete
descent
MEDIUM SR-11
SS8 Xbee radios 24 Data transfer HIGH SR-9 CDH11-14 X
SS9 Rotor rate sensor 21 Measuring the rotation
rate of auto gyro relative
to the stablised portion of
the cansat
HIGH X X X X
Ss10 Impact force of the science
vechile should be measured after
it is landed
derived To measure the impact
forces
HIGH CDH09 X X

Team Logo
Here
(If You Want)
INTERNATIONAL)
36
Altitude And Internal temperature
Sensor Summary
Bosch BMP085 is chosen as Non-GPS altitude sensor :
• Small Size
• Integrated Temperature Sensor
• Low cost
• Can be easily integrated with I2C bus
Manufacturer Model Accuracy Mass Power/voltage Dimensions
(mm)
A/D
BOSCH BMP085 ±1.0% 5g 0.5mA/5V 16.5*16.5 A
Type Range Accuracy Units
Altitude 9000-500 1.68 m
Temperature -20-(+65) 0.5
°C

Team Logo
Here
(If You Want)
INTERNATIONAL)
37
Sensor Summary
Temperature Calculation:
• X1=(UT-AC6)*AC5/215
• X2=MC*211 /(X1+MD)
• B5=X1+X2
• T=(B5+8)/24

Team Logo
Here
(If You Want)
INTERNATIONAL)
38
Sensor Summary
Pressure Calculation:
• B6=B5-4000
• X1=(B2*(B6*B6/212))/211
• X2=X1+X2
• B3=((AC1*4+x#)<<oss+2)/4
• X1=AC3*B6/213
• X2=(B1*(B6*B6/212))/216
• X3=((X1+X2)+2)/22
• B4=AC4*(unsigned long)(X3+32768)/215
• B7=((unsigned long)UP-B3)*(50000>>oss)
• if(B7<0x80000000){p=(B7*2)/B4}
• else{p=(B7/B4)*2}
• X1=(p/28)*(p/28)
• X1=(X1*3038)/216
• X2=(-7357*p)/216
• P=p+(X1+X2+3791)/24

Team Logo
Here
(If You Want)
INTERNATIONAL)
39
Sensor Summary
Barometric Altitude Calculation:

Team Logo
Here
(If You Want)
INTERNATIONAL)
40
Snapshot:

Team Logo
Here
(If You Want)
Process Sequence:
• Read temperature and pressure data from the sensor via I2C Protocol.
• Save the data to SD card through SPI
• Transmit same data via XBEE PRO
• Calculate the altitude on ground system using pressure obtained form
the sensor with the help of following equation:
INTERNATIONAL)
41

Team Logo
Here
(If You Want)
INTERNATIONAL)
42
Internal Air Temperature Sensor
Summary
• Air temprature sensor chosen- VTI TECH SCP1000
 High resolution
Model Physical Characteristic
s
Electrical Characteristic
s
dimensions weight Nominal
operating
resolution
range
Data
interface
VTITECH-
SCP1000
-- -- 2.4 – 3.33V 14 bits -20 -70˚C SPI
Type Range Accuracy Units
Temperature (-20)- 70 1 °C

Team Logo
Here
(If You Want)
INTERNATIONAL)
43
Camera Summary
• Footage will be stored on a 32 Gb micro SD card and downloaded after
recovery.
• Camera already has timestamp software installed.
• Battery life exceeds 1.5 hours.
Presenter: Vedant Kumaar
Module Physical Characteristics Electrical Characteristics
Dimensions
Weight
Nominal
operating
resolution
Set-up
Super Mini h
igh
definition ca
mera
27*22*26mm 11g 3.7V 640*480 plugged and play

Team Logo
Here
(If You Want)
INTERNATIONAL)
44
Camera Stabilization
Flight software shall stabilize camera through sensor analysis.
• Stabilization mechanism will consist mainly of:
- A magnetometer
- A rotating servo.
- A camera platform.
• The magnetometer shall determine the orientation of
camera.
• Based on the orientation, the continuous rotating servo shall
rotate to maintain constant camera orientation.
• Camera shall be placed on the camera platform.

Team Logo
Here
(If You Want)
INTERNATIONAL)
45
3-Axis Accelerometer Sensor
Trade & Selection
Accuracy
3-Axis Accelerometer chosen- MPU 9150
• Full scale range of selectable g
• High sensitivity
• Low power
• Low price
Model Sensing
axis
Range Output data
rate(bit)
Voltage
supply(V)
Current
supply(micro A)
Temp
range(˚C)
Price
LIS331HH X,Y,Z 6g,12g,24g 16 2.16-3.6 Min10 -40 to+85 $9.95

Team Logo
Here
(If You Want)
INTERNATIONAL)
46
Trade & Selection
Snapshot:

Team Logo
Here
(If You Want)
INTERNATIONAL)
47
Trade & Selection
Process Sequence:
• Read acceleration data from the sensor via I2C Protocol.
• Save the data to SD card through SPI
• Transmit same data via XBEE PRO

Team Logo
Here
Descent Control Design
Presenter Name :YASHVARDHAN

Team Logo
Here
(If You Want)
INTERNATIONAL)
49
Descent Control Overview
• The mechanism used for descending is a parachute and a helicopter recovery
system
• The parachute material is a rip stop nylon and it will be provided with spill holes to
reduce drift.
• The helicopter recovery system includes rotator blades made up of aluminum.
• Proper designing of parachutes and efficient choice of materials for the blades of
the recovery system will be of utmost importance for stabilization of system as well
as for recording data.
• The parachute will be connected to the re entry container carrying science vehicle.
• The rotating blades will be connected to the science vehicle inside the re-entry
container.
• Parachute will inflate automatically after being deployed from the rocket due to air
flow and to reduce the descent to around 10m/s.
• At a suitable height the science vehicle carrying an egg will separate from the
container and from then passive rotating blades will further reduce its descent rate
to less than 10m/s and more than 4m/s.
• The spill hole at the top will ensure continuous air flow through the parachute,
thereby stabilizing it and ensuring descent at required speeds.
Presenter: YASHVARDHAN

Team Logo
Here
(If You Want)
Descent Control Requirements
Presenter: YASHVARDHAN
ID REQUIREMENT RATIONALE PRIORITY PARENT CHILDREN
A
V
I
M
T D
DCS1 Container with parachutes
and science vehicle with
blades should occupy
allotted space
To ensure proper
fitting inside rocket
HIGH SR-3,SR-5 MS02
x x
DCS2 Carrier chute size such,
descent rate below 10m/s
Competition
requirement
HIGH SR-1,SR-3 MS01,FSC01
x
DCS3 Blades size longer than the
diameter of vehicle to
maintain the descent rate
between 4m/s-10m/s
Competition
requirement
HIGH SR-3,SR-
7,SR-12
x
DCS4 Material used light, durable
and inflammable
To minimize volume
requirement and for
safety purpose
MEDIUM SR-6,SR-
8,SR-16

Team Logo
Here
(If You Want)
Container Descent Control Hardware
Summary
• The container is orange in color as per competition
requirement.
• The container will survive 50 Gs of shock.
• A parachute with spill holes of rip stop nylon cloth(for
proper blocking of air and easy availability) will be
connected to the container to reduce its descend
velocity below 10m/s.
• The parachute is rigorously tested under various
weather conditions.

Team Logo
Here
(If You Want)
Summary
INTERNATIONAL)
52
Parachute testing was
conducted in our
college

Team Logo
Here
(If You Want)
Summary
INTERNATIONAL)
53
parachute

Team Logo
Here
(If You Want)
Payload Descent Control Hardware
Summary
• The science vehicle (payload) will separate from the
container at a suitable height after deployment.
• To stabilize the vehicle after separation helicopter
recovery system is used to maintain its descend rate
between 4-10m/s.
• The passive rotating blades used will be of
acrylene(light weight and easy availability).
• The science vehicle will be orange in color.
• The blades of the attached to the vehicle will have a
length of 20cm approx.

Team Logo
Here
(If You Want)
INTERNATIONAL)
55
Payload Descent Control Strategy
Selection
• The payload will be resting on the base
plate of the cylinder .
• The base plate will be attached to the
cylinder surface by means of hook arrangement .
Presenter: Siddhesh Gosavi
Base plate
Servo
Hook arrangement

Team Logo
Here
(If You Want)
Payload Descent Control Strategy
Selection
component Chosen Design Concept
Propeller Pitch • Pitch twist
Propeller Shape • Rectangular propeller
Propeller Material • Acrylic
Propeller Joint • Separate twist and bending joints
Propeller Folding Joint • Separate Rotational and Bending Joints
Main Shaft • Aluminum
Central Bearing • Flanged Steel Ball Bearing
INTERNATIONAL)
56

Team Logo
Here
(If You Want) Changes since PDR
1. PDR: Six blades were going to be used of shorter
length .
Change: Four long blades are going to be used.
Reason: Since we are going to use folded blades ,the
overall surface area is increased hence the four blades are
sufficient to provide the required lift.
2. PDR: Aluminum rod were going to be used.
Change: T shape aluminum channel are used.
Reason: T shape aluminum channel serve as good
base support which keeps the orientation of science
vehicle straight and prevents it from tilting. Besides they
can be easily machined and are light in weight as
compared to aluminium rods
INTERNATIONAL)
57

Team Logo
Here
(If You Want)
Descent Rate Estimates
As our container is working on a parachute based
descent mechanism, the size of the parachutes is fixed
by calculation from the following relation.
r = sqrt( (2 m g) / (π p Cd v^2) )
• where, π = 3.14159265359
• ρ = 1.146 kg/m3 (density of air at 35 °C )
• Cd =1.5 (drag coefficient of the chute for a hemisphere
chute)
• v =terminal velocity achieved (from mission required)
• r = radius of the chute
• g = acceleration due to gravity

Team Logo
Here
(If You Want) Descent Rate Estimates
Container(including science vehicle)
• Mass=600g(approx.)
• Velocity=4-10m/s(approx.)
• Radius before Cd consideration=18-29cm
• Radius after Cd consideration=29 cm
Assumptions
• Cd will not be 1.5 as parachute will not be completely
hemispherical.
• Spill hole stabilizes the cansat by allowing air to flow.
• The radius of the spill hole(3cm) has been finalized by
some tests performed from a height of ~50m and
descent rate is measured as 5.1m/s
CanSat 2015 CDR: Team (2701 and KEYA INTERNATIONAL) 59Presenter: Yashvardhan

Team Logo
Here
As our Science vehicle is working on helicopter recovery system , therefore some
calculation is required to measure the drag on the auto gyro blades and to attain the
desired descend rate.
ρ  1.225 kg/m3 (density of air)
Cd  Coefficient of drag (dependent on pitch angle)
D  Drag Force in Newtons (D=mg)
m  mass of science vehicle in kilograms
g  9.81 m/s2 (Acceleration due to gravity)
S  Surface area of single auto gyro blade (S=b∙c)
c  chord of autogyro blades in meters
N  number of blades
CanSat 2015 CDR: Team (2701 and KEYA INTERNATIONAL) 60Presenter: Yashvardhan

Team Logo
Here
Calculating the descent rate of the science vehicle
V=√(2*0.380*9.81)/(1.225*1.08*0.016m^2*4(blades))
=9.38 m/s
INTERNATIONAL)
61

Team Logo
Here
Configuration Altitude (m) Mass (g) Descent rate (m/s)
Science payload
and container
670-500 600 . Above 10 m/s
Science payload 500-0 380 . 9.38 m/s
Container 500-0
220(including
parachute) .
5.1 m/s
INTERNATIONAL)
62

Team Logo
Here
INTERNATIONAL)
63
Mechanical Subsystem Design
Siddhesh Gosavi

Team Logo
Here
(If You Want)
INTERNATIONAL)
64
Mechanical Subsystem Overview
• The cansat consists of a container and a science
vehicle. The science vehicle is totally contained in the
container.
• Whole can sat will be made using aluminum metal.
• Sensors are placed onto the egg container
appropriately.
• The Container shall be a florescent colour, pink or
orange and will use a parachute during its descent.
• The container will use a parachute and science vehicle
will use a helicopter recovery system.

Team Logo
Here
(If You Want)
Mechanical Subsystem
Changes Since PDR
1. PDR: Six blades were going to be used .
Change: Four blades are going to be used.
Reason: Since we are going to use folded blades ,the
overall surface area is increased hence the four blades are
sufficient to provide the required lift.
2. PDR: Aluminum rod were going to be used.
Change: T shape aluminum channel are used.
Reason: T shape aluminum channel serve as good
base support which keeps the orientation of science
vehicle straight and prevents it from tilting. Besides they
can be easily machined and are light in weight as
compared to aluminium rods.
INTERNATIONAL)
65

Team Logo
Here
(If You Want)
Mechanical Subsystem
Changes Since PDR
• The container-payload interface has been changed and
2 servos are being used
Reason-Earlier we were using electronic clips to separate
science vehicle and container but due to complicated
coding and was creating problem during seperation.
INTERNATIONAL)
66

Team Logo
Here
(If You Want)
INTERNATIONAL)
67
Mechanical Sub-System
Requirements
• Overview of mechanical sub-system requirements
– Use bullets or a table to demonstrate an understanding
of the mission requirements
• This chart may be expanded to multiple charts as
needed
• The purpose of the chart is to demonstrate to the
judges that the team understands the requirements that
apply to this sub-system
• Clearly indicate:
– Which Competition Guide Requirements are allocated to
this subsystem
– Any derived requirements for the subsytem
ID Requirement Rationale Parent Priority
A
V
I
M
T D
MS01 Total mass of the CanSat (Container and
Science Vehicle) shall be 600 grams +/-
10 grams not including the egg.
Not much mass can be carried in
space.
SR-1 HIGH X
MS02 The Container shall fit in the envelope of
125 mm x 310 mm including the Container
passive descent control system.
Should fit in the rocket during the
launch.
SR-3 HIGH X X
MS03 The Container shall be a florescent color,
pink or orange.
So that it is easily noticeable. SR-4 MEDIUM
MS04 The Science Vehicle shall use a helicopter
recovery system. The blades must rotate.
No fabric or other materials are allowed
between the blades.
SR-7 HIGH X
MS05 All electronic components shall be
enclosed and shielded from the
environment with the exception of
sensors.
Placement of Sensors and
Antennas have to be appropriate
for proper Transmission and
Reception.
SR-4 SR-8
SR 16
HIGH
MS06 All descent control device attachment
components shall survive 50 Gs of shock
Egg should not break during
landing.
SR-6 HIGH X

Team Logo
Here
(If You Want)
INTERNATIONAL)
68
Egg Protection Overview
• Details of how the egg will be protected during flight
and landing
Egg
Foam
Spring
The foam is fixed into the spring . Any motion in the foam will produce relative
motion in the spring.

Team Logo
Here
(If You Want) Egg Protection Overview
Advantages :
• One end of the spring will be fixed in the foam while the
other end will be soldered to the support stand.
• The foam and the spring system will minimize the
impact load on the egg.
• Whenever there is any disturbance or change in
orientation of vehicle ,the spring system will restore the
so that the egg always lies on the central axis of the
vehicle.
• The foam-spring system is very light in weight.
INTERNATIONAL)
69

Team Logo
Here
(If You Want)
Mechanical Layout of Components-
Science Vehicle
INTERNATIONAL)
70Presenter: Siddhesh Gosavi

Team Logo
Here
(If You Want)
Science Vehicle
• During the initial stage of flight the science vehicle is
enclosed in the cylindrical container.
• Clearance of 15 mm is provided between the blades and
the inner cylindrical surface
Reason: Clearance is given to avoid the interaction of
the blades with the cylindrical surface at the time of ejection.
INTERNATIONAL)
71
Hook for attaching chute
Science vehicle
Container
Folded blades

Team Logo
Here
(If You Want)
Science Vehicle
• Four aluminum channels are for providing the support
for the structure.
• The aluminum channel of T shape are selected because
of
1. Easy machining
2. Strong base support and
3. Light weight
• The electronic setup is mounted on the circular plate.
• The circular plate is then connected to the T Shape
channel through L and C brackets .
INTERNATIONAL)

Team Logo
Here
(If You Want)
Cylindrical container
• Material used-Aluminum
• Thickness:0.6mm
• Height :310mm
• Diameter:125mm
Aluminum is used due to its light weight and anti
corrosive nature. Aluminum sheet of 0.6mm was folded
and welded to obtain the required cylinder
INTERNATIONAL)
73
Front view of cylinder

Team Logo
Here
(If You Want)
INTERNATIONAL)
74
Container - Payload Interface
• The payload will be resting on the base
plate of the cylinder .
• The base plate will be attached to the
cylinder surface by means of hook arrangement .
Base plate
Servo
Hook arrangement

Team Logo
Here
(If You Want) Container - Payload Interface
• After the Cansat stabilizes and reaches the desired
altitude, the hook arrangement will be disengaged and
thus the base plate will fall off instantaneously.
• The disengagement will be done through servo
mechanism.
• Since the science vehicle is resting on the base plate , it
will also fall down with the separation of the base plate.
INTERNATIONAL)
75
Base plate
Rotation of hook

Team Logo
Here
(If You Want) Structure Survivability
Simulation:
Structural analysis was performed. During the simulation
impact force of 50Gs was applied on the cylinder and the
structural behavior under such instantaneous load
conditions was studied.
Results: It is inferred that the aluminum cylinder of the
given dimensions can withstand shock of 50Gs
INTERNATIONAL)

Team Logo
Here
(If You Want)
INTERNATIONAL)
77
Mass Budget
Container Weight (gm)
Mass of container 190
parachute 30
Science vehicle Weight (gm)
Mass of the body 100
Mass of electronics 50
Helicopter recovery
system
120
Egg and cushioning 100
Battery 70
Total mass 380
Total mass 660
Total mass excluding egg 600

Team Logo
Here
INTERNATIONAL)
78
Communication and Data Handling
Subsystem Design
Vedant Kumar
Amarendra Rout

Team Logo
Here
(If You Want) CDH Overview - Science Vehicle
• Arduino Mega is used as microcontroller board to process and control all the
communication, data acquisition and data handling.
• BMP085 sensor will give the temperature and pressure data. It will communicate
to microcontroller through I2C protocol.
• MPU 9150 is used to measure the 3 axis accelerometer data and it will also
communicate to microcontroller through I2C protocol.
• A Micro SD Card is used for storing all the sensor data. It will maintain the
backup of telemetry in case of a communication failure. Data is stored in SD
card through SPI mode, and hence SPI pins on Arduino are used for the same.
• GPS sends data serially to the Arduino and hence we use the Rx pin on
Arduino.
INTERNATIONAL)
79

Team Logo
Here
(If You Want) CDH Overview - Science Vehicle
• XBee Pro S1 is used as radio module that will telemeter data from science
vehicle to ground station. RF 2.4 GHz communication will be used through
Zigbee protocol (IEEE 802.15.4).
• Arduino communicate with XBee serially using TX3 pin in Arduino Mega. All the
data send to XBee serially.
INTERNATIONAL)
80

Team Logo
Here
(If You Want)
INTERNATIONAL)
81
CDH Overview - Science Vehicle
Arduino
Mega
BMP085
GPS
Micro
SD_Card
Xbee Pro
MPU9160
(Accelerometer)
Ground Station
Battery Voltage
I2C DATA
SPIMode
Serial
data
I2C DATA
ADC
Xbee Pro
servo motor

Team Logo
Here
(If You Want) CDH Overview – Re-Entry Container
• To perform the task of science vehicle deployment, an Arduino pro mini
is used with servo motor.
• It will communicate with servo motor serially
INTERNATIONAL)
82

Team Logo
Here
(If You Want) CDH Overview – Re-Entry Container
INTERNATIONAL)
83
Arduino
Pro mini
Servo
Motor
Serial data

Team Logo
Here
(If You Want) CDH Changes Since PDR
• In PDR, we have only used on chip Flash Memory, now a
micro_sd card is added.
INTERNATIONAL)
84Presenter: Vedant Kumar

Team Logo
Here
(If You Want)
INTERNATIONAL)
85
CDH Requirements- Science Vehicle
Presenter: Amarendra
ID Requirement Rationable Parent Priority VM
A I T D
CDH
01
Transmit GPS Data
Stream
Descent Telemetry
packet (transmitted
every 2 seconds)
SS6 HIGH x x
CDH
02
Transmit Altitude in
meters
Descent Telemetry
packet (transmitted
every 2 seconds)
SS1 HIGH X x
CDH
03
Transmit Air
Temperature in Celsius
Descent Telemetry
packet (transmitted
every 2 seconds)
SS2 HIGH x x
CDH
04
Transmit Battery
Voltage in Volts
Descent Telemetry
packet (transmitted
every 2 seconds)
SS3 HIGH X x x
CDH
05
Terminate Telemetry Terminate Telemetry
within 5 minutes of
landing.
HIGH X x x
CDH
06
Store Telemetry Data For Post Processing
in case of
Communication
Failure
LOW

Team Logo
Here
(If You Want) CDH Requirements – Science Vehicle
INTERNATIONAL)
86
ID ID Requirement Rationable Parent Priority VM
A I T D
CDH
07
CDH
07
Store Lander
Altitude
Measured
Descent
Telemetry
packet (stored
every 2
seconds)
HIGH x x
CDH
08
CDH
08
Store Lander
Battery Voltage
Descent
Telemetry
packet (stored
every 2
seconds)
SS3 HIGH X x
CDH
09
CDH
09
Storing the
Impact Force
Impact force
(stored when
science vehicle
hits the ground)
SS10 HIGH
CDH
10
CDH
10
Send stored
descent
telemetry to
Ground Control
For post-
processing
following
retrieval of
science vehicle
SR-9 HIGH x x

Team Logo
Here
(If You Want) CDH Requirements – Ground Station
INTERNATIONAL)
87
A I T D
CDH
11
Receive GPS Data
Stream
Descent Telemetry
packet ((received
every 2 seconds)
SS8 HIGH x x
CDH
12
Receive Altitude in
meters
Descent Telemetry
packet (received
every 2 seconds)
SS8 HIGH X x
CDH
13
Receive Air
Temperature in
Celsius
Descent Telemetry
packet (transmitted
every 2 seconds)
SS8 HIGH x x
CDH
14
Receive Battery
Voltage in Volts
Descent Telemetry
packet (received
every 2 seconds)
SS8, SS3 HIGH X x x

Team Logo
Here
(If You Want)
INTERNATIONAL)
88
Processor & Memory Selection
Microcontroller Processor
Speed(MHz)
Memory
Storage
Size(cm x
cm)
DATA
INTERFACE
Input Voltage Prize in
USD
(ATmega2560)
16 MHz 256 KB
Flash, 4 KB
EEPROM,
8KB SRAM
Diameter-
8.8 c.m
USART- 4,
SPI- 4, I2C-1,
Digital I/O Pins
– 54,
Analog Input
Pins- 16
7-12V
(recommended)
, 6-20 V (limit)
50.68
Arduino Pro Mini
328 5V(ATmega328)
16 MHz 32 KB
Flash, 1 KB
EEPROM, 2
KB SRAM
33mm(L)
x18 mm(W)
x 6mm(H)
USART- 1, I2C-
1, Digital I/O
Pins – 14,
Analog Input
Pins- 6
5-12V $18.95

Team Logo
Here
(If You Want) Processor & Memory Selection
Science Vehicle
• – Arduino Mega is chosen for the microcontroller.
• –Easy interfacing, sufficient digital outputs for data handling.
• –Low cost and size.
• –Sufficient modes of communication available.
Re Entry Container
• –Arduino pro mini is chosen for the microcontroller.
• – servo motor is interfaced with Arduino pro mini to perform the deployment.
INTERNATIONAL)
89

Team Logo
Here
(If You Want)
Processor & Memory Selection- SD
Card
2 GB, Micro-SD card is used for external memory
• The files in an SD memory card are stored using FAT16 .
• Micro –SD card is interfaced using the SPI bus the four channel Logic Level
Converter modules.
• Large amounts of data can be stored.
• Non-volatile.
• Easy to retrieve data on laptop.
INTERNATIONAL)
90

Team Logo
Here
(If You Want) Real-Time Clock Trade Selection
• DS3231 AT24C32 IIC RTC placed in science vehicle
– Low cost, with IIC RTC and inbuilt temperature compensated
crystal oscillator.
– AT24C32 memory chip( storage capacity 32K)
– Battery backup input for time-keeping if main power is interrupted.
– Operating voltage is 3.3V-5V.
– dimension 38mm(l)*22mm(b)*14mm(h)
INTERNATIONAL)
91Presenter: Amarendra

Team Logo
Here
(If You Want)
INTERNATIONAL)
92
Antenna Selection- Characteristics
• An integrated whip antenna (XB24-AWI-001) is selected for CanSat
which is used in XBee Pro S1 module.
Characteristics of antenna
Operating
Frequency
Power Gain Antenna
Type
2.4 GHz 60 mW 1.5 dBi Dipole

Team Logo
Here
(If You Want)
Antenna Selection- Performance &
mass
Performance:
Mass: 4g ( 0.15oz)
INTERNATIONAL)
93
Indoor Range 300 ft (100 m)
Outdoor/RF Line-of-Sight Range 1 mi (1600 m)
Transmit Power 60 mW (+18 dBm)
Receiver Sensitivity (1% PER) -100 dBm

Team Logo
Here
(If You Want)
Radio Configuration
General Configuration
 X-CTU Software will be used to configure the radio modules.
 Unicast mode will be used to avoid the interference with other radio modules.
 Configured to API mode for data transfer.
XBEE Requirements
 2.4 Ghz Series 1 XBEE Pro Radio.
 NETID/PANID set to the team number which is equal to 2701.
 Ground Station and Science Vehicle shall use the same NETID/PANID.
Transmission Control
 Transmissions will not start until Science Vehicle has released from container.
 Radio module on science vehicle will send data to ground station.
 The ground station software identifies packets from Science Vehicle.
 Telemetry Packet will contain start bit, Sensor Data, GPS Data and Checksum.
INTERNATIONAL)
94

Team Logo
Here
(If You Want) Telemetry Format
The following telemetry data will be send to ground station:
• TEAM ID
• MISSION TIME (s)
• Altitude (m)
• OUTSIDE_TEMP (°C)
• INSIDE_TEMP (°C)
• VOLTAGE (V)
• FSW_STATE
• 3 Axis accelerometer m/s2 (BONUS)
 The data rate of each packet shall be at 1 Hz.
 Science vehicle data will be stored to internal micro SD card.
 Telemetry data will be transmitted in ASCII format to ground station.
 Telemetry for the entire mission will be saved on the ground station computer as a .csv file
to be examined by judges.
INTERNATIONAL)
95

Team Logo
Here
TEAM ID
MISSION_TIME
ALT_SENSOR
OUTSIDE_TEMP
INSIDE_TEMP
VOLTAGE
FSW_STATE
BONUS
INTERNATIONAL)
96
Start Delimiter
Length Bytes
API ID
API Frame ID
Option Byte
Sensor and GPS
Data Packet
Checksum

Team Logo
Here
Science Vehicle Telemetry Format
 The telemetry data is transmitted as XBeeAPI Packet frame data packet. The
FSW puts transmission requests to Xbee radio on continuous 1Hz interval.
 Data Packet will be arranged in the following order
Start Byte => Sensor Data => GPS Data => Checksum
INTERNATIONAL)
97
Start Byte Sensor Data GPS DATA Checksum

Team Logo
Here
INTERNATIONAL)
98
Electrical Power Subsystem Design
Amarendra Rout

Team Logo
Here
(If You Want)
INTERNATIONAL)
99
EPS Overview
Presenter: : Amarendra
Design
considerations
• All power and
electrical
requirements are
met
• 1
Voltage
Regulation
• Use two
voltage
regulators for
3.3v and 5v for
level shifting
• 2
Power
Monitoring
• Done by
additional
hardware
• 3

Team Logo
Here
(If You Want) EPS Changes Since PDR
• Earlier we were using some battery voltage to drive auto
gyro motor and servo motor. Now we are just using
servo motor.
• Earlier our camera was also driving its power by the
battery. But now we are using mini camera with an
inbuilt rechargeable battery which we will recharge
before placing it in the base of the science vehicle.
INTERNATIONAL)
100

Team Logo
Here
(If You Want)
INTERNATIONAL)
101
EPS Requirements
Presenter: : Amarendra
A I T D
EP
01
Voltage Requirement
(3.3v 5v)
5 v required for
microcontroller ,
temperature ,pressure
sensor
For Auto gyro
3.3v required for flash
memory
_ HIGH x x
EP
02
Battery requirement
9v
For powering the flight
period
EP01 HIGH X x
EP
03
Measurement Accuracy
and Resolution
Voltage has to be
stored and measured
_ HIGH x x

Team Logo
Here
(If You Want)
ELECTRICAL BLOCK DIAGRAM (Science
Vehicle)
INTERNATIONAL)
102
Micro-
controller
At-Mega
2560 ADC
Buck
converter
5v
SPI
Interface
Mem
3.3 v
voltage
regulator
Buck
converter
5v
Voltage
Divider
Hardware
9V power
Supply
PRESSURE
SENSOR
External Power Switch will be present to control the power flow in the system. Battery
Voltage will be read by voltage tester interfaced with microcontroller.

Team Logo
Here
(If You Want)
INTERNATIONAL)
103
ELECTRICAL BLOCK DIAGRAM
(Container)
Arduino pro
mini
328
9.6V
Duracell
battery
Servo motor
AV9A
3.3v voltage
regulator
3.3v voltage
regulator

Team Logo
Here
(If You Want)
Payload Power Source
Trade Selection
INTERNATIONAL)
104

Team Logo
Here
(If You Want)
INTERNATIONAL)
105
Power Budget
Component
Voltage
[VDC]
Current
[mA]
Power
[mW]
Duty Cycle
[min.]
Energy
[mWh]
Arduino Mega 5 50 250 10 42
GPS 3.3 25 82.5 10 14
BMP085 3.3 0.1 0.33 10 0
MPU9150 3.3 0.1 .33 10 0
XBEE Tx 2.8 – 3.4 215 709.5 6 83
XBEE Rx 2.8 – 3.4 55 181.5 6 18
Motor 5 300 1500 1 25
Buzzer 5 8 40 180 120
Total 334
Available 750
Souce/uncer
-tainity
datasheet
datasheet
datasheet
datasheet
datasheet
datasheet
datasheet
datasheet

Team Logo
Here
(If You Want)
INTERNATIONAL)
106
Power Bus Voltage Measurement
Trade selection
Battery Voltage is measured by giving
a high impedance voltage divider without
sourcing and then interfaced to the
ADCport

Team Logo
Here
INTERNATIONAL)
107
Flight Software (FSW) Design
M.Kiran Sai Reddy

Team Logo
Here
(If You Want) FSW Overview
• Arduino is used as the working environment for lander and carrier
functions.
• Software will control the time at which the parachute of the science
vehicle and the propellers start working.
• This is done depending on the altitude of the science vehicle
• After the propellers start working at the required height the data
recorded by the sensors is stored in the SD card in the board.
• Communication with the ground center is maintained with the help
of xbees connected initially.
• This data is plotted on real time graphs using matlab.
• The FSW for the Science vehicle will to collect data from the
altitude sensor, impact sensor and from all the other sensor and
store it onto the onboard memory so as to be analyzed later.
INTERNATIONAL)
108Presenter: M.Kiran Sai Reddy

Team Logo
Here
• The release of the Science vehicle is done by the Rotary motion.
• Overview of the design
– FSW Architecture
• Initialise the network and check errors
• Initialise sensors and check errors
• Initialise device working and check errors
INTERNATIONAL)

Team Logo
Here
INTERNATIONAL)
110
Micro-
controller
At-Mega
128 ADC
Buck
converter 5v
SPI
Interface
Mem
3.3 v voltage
regulator Buck
converter 5v
Voltage
Divider
Hardware
9V power
Supply
PRESSURE
SENSOR
Presenter: M.Kiran Sai Reddy

Team Logo
Here
(If You Want)
INTERNATIONAL)
111
FSW Requirements
• Overview of mechanical sub-system requirements
• Use bullets or a table to demonstrate an
understanding of the mission requirements
• This chart may be expanded to multiple charts as
needed
• The purpose of the chart is to demonstrate to the
judges that the team understands the requirements
that apply to this sub-system
• Clearly indicate:
– Which Competition Guide Requirements are allocated
to this subsystem
– Any derived requirements for the subsytem

Team Logo
Here
(If You Want)
INTERNATIONAL)
112
Software(re-entry Container) Flow
Diagram
Stabilize the
environment for
deploying Science
vehicle
START

Team Logo
Here
(If You Want)
INTERNATIONAL)
113
Software(Science vehicle) Flow
Diagram
START
Collect
Accelerometer
X,Y,Z values,
Battery Voltage
Convert pressure value
to Height, Find the net
force on Science
vehicle by
superposition of X,Y,Z
values of acceleration
Collect values
from all other
sensors
Store Data
Packets in
assigned
memory

Team Logo
Here
(If You Want) FSW Requirements
ID Requirements Rationale Priority A I T D
FSSV01 For testing sample programs will
be made to simulate significant
events such as the need for
separation and approaching
ground to ensure the appropriate
action is taken
Our separation
mechanism and
other things like it
need to be tested
before actual drop
testing.
high X X X
FSSV02 Data will be sampled for all
subsystems except for
accelerometer at rate of at least
0.5 Hz
Transmission must
occur every 0.5 Hz
so this will ensure
new data for all
subsystems
medium X X X
FSSV03 Software shall back-up all data read on
a SD-CARD.(BOTH)
The Arduino
microcontroller does
not have enough
on-board memory
so we have selected
an external module.
medium X X X
FSSV04 Software shall keep a log of important
flight events and subsystems
(BOTH)
Will be used at tests to spot errors and
also it will aid us in interpretetion of
sensor data
medium X X X
FSSV05 Telemetry will include Altitude in meters
above sea level, Air Temperature,
Battery
voltage and flight state as well as
mission
time
Necessary telemetry data will be
recorded
high X X X
INTERNATIONAL)

Team Logo
Here
(If You Want) FSW Changes Since PDR
NO changes were made since PDR
INTERNATIONAL)

Team Logo
Here
(If You Want)
INTERNATIONAL)
116
Sensors
• Pressure Sensor:
1) Interfaced via ADC
2) Sampled at 50kHz
• Temperature Sensor: VTI TECH SCP1000
2) Sampled at 50kHz.
• Battery Voltage Sensor:
2) Sampled at 50kHz.
• GPS:
1) Interfaced via
2) Sampled at 1Hz.

Team Logo
Here
(If You Want)
INTERNATIONAL)
117
Sensors
• Altitude Sensor : Motorola
• 3-Axis Accelerometer : LIS331HH
1) Interfaced via ADC.
2) Sampled at 100Hz.
• Memory : Memory chip is interfaced via SPI
A total of 90 KB of accelerometer data is stored for a flight time of 5 minute.
A total of 1.5 KB of sensor data is stored for a flight time of 5 minute.

Team Logo
Here
(If You Want) FSW for science vehicle
INTERNATIONAL)
118
Sensors
FSW (For Science
vehicle)
Antenna
Memory

Team Logo
Here
(If You Want) FSW for carrier and container
INTERNATIONAL)
119
FSW (for re-entry
Container)
Stabilize the environment for
deploying of Science vehicle

Team Logo
Here
(If You Want) CanSat FSW State Diagram
INTERNATIONAL)
120
Launching
After
launch
detachment
Science
vehicle
And
container
landing

Team Logo
Here
INTERNATIONAL)
121
Ground Control System (GCS) Design
Vaibhav Kumar Singh
Saumik Nandi

Team Logo
Here
(If You Want)
INTERNATIONAL)
122
GCS Overview
GCS Laptop System Xbee Explorer
Board – via USB
XBEE-Pro Module
Science Vehicle

Team Logo
Here
(If You Want)
• GCS is used for the real-time plotting of the data
received from the CANSAT. The software indicates the
phases of flight, i.e. pre-launch, ascending, deployment,
descending, etc. of the CANSAT.
INTERNATIONAL)
123

Team Logo
Here
(If You Want) GCS Changes Since PDR
• There are currently no changes made since the PDR.
INTERNATIONAL)
124

Team Logo
Here
(If You Want)
INTERNATIONAL)
125
GCS Requirements
Presenter: Vaibhav Kumar Singh
Saumik Nandi
ID Requirement Rationale Priority Parent Children
VM
A I T D
GCS01 Antenna Placement : The
Antenna must point
upwards, towards the
CANSAT.
For better signal
reception.
medium none GCS02
GCS03
x x
GCS02 Computational
requirements : Data is
received at 1 Hz.
Computational
speed is not a big
issue. (Assuming
GCS laptop has a
reasonably fast
processor) .
low GCS01 none x
GCS03 Power Requirement :
Should be able to receive
and display data for about
4 hrs.
GCS has to be
ready always fort
he communication.
Not a big issue as
ample power is
available.
medium GCS01 GCS05 x x x
GCS04 Analysis Software
requirements : Should
support MATLAB.
To be able to run
analysis software
high None None x x x
GCS05 Mission operations :
Includes the detection of
various phases by the
GCS .
To be able to
distinguish
between various
states of flight.
medium Medium GCS03 X x x

Team Logo
Here
(If You Want)
INTERNATIONAL)
126
GCS Antenna
• An integrated whip antenna (XB24-AWI-001) is selected for CanSat which
is used in XBee Pro S1 module.
• The antenna is placed on the XBee itself.
• The coverage of the Antenna is around 1600m ( Line of Sight range).
Xbee antenna

Team Logo
Here
(If You Want)
• Distance link performance and margins :-
INTERNATIONAL)
127
Indoor Range 300ft (100m)
Outdoor/RF Line-of-Sight Range 1 mi (1600m)
Transmit Power 60 mW (+18dBm)
Receiver Sensitivity (1% PER) -100dBm

Team Logo
Here
(If You Want) GCS Command Screen (GUI)
INTERNATIONAL)
128

Team Logo
Here
(If You Want) Telemetry (Snapshots)
INTERNATIONAL)
129
GPS Real-time telemetry data :-

Team Logo
Here
(If You Want)
INTERNATIONAL)
130
Temperature and Pressure Real-time telemetry data :-

Team Logo
Here
(If You Want)
INTERNATIONAL)
131
XBee Configuration 1 :- Xbee Configuration 2 :-

Team Logo
Here
(If You Want)
INTERNATIONAL)
132
Base Station :-

Team Logo
Here
(If You Want)
INTERNATIONAL)
133
Science Vehicle :-

Team Logo
Here
(If You Want) GCS Software
• The Software development environment taken is
MATLAB.
• There is no use of COTS software.
• The Data receiving from XBEEs is done via USART.
- Successfully completed since PDR.
• Currently GUI software under Development.
• Data Archiving is done in .csv format (comma separated
value file)
- Successfully completed since PDR.
- The telemetry data file shall be named as follows:
CANSAT2015_TLM_<TEAM_ID>.csv
INTERNATIONAL)
134

Team Logo
Here
INTERNATIONAL)
135
CanSat Integration and Test
MANMEET SINGH BEHL

Team Logo
Here
(If You Want)
INTERNATIONAL)
136
CanSat Integration and Test Overview
Cansat has following subsystems:
1 Mechanical Subsystem
2 Decent Control System
3 Sensor and Data Communication System
4 Electrical Power Subsystem
5 Software Subsystem
SYSTEM LEVEL TESTS ON THE INTEGRATED CANSAT:
1 Clearance Test
2 Weight Test
3 Body Strength
4 Shock Absorption Test
5 Decent Rate Controller(Parachute and Auto-Gyro)
6 EPS Testing
7 Sensor Testing
8 FSW Testing
9 Detachment Of Science Vehicle
10 Communication Linking
11 GCS Testing
12 Handling Data
13 Testing The Integrated Model

Team Logo
Here
(If You Want)
INTERNATIONAL)
137
SUBSYSTEM SEQUENCE INTEGRATION:
1 Design and build payload :
• Re-entry Container is designed.
• Science Vehicle is accommodated inside the container.
2 Decent Control System:
• Re-entry container is attached with a parachute to control decent rate to 4-10m/s.
• Auto-Gyro mechanism used to control the science vehicle.
3 Design of integrated board :
• Coordination of sensor with FSW.
4 Development of FSW:
• Coordinate output pin with EPS.
5 Design and Build Ground Station
• Data communication with the help of XBEE Pro.
• Development of our own ground station.

Team Logo
Here
(If You Want)
INTERNATIONAL)
138
TEST EQUIPMENT AND ENVIRONMENT
MECHANICAL:
1 High rise building to conduct drop and decent test(70m).
2 Use of Annsys software to check the survivability of structure experimentally.
3 Egg Protection test:
• Drop Test(6-7m).
• Stress values were obtained by stacking weights on the egg canister.
• Proper positing of egg to all only longitudinal force.
ELECTRONICS and FSW:
1 Verify altitude calculation(college building 15th floor).
2 Temperature Testing:
• Using thermacol sheets.
• Vacuum chambers.
3 Sending data to ground station using XBEE Pro:
• Sending telemetry through moving cars.
• Sending telemetry from distances.
4 LDR:
• By varying light intensity.

Team Logo
Here
(If You Want) Sensor Subsystem Testing Overview
The testing for the sensor subsystem will include the following:
1.Non GPS Altitude Sensor:
A Testing Description:
• Interfacing with microcontroller
• variation of altitude(comparing with GPS)
B Test Constraints:
• Sensor availability
• GPS should be already tested
C Result Criteria:
• Receiving data in the proper order
• Variation in GPS and Non-GPS measurer should be less(<4m)
D Result:
• Pass, Accuracy achieved 3.2m
INTERNATIONAL)
139

Team Logo
Here
2.Temperature Sensor:
• Testing with ice placed in isolated thermocol container
• Cross checked with thermometer.
B Test Constraints:
• Preventing it from getting wet.
C Result Criteria:
• Difference in reading should be less than 0.8 degree Celsius
D Result:
• Passing accuracy achieved when properly caliberated.
INTERNATIONAL)
140

Team Logo
Here
3.GPS Sensor:
• Interfacing with microcontroller
• Data collected from travelling car.
B Test Constraints:
• GPS availability in circuit board.
C Result Criteria:
• Reception of data in the proper format
D Result:
• Pass
INTERNATIONAL)
141

Team Logo
Here
(If You Want)
INTERNATIONAL)
142
3-Axis Accelerometer Testing
• Checking for acceleration values(eg: lift etc)
• Interfacing with the microcontroller
B Test Constraints:
• Moving of microcontroller and accelerometer with source
C Result Criteria:
• Reception of data in the proper format
D Result:
• Pass

Team Logo
Here
(If You Want)
INTERNATIONAL)
143
Light Sensor Testing Overview
• Confirm sensitivity
• Detection of range provided by the datasheet
B Test Constraints:
• Varying the light intensity
• Varying the light spectrum( U.V, infrared etc)
C Result Criteria:
• Overall accuracy of 90% is needed
D Result:
• Pass

Team Logo
Here
(If You Want) DCS Subsystem Testing Overview
• Throwing of object(650gm) from height(70m) attached with parachute
• Stabilizing object using auto-gyro recovery.
• Unfolding of propellers
B Test Constraints:
• Attaining appropriate height for releasing parachute and auto-gyro.
C Result Criteria:
• Decent speed of 4-10m/s should be achieved
• Parachute should unfold itself without shroud lines entangling
D Result:
• Partially pass(shroud was entangling)
INTERNATIONAL)
144

Team Logo
Here
(If You Want)
Mechanical Subsystem Testing
Overview
• 30G’s equivalent force and 15G’s of acceleration is applied
• Separation of re-entry container and science vehicle
• Egg protection system
• Compatibility of CanSat in provided rocket envelope
B Test Constraints:
• Strength tested in both longitudinal and latitudinal directions(experimentally and practically)
• Actual friction characteristics remain undetermined
• Launch location may have different ground softness and hence different impact force
• Error may come in the metal container’s cylindricity due to human error
C Result Criteria:
• Structure should be able to withstand the load without failure and low distortions
• Capacity to hold load maximum load possible(700gm)
• Egg should be recovered safely
D Result:
• Partially pass(Compatibility of CanSat cannot be determined here)
INTERNATIONAL)
145

Team Logo
Here
(If You Want) CDH Subsystem Testing Overview
• Communication link tested by sending and receiving data(XBEE Pro)
• Range of buzzer tested
• Arduino board used for testing SD card
B Test Constraints:
• XBEE Pro module, GCS software
• Buzzer with sufficient battery
• SD card reader, SD card , Arduino board
C Result Criteria:
• Reception of data without any error
• Buzzer should be audible within range of 100m
• Data should be readily accessible and not corrupted.
D Result:
• Pass
INTERNATIONAL)
146

Team Logo
Here
(If You Want) EPS Testing Overview
• Use of potentiometer for checking regulated output of external voltage applied(9v)
• Battery life is tested using buzzer to drain it
B Test Constraints:
• Op-amp,Resistors,9v battery and potentiometer
• Buzzer, stop watch and battery
C Result Criteria:
• For 9v input regulated 5v should be obtained
• Buzzer should buzz for minimum of 5hrs
D Result:
• Pass(Battery Life:5hrs 30min)
INTERNATIONAL)
147

Team Logo
Here
(If You Want) FSW Testing Overview
• Continuity Test
• State Transition Test
• Data Recovery Test
B Test Constraints:
• The GCS along with the Arduino IDE is used to receive the data.
• All subsystems excluding the GCS are required
C Result Criteria:
• The microcontroller should not get struck in an infinite loop
• Transition rate found to be 1s without producing errors
• Ensure that this software is properly transitioning between flight states
• No data is lost in the event of a power loss
D Result:
• Pass
INTERNATIONAL)
148

Team Logo
Here
(If You Want) GCS Testing Overview
• CanSat circuit is powered on and monitored through the GCS
• Collecting the data from the CanSat over an hour
• GCS is monitored while the CanSat is 100m away from ground station
B Test Constraints:
• FSW and CDH subsystem are required
• Battery backup of laptop should be more than 2hrs
C Result Criteria:
• Data should be received and graphed in real time
• The link between the CanSat and GCS will continue until the maximum range is reached
• The GCS software should run continuously
D Result:
• Data was successfully received by the GCS
• No problem aroused during an hour period of testing
INTERNATIONAL)
149

Team Logo
Here
CanSat 2015 CDR: Team (2701 and KEYA 150
Mission Operations & Analysis
JOE JACOB THOMAS

Team Logo
Here
(If You Want)
INTERNATIONAL)
151
Overview of Mission Sequence of
Events
CanSat 2015 PDR: Team (Number and KEYA
INTERNATIONAL)
151
Overview of Mission Sequence of
Events
Arrive
Setup
Ground
station crew
Perform
CANSAT fit
check
Perform way
CANSAT
crew
Score mission
and retrieve
CANSAT part
Recovery
crew
Provide field
judge with
score card
Recovery
crew
Monitor
telemetry
during descent
Ground control
crew
Initiate when
instructed
Mission
Control officer
Prepare and
test CANSAT
crew
Integrate with
rocket and
pad CANSAT
crew
Initiate telemetry
transmission with
line judge ground
station crew
Confirm
telemetry
reception
Control officer
Deliver
telemetry to
field judges
ground
station crew

Team Logo
Here
(If You Want)
INTERNATIONAL)
152
Field Safety Rules Compliance
• The mission operation manual will be developed based on
the provided competition mission operation manual
• The mission operation will include the following
 Configuring the ground stations
 Repairing the CANASAT
 Integrating CANSAT with the rocket
 Launch preparation procedure
 Launch procedure
 Removal procedure
• Each section begins at start of new page
• Two finalized copies will be assembled into three ring
binders
• The mission operation manual will be used in prelaunch
rehearsal activities

Team Logo
Here
(If You Want)
INTERNATIONAL)
153
CanSat Location and Recovery
• Reentry container recovery
– We will use shiny and bright colored parachute so that
we can spot it from some distance
– Besides this all team members will be carefully watching
the descent of the reentry container
• Science vehicle recovery
– Science will have a buzzer inside it which will activated
after the landing
– We will use shiny and bright colored propellers so that
the vehicle is easily spotted
– We will use a GPS sensor that will give us the exact
coordinates

Team Logo
Here
(If You Want)
INTERNATIONAL)
154
CanSat Location and Recovery
• Return address leveling will be placed in visible area on
each component of the CANSAT and include –
– Team name
– Mailing address
– Phone number
– Email address

Team Logo
Here
(If You Want) Mission Rehearsal Activities
• Ground station radio link check procedures
– It was done after sending a simple data to Xbee from a
distant PC. Then the same data was send from Xbee
transmitter to the distant PC. The process was completed
without any issues.
– Loading the egg payload:- the egg protection system was
tested by dropping from various heights .To check the
cushion material(the orientation of the egg should be
such that only longitudinal force is applied on the egg)
– Powering on/off the CanSat-an external switch is used to
power on and off the CanSat
– Launch configuration preparation :-complete rehearsal is
projected to begin on 28th of april
INTERNATIONAL)
155

Team Logo
Here
(If You Want) Mission Rehearsal Activities
• Loading the CanSat in the launch vehicle
• The prototype test launches (balloon test) will begin on 28th of April
• Telemetry processing ,archiving, and analysis
• We have already tested the sensors individually , a final test of the
prototype will be conducted on 28th April
• Recovery
• We have tried to locate it using parachute and propellers colors. With
buzzer it will be conducted on 28th of April
• Description of written procedures developed/required
• Development environment for GCS is MATLAB , currently under
development
• FSW is under development code is written using Arduino IDE
INTERNATIONAL)
156

Team Logo
Here
INTERNATIONAL)
157
Requirements Compliance
JOE JACOB THOMAS

Team Logo
Here
(If You Want) Requirements Compliance Overview
• The current design is compliment to all mission requirements
• Components overview
– Total mass under limit requirement
– Re-entry Container fully contains science payload
– CanSat fits in envelope of 125mm x 310mm
– No lithium polymer battery was used
– Electronics well enclosed and protected
– CanSat was designed to meet descent rate requirements
– CanSat contains all required sensors
– Xbee radios configured according to requirements
– external power connection is available
– No material is used between the blades
– The structure has been designed to survive 30Gs of shock and 15Gs of
acceleration
– All descent control shall survive 50 Gs of shock
INTERNATIONAL)
158

Team Logo
Here
(If You Want)
INTERNATIONAL)
159
S
NO.
REQUIREMENTS COMPLY/NO
COMPLY/PARTI
AL
X-REF SLIDES
DEMONSTRATIN
G COMPLIANCE
TEAM COMMENTS OR NOTES
1. Total mass of the CanSat (Container and Science Vehicle)
shall be 600
grams +/- 10 grams not including the egg.
comply 77
2. The Science Vehicle shall be completely contained in the
Container. No
part of the Science Vehicle may extend beyond the
Container
comply 25
3. The Container shall fit in the envelope of 125 mm x 310
mm including the
Container passive descent control system. Tolerances are
to be included to
facilitate Container deployment from the rocket fairing.
comply 25,22
4. The Container shall use a passive descent control system.
It cannot free
fall. A parachute is allowed and highly recommended.
Include a spill hole to
reduce swaying.
comply 23,24
5. The Container shall not have any sharp edges to cause it
to get stuck in the
rocket payload section.
comply 12
6. The Container shall be a florescent color, pink or orange comply 51

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTI
AL
X-REF SLIDES
DEMONSTRATI
NG
COMPLIANCE
7. The rocket air frame shall not be used to restrain any deployable
parts of the CanSat.
comply 19-23
8. The rocket air frame shall not be used as part of the CanSat
operations.
comply 19-23
9. The CanSat (Container and Science Vehicle) shall deploy from the
rocket
payload section
comply 21-22
10. The Container or Science Vehicle shall include electronics and
mechanisms
to determine the best conditions to release the Science Vehicle
based on
stability and pointing. It is up to the team to determine appropriate
conditions for releasing the Science Vehicle.
comply 54
11. The Science Vehicle shall use a helicopter recovery system. The
blades
must rotate. No fabric or other materials are allowed between the
blades.
comply 55-57
12. All descent control device attachment components shall survive 50
Gs of
shock.
comply 76,51
INTERNATIONAL)
160

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTI
AL
X-REF SLIDES
DEMONSTRATIN
G COMPLIANCE
13 All descent control devices shall survive 50 Gs of shock. comply 76,51
14 All electronic components shall be enclosed and shielded from the
environment with the exception of sensors.
comply 24,25
15. All structures shall be built to survive 15 Gs acceleration. comply 51
16 All structures shall be built to survive 30 Gs of shock. comply 51,76
17 All electronics shall be hard mounted using proper mounts such as
standoffs, screws, or high performance adhesives.
comply 23,24
18 All mechanisms shall be capable of maintaining their configuration or
states under all forces
comply 51,76
19
Mechanisms shall not use pyrotechnics or chemicals. comply 99
20
Mechanisms that use heat (e.g., nichrome wire) shall not be exposed to
the outside environment to reduce potential risk of setting vegetation
on fire.
comply NA
INTERNATIONAL)
161

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTIA
L
X-REF SLIDES
DEMONSTRATIN
G COMPLIANCE
21 During descent, the Science Vehicle shall collect and telemeter air
pressure (for altitude determination), outside and inside air temperature,
flight
software state, battery voltage, and bonus objective data (accelerometer
data and/or rotor rate).
comply 78
22 The Science Vehicle shall transmit telemetry at a 1 Hz rate. comply 78
23 Telemetry shall include mission time with one second or better resolution,
which begins when the Science Vehicle is powered on.
comply 78-97
24 XBEE radios shall be used for telemetry. 2.4 GHz Series 1 and 2 radios
are
allowed. 900 MHz XBEE Pro radios are also allowed..
comply 78-97
25 XBEE radios shall have their NETID/PANID set to their team number
(decimal).
comply 78-97
26 XBEE radios shall not use broadcast mode. comply 78-97
INTERNATIONAL)
162

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTI
AL
X-REF SLIDES
DEMONSTRATIN
G COMPLIANCE
27 The Science Vehicle shall have a video camera installed and recording
the complete descent from deployment to landing. The video recording
can start at any time and must support up to one hour of recording.
comply 43
28 The video camera shall include a time stamp on the video. The time
stamp
must work from the time of deployment to the time of landing.
comply 43
29 The descent rate of the Science Vehicle shall be less than 10
meters/second and greater than 4 meters/second.
comply 49
30 During descent, the video camera must not rotate. The image of the
ground shall maintain one orientation with no more than +/- 90 degree
rotation.
comply 43
31 Cost of the CanSat shall be under $1000. Ground support and analysis
tools are not included in the cost.
comply 167
32 Each team shall develop their own ground station comply 121
INTERNATIONAL)
163

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTI
AL
X-REF SLIDES
DEMONSTRATIN
G COMPLIANCE
33 All telemetry shall be displayed in real time during descent.. comply 78
34 All telemetry shall be displayed in engineering units (meters,
meters/sec,Celsius, etc.)
comply 78
35 Teams shall plot data in real time during flight on the ground station
computer.
comply 78
36 The ground station shall include one laptop computer with a minimum
of two hours of battery operation, XBEE radio and a hand held or table
top
antenna.
comply 121
37 The ground station shall be portable so the team can be positioned at
the
ground station operation site along the flight line. AC power will not be
available at the ground station operation site.
comply 121
38 The Science Vehicle shall hold one large raw hen’s egg which shall
survive launch, deployment and landing.
comply 69
INTERNATIONAL)
164

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTI
AL
X-REF SLIDES
DEMONSTRATIN
G COMPLIANCE
39 Both the Container and Science Vehicle shall be labeled with team
contact information including email address.
comply NA
40 The CanSat flight software shall maintain and telemeter a variable
indicating
its operating state. In the case of processor reset, the flight software
shall
re-initialize to the correct state either by analyzing sensor data and/or
reading stored state data from non-volatile memory. The states are to
be
defined by each team. Example states include: PreFlightTest(0),
LaunchWait(1), Ascent(2), RocketDeployment(3), Stabilization(4),
Separation(5), Descent(6), and Landed(7).
comply 78
41 No lasers are allowed. comply NA
42 The Science Vehicle shall include an easily accessible power switch
which
does not require removal from the Container for access. An access hole
or
panel in the Container is allowed.
comply NA
43 The Science Vehicle must include a battery that is well secured.. (Note:
a
common cause of failure is disconnection of batteries and/or wiring
during
launch.)
comply 24
44 Lithium polymer cells are not allowed due to being a fire hazard. comply 24
INTERNATIONAL)
165

Team Logo
Here
(If You Want)
S
NO.
COMPLY/PARTIAL
X-REF SLIDES
DEMONSTRATING
COMPLIANCE
45 Alkaline, Ni-MH, lithium ion built with a metal
case, and Ni-Cad cells are
allowed. Other types must be approved before
use.
comply 98
46 The Science Vehicle and Container must be
subjected to the drop test as
described in the Environmental Testing
Requirements document
comply 135
47 The Science Vehicle must be subjected to the
vibration testing as described
in the Environmental Testing Requirements
document.
comply 135
48 CanSat Science Vehicle and Container must
be subjected to the thermal
test as described in the Environmental Testing
Requirements document.
comply 138
49 Environmental test results must be
documented and submitted to the judges
at the flight readiness review.
comply 138
INTERNATIONAL)
166

Team Logo
Here
Management
Yashvardhan

Team Logo
Here
(If You Want) Status of procurements
Name Status Order date Arrival date
PCB(with all
required sensors)
Manufactured 27/2/15 4/3/15
Mechanical
structure
Fabricated 18/3/15 20/3/15
Science vehicle Under process - -
Parachute Manufactured 27/2/15 4/3/15
Propellers Under process - -
Xbee pro,servos
and mini pro
arduino
ordered 6/3/15 11/3/15
INTERNATIONAL)
168

Team Logo
Here
(If You Want)
CanSat Budget – Hardware
SUBSYSTEM COMPONENTS COST(in USD)
CDH Atmega2560 microcontroller 23.18
Sensor Temperature sensor 0.799
Sensor 3- axis Accelerometer 4.79
EPS Battery 3.99
Sensor Electronic Clips 15
Mechanical Propellers 5(estimated per 2 wings)
Sensor Altitude sensor 8.79
Sensor Camera 55
CDH Xbee(2) 70
CDH GPS 12.79
Descent control Rip-Stop Nylon 15.2(per metre)
Mechanical (including fabrication of board) Structural material & fabrication 150
Electronics Electronics system(servo ,pro mini,etc) 20
Miscellaneous 50
Margin 20%
Total 434.539 $

Team Logo
Here
(If You Want)
CanSat Budget – Other Costs
Components Cost (in USD)
Ground Control Station 800(for laptop)
Test facilities and equipment 40
Rental 400( for 4 person)
Travel 4838.70(5 persons)
Total 6078.7$
Any external financial
support for the
project is not yet
available.

Team Logo
Here
(If You Want)
Program Schedule
ELECTRONICS TEAM SCHEDULE
TASK SCHEDULED DATES(dd/mm/yy) ACTUAL DATES(dd/mm/yy) REASONS FOR NOT
COMPLETING
1.Identification of task 1/12/14 3/12/14
2.
Allocation and Division of Tasks
15/12/14 19/12/14
3.
Identification of Systems and its
layout
22/12/14 25/12/14
4.
Testing of Available components
and getting them
31/12/14 31/12/14
5.
PDR Report and Presentation
1/2/15 1/2/15
6.
Hardware analysis and assembling
begins
15/2/15 – 25/2/15 27/2/15
7.System integration 26/2/15 -10/3/15 9/3/15
8.work on sensors and image
sensing
11/3/15 – 24/3/15 15/3/15
9.
CDR PPT and PDF
25/3/15 – 27/3/15 31/3/15
10.Accelerometer and servo
interfacing
1/4/15 – 5/4/15

Team Logo
Here
(If You Want)
7.System integration 26/2/15 -10/3/15
8.work on sensors and image
sensing
11/3/15 – 24/3/15
9.
CDR PPT and PDF
25/3/15 – 27/3/15
10.Accelerometer and servo
interfacing
1/4/15 – 5/4/15

Team Logo
Here
(If You Want)
TASK SCHEDULED
DATES(dd/mm/yy)
ACTUAL DATES(dd/mm/yy) REASONS FOR NOT
COMPLETING
11.
Flight Software Development
5/4/15 – 20/4/15
12.
Testing of Prototype
21/4/15 – 28/4/15
13. Fabrication of Final PCB 29/4/15 – 6/5/15
14. Field Testing of Hardware with System 7/5/15 – 12/5/15
15. Flight Operations Preparation 13/5/15 – 16/5/15

Team Logo
Here
(If You Want)
MECHANICAL TEAM SCHEDULE
TASK SCHEDULED DATES(dd/mm/yy) ACTUAL DATES(dd/mm/yy) REASONS FOR NOT COMPLETING
1.
Recognition of Tasks
1/12/14 3/12/14
2.
Allocation and Division of Tasks
15/12/14 19/12/14
3.
Designing of science vehicle and
container
22/12/14 25/12/14
4.
Testing of materials used in safe
landing of egg
31/12/14 31/12/14
5.
PDR Report and Presentation
31/1/15 31/1/15
6.
Descent Control Hardware
1/2/15 – 10/2/15 9/2/15
7.
Integrating Descent Control with Egg
Canopy
11/2/15 – 19/2/15 17/2/15
8.
Testing of Structure for operation
20/2/15 – 27/2/15 27/2/15

Team Logo
Here
(If You Want)
6.
Descent Control Hardware
1/2/15 – 10/2/15 9/2/15
7.
Integrating Descent Control
with Egg Canopy
11/2/15 – 19/2/15 15/2/15
8.
Testing of Structure for
operation
20/2/15 – 27/2/15 26/2/15

Team Logo
Here
(If You Want) Shipping and Transportation
We will use international courier service but we haven't
decided on a particular service yet.
INTERNATIONAL)
176Presenter: Name goes here

Team Logo
Here
(If You Want)
Conclusions
MAJOR ACHIEVEMENTS
• The team has come together
• Components are chosen and purchased
• Science vehicle subsystem is designed
• Cost and income are well balanced
• Container and PCB(with all sensors) fabricated
• Software testing of all sensors done
MAJOR UNFINISHED WORK
• Making science vehicle completely
• Testing few leftover part of GCS
• Shipment not yet decided.

Team Logo
Here
(If You Want)
THANK YOU

CanSat2015_2701_CDR_V01

Recommended

Recommended

More Related Content

What's hot

What's hot (20)

Similar to CanSat2015_2701_CDR_V01

Similar to CanSat2015_2701_CDR_V01 (20)

CanSat2015_2701_CDR_V01