Cansat2015_2446_PFR_v01

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CanSat 2014 CDR: Team ### (Team Number and Name) 11
Team Number – 2446
Team Name – SRM VAIMAANIX
CanSat 2015 Post Flight Review
cansat-srmuniversity.blogspot.com
Department of Electronics & Instrumentation Engineering, Faculty of
Engineering and Technology, SRM University
I N D I A
CanSat 2015 PFR: Team 2446 SRM VAIMAANIX

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2
Presentation Outline
Sr.no
Contents
01> PFR Introduction
02> Systems Overview
03> Concepts of Operation & Sequence of Events
04> Flight Data Analysis
05> Mechanical Subsystem Design
06> Flight Data Analysis
07> Failure Analysis
08> Lessons Learned
CanSat 2015 PFR: Team 2446 SRM VAIMAANIXCanSat 2015 PFR: Team 2446 SRM VAIMAANIX

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Team Organization
Rahul Ramesh
(Team Leader)
Tuhin Ranjan
(Alt. Team
Leader)
Mrs Karnam
Sunitha
(Team Mentor)
M V
Bharadhwaj
Abishek N
Goutham
Sharma
Shivam
Prakash
A.S. Anirudh
Arthesth
Aadhran
Electronics and Programming Mechanical and Aerodynamics

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CanSat 2014 CDR: Team ### (Team Number and Name)
44
Team Organization
Name
Year of
study
Department Position Contact details
Rahul Ramesh 3rd Elec. & Inst.
Team Leader,
Electronics Team Leader
rahul.vaimaanix@gmail.com
Tuhin Ranjan 3rd Elec. & Inst
Alt. Team Leader,
Mechanical Team Leader
tuhin.vaimaanix@gmail.com
Shivam Prakash 4th Elec. & Inst.
Fabrication and descent
control
shivam.cansat@gmail.com
A S Anirudh 4th Elec. & Inst. Container’s components
selection & implementation
anirudh.cansat@gmail.com
Arthesth Aadhran 3rd Elec. & Inst
Ground station GUI
development
arth.vaimaanix@gmail.com
Abishek N 3rd Elec. & Inst
Managerial activities manchandaprabhav@gmail.co
m
Goutham Sharma 2nd Itce
Separation mechanism
selection and analysis
t.gouthamsharma@gmail.com
M V Bharadhwaj 2nd Itce
Sensor programming and
development
bharat.vaimaanix@gmail.com

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CanSat 2014 CDR: Team ### (Team Number and Name) 5CanSat 2015 PFR: Team 2446 SRM VAIMAANIX
System Overview

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6CanSat 2014 PDR: Team ### (Team Number and Name)
MISSION:
To launch an autonomous CanSat with a deployable payload containing a large raw hen egg and record
the descend of the payload usingcamera.
OBJECTIVES IN BRIEF:
 To place the egg in the payload and ensure that it remains safe and intact for the entire flight .
 To maintain the descent rate of the container at 12 m/s or less using any passive descent control
system .
 To deploy the payload from container at altitude of 500 meters which will have its own descent
control system and a descent rate of 10 m/s or less and more than 4 m/s without using a
parachute, para-foil, streamer, or any similar device to reduce its speed.
 The payload will send telemetry signal to the ground station throughout the flight and the
collection of telemetry signal from the CanSat system during flight shall be 1Hz.
 Payload shall stabilize and record the video of its descend using camera. The camera must point
towards the earth.
 Safe recovery of payload and container in time without damaging the egg.
SELECTED BONUS OBJECTIVE:
To measure the stability and angle of descent of the payload during it’s descent using a three axis
accelerometer.
CanSat 2014 CDR: SRM VAIMAANIX - 3784Presenter: Aniket Padgilwar CanSat 2015 CDR: SRM VAIMAANIX - 3784Presenter: Tuhin Ranjan CanSat 2015 PDR: Team 2446 SRM VAIMAANIXCanSat 2015 PDR: Team 2446 SRM VAIMAANIX
Mission Summary

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CanSat 2014 CDR: Team ### (Team Number and Name) 7CanSat 2015 PFR: Team 2446 SRM VAIMAANIXCanSat 2015 PFR: Team 2446 SRM VAIMAANIX
Cansat Overview
CONTAINER:
Total height: 308 mm
Diameter: 117 mm
Weight: 123 grams
PAYLOAD :
Total height: 225 mm
Diameter: 108 mm
Weight: 479 grams
The CanSat was divided into three sections, namely as
1. DCS section
2. Egg protection section
3. Electronics section
4. Camera section
Where each section was independent and was
removable .

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Cansat Overview
THE WHOLE CANSAT (EACH AND EVERY MECHANICAL ASPECT) WAS MADE
BY OUR OWN HANDS.

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Cansat Overall Cost
- Container
S.No. Component Quantity Cost ($, USD)
1. Paper 2 sheets A4 size 0.20
2. Craft Glue 1 whole pack 0.5
3. Poly propylene disc 1 0.5
4. Servo motor 1 18.99
5. Arduino Pro mini 1 24.99
6. BMP180 altitude sensor 1 19
7. Soldering board 1 0.7
8. Buzzer 1 1.2
9. battery 1 3.4
TOTAL = 69.48

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Cansat Overall Cost
- payload
1. Poly Propylene disc 2 1.0
2. Balsa Wood 2 sheets 6
3. Plastic Ball Bearings 3 18
4. 5mm Nuts 18 2
5. Plastic rods 3 0.5
6. Carbon Fibre Rods 1 1
7. Bubble sheet 1 sheet 1.5
8. Straws 1 packet 2
9. Arduino Pro mini 1 24.99
10. GY-80 Sensor imu 1 25
11. Xbee transceiver 2 45
12. Xbee adapter for arduino 1 21

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Cansat Overall Cost
- Container
13. Electronics pcb 1 1.2
14. TMP102 temperature sensor 1 66
15. LDRs 3 0.4
16. 5v motor 1 0.6
17. Keychain camera 1 17
18. Capacitors 4.7mf 2 0.1
19. L293d motor driver 1 1
20. Female buckstrip 8 3
21. Plastic all purpose containers 2 2
Total = 232.39 $
Total Cansat cost = 69.48 + 232.39 = 301.77$

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Cansat Overall Cost - other
OTHER EXPENDITURE Cost
1. Flight Tickets from india to USA and
back to india
~ 1200 $
2. Hotel accommodation charges ~ 1075 $

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Physical Layout
KEY DESIGN FEATURES:
The container was made just out of a single layer of
rectangular paper pieces of dimension 40mm X 20mm
stuck together with the use of craft glue.
• The container had a servo motor which uses a hook to
hold on to the payload.
• The parachute was made out a very light weight cloth-like
fabric, having minute pores which was filled by a layer of
black spray paint over it.
The weight of the parachute was 8 grams.
• The parachute was suspended with the means of nylon
thread over 8 attachments over the container.
• The payload was made of polypropylene discs, nylon
rods, plastic rods and carbon fibre rods, and all purpose
plastic readymade containers.

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Physical Layout
KEY DESIGN FEATURES:
• The egg protection consisted of a layer of bubble sheet
with plastic straws in the circumference and some straw
cushion.
• We designed our own PCB for the whole electronics
section, hence we had no wires in our electronics cabin.
• We used a gyroscopic precession based camera
stabilization scheme.

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Concept of operations
and
Sequence of events

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Comparision of Planned and
Actual Con-Ops
EGG submission
Planned Actual
12:00 pm 11:25 pm
GCS Setup
Planned Actual
2:25pm 2:25pm
Launch
Planned Actual
2:30pm 2:35pm
Recovery(payload)
Planned Actual
2:45pm 3:00pm
Our cansat was ready and the egg was loaded
very quickly since the compartment was easily
openable.
The ground station was setup as per the time
and we received confirmation telemetry as
per our schedule.
Everything was setup as per the schedule and
the cansat was loaded in the rocket
The recovery of payload took a lot of time than
what we expected, which is due to the large
translator motion of cansat due to our DCS and
cross winds

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Release Logic
The release mechanism was to be triggered when the altitude of 550 metres from
the ground level was attained, the program was designed as follows:
first the ground level is calliberated to zero and the subsequent altitudes are
calculated with that reference.
Then we initiate separation when the subsequent altitudes are lesser than the
former.
Then we set a band of 550m-220m. So because of errors in ground the
separation does not occur.
Altitu
de
Ground
(435.2m)
Seperati
on
(982.73m
)

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Comparision of Planned and
actual SOE
When the payload was released from the container, the descent control strategy
worked very properly, just as we expected and the telemetry was received till the last
second until the point of impact, when the payload hit the ground, the buzzer rang but
the telemetry stopped and one of our supporting rod was broken which was highly
unexpected

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Flight data analysis

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Payload separation Altitude
Planned: <550m,
Actual: around 547.53m.
1. Altitude separation happened as planned!
2. The altitude was found on the basis of the telemetry data after the highest peak,
the descent rate was averaged at 6.5m/s before that point and 8.2m/s after that point.
Altitude
Ground
(435.2m)
Seperation
(982.73m)

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Descent Rate Before Separation
Descent rate before separation was averaged at 6.49m/s.
It was calculated at 5.34m/s.
Causes of Error:
The parachute had small pores holes that must have reduced the drag.
Point of separation
As seenfrom
the graph, the
slope of the
graph
increases after
the point of
separation

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Payload Descent Rate
Planned: <7m/s
The payload Descent rate was averaged at 8.2m/s.
But the numbers looks quite satisfying. The autogyro must have taken some time to
deploy.
There was also high crosswinds during launch sequence.
Average
descentrate of
8.2 m/s

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Video
#The recording had stopped unexpectedly so the file generated was corrupted
and cannot be played
This was occurred due to the motor which had sucked more current than expected
Hence forcefully turning off the camera during descent.

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Payload Telemetry
Telemetry as received in GCS

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Payload Telemetry
Outside Temperature:
Outside temperature
Temperature
Altitude Altitude
Temperature
Inside temperature
Temperature inside the rocket is high and constant.
Outside Temperature:
- the temperature sharply fell after deployment.
- The heat was easily radiated.
Inside Temperature:
- It had been a little colderthan outside.
-There is a slight insulation which prevents temp. fall

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Payload Telemetry
Telemetry:
Telemetry
Time Time
SD Card
Altitude
Altitude
*About 33 packets were received at GCS in 1Hz and about 8 were broken!

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Payload Telemetry
Power Supply:
Time
Voltage
A thick band between 4.2V and 4.3V, determines a very good supply to the system.
Batteries performed correctly.
As seen form the graph, the
voltage drop across the
voltage measurement unit had
changed continuously, but as
seen, the average is seen at
4.25volts from a 4.5volts
voltage source

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Payload stability(Bonus OBJ)
CanSat Orientation
Deploy InFlight Near Land

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Payload stability(Bonus OBJ)
CanSat Orientation
Series1- X axis,
Series2- Y axis,
Series3- Z axis.

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Failure Analysis

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Overview
The list of all the subsystems that failed or didn’t work as we expected are as
follows:
1. The percentage of the package received was only 41% during the whole flight
time
2. The structure of the payload got deformed and the supporting plastic rods broke
on impact, hence our payload which was in one piece during the whole descent,
broke at the point of impact with the ground.
3. The camera failed to produce a credible output, since the file obtained turned out
to be corrupt due to abrupt halt In the recording process.

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Corrective measures and root
causes
1. The received telemetry was only 41%
-This could have been corrected if an appropriate signal booster was used along with
the xbee radio.
- It was noted that the telemetry was lost mostly when the CanSat reached the peak
altitude, and since our antennae was unidirectional, some packets were lost, hence proper
selection of antennae could have solved the issue.
- The ground station should have been more organized, since someone had stepped
on the antennae wire and xbee receiver radio was disconnected during the last stages of
descent.

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causes
2. The structureof the Payload broke and got deformed upon impact
with the ground
1. This can be connected if we use 4 or more supporting rods instead of three
for better load transfer.
2. This failure can also be averted if a better composite material was used
instead of the plastic rods to sustain higher loads

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causes
The camera failed to produce any recording during descent
1. Our scheme used a gyroscopic precession mechanism which involved a motor
spinning a disc at high speed to stabilize the camera. The motor was connectod
to the same supply as the camera was connected to, hence during starting of the
motor after separation, it would have pulled a lot of current than expected (which
was more than expected, since we used capacitors) hence turning off the camera
forcefully

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Lessons Learned

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What Worked and What didn’t
What worked- What didn't work
1)The DCS we designed
worked very effectively.
2)The egg protection unit
saved the egg brilliantly.
3)We were able to recover
41% of the telemetry data
successfully.
4)90% of the mechanical
Structure survived the
launch and the impact.
Except the nylon rods
supporting the egg unit and
the camera unit.
5)The Camera stabilisation
system worked quite well.
6)The separation
mechanism worked .
1)The nylon rods we used
couldn't survive the impact.
2)Camera Stopped in the
middle of the flight and the
video file got corrupted.
3)The Container couldn't be
retrieved for further
analysis.

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Conclusions
• The Egg protection unit worked very effectively and the egg got
saved
• We were able to retrieve 41% of the telemetry data.
• Each and every component of the mechanical and electrical
subsystem was made out our own hands including the PCB’s.
Out of which, 90% of the overall payload worked quite well.
• We got data from the SD card of the whole launch procedure.
• We should focus on structure integrity and stiffness and not used
weaker materials for reducing weight.
• Camera stabilisation and video recording unit circuits should be
made in such a way that their functions do not intervene with each
other.
• Ground station should be more organised and the antenna wire
should be isolated properly in order to avoid any wire problems
from external sources like the crowd of people over there.
• Binoculars should be kept in handy for better recovery operation.

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CanSat 2014 CDR: Team ### (Team Number and Name) 38CanSat 2014 PFR: Team ### (Team Number and Name) 38
Thank You
….
CanSat-srmuniversity.blogspot.com
SRM VAIMAANIX

Cansat2015_2446_PFR_v01

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