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Team Logo 
Here CanSat 2012 Preliminary Design Report 
Team 7634 
Garuda 
Indian Institute of Technology, Delhi 
CanSat 20...
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(If You Want) Presentation Outline 
•Introduction 
–Team Garuda.............................................
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•Descent control Design 
–Descent control overview......................
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(If You Want) Presentation Outline 
•Communication and Data Handling Subsystem Design 
–CDH overview........
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(If You Want) Presentation Outline 
•Ground Control System Design 
–GCS overview............................
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(If You Want) Team Garuda 
Contact Details: <firstname>@teamgaruda.in 
CanSat 2012 PDR: Team 7634 (Garuda...
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(If You Want) Team organization CanSat 2012 PDR: Team 7634 (Garuda) Team Leader 
Faculty Mentor Mechanica...
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(If You Want) Acronyms 
Abbreviation 
Meaning 
μC 
Microcontroller 
ACK 
Acknowledgement 
ADC 
Analog to ...
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(If You Want) Acronyms 
Abbreviation 
Meaning 
ERL 
Effective Rigging Line Length 
Est 
Estimated 
FAT 
F...
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(If You Want) 
Acronyms 
Abbreviation 
Meaning 
PCB 
Printed Circuit Board 
RF 
Radio Frequency 
SD 
Secu...
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Systems Overview 
Presenters: Harsh Parikh, Rajat Gupta 
CanSat 2012 PDR: Team 7634 (Garuda) 
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(If You Want) Mission Summary CanSat 2012 PDR: Team 7634 (Garuda) 
The Main Objective: 
The main purpose ...
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(If You Want) System Requirements 
CanSat 2012 PDR: Team 7634 (Garuda) 
ID 
Requirements 
Priority 
Ratio...
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(If You Want) System Requirements 
CanSat 2012 PDR: Team 7634 (Garuda) 
ID 
Requirements 
Priority 
Ratio...
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(If You Want) 
System Requirements 
CanSat 2012 PDR: Team 7634 (Garuda) 
ID 
Requirements 
Priority 
Rati...
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System Level CanSat Configuration Trade & Selection 
•First Design- NESTED DESIGN 
 Lande...
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(If You Want) System Concept of Operations CanSat 2012 PDR: Team 7634 (Garuda) 
On CanSat Keep CanSat in ...
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System Concept of Operation 
•Briefing 
•Last Mechanical control 
•Last Electrical control...
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(If You Want) Context Diagram CanSat 2012 PDR: Team 7634 (Garuda) 
CanSat Processor 
Flight Software 
Pow...
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Physical Layout- CanSat 
Presenter: Rajat Gupta 
151mm 94mm 126mm 
Space for Electronics P...
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Physical Layout- Lander 125mm 
Space for parachutes 
Electronic Components Egg 
Egg protec...
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Launch Vehicle Compatibility 
•The starting point of design of CanSat body was the inner d...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Sensor Subsystem Design 
Presenter: Arpit Goyal 
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) 
Sensor Subsystem Overview 
•Carrier Sensor Sub-system ...
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Sensor Subsystem Overview CanSat 2012 PDR: Team 7634 (Garuda) 
•Lander Sensor Sub-system o...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) 
Sensor Subsystem Requirements 
ID 
Requirement 
Ration...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Sensor Subsystem Requirements 
ID 
Requirement 
Rationa...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Carrier GPS Trade & Selection 
RKI-1543 from Robokits...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Carrier Non-GPS Altitude and Temperature Sensor Trade...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Lander Altitude Sensor Trade & Selection 
Bosch BMP085 ...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Lander Impact Force Sensor Trade & Selection 
MMA7361...
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Here Descent Control Design 
Presenter: Prateek Gupta 
CanSat 2012 PDR: Team 7634 (Garuda) 32
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Descent Control Overview 
The descent mechanism selecte...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Descent Control Requirements 
ID 
Requirement 
Ration...
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Descent Rate Control Strategy Selection and Trade 
MECHANISM SELECTION 
Presenter: Prateek...
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(If You Want) Descent Rate Control Strategy Selection and Trade 
Material 
Benefits 
Problems 
Decision 
...
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Descent Rate Control Strategy Selection and Trade 
MATERIAL SHAPE SELECTION 
Presenter: Pr...
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Descent Rate Control Strategy Selection and Trade 
DESCENT RATE CALCULATIONS FOR CanSat 
D...
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Descent Rate Control Strategy 
Selection and Trade 
ASSUMPTIONS: 
• Each parachute weighs ...
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Descent Rate Control Strategy Selection and Trade 
EFFECTIVE RIGGING LINE LENGTH(ERL) 
To ...
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•Plumb line with very low weight as compared to payload 
•Length of string to be very long...
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(If You Want) Descent Rate Calculations 
Formula used for calculating the terminal velocity 
Where 
Vt= T...
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(If You Want) Descent Rate Calculations 
Density of air is not 
constant. 
@ 600m 
density=1.13 kg/m3 
@S...
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Descent Rate Estimates 
*Use of spill hole deviates the equivalent diameter only by a smal...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Mechanical Subsystem Design 
Presenters: Rajat Gupta, Akash Verma 
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) 
Mechanical Subsystem Overview 
•The design of the stru...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Mechanical System Requirements 
ID 
Requirement 
Rati...
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(If You Want) Mechanical System Requirements 
CanSat 2012 PDR: Team 7634 (Garuda) 
ID 
Requirement 
Ratio...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Lander Egg Protection Trade & Selection 
•The selecte...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Mechanical Layout of Components Trade & Selection 151...
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(If You Want) Material Selections 
CanSat 2012 PDR: Team 7634 (Garuda) 
FRP (fiber reinforced plastic) 
•...
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CanSat 2012 PDR: Team 7634 (Garuda) 
Carrier-Lander Interface Presenter: Akash Verma 
•The...
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Structure Survivability Trades 
CanSat 2012 PDR: Team 7634 (Garuda) 
•The electronic compo...
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(If You Want) Finite Element Analysis for Structural Survivability 
CanSat 2012 PDR: Team 7634 (Garuda) 
...
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Mass Budget 
CanSat 2012 PDR: Team 7634 (Garuda) 
Carrier components 
Weight (g) 
Arduino ...
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(If You Want) Tests Performed 
•The egg protection system was system was tested by dropping under free fa...
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Here CanSat 2012 PDR: Team 7634 (Garuda) Communication and Data Handling Subsystem Design 
Presenter: Aman Mitt...
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CanSat 2012 PDR: Team 7634 (Garuda) 
CDH Overview 
•Carrier 
– All data will be transmitte...
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CanSat 2012 PDR: Team 7634 (Garuda) 
CDH Requirements 
ID 
Requirement 
Rationale 
Priorit...
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CDH Requirements 
ID 
Requirement 
Rationale 
Priority 
Parents 
Children 
VM 
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I 
T 
D ...
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(If You Want) CDH Requirements 
ID 
Requirement 
Rationale 
Priority 
Parents 
Children 
VM 
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D 
...
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(If You Want) Processor and Memory Trade Selection 
Arduino Uno 
Arduino Mega 2560 
Custom ATMega 32 Boar...
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Processor and Memory Trade Selection 
•Carrier 
– Arduino Uno is chosen for the microcontr...
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(If You Want) Memory Selection 
•SD card is used for external memory 
–Standard FAT 32 file system. 
–Lar...
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(If You Want) Carrier Antenna Trade and Selection 
A24 HASM450 
A24 HABUF-P51 
Gain(dB) 
2.1 
2.1 
Freque...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Radio Configuration 
•The X-bee radios are to be used t...
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(If You Want) RADIO CONFIGURATION CanSat 2012 PDR: Team 7634 (Garuda) •Both xbees connect to each other. ...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Carrier Telemetry Format-1 
•Data to be transmitted- 
–...
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(If You Want) Carrier Telemetry Format-2 
•The data from GPS will be first processed by the microcontroll...
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(If You Want) Carrier Telemetry Format-3 CanSat 2012 PDR: Team 7634 (Garuda) 
Characters Sent 
Definition...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Activation of Telemetry Transmissions 
•The telemetry w...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Locator Device Trade & Selection 
•The locator device w...
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Here Electrical Power Subsystem 
Presenter: Sarthak Kalani 
CanSat 2012 PDR: Team 7634 (Garuda) 73
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(If You Want) EPS Schematic Overview CanSat Power System Carrier battery source Lander battery source 
Se...
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(If You Want) EPS Overview 
•2 supplies: Carrier + Lander 
•Most power consumers: GPS sensor and buzzer. ...
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(If You Want) EPS Requirements-Carrier 
ID 
Requirement 
Rationale 
Priority 
Parent 
Children 
VM 
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I ...
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(If You Want) EPS Requirements-Lander 
ID 
Requirement 
Rationale 
Priority 
Parent 
Children 
VM 
A 
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EPS Requirements-Lander 
ID 
Requirement 
Rationale 
Priority 
Parent 
Children 
VM 
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I ...
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(If You Want) Carrier Electrical Block Diagram CanSat 2012 PDR: Team 7634 (Garuda) Arduino (9V) 
GPS(5V) ...
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(If You Want) Lander Electrical Block Diagram 
CanSat 2012 PDR: Team 7634 (Garuda) Arduino (9V) GPS(5V) P...
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(If You Want) Power Budget - Carrier CanSat 2012 PDR: Team 7634 (Garuda) 
S. No. 
Component 
Voltage (V) ...
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Power Budget - Lander 
CanSat 2012 PDR: Team 7634 (Garuda) 
S. No. 
Component 
Voltage (V)...
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CanSat 2012 PDR: Team 7634 (Garuda) 
External Power Control Mechanism 
•Separate on off sw...
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(If You Want) Power Source Trade and Selection CanSat 2012 PDR: Team 7634 (Garuda) 
S. No. 
Battery Name ...
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Battery Voltage Measurement 
Trade And Selection 
CanSat 2012 PDR: Team 7634 (Garuda) 
 A...
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Here CanSat 2012 PDR: Team 7634 (Garuda) Flight Software Design 
Presenter: Sudeepto Majumdar 86
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) FSW Overview 
•Programming Language : .NET/JAVA 
•Devel...
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CanSat 2012 PDR: Team 7634 (Garuda) 
FSW Requirements 
ID 
Requirement 
Rationale 
Priorit...
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(If You Want) 
FSW Requirements 
CanSat 2012 PDR: Team 7634 (Garuda) 
ID 
Requirement 
Rationale 
Priorit...
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(If You Want) Carrier CanSat FSW Overview CanSat 2012 PDR: Team 7634 (Garuda) 90 
Presenter: Sudeepto Maj...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Lander CanSat FSW Overview 
Presenter: Sudeepto Majumda...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Software Development Plan 
•The GCS software is ready f...
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CanSat 2012 PDR: Team 7634 (Garuda) Ground Control System Design 
Presenters: Kshiteej Mah...
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CanSat 2012 PDR: Team 7634 (Garuda) 
GCS Overview Presenter: Rishi Dua Antenna receives Si...
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CanSat 2012 PDR: Team 7634 (Garuda) 
GCS Requirements 
ID 
Requirement 
Rationale 
Priorit...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) 
GCS Requirements 
ID 
Requirement 
Rationale 
Priority...
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(If You Want) CanSat 2012 PDR: Team 7634 (Garuda) GCS Antenna Trade & Selection 
•The antenna to be used ...
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(If You Want) GCS Antenna Trade and Selection 
>3.5 m Via UART through FTDI connected to Xbee. Via level ...
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GCS Software 
•Data taken currently from CSV file (which is updated every 2 seconds), late...
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GCS Software Description 
CanSat 2012 PDR: Team 7634 (Garuda) 
Data file Settings Graph Se...
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CanSat Integration and Test 
Presenter: Akash Verma 
CanSat 2012 PDR: Team 7634 (Garuda) 101
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(If You Want) CanSat Integration and Test Overview 
•With a project with large number of subsystems it be...
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(If You Want) CanSat Integration 
Phase One: Procurement and isolated Testing 
•In this phase all the com...
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CanSat Integration 
•Phase two: Subsystem Integration 
–Ensuring proper deployment of desc...
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Tests Performed 
Mechanical testing of egg protection system: 
•The egg protection system ...
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(If You Want) Tests to be performed 
•Sensors testing 
•Communication testing 
•Detachment of lander test...
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Presenter: Arpit Goyal 
CanSat 2012 PDR: Team 7634 (Garuda) 107
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(If You Want) 
Overview of Mission Sequence of Events 
CanSat 2012 PDR: Team 7634 (Garuda) 
•Briefing 
•L...
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(If You Want) Mission Operations Manual Development Plan 
•Mission Operation consist of 4 steps: 
–CanSat...
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(If You Want) 
CanSat Integration 
•The CanSat system is basically divided into three parts: 
–The Lander...
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(If You Want) Launch Preparation 
•Take rocket to flight line and get launch pad assignment 
•Walk out wi...
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(If You Want) Launch Procedure 
•Request a GO/NO GO from GS 
•Verify recovery crew is in place and ready ...
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(If You Want) Removal Procedure 
•Command ground station crew to disable telemetry from CanSat. 
•Team wa...
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(If You Want) CanSat Location and Recovery 
•The CanSat is integrated with GPS sensor and buzzer. 
•The G...
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Here Management 
Presenter: Rishi Dua 
CanSat 2012 PDR: Team 7634 (Garuda) 115
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(If You Want) CanSat Budget – Hardware 
S.No. 
Component 
Quantity 
Rate (USD) 
Cost (USD) 
1 
Arduino Bo...
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(If You Want) 
Components 
Cost (USD) 
Laptop for GCS 
None 
Travel 
12000 
Rental 
2000 
Test facilities...
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(If You Want) Sponsorship Plans 
•Website made: www.teamgaruda.in 
•Sponsorship brochure ready for distri...
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Program Schedule 
CanSat 2012 PDR: Team 7634 (Garuda) 119 
NOV 
20-30 
DEC 
1-31 
JAN 
1-1...
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(If You Want) Program Schedule 
CanSat 2012 PDR: Team 7634 (Garuda) 120 
NOV 
20-30 
DEC 
1-31 
JAN 
1-15...
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(If You Want) Program Schedule CanSat 2012 PDR: Team 7634 (Garuda) 121 
NOV 
20-30 
DEC 
1-31 
JAN 
1-15 ...
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Conclusions 
•Major accomplishments 
1.The ground station software is ready 
2.Website (ht...
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Team Garuda Cansat 2012 PDR

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Preliminary Design Review (PDR) of Team Garuda at the International Student CanSat competition. Team Garuda secured International Rank 3 out of 40 Teams at the International Student CanSat Competition 2012 at Abilene, TX, USA. Visit http://www.rishidua.com/cansat/ for more information about the team.

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Team Garuda Cansat 2012 PDR

  1. 1. Team Logo Here CanSat 2012 Preliminary Design Report Team 7634 Garuda Indian Institute of Technology, Delhi CanSat 2012 PDR: Team 7634 (Garuda) 1
  2. 2. Team Logo Here (If You Want) Presentation Outline •Introduction –Team Garuda...................................................................................................................................................................................6 –Team organization...........................................................................................................................................................................7 –Acronyms.........................................................................................................................................................................................8 •System Overview –System Requirements...................................................................................................................................................................12 –System level CanSat Configuration Trade & Selection................................................................................................................16 –System Concepts of Operations...................................................................................................................................................17 –Context Diagram...........................................................................................................................................................................19 –Physical Layout-CanSat................................................................................................................................................................20 –Physical Layout-Lander.................................................................................................................................................................21 –Launch Vehicle Compatibility........................................................................................................................................................22 •Sensor Subsystem Design –Carrier Sensor Subsystem overview.............................................................................................................................................24 –Lander Sensor Subsystem overview............................................................................................................................................25 –Sensor Subsystem requirements..................................................................................................................................................26 –Carrier GPS trade & selection.......................................................................................................................................................28 –Carrier non-GPS Altitude and temperature sensor Trade and Selection.....................................................................................29 –Lander altitude sensor trade & selection.......................................................................................................................................30 –Lander Impact force Sensor Trade & Selection............................................................................................................................31 CanSat 2012 PDR: Team 7634 (Garuda) Presenter: Arpit Goyal 2
  3. 3. Team Logo Here (If You Want) Presentation Outline •Descent control Design –Descent control overview..............................................................................................................................................................33 –Descent Control requirements......................................................................................................................................................34 –Descent rate control Strategy Selection and Trade......................................................................................................................35 •Mechanism selection..............................................................................................................................................................35 •Metal selection......................................................................................................................................................................36 •Shape selection.....................................................................................................................................................................37 •Descent Rate calculations..........................................................................................................................................................38 •Assumptions..........................................................................................................................................................................39 •Mechanical Subsystem Design –Mechanical Subsystems Overview...............................................................................................................................................46 –Mechanical Subsystems Requirements........................................................................................................................................47 –Lander Egg protection Trade and Selection.................................................................................................................................49 –Mechanical Layout of Components...............................................................................................................................................50 –Material Selection..........................................................................................................................................................................51 –Carrier-Lander interface................................................................................................................................................................52 –Structure Survivability Trades.......................................................................................................................................................53 –FEA for Structural Survivability.....................................................................................................................................................54 –Mass Budget..................................................................................................................................................................................55 –Tests Performed............................................................................................................................................................................56 CanSat 2012 PDR: Team 7634 (Garuda) 3 Presenter: Arpit Goyal
  4. 4. Team Logo Here (If You Want) Presentation Outline •Communication and Data Handling Subsystem Design –CDH overview................................................................................................................................................................................58 –CDH requirements.........................................................................................................................................................................59 –Processor and memory Trade & Selection..................................................................................................................................62 –Carrier Antenna Trade & Selection...............................................................................................................................................65 –Radio Configuration.......................................................................................................................................................................66 –Carrier Telemetry Format..............................................................................................................................................................67 –Activation of Telemetry Transmissions.........................................................................................................................................71 –Locator Device Trade & Selection................................................................................................................................................72 •Electrical Power Subsystem –EPS overview................................................................................................................................................................................74 –EPS requirements for Carrier........................................................................................................................................................76 –EPS requirements for Lander........................................................................................................................................................77 –Carrier Electrical Block Diagram...................................................................................................................................................79 –Lander Electrical Block Diagram...................................................................................................................................................80 –Power Budget................................................................................................................................................................................81 –External Power Control Mechanism..............................................................................................................................................83 –Power Source Trade and Selection..............................................................................................................................................84 –Battery Voltage Measurement.......................................................................................................................................................85 •Flight Software Design –FSW overview...............................................................................................................................................................................87 –FSW Requirements.......................................................................................................................................................................88 –Carrier FSW overview...................................................................................................................................................................90 –Lander FSW overview...................................................................................................................................................................91 –Software development plan...........................................................................................................................................................92 CanSat 2012 PDR: Team 7634 (Garuda) 4 Presenter: Arpit Goyal
  5. 5. Team Logo Here (If You Want) Presentation Outline •Ground Control System Design –GCS overview................................................................................................................................................................................94 –GCS requirements.........................................................................................................................................................................95 –GCS Antenna Trade & Selection..................................................................................................................................................97 –GCS software Description.............................................................................................................................................................99 •CanSat Integration and Test –CIT overview................................................................................................................................................................................102 –CanSat integration.......................................................................................................................................................................103 –Test Performed............................................................................................................................................................................105 –Tests to be performed.................................................................................................................................................................106 •Mission Operation & Analysis –MOA overview.............................................................................................................................................................................108 –MOA manual development plan..................................................................................................................................................109 •CanSat Integration..................................................................................................................................................................110 •Launch Preparation................................................................................................................................................................111 •Launch Procedure..................................................................................................................................................................112 •Removal Procedure................................................................................................................................................................113 –CanSat Location recovery...........................................................................................................................................................114 •Management –CanSat Budget............................................................................................................................................................................116 –Sponsorship Plans......................................................................................................................................................................118 –Program Schedule.......................................................................................................................................................................119 –Conclusions................................................................................................................................................................................ 122 CanSat 2012 PDR: Team 7634 (Garuda) 5 Presenter: Arpit Goyal
  6. 6. Team Logo Here (If You Want) Team Garuda Contact Details: <firstname>@teamgaruda.in CanSat 2012 PDR: Team 7634 (Garuda) Name Major with Year Arpit Goyal Electrical Engineering, Senior Rajat Gupta Mechanical Engineering, Senior Kshiteej Mahajan Computer Science, Senior Aman Mittal Electrical Engineering, Junior Prateek Gupta Mechanical Engineering, Junior Sarthak Kalani Electrical Engineering, Junior Sudeepto Majumdar Electrical Engineering, Junior Akash Verma Mechanical Engineering, Sophomore Rishi Dua Electrical Engineering, Sophomore Harsh Parikh Computer Science, Freshman 6 Presenter: Arpit Goyal
  7. 7. Team Logo Here (If You Want) Team organization CanSat 2012 PDR: Team 7634 (Garuda) Team Leader Faculty Mentor Mechanical Designs Akash Verma Prateek Gupta Electrical Systems Arpit Goyal Sarthak Kalani Sudeepto Majumdar Software Control Harsh Parikh Kshiteej Mahajan Rishi Dua Team Mentor Alternate Team Leader Aman Mittal Rajat Gupta 7 Presenter: Arpit Goyal
  8. 8. Team Logo Here (If You Want) Acronyms Abbreviation Meaning μC Microcontroller ACK Acknowledgement ADC Analog to Digital Convertor CAD Computer-aided design CDH Communication and Data Handling CIT CanSat Integration and Test DC Descent Control DS Data Sheet EMRR Essence's Model Rocketry Reviews EPS Electrical Power Subsystem EPS Electrical Power Subsystem CanSat 2012 PDR: Team 7634 (Garuda) 8 Presenter: Arpit Goyal
  9. 9. Team Logo Here (If You Want) Acronyms Abbreviation Meaning ERL Effective Rigging Line Length Est Estimated FAT File Allocation Table FEA Finite element Analysis FRP Fibre-reinforced plastic FSW Flight Software GCS Ground Control Station GPS Global positioning system GPS Global Positioning System IDE Integrated Development Environment Meas Measured experimentally MOA Mission Operation and Analysis P&T Pressure and Temperature CanSat 2012 PDR: Team 7634 (Garuda) 9 Presenter: Arpit Goyal
  10. 10. Team Logo Here (If You Want) Acronyms Abbreviation Meaning PCB Printed Circuit Board RF Radio Frequency SD Secure Digital SPI Serial Peripheral Interface SPL Sound Power Level SSS Sensor Subsystem UART Universal asynchronous receiver/transmitter USD United States Dollar VSWR Voltage Standing Wave Ratio CanSat 2012 PDR: Team 7634 (Garuda) 10 Presenter: Arpit Goyal
  11. 11. Team Logo Here Systems Overview Presenters: Harsh Parikh, Rajat Gupta CanSat 2012 PDR: Team 7634 (Garuda) 11
  12. 12. Team Logo Here (If You Want) Mission Summary CanSat 2012 PDR: Team 7634 (Garuda) The Main Objective: The main purpose of CanSat is to provide egg safety from launch to landing Auxiliary Objectives: •launching CanSat •descent CanSat from 600m to 200m at a constant descent rate of 10 m/s ± 1 m/s •changing constant descent rate to 5 m/s ± 1m/s at 200m •releasing the lander with egg at 91 m altitude •landing lander with descent rate less than 5m/s without damaging egg •collecting data at ground station from sensors in CanSat through Xbee radio modules Selectable Mission: Calculating thrust force after lander has landed; data should be collected at rate more than 100Hz and stored on board for post-processing. Selection Rationale: •Easy implementation •Criteria: Cost, weight, reliability, power and space effective. Presenter: Harsh Parikh 12
  13. 13. Team Logo Here (If You Want) System Requirements CanSat 2012 PDR: Team 7634 (Garuda) ID Requirements Priority Rationale Parent Children VM A I T D SYS-01 CanSat constraints will be: Diameter: less than 127mm Total mass 400g - 750g High Justifies concept of CanSat X SYS-02 CanSat egg placed inside will be recovered safely High Competition requirement SSS-05 SSS-06 SSS-08 DC-02 DC-03 GCS-03 X X SYS-03 The CanSat shall deploy from the launch vehicle payload section and no protrusions High Easy to leave rocket MS-03 X SYS-04 The descent control system shall not use any flammable or pyrotechnic devices High To comply with field safety SYS-09 X SYS-05 Descent rate should be 10m/s till 200m altitude. descent rate fall to 5m/s at 200m High Competition requirement DC-01 FSW-03 X X X 13 Presenter: Harsh Parikh
  14. 14. Team Logo Here (If You Want) System Requirements CanSat 2012 PDR: Team 7634 (Garuda) ID Requirements Priority Rationale Parent Children VM A I T D SYS-06 Detachment of lander at 91m and lander velocity will be less than 5m/s High Competition requirement DC-01 FSW-04 X X SYS-07 During descent the carrier shall transmit required sensor data telemetry data once every two second via XBEE Lander descent telemetry shall be stored on –board for post processing following retrieval of the lander High Competition requirement SSS-01 SSS-02 SSS-03 GCS-02 FSW-05 X X SYS-08 The cost of CanSat flight hardware shall be under1000$ (other costs are excluded) High Feasible to design X SYS-09 The CanSat and associated operations shall comply with all field safety regulations. Medium Competition requirement SYS-04 X SYS-10 Impact parameter data shall be measured and stored on data card on sensor Medium Data backup SSS-04 X X 14 Presenter: Harsh Parikh
  15. 15. Team Logo Here (If You Want) System Requirements CanSat 2012 PDR: Team 7634 (Garuda) ID Requirements Priority Rationale Parent Children VM A I T D SYS-11 Spin of CanSat should be less than 10 revolutions per minute High Required for stable operations MS-02 X X 15 Presenter: Harsh Parikh
  16. 16. Team Logo Here (If You Want) System Level CanSat Configuration Trade & Selection •First Design- NESTED DESIGN  Lander inside the carrier  Electronic components to be fitted at the sides  Parachutes will be collected at the top portion  Easy to fit components in a cylinder of 152mm height •Second design- One above the Other Carrier above the lander  Electronic components to be on the discs arranged horizontally or on vertical plates on the side Height required is more. Can’t fit inside 152mm.  Chosen Configuration: NESTED DESIGN CanSat 2012 PDR: Team 7634 (Garuda) 16 Presenter: Harsh Parikh
  17. 17. Team Logo Here (If You Want) System Concept of Operations CanSat 2012 PDR: Team 7634 (Garuda) On CanSat Keep CanSat in rocket Launch Rocket Leaving CanSat from rocket at 600m descending Rocket at constant rate of 10m/s from 600 to 200m descent Speed decrease to 5m/s at 200m Detaching lander at 91m Collecting data from sensors Sending Data to ground station Data Analysis Calculating collision force Detecting CanSat Off CanSat 17 Presenter: Harsh Parikh
  18. 18. Team Logo Here (If You Want) System Concept of Operation •Briefing •Last Mechanical control •Last Electrical control •Coming at Competition Arena Pre Flight •Pre-Flight operation •Launch Flight •Deploy CanSat at 600m •Opening parachute •Controlling descent rate to 10m/s + - 1m/s up to 200m •Data collection and transmission •Reducing descent rate to 5m/s at 200m •Detaching Lander at 91m •Landing and Locating CanSat Launch and Flight •Saving Data •Analyzing Data •Preparing PFR •PFR Presentation Post Flight CanSat 2012 PDR: Team 7634 (Garuda) 18 Presenter: Harsh Parikh
  19. 19. Team Logo Here (If You Want) Context Diagram CanSat 2012 PDR: Team 7634 (Garuda) CanSat Processor Flight Software Power System Mechanical System Sensor System XBee System Ground Antenna Receiver Computer Analyser Environment Mechanical System descent Control Lander Release 19 Presenter: Harsh Parikh
  20. 20. Team Logo Here (If You Want) Physical Layout- CanSat Presenter: Rajat Gupta 151mm 94mm 126mm Space for Electronics Parachute on top Lander detachment from bottom Lander Actuator CanSat 2012 PDR: Team 7634 (Garuda) 20
  21. 21. Team Logo Here (If You Want) Physical Layout- Lander 125mm Space for parachutes Electronic Components Egg Egg protection system CanSat 2012 PDR: Team 7634 (Garuda) 21 Presenter: Rajat Gupta
  22. 22. Team Logo Here (If You Want) Launch Vehicle Compatibility •The starting point of design of CanSat body was the inner dimensions of payload section of rocket. •Outer diameter of body is 126mm giving 1 mm clearance. •Total height of CanSat system is 151mm which is smaller than the given envelop. •Hence there are no protrusions from the CanSat which could hamper the smooth deployment from rocket •As the rocket compartment opens up, CanSat is deployed by action of gravity. Presenter: Rajat Gupta 151mm 94mm CanSat 2012 PDR: Team 7634 (Garuda) 22
  23. 23. Team Logo Here CanSat 2012 PDR: Team 7634 (Garuda) Sensor Subsystem Design Presenter: Arpit Goyal 23
  24. 24. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Sensor Subsystem Overview •Carrier Sensor Sub-system overview Presenter: Arpit Goyal Micro-controller GPS Sensor Robokits India (RKI-1543) Pressure Sensor Bosch (BMP085) Non-GPS Altitude Calculation Battery Voltage Data Temperature Sensor BMP085 24
  25. 25. Team Logo Here (If You Want) Sensor Subsystem Overview CanSat 2012 PDR: Team 7634 (Garuda) •Lander Sensor Sub-system overview 25 Micro-controller GPS Sensor Robokits India (RKI-1543) Pressure Sensor + Temperature Sensor Bosch (BMP085) Non-GPS Altitude Calculation Battery Voltage Data Accelerometer MMA7361L Presenter: Arpit Goyal
  26. 26. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Sensor Subsystem Requirements ID Requirement Rationale Priority Parent Children VM A I T D SSS-01 GPS data shall be measured in carrier (±1.5m) Required as main objective and for locating carrier after it has landed. GPS data will be telemetered to the ground HIGH SYS-07 SSS-07 X X SSS-02 Altitude shall be measured without using a non-GPS sensor in carrier and lander both (±1.0m) Required as main objective and to calculate height from ground. This will be telemetered to ground and will be used to calculate descent rate HIGH SYS-07 SSS-07 X X X SSS-03 Air Temperature shall be measured in carrier (±2°C) Required as base objective and for descent telemetry HIGH SYS-07 SSS-07 SSS-09 X X X SSS-04 Impact Force shall be measured in lander after it has landed (at rate of at least 100 Hz) (6g) Required as part of selectable objective HIGH SYS-10 SSS-07 X X X 26 Presenter: Arpit Goyal
  27. 27. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Sensor Subsystem Requirements ID Requirement Rationale Priority Parent Children VM A I T D SSS-05 Data Interfaces from sensors, like SPI or UART should be limited Limited UART and SPI interface in μC MEDIUM CDH SYS-02 X SSS-06 Both lander and carrier will have an audio beacon of SPL at least 80 dB Required to retrieve lander and carrier after they have landed HIGH SYS-02 X X X SSS-07 Sensors should have high resolutions and high range For accurate data LOW SSS-01 SSS-02 SSS-03 SSS-04 X SSS-08 GPS sensor will be used in lander It will be used to locate lander after it has landed apart from audio buzzer MEDIUM SYS-02 X X SSS-09 Temperature will be measured in lander For data matching with of carrier LOW SSS-03 X 27 Presenter: Arpit Goyal
  28. 28. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Carrier GPS Trade & Selection RKI-1543 from Robokits India is chosen as GPS sensor due to: •Small size •Low weight •Low cost •Easily available in India Manufacturer Model Accuracy (m) Dimensions (mm) Mass (g) Voltage (V) Cost (USD) Wi2Wi W2SG0006 3 15.5X15.5X2.5 8 3.6 42.5 USGlobalSat GPS_EM- 406A 5 30X30X10.5 7.6 5 40 Robokits India RKI-1543 3 16X16X6 6 5 40 28 Presenter: Arpit Goyal
  29. 29. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Carrier Non-GPS Altitude and Temperature Sensor Trade & Selection Bosch BMP085 is chosen as Non-GPS altitude sensor and temperature sensor due to: •Small Size •Integrated Temperature Sensor •Low cost •Can be easily integrated with I2C bus Manufacturer Model Accuracy (%) Dimensions (mm) Operating Supply Voltage (V) Output Type (A/D) Cost (USD) Bosch BMP085 ± 1.0 16.5X16.5 5 D 20 Honeywell SSCDRNN015PAAA5 ± 0.25 18X12.5 5 A 30 29 Presenter: Arpit Goyal
  30. 30. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Lander Altitude Sensor Trade & Selection Bosch BMP085 is chosen as lander altitude sensor due to: •Small Size •Integrated Temperature Sensor •Low cost Though we don’t need temp. measurement but still this sensor is cheaper than other sensors and is easily compatible with Arduino board. Having another temp sensor will be useful as it can be used to match data from carrier temp sensor. Manufacturer Model Accuracy (%) Dimensions (mm) Operating Supply Voltage (V) Output Type (A/D) Cost (USD) Bosch BMP085 ± 1.0 16.5X16.5 5 D 20 Honeywell SSCDRNN015PAAA5 ± 0.25 18X12.5 5 A 30 30 Presenter: Arpit Goyal
  31. 31. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Lander Impact Force Sensor Trade & Selection MMA7361L from Freescale Semiconductors is chosen due to: •Low cost •ADC as data interface, Micro-controller have limited I2C interface. •Higher range Manufacturer Model Dimensions (mm) Output (A/D) Range Cost (USD) Analog Devices ADXL335 17.8X17.8 D ± 3g 25 ST Microelectronics LIS331 21.9X13.5 D ± 6g 28 Freescale Semiconductors MMA7361L 23.8X12.6 A ± 6g 12 31 Presenter: Arpit Goyal
  32. 32. Team Logo Here Descent Control Design Presenter: Prateek Gupta CanSat 2012 PDR: Team 7634 (Garuda) 32
  33. 33. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Descent Control Overview The descent mechanism selected is parachutes with thorough calculation of the drag area. The material selected after careful consideration is ripstop nylon and it will be provided with spill holes to reduce drift. 2 parachutes are chosen for each level of descent for carrier. 1st parachute will bring down the velocity of CanSat to 10m/s. 2nd parachute will be deployed in addition to 1st, at 200m altitude to bring down the velocity to 5m/s To avoid the free body wake effects, the effective rigging line length is calculated. Proper orientation of both parachutes will avoid entanglement. The parachute in the lander directly brings it descent rate to below 5m/s Before deployment the parachutes are folded to occupy the allotted minimum space Presenter: Prateek Gupta 33
  34. 34. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Descent Control Requirements ID Requirement Rationale Priority Parent Children VM A I T D DC-1 Use of two parachutes in Carrier and one in lander To attain required descent rates HIGH SYS-05 SYS-06 X X X X DC-2 Parachute should have a shiny colour To locate carrier and lander easily HIGH SYS-02 X DC-3 Spill holes should be used in parachutes To reduce drift MEDIUM SYS-02 X X X DC-4 At 200 m the 2nd parachute shall not entangle with the 1st one Proper orientation and deployment mechanism is required for 2nd parachute HIGH X X 34 Presenter: Prateek Gupta
  35. 35. Team Logo Here (If You Want) Descent Rate Control Strategy Selection and Trade MECHANISM SELECTION Presenter: Prateek Gupta Drag Mechanism Benefits Problems Decision Parachute(without spill hole) Large coefficient of drag, Drifting, Oscillations Not to be used Parachute(with spill hole) Reduced drifting and oscillations, Lesser material and weight Descent rate has increased, Selected Streamers Faster recovery, Reduced Drifting, Lesser drag, Heavier, Occupies larger volume, Not to be used Paraglide Descent control methods include drag and lift Drift need to be there to enable it to control descent via lift Not to be used CanSat 2012 PDR: Team 7634 (Garuda) 35
  36. 36. Team Logo Here (If You Want) Descent Rate Control Strategy Selection and Trade Material Benefits Problems Decision Ripstop nylon Lower porosity, Dyed in many colours, Easily available Slightly expensive To be used Mylar Thin, Light, Cd=0.14(approx.) Not easily available Can’t be used Flex Alternative to Mylar Heavy and more porous Not to be used Retired Hot air balloon Alternative to ripstop nylon as it will be less expensive Fewer colour options, Need to be washed several times to get the smell of the gas out, need to be replaced after certain time of usage Can’t be used MATERIAL SELECTION CanSat 2012 PDR: Team 7634 (Garuda) 36 Presenter: Prateek Gupta
  37. 37. Team Logo Here (If You Want) Descent Rate Control Strategy Selection and Trade MATERIAL SHAPE SELECTION Presenter: Prateek Gupta Shape Payload Diameter Descent rate Decision Round 750g 10cm 44m/s Selected Square 750g 10cm 55m/s Not to be selected Hexagon 750g 10cm 48m/s Can be considered CanSat 2012 PDR: Team 7634 (Garuda) 37
  38. 38. Team Logo Here (If You Want) Descent Rate Control Strategy Selection and Trade DESCENT RATE CALCULATIONS FOR CanSat DESCENT RATE CALCULATIONS FOR LANDER(91m) Payload Diameter (1st Parachute) Descent rate (600m) Payload Diameter (2nd Parachute) Descent Rate (200m) 725g 40cm 10.82m/s 700g 40cm 7.51m/s 725g 44cm 9.83m/s 700g 44cm 6.83m/s 725g 48cm 9.01m/s 700g 48cm 6.26m/s 725g 48cm 9.01m/s 700g 52cm 6m/s Payload Diameter Descent rate 200g 40cm 5.68m/s 200g 50cm 4.54m/s 200g 60cm 3.78m/s 200g 55cm 4.13m/s CanSat 2012 PDR: Team 7634 (Garuda) 38 Presenter: Prateek Gupta
  39. 39. Team Logo Here (If You Want) Descent Rate Control Strategy Selection and Trade ASSUMPTIONS: • Each parachute weighs 25gm • All parachutes in a cluster must be identical to prevent unbalancing of drag forces. This requirement is relaxed by having slightly different diameters of 2 parachutes • Spill hole of 5cm diameter is not going to affect the equivalent diameter. • Equivalent diameter for cluster is calculated using: • All calculations are based on EMRR’s Calculator CanSat 2012 PDR: Team 7634 (Garuda) 2 2 Deq  D1  D2 Presenter: Prateek Gupta 39
  40. 40. Team Logo Here (If You Want) Descent Rate Control Strategy Selection and Trade EFFECTIVE RIGGING LINE LENGTH(ERL) To avoid effects of ‘forebody wake effects’ which reduces 25% of drag in parachute ERL =풏D ERL= 63 cm (approx.) Deployment of 2nd parachute : Deployment mechanism to be decided CanSat 2012 PDR: Team 7634 (Garuda) 40 Presenter: Prateek Gupta
  41. 41. Team Logo Here (If You Want) •Plumb line with very low weight as compared to payload •Length of string to be very long •Calculate the descent rate by simple formula – Velocity = Plumb Line LengthTime Descent Rate Control Strategy Selection and Trade TESTING OF DESCENT RATE (LANDER): STRATEGY CanSat 2012 PDR: Team 7634 (Garuda) 41 Presenter: Prateek Gupta
  42. 42. Team Logo Here (If You Want) Descent Rate Calculations Formula used for calculating the terminal velocity Where Vt= Terminal Velocity W= Payload Cd= Coefficient of Drag (1.5 for round and hemisphere) ρ =Density of Air (It varies from 600m to ground level) A= Equivalent area of Parachute or cluster of them ((pi*d2)/4) CanSat 2012 PDR: Team 7634 (Garuda) 42 C A W V d t  2  Presenter: Prateek Gupta
  43. 43. Team Logo Here (If You Want) Descent Rate Calculations Density of air is not constant. @ 600m density=1.13 kg/m3 @Sea level Density= 1.2 kg/m3 Terminal velocity will decrease as it approaches ground. There is not much variation in density and hence we can assume it to be constant and calculate for the worst case i.e. 1.13 kg/m3. CanSat 2012 PDR: Team 7634 (Garuda) 43 Presenter: Prateek Gupta
  44. 44. Team Logo Here (If You Want) Descent Rate Estimates *Use of spill hole deviates the equivalent diameter only by a small amount so these values should hole in actual scenario. Cd will be slightly less than 1.5. Object Altitude Weight Terminal Velocity Carrier + Lander 600m 725g 9.01m/s Carrier + Lander 200m 700g 6m/s(to be improved) Carrier 91m 500g 5.7m/s(Using non identical chutes) Lander 91m 200g 4.54m/s CanSat 2012 PDR: Team 7634 (Garuda) 44 Presenter: Prateek Gupta
  45. 45. Team Logo Here CanSat 2012 PDR: Team 7634 (Garuda) Mechanical Subsystem Design Presenters: Rajat Gupta, Akash Verma 45
  46. 46. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Mechanical Subsystem Overview •The design of the structure was governed by the designated payload envelop. For the given dimensions of payload, concentric arrangement of carrier and lander one-inside-the-other was perceived to be best suited. •The body will be fabricated with fiber re-enforced plastic which provides good impact resistance •The bottom of carrier opens up on initialization of lander deployment with help of linear actuator and the lander falls due to gravity. •The structural rods are made of aluminum and provide structural integrity. •All electrical components are placed strategically to bring the centre of gravity as close to the centre as possible for balance of the system •The egg protection system uses a combination of impact force distributor and shock absorbing material. Presenter: Rajat Gupta 46
  47. 47. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Mechanical System Requirements ID Requirement Rationale Priority Parent Child VM A I T D MS-01 There shall be no protrusions beyond the payload envelop until CanSat deployment Protrusions may interfere with smooth deployment. High SYS-03 X MS-02 The various components shall be located strategically so as to bring the CG near the centre line. The mass distribution of the rocket should be fairly uniform for stable operations Medium SYS-11 X MS-03 The electronics shall be bolted inside the structure To ensure protection of electronics High X MS-04 All electronics should be shielded from environment To ensure protection High X 47 Presenter: Rajat Gupta
  48. 48. Team Logo Here (If You Want) Mechanical System Requirements CanSat 2012 PDR: Team 7634 (Garuda) ID Requirement Rationale Priority Parent Child VM MS-05 The structure must support 30gees of shock force and 10 gees of acceleration The structure has to withstand various forces during takeoff and landing High X X 48 Presenter: Rajat Gupta
  49. 49. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Lander Egg Protection Trade & Selection •The selected egg protection system consists of a force distributor at bottom and surrounded by a shock absorbing and dampening material. –The hip bone protector(used by elderly people) is used as a force distributor to distribute the impact forces sideways and protect the egg from breaking –The egg is placed in a spherical foam ball with cavity carved inside to provide protection from all sides. It is covered from top by more foam pieces. Presenter: Rajat Gupta •Other alternates: cotton & bubble wrap are also tested for cushioning effect. •In final configuration, Egg is wrapped with a layer bubble wrap to protect from self crushing force from foam ball •Polystyrene balls are filled in any space left to provide extra cushion. •All the materials: foam, bubble wrap, polystyrene balls are easily available lightweight and inexpensive. Hip protector was available in our lab as part of ongoing product developed with patented research. 49
  50. 50. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Mechanical Layout of Components Trade & Selection 151mm 94mm 125mm Electronics Space for parachute Egg Protection system Actuator Main Structure 50 Presenter: Rajat Gupta
  51. 51. Team Logo Here (If You Want) Material Selections CanSat 2012 PDR: Team 7634 (Garuda) FRP (fiber reinforced plastic) •Density = 1799.19381 kg / m^3 •chemical, moisture, and temperature resistance •superior tensile, flexural and impact strength behaviour •High Strength to Weight Ratio •Easy to mold and cast in our lab •Cheap and easily available Aluminum rods •Density 2.63 g/cc •Ultimate strength 248 MPa •Light weight and strong enough for the CanSat •Easily available in various diameters Torsional spring For quick opening of bottom flap of the carrier The material chosen for structure is FRP body with aluminum support rods due their superior qualities at affordable price as shown below. 51 Presenter: Rajat Gupta
  52. 52. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Carrier-Lander Interface Presenter: Akash Verma •The lander will be placed inside the carrier. •The bottom part of the carrier is a spring loaded flap. • A linear actuator is used for holding the bottom flap. At 91m actuator pulls the locking rod and flap opens by gravity and spring force. •Lander comes out by gravitational force. Release of the lander results in opening of the parachute which is above the lander. 52
  53. 53. Team Logo Here (If You Want) Structure Survivability Trades CanSat 2012 PDR: Team 7634 (Garuda) •The electronic components will be soldered on a PCB which will be bolted to the structure for robust mountings. •Holes can be easily drilled in the plastic structure wherever required accordingly. •The components which can’t be bolted will be secured using superior glue adhesive. •The structure is designed with suitable material thickness to withstand the requisite shock forces. •The fibers in the structure will provide strength and resistance from impacts in the longitudinal direction of fibers. A preliminary Finite element analysis was carried out to ensure that the structure is robust enough (Results shown in next slide) •Physical testing to be done later when structure is fabricated. 53 Presenter: Akash Verma
  54. 54. Team Logo Here (If You Want) Finite Element Analysis for Structural Survivability CanSat 2012 PDR: Team 7634 (Garuda) The preliminary FEA results of the structure for load due 20gees average deceleration shows resultant displacement and von-mises stress way below limits. Max resultant disp.: .01mm Max von-mises stress= 0.23 Mpa *The analysis is for static forces equivalent to 20g impact for fixed end boundary conditions with material properties assumed to be uniform. In real case the properties are different in direction of fibers for FRP 54 Presenter: Akash Verma
  55. 55. Team Logo Here (If You Want) Mass Budget CanSat 2012 PDR: Team 7634 (Garuda) Carrier components Weight (g) Arduino board 32 LCD 35 Parachutes 60 Structure 250 Battery 24 Other electronics 20 Total carrier mass 421 Lander components Weight (g) Arduino board 32 LCD 35 Parachutes 30 Structure 100 Battery 24 Other electronics 20 Egg protection(without egg) ~60 Total carrier mass(without egg) 241 The initial estimates with mass are from component specifications and CAD model with expected errors. 55 Presenter: Akash Verma
  56. 56. Team Logo Here (If You Want) Tests Performed •The egg protection system was system was tested by dropping under free fall from various heights to choose the cushion material. •In all tests, the hip protector is placed in the bottom. •From these tests, the foam ball + bubble wrap with egg in vertical orientation was finalized. CanSat 2012 PDR: Team 7634 (Garuda) Trial Material Drop height (ft) Impact velocity (m/s) Orientation Result 1. Bubble wrap 4 4.9 horizontal Fail Bubble wrap 4 4.9 vertical Fail Cotton 4 4.9 horizontal Fail Cotton 4 4.9 vertical Pass Cotton 10 7.7 vertical Fail Foam ball + bubble wrap 10 7.7 vertical Pass Foam ball +bubble wrap 20 11 vertical Pass Foam ball +bubble wrap 40 15 vertical Fail 56 Presenter: Akash Verma
  57. 57. Team Logo Here CanSat 2012 PDR: Team 7634 (Garuda) Communication and Data Handling Subsystem Design Presenter: Aman Mittal 57
  58. 58. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) CDH Overview •Carrier – All data will be transmitted from the sensors to the microcontroller on board via serial interface. –The data will be stored on an SD card for later retrieval. –Transmission of data to take place from X-Bee Pro module XBP24BZ7SIT-004J with in built antenna. • Lander –The data from the sensors to be collected from serial communication and sent to the microcontroller. –The data will be processed on Arduino and stored in an SD card. Presenter: Aman Mittal 58
  59. 59. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) CDH Requirements ID Requirement Rationale Priority Parent(s) Children VM A I T D CDH -01 Sensor data will be sent Base mission requirements HIGH X X CDH-02 Carrier data will be stored Store all data to be transmitted as backup MEDIUM X CDH-03 Store lander data Base mission requirement for velocity data HIGH X X CDH-04 Accelerometer data ADC data for force calculation HIGH X CDH-05 Micro-controller speed>1MHz To process all data and send telemetry MEDIUM X CDH-06 Telemetry from Xbee will be used Base Station Requirements HIGH X 59 Presenter: Aman Mittal
  60. 60. Team Logo Here (If You Want) CDH Requirements ID Requirement Rationale Priority Parents Children VM A I T D CDH-07 AT Mode for Xbee will be used Base Mission Requirement HIGH X X CDH-08 Locating device active on landing Base mission requirements and to save power HIGH X X CDH-09 SPL for Buzzer shall be greater than 80dB For location HIGH X CDH-10 Handheld locator will trigger buzzer To provide ease in locating MEDIUM X X CDH-11 Buzzer will be off before landing Base mission requirements and to save power HIGH X CDH-12 CanSat will stop transmitting when triggered off Saving power MEDIUM X X CanSat 2012 PDR: Team 7634 (Garuda) 60 Presenter: Aman Mittal
  61. 61. Team Logo Here (If You Want) CDH Requirements ID Requirement Rationale Priority Parents Children VM A I T D CDH-13 The Pan ID of Xbee module should be set as Team Number To avoid interference HIGH X CanSat 2012 PDR: Team 7634 (Garuda) 61 Presenter: Aman Mittal
  62. 62. Team Logo Here (If You Want) Processor and Memory Trade Selection Arduino Uno Arduino Mega 2560 Custom ATMega 32 Board Processor Speed(MHz) 16 16 16 Operating Voltage 5 5 5 Data Interface (D/A) 14/6 54/16 Configurable Size(cm x cm) 6.5x5.2 10.1x5.2 ~5x6 Flash Memory(kB) 32 128 32 Price(in USD) 25 65 30 CanSat 2012 PDR: Team 7634 (Garuda) 62 Presenter: Aman Mittal
  63. 63. Team Logo Here (If You Want) Processor and Memory Trade Selection •Carrier – Arduino Uno is chosen for the microcontroller. –Easy interfacing, sufficient digital outputs for data handling. –Low price and size. •Lander –Arduino Uno is chosen for the microcontroller. –Same design for the carrier and Lander. CanSat 2012 PDR: Team 7634 (Garuda) 63 Presenter: Aman Mittal
  64. 64. Team Logo Here (If You Want) Memory Selection •SD card is used for external memory –Standard FAT 32 file system. –Large amounts of data can be stored. –Non-volatile. –Easy to retrieve data on laptop. CanSat 2012 PDR: Team 7634 (Garuda) 64 Presenter: Aman Mittal
  65. 65. Team Logo Here (If You Want) Carrier Antenna Trade and Selection A24 HASM450 A24 HABUF-P51 Gain(dB) 2.1 2.1 Frequency(GHz) 2.4 2.4 Application Fixed/Mobile Fixed Price (in USD) 6 5 •Carrier Antenna – –Here we are using XBP24BZ7SIT-004J with RPSMA connector module due to – •Ability to tilt the antenna in multiple ways . •Robustness of design and high gain. •Frequency – 2.4 GHz •VSWR<2 •Standard interface. CanSat 2012 PDR: Team 7634 (Garuda) Presenter: Aman Mittal 65
  66. 66. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Radio Configuration •The X-bee radios are to be used that will be set in the unicast mode. •Both the modules will be configured in AT mode. This makes the programming easy and allows transparent communication. •The Ground Station –The module will be configured as COORDINATOR AT. –This module will be communicating data with CanSat module which will be indicated in the destination address in SH and SL parameters –The PANID will be set as team no. •The CanSat Xbee Module –The CanSat module will be configured as ENDPOINT AT. –This module will have the destination address set as the ground station radio. –The PANID will be set as the team number. 66 Presenter: Aman Mittal
  67. 67. Team Logo Here (If You Want) RADIO CONFIGURATION CanSat 2012 PDR: Team 7634 (Garuda) •Both xbees connect to each other. •Ground station sends start command to CanSat and receives an ACK. Before Launch •Send packets of altitude and position to the ground. •At reaching the top, ground station sends command to send all sensor data. During Rise •The sensor data will be sent to the ground station. During Fall •The GPS position will be transmitted to the ground station. After Landing 67 Presenter: Aman Mittal
  68. 68. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Carrier Telemetry Format-1 •Data to be transmitted- –From Carrier •GPS data •Pressure and Temperature Sensor data •Battery Voltage data. •Velocity data. –From Lander •GPS data to the handheld device. •Data rate –The data will be sent once every 2 seconds. 68 Presenter: Aman Mittal
  69. 69. Team Logo Here (If You Want) Carrier Telemetry Format-2 •The data from GPS will be first processed by the microcontroller before sending. •The table shows the data that will be sent. •Typical GPS data – –$GPGGA,123519,4807.038,N,01131.000,E,1,08,0.9,545.4,M,46.9,M,,*47 CanSat 2012 PDR: Team 7634 (Garuda) Where: GGA Global Positioning System Fix Data •123519 Fix taken at 12:35:19 UTC •4807.038,N Latitude 48 deg 07.038' N •01131.000,E Longitude 11 deg 31.000' E •1 Fix quality •08 Number of satellites being tracked •0.9 Horizontal dilution of position •545.4,M Altitude, Meters, above mean sea level •46.9,M Height of geoid (mean sea level) above WGS84 ellipsoid •(empty field) time in seconds since last DGPS update •(empty field) DGPS station ID number •*47 the checksum data, always begins with * 69 Presenter: Aman Mittal
  70. 70. Team Logo Here (If You Want) Carrier Telemetry Format-3 CanSat 2012 PDR: Team 7634 (Garuda) Characters Sent Definition Hhmmss UTC Time LLLL.LLL Latitude LLLLL.LLL Longitude AAA.A Altitude TT No. of satellites tracked AAA.A Pressure Sensor – Altitude TT.T Air Temperature 70 Presenter: Aman Mittal
  71. 71. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Activation of Telemetry Transmissions •The telemetry will be enabled by sending a start command from the Ground station radio. •The CanSat radio will send an ACK, which will mark the start of telemetry. •The Ground Station will resend a START command in case the ACK is not received in a fixed timeframe. Presenter: Aman Mittal 71
  72. 72. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Locator Device Trade & Selection •The locator device will include a buzzer and a handheld device with GPS and Xbee. •The lander and carrier will both have a buzzer on them. •The buzzer will be activated by 2 means – –The data for GPS altitude is constant for 5 sec. –The ground station/handheld sends an ON command. •The deactivation will be through a switch on-board the buzzer PCB. •The handheld will get the GPS location of the carrier and lander, and with the help of its own GPS data, it can track the carrier and lander. 72 Presenter: Aman Mittal
  73. 73. Team Logo Here Electrical Power Subsystem Presenter: Sarthak Kalani CanSat 2012 PDR: Team 7634 (Garuda) 73
  74. 74. Team Logo Here (If You Want) EPS Schematic Overview CanSat Power System Carrier battery source Lander battery source Sensors + Xbee Arduino Board Buzzer and actuator Sensors + Xbee Arduino Board Buzzer 74 CanSat 2012 PDR: Team 7634 (Garuda) Presenter: Sarthak Kalani
  75. 75. Team Logo Here (If You Want) EPS Overview •2 supplies: Carrier + Lander •Most power consumers: GPS sensor and buzzer. •Power supply: –Main supply used : 9V. –Supply to components via 3.3V and 5V regulator ICs. –Rationale: Constant voltage to components. •Use of GPS and radio on Lander: –Rationale: Easy retrieval. –Cost, space, power and weight: not a limiting factor. •Power saving: –High power components switched on only in case of flight time. –Sleep mode used during 1hour wait time and before retrieval (except buzzer) via communication. CanSat 2012 PDR: Team 7634 (Garuda) 75 Presenter: Sarthak Kalani
  76. 76. Team Logo Here (If You Want) EPS Requirements-Carrier ID Requirement Rationale Priority Parent Children VM A I T D EPS-01 All electronic components of carrier will be powered. Necessary for the working of CanSat. High X EPS-02 Power shall be supplied by 3.3V and 5V regulator ICs (LM7833 and LM7805 used) Components require 3.3V and 5V regulated power supplies High X EPS-03 Voltage should displayed on LCD Efficient monitoring of battery voltage Low X X EPS-04 External switch and LED shall be used for initial and final on/off Easy power turn on/off mechanism High X EPS-05 Actuator should have an external switch for manual override. Easy process of testing Medium X X X CanSat 2012 PDR: Team 7634 (Garuda) 76 Presenter: Sarthak Kalani
  77. 77. Team Logo Here (If You Want) EPS Requirements-Lander ID Requirement Rationale Priority Parent Children VM A I T D EPS-06 All electronic components of lander will be powered. Necessary for the working of CanSat. High X EPS-07 Power shall be supplied by 3.3V and 5V regulator ICs (LM7833 and LM7805 used) Components require 3.3V and 5V regulated power supplies High X EPS-08 Voltage should displayed on LCD Efficient monitoring of battery voltage Low X X EPS-09 External switch and LED shall be used for initial and final on/off Easy power turn on/off mechanism High X CanSat 2012 PDR: Team 7634 (Garuda) 77 Presenter: Sarthak Kalani
  78. 78. Team Logo Here (If You Want) EPS Requirements-Lander ID Requirement Rationale Priority Parent Children VM A I T D EPS-15 Power to extra hardware to measure battery voltage Voltage level to be transmitted and so its hardware needs power. High EPS-16 External switch to turn lander on/off Easy mechanism for turning lander on/off High EPS-17 LED Display on/off power of lander High EPS-18 Power to accelerometer Need to measure external force with the same High CanSat 2012 PDR: Team 7634 (Garuda) 78 Presenter: Sarthak Kalani
  79. 79. Team Logo Here (If You Want) Carrier Electrical Block Diagram CanSat 2012 PDR: Team 7634 (Garuda) Arduino (9V) GPS(5V) P&T Sensor(3.3V) Actuator(3.3V) SD card(3.3V) Buzzer(9V) LCD(5V) Voltage Measurement Hardware(9V) Radio Transceiver(3.3V Power Source 3.3V regulator 5V regulator 9V supply 79 Presenter: Sarthak Kalani
  80. 80. Team Logo Here (If You Want) Lander Electrical Block Diagram CanSat 2012 PDR: Team 7634 (Garuda) Arduino (9V) GPS(5V) P&T Sensor(3.3V) Accelerometer(3.3V) SD card(3.3V) Buzzer(9V) LCD(5V) Voltage Measurement Hardware(9V) Radio Transceiver(3.3V Power Source 3.3V regulator 5V regulator 9V supply 80 Presenter: Sarthak Kalani
  81. 81. Team Logo Here (If You Want) Power Budget - Carrier CanSat 2012 PDR: Team 7634 (Garuda) S. No. Component Voltage (V) Current drawn (mA) Power (mW) Duty Cycle/ Time of operation Uncertainty (%) Capacity required (mAh)* Total Power Consumed (mW)* Source 1 Arduino (Board only) 9 0.02 18 100% 20 0.03 22 Meas 2 P&T Sensor 3.3 0.1 0.33 100% 10 0.15 0.4 DS 3 GPS Module 3.3 45 200 100% 10 50.0 160 DS 4 Transceiver Module 3.3 65 330 10% 10 7.50 33 DS 5 Actuator 3.3 30 99 1% 15 0.40 2 Est 6 Buzzer 9 15 135 3hrs 20 20.0 165 Est 7 SD card 3.3 50 165 5% 10 3.0 10 Est 8 Extra h/w (regulator ICs + voltage measurement h/w)** 9 0.1 0.9 100% 20 0.2 1 Meas 9 LCD 5 40 200 5% 10% 0.4 10 DS Total 81.28 403.4 * All values are assumed to be on higher side. ** Peak values attained. 81 Presenter: Sarthak Kalani
  82. 82. Team Logo Here (If You Want) Power Budget - Lander CanSat 2012 PDR: Team 7634 (Garuda) S. No. Component Voltage (V) Current drawn (mA) Power (mW) Duty Cycle/ Time of operation Uncertainty (%) Capacity required (mAh)* Total Power Consumed (mW)* Source 1 Arduino (Board only) 9 0.02 18 100% 20 0.03 22 Meas 2 P&T Sensor 3.3 0.1 0.33 100% 10 0.15 0.4 DS 3 GPS Module 3.3 45 200 100% 10 50.0 160 DS 4 Transceiver Module 3.3 65 330 10% 10 7.50 33 DS 5 Accelerometer 3.3 0.4 1.32 5% 10 0.02 0.1 DS 6 Buzzer 9 15 135 3hrs 20 20.0 165 Est 7 SD card 3.3 50 165 5% 10 3.0 10 Est 8 Extra h/w (regulator ICs + voltage measurement h/w)** 9 0.1 0.9 100% 20 0.2 1 Meas 9 LCD 5 40 200 5% 10% 0.4 10 DS Total 80.9 401.5 * All values are assumed to be on higher side. ** Peak values attained. 82 Presenter: Sarthak Kalani
  83. 83. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) External Power Control Mechanism •Separate on off switch both for carrier and lander •2 level Power monitoring system: –LED shows whether 9V battery is switched on/off –LCD screen displays the battery voltage level, thus displaying whether microcontroller is working properly or not. •All components put to sleep mode during 1hour prelaunch time and in the post flight period with the use of radio communication with CanSat. This prevents faster battery drain. 83 Presenter: Sarthak Kalani
  84. 84. Team Logo Here (If You Want) Power Source Trade and Selection CanSat 2012 PDR: Team 7634 (Garuda) S. No. Battery Name Battery Type Weight (gm.) Typical Voltage (V) Capacity (mAh) Energy (Wh) Cost (USD) Decision 1 Duracell ultra Alkaline 45 8.4 550 4.5 2.40 S 2 GP20R8H NiMH 42.5 7.9 210 1.8 2.96 NS 3 Li-9V500 Li-ion 48 8.2 500 4.5 3.88 NS 4 Energizer EN22 Alkaline 45.6 8.4 500 4.4 3.05 NS •Finally selected battery: Duracell Ultra. •Power available is 550mAh and 4.5Wh. •Power consumed (3hrs of working) is 250mAh and 0.5Wh •Available margin assuming 3 hours of working: 300mAh (55%) •Minimum time of operation assuming full operation of all components : 5hour. •Selection criteria: •Reliability •Cost •Easy availability •Service hours provided 84 Presenter: Sarthak Kalani
  85. 85. Team Logo Here (If You Want) Battery Voltage Measurement Trade And Selection CanSat 2012 PDR: Team 7634 (Garuda)  Additional hardware is comprised of voltage follower by inverting amplifier (used for attenuator here)  Voltage follower helps in isolation of output and input. Inverting amplifier corrects sign and provides given output as . Taking Rf as 10kΩ, Ri as 20kΩ,we get Vmax up to 5V.  ADC output multiplied by 2 gives exact Voltage value.  This is better than potential divider because • Consumes almost no current. • Has much better stabilization characteristics i f R R Presenter: Sarthak Kalani 85
  86. 86. Team Logo Here CanSat 2012 PDR: Team 7634 (Garuda) Flight Software Design Presenter: Sudeepto Majumdar 86
  87. 87. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) FSW Overview •Programming Language : .NET/JAVA •Developing Environment : Arduino IDE (processing language) •Flight software is responsible for ensuring that: –Carrier releases the Lander at the right time. –Lander is aware when its released. –All sensors and GPS data are read and the data packet for RF Transmission is prepared. –All read data and detailed flight log are stored on SD-Card. –Communication with ground station is maintained. –Speed of descent is controlled. Presenter: Sudeepto Majumdar 87
  88. 88. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) FSW Requirements ID Requirement Rationale Priority Parent(s) Child(ren) VM A I T D FSW-01 FSW shall initialize the sleep mode To save power MEDIUM X X FSW-02 FSW shall start telecommunication To avoid transmission of data while not in flight mode HIGH X X X FSW-03 FSW will be responsible for opening of parachute at 200m Base Mission Requirement HIGH SYS-05 X X X X FSW-04 FSW shall be responsible for releasing the lander at 91m Mission Requirement HIGH SYS-06 X X X X FSW-05 FSW shall collect data from sensors and then store and telemeter to the ground Base Mission Requirement HIGH SYS-07 X X X 88 Presenter: Sudeepto Majumdar
  89. 89. Team Logo Here (If You Want) FSW Requirements CanSat 2012 PDR: Team 7634 (Garuda) ID Requirement Rationale Priority Parent(s) Child(ren) VM A I T D FSW-06 FSW shall activate impact sensor after the lander is released To avoid sensor operations when not required MEDIUM X X X FSW-07 FSW shall stop telemetry of data after CanSat has landed To avoid transmission when not required MEDIUM X X 89 Presenter: Sudeepto Majumdar
  90. 90. Team Logo Here (If You Want) Carrier CanSat FSW Overview CanSat 2012 PDR: Team 7634 (Garuda) 90 Presenter: Sudeepto Majumdar
  91. 91. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Lander CanSat FSW Overview Presenter: Sudeepto Majumdar 91
  92. 92. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Software Development Plan •The GCS software is ready for use. •Development team: Kshiteej Mahajan, Rishi Dua •Testing: Initially testing done by taking Data manually generated from CSV file so as not to wait for Electrical Team. Later on, the input can be changed to serial input. •The FSW remains to be developed •Since the components are finalized and procurement is in process, Flight software design will be ready soon. •We need Arduino for lander and carrier, coding for which can be easily done in Arduino IDE. 92 Presenter: Sudeepto Majumdar
  93. 93. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) Ground Control System Design Presenters: Kshiteej Mahajan, Rishi Dua 93
  94. 94. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) GCS Overview Presenter: Rishi Dua Antenna receives Signal from Carrier Microcontroller provides serial input to the computer Computer processes, stores and displays the data 94
  95. 95. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) GCS Requirements ID Requirement Rationale Priority Parents Children VM A I T D GCS-01 Antenna shall point upwards and be at least 1m above the ground To prevent interference High X GCS-02 Data will be processed and stored To meet base mission requirements High SYS-07 X X GCS-03 Recovery of CanSat To avoid loss of carrier, lander and egg Medium SYS-02 X X GCS-04 Mission operations: Includes the detection of various phases by the GCS To ensure base mission requirements are met Medium X X X GCS-05 Real-time online uploading of data on a remote server For Remote Access Medium X X 95 Presenter: Rishi Dua
  96. 96. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) GCS Requirements ID Requirement Rationale Priority Parents Children VM A I T D GCS-06 Software made using JAVA and PHP Cross platform support and faster High X GCS-07 Power Backup for 4 hours Should not fail in case of power outage Low X 96 Presenter: Rishi Dua
  97. 97. Team Logo Here (If You Want) CanSat 2012 PDR: Team 7634 (Garuda) GCS Antenna Trade & Selection •The antenna to be used is A24HASM-450 – ½ wave dipole antenna. •The coverage of the antenna module is about the range of 2 km. •This antenna has omni-directional pattern when places in vertical direction. •The antenna should be able to cover a drift of up to 1km, so we have a margin of 500m from our design. •The antenna will be facing at an angle to the launch site to increase coverage. Presenter: Rishi Dua 97
  98. 98. Team Logo Here (If You Want) GCS Antenna Trade and Selection >3.5 m Via UART through FTDI connected to Xbee. Via level shifter At an angle to the launch site, to be decided based on testing and further reading. CanSat 2012 PDR: Team 7634 (Garuda) 98 Presenter: Rishi Dua
  99. 99. Team Logo Here (If You Want) GCS Software •Data taken currently from CSV file (which is updated every 2 seconds), later on plan to use serial input. •Data plotted and also uploaded simultaneously on the internet so that it can be remotely accessed. •Data plotted using Java library (Live-Graph). •Data can be exported into Excel file, XML, SQL and the Graph can be exported into JPEG image. •Since it is based on JAVA, PHP and SQL, it will be faster and more reliable than third party tools like Matlab. Moreover, all tools used are open source. •GPS data to be embedded in Google Maps, to possibly help recover location of the CanSat. CanSat 2012 PDR: Team 7634 (Garuda) Presenter: Kshiteej Mahajan 99
  100. 100. Team Logo Here (If You Want) GCS Software Description CanSat 2012 PDR: Team 7634 (Garuda) Data file Settings Graph Settings Graph Data Series Settings Presenter: Kshiteej Mahajan 100
  101. 101. Team Logo Here CanSat Integration and Test Presenter: Akash Verma CanSat 2012 PDR: Team 7634 (Garuda) 101
  102. 102. Team Logo Here (If You Want) CanSat Integration and Test Overview •With a project with large number of subsystems it becomes important to coordinate the multi disciplinary subsystems effectively keeping in mind that: –No team member is unutilized in wait of inputs from other subsystem –Each subsystem is working in the correct direction ensuring smooth integration in the fist go with minimum iterations. Hence in initial phase of execution, each subsystem is worked upon in parallel and merged on step-by-step catering to the needs and objectives as and when required. Tests would be performed for each subsystem in isolation and in integration with other systems in phased manner as explained in following slides. Presenter: Akash Verma CanSat 2012 PDR: Team 7634 (Garuda) 102
  103. 103. Team Logo Here (If You Want) CanSat Integration Phase One: Procurement and isolated Testing •In this phase all the components already decided will be procured like sensors, Xbee module, microcontrollers, parachutes, etc. •Based on the size inputs of various components, structural design will be finalized with any modifications if necessary. Fabrication of structure to be completed henceforth. •Each subsystem would be tested in isolation: –Data transfer through Xbee module –Operational testing of sensors –Testing parachutes for descent rates –Testing for structural integrity of body for impact forces –Verification of power specification for various components for any deviations. –Testing of flight software with dummy data CanSat 2012 PDR: Team 7634 (Garuda) 103 Presenter: Akash Verma
  104. 104. Team Logo Here (If You Want) CanSat Integration •Phase two: Subsystem Integration –Ensuring proper deployment of descent control mechanism and detachment of lander. –Integrating sensors and Flight software with the CDH –Physical integration of the electronics system into the mechanical structure •Phase three: Final Integration –Final integration of the systems and testing of whole system as a unit in a scenario as close to mission scenario as possible. CanSat 2012 PDR: Team 7634 (Garuda) 104 Presenter: Akash Verma
  105. 105. Team Logo Here (If You Want) Tests Performed Mechanical testing of egg protection system: •The egg protection system was system was tested by dropping under free fall from various heights to choose the cushion material. •In all tests, the hip protector is placed in the bottom. •From these tests, the foam ball + bubble wrap with egg in vertical orientation was finalized. Trial Material Drop height(ft) Impact velocity (m/s) Orientation Result 1. Bubble wrap 4 4.9 horizontal Fail Bubble wrap 4 4.9 vertical Fail Cotton 4 4.9 horizontal Fail Cotton 4 4.9 vertical Pass Cotton 10 7.7 vertical Fail Foam ball + bubble wrap 10 7.7 vertical Pass Foam ball +bubble wrap 20 11 vertical Pass Foam ball +bubble wrap 40 15 vertical Fail CanSat 2012 PDR: Team 7634 (Garuda) 105 Presenter: Akash Verma
  106. 106. Team Logo Here (If You Want) Tests to be performed •Sensors testing •Communication testing •Detachment of lander testing •Deployment of descent control system •Final Integrated testing of unit CanSat 2012 PDR: Team 7634 (Garuda) 106 Presenter: Akash Verma
  107. 107. Team Logo Here Mission Operations & Analysis Presenter: Arpit Goyal CanSat 2012 PDR: Team 7634 (Garuda) 107
  108. 108. Team Logo Here (If You Want) Overview of Mission Sequence of Events CanSat 2012 PDR: Team 7634 (Garuda) •Briefing •Last Mechanical control •Last Electrical control •Coming at Competition Arena Pre Flight •Pre-Flight operation •Launch Flight •Deploy CanSat at 600m •Opening parachute •Controlling descent rate to 10m/s + - 1m/s up to 200m •Data collection and transmission •Reducing descent rate to 5m/s at 200m •Detaching Lander at 91m •Landing and Locating CanSat Launch and Flight •Saving Data •Analyzing Data •Preparing PFR •PFR Presentation Post Flight 108 Presenter: Arpit Goyal
  109. 109. Team Logo Here (If You Want) Mission Operations Manual Development Plan •Mission Operation consist of 4 steps: –CanSat Integration –Launch Preparation –Launch Operation –Removal Operation CanSat 2012 PDR: Team 7634 (Garuda) 109 Presenter: Arpit Goyal
  110. 110. Team Logo Here (If You Want) CanSat Integration •The CanSat system is basically divided into three parts: –The Lander –The Carrier –Electrical and Electronic System •The integrated parts are to be assembled to make CanSat. •The Electrical System is first integrated with Lander and Carrier •The Carrier and Lander will be integrated and CanSat is ready for Launch. CanSat 2012 PDR: Team 7634 (Garuda) 110 Presenter: Arpit Goyal
  111. 111. Team Logo Here (If You Want) Launch Preparation •Take rocket to flight line and get launch pad assignment •Walk out with the pad manager and have rocket installed on rail. •Pad manager installs igniter. •Pad manager verifies igniter continuity if launcher has continuity tester. •Team’s picture next to Rocket •Team goes back to flight line and assigned crew position CanSat 2012 PDR: Team 7634 (Garuda) 111 Presenter: Arpit Goyal
  112. 112. Team Logo Here (If You Want) Launch Procedure •Request a GO/NO GO from GS •Verify recovery crew is in place and ready •Verify launch control officer is ready •Verify flight coordinator is ready. •Command ground station crew to activate the CanSat telemetry. •Verify with ground station crew that telemetry is being received. •Request GO/NO GO from ground station crew, recovery crew and flight coordinator. •Command launch control officer to proceed countdown and launch. CanSat 2012 PDR: Team 7634 (Garuda) 112 Presenter: Arpit Goyal
  113. 113. Team Logo Here (If You Want) Removal Procedure •Command ground station crew to disable telemetry from CanSat. •Team wait until all other launches are completed. •Command launch control officer to disarm the launch pads. •Launch control officer removes the arming key to the launch controller. •Pads are declared safe. •Team can go with the pad manager and removed the CanSat. CanSat 2012 PDR: Team 7634 (Garuda) 113 Presenter: Arpit Goyal
  114. 114. Team Logo Here (If You Want) CanSat Location and Recovery •The CanSat is integrated with GPS sensor and buzzer. •The GPS latitude will give data of co-ordinates with 1.5m uncertainty, this will give tentative position of CanSat •The buzzer will start beeping as soon as it will touch the ground •The buzzer beep will eventually help in locating and Recovering CanSat. •Also the physical appearance of parachute will help in detecting it CanSat 2012 PDR: Team 7634 (Garuda) 114 Presenter: Arpit Goyal
  115. 115. Team Logo Here Management Presenter: Rishi Dua CanSat 2012 PDR: Team 7634 (Garuda) 115
  116. 116. Team Logo Here (If You Want) CanSat Budget – Hardware S.No. Component Quantity Rate (USD) Cost (USD) 1 Arduino Board Uno 2 27.6 55.2 2 Pressure Sensor Bosch 2 20.0 40.0 3 GPS sensor 2 40.0 80.0 4 Accelerometer 1 12.0 12.0 5 Xbee Radios 2 pairs 50.6 101.2 6 Battery Duracell 10 (2 to be used, 8 spare) 2.4 24.0 7 Audio Buzzer 2 1.5 3.0 8 Antenna A24HSM450 2 6.0 12.0 9 Parachutes 3 25.0 75.0 10 Material for structure and fabrication N.A 50.0 50.0 11 Linear actuator 1 5.0 5.0 TOTAL 457.4 CanSat 2012 PDR: Team 7634 (Garuda) 116 Presenter: Rishi Dua
  117. 117. Team Logo Here (If You Want) Components Cost (USD) Laptop for GCS None Travel 12000 Rental 2000 Test facilities 100 Total 14100 CanSat 2012 PDR: Team 7634 (Garuda) CanSat Budget – Other Costs Any external financial help is not received yet. But plans have been made to avail external sponsorship. Next slide will show some of the strategies. 117 Presenter: Rishi Dua
  118. 118. Team Logo Here (If You Want) Sponsorship Plans •Website made: www.teamgaruda.in •Sponsorship brochure ready for distribution. •Online publicity Partner: Teknovates •Currently in talk with companies for title sponsor and co-title sponsor. •Publicity of Project through social marketing: Facebook and Twitter. CanSat 2012 PDR: Team 7634 (Garuda) Presenter: Rishi Dua
  119. 119. Team Logo Here (If You Want) Program Schedule CanSat 2012 PDR: Team 7634 (Garuda) 119 NOV 20-30 DEC 1-31 JAN 1-15 JAN 16-31 FEB 1-15 FEB 16-29 MAR 1-15 MAR 16-31 APR 1-15 APR 16-30 MAY 1-31 JUN 1-10 ELECTRICAL SYSTEMS IDENTIFYING SYSTEM REQUIREMENTS SELECTION OF COMPONENTS REQUIRED PROCUREMENT OF COMPONENTS AND TESTING IMPLEMENTATION OF ELECTRICAL SYSTEM DESIGN OVERALL TESTING OF ELECTRICAL SYSTEM Presenter: Rishi Dua
  120. 120. Team Logo Here (If You Want) Program Schedule CanSat 2012 PDR: Team 7634 (Garuda) 120 NOV 20-30 DEC 1-31 JAN 1-15 JAN 15-31 FEB 1-15 FEB 16-29 MAR 1-15 MAR 16-31 APR 1-15 APR 16-30 MAY 1-31 JUN 1-10 MECHANICAL DESIGN IDENTIFYING DESIGN REQUIREMENTS DESIGN OF DESCENT CONTROL SYSTEM CAD MODELLING TESTING THROUGH SIMULATIONS SELECTION OF MATERIALS PROCUREMENT OF MATERIALS IMPLEMENTATION OF MECHANICAL DESIGN TESTING OF MECHANICAL DESIGN Presenter: Rishi Dua
  121. 121. Team Logo Here (If You Want) Program Schedule CanSat 2012 PDR: Team 7634 (Garuda) 121 NOV 20-30 DEC 1-31 JAN 1-15 JAN 15-31 FEB 1-15 FEB 16-29 MAR 1-15 MAR 16-31 APR 1-15 APR 16-30 MAY 1-31 JUN 1-10 SOFTWARE CONTROLS IDENTIFYING SOFTWARE REQUIREMENTS DECISION ON SOFTWARE PLATFORM FOR GCS ALGORITHM DESIGN FOR FSW IMPLEMENTATION AND TESTING OF GCS SOFTWARE IMPLEMENTATION OF FSW FSW SYNC WITH ELECTRICAL SYSTEM COMPLETE SYSTEM TESTING Presenter: Rishi Dua
  122. 122. Team Logo Here (If You Want) Conclusions •Major accomplishments 1.The ground station software is ready 2.Website (http://www.teamgaruda.in) ready for sponsors 3.Subsystems are designed including material selection 4.Cost and income are balanced •Major unfinished work 1.We will produce CanSat prototype for testing 2.Looking for title sponsor We have been successful in all the duties until now. We will go on according to schedule until competition. CanSat 2012 PDR: Team 7634 (Garuda) 122 Presenter: Rishi Dua

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