1. CanSat Interim Presentation II
Samuel Rustan (EE)
Yasmin Belhaj (ME)
Andrew Guerr (CE)
Andrew Grant (ME)
Maxwell Sandler (ME)
Technical Advisors: Dr. David Cartes, Dr. Victor DeBrunner
Course Instructors: Dr. Kamal Amin, Dr. Michael Frank
ME Senior Design Team #18
ECE Senior Design Team #10
March 19, 2013

2. Overview Mission Recap Finalized design and configurations
Fabrication Update
Electronics and Integration
Software development
Timeline and Budget
Tasks remaining
Presenter: Samuel Rustan

3. CanSat Project Overview
Design a container/payload system to be launched via rocket and develop autonomous descent control strategy to safely land CanSat
Container will house payload for initial descent
Payload will house electronic components and “sensor” (egg)
Telemetry data will be transmitted for flight duration
Sample Design Parameters and Restrictions
Size
Mass
Material
Descent Control Strategy
Presenter: Samuel Rustan

4. CanSat Project Overview
Sequence of action
Rocket supplied by AIAA, with specified rocket bay dimensions
Phase 1 from rocket detachment to 400 m: Per guidelines, a parachute or streamer must be used to decrease velocity to 20 m/s by 400 m mark.
Phase 2 from 400 m to ground level: Payload must detach from container. An aero-braking device (non-parachute) must deploy at 400 m to safely land Payload. The initial parachute will continue to control descent of container.
Telemetry data transmitted includes GPS data, altitude, air temperature, battery voltage, and flight software state.
Force sensor will be used to calculate force of impact from Payload.
Presenter: Samuel Rustan

5. Previous Benchmarks Finalized design for launch and descent
Compared passive braking method
Parachute vs. Streamer
Determined egg protection strategy
Iterative trials, various materials
Selectable Objective – Impact Force Sensor
Procured and tested electronic components
Delivered successful Preliminary Design Review (PDR)
Feedback: Scored 92% from AIAA/NASA Panel
Presenter: Samuel Rustan

6. Updated Launch Configuration
Container
Payload
Egg Compartment
Electronic
Components
Shelving
Separation
Mechanism
Parachute
Aero-braking
Structure
Explain selection of each subsystem:
Container is the entire length of structure. Made of plastic, it is open on the bottom.
Payload is the portion inside that houses the electronic components and the raw egg.
Parachute was selected by conducting an experiment on the braking efficacy and ease of implementation of parachutes and streamers for this application. The diameter of the parachute was calculated to achieve the desired 20 m/s at 400m.
While under descent of parachute, the payload will detach from the container via this separation mechanism. A motor will provide the rotation of this ring to allow the payload to fall from out from the bottom.
The aero-braking structure is secured in its launch configuration, surrounding the payload. Support rods connect the top and bottom portions of the aero-braking structure to the payload.
Electronic components are in the top portion of the payload, and the egg is housed near the bottom.

7. Updated Descent Configuration
-Maintained idea to use ABS Plastic and 3-D print top and bottom of aero-braking structure, on top of which we can mount the motor that controls the separation mechanism
-Torsional springs will be used to deploy these rods which have fabric attached in between
-These springs are held in compression by a wire running through the bottom, and released when a heating element breaks the wire slightly below 400m
-New components include a wire running from the bottom of the aero-braking structure to the ends of the rod, to secure the angle during deployment
Torsion Spring Torque of
2.14 [in*lb]

8. Fabrication Update Parts have been procured and machined
-Still waiting on parachute
-Dimensions have not been changed since last presentation
-Allow clearance in the rocket section of 130 mm x 250 mm
-Overcome sizing issues of micro-controller, motor, and payload
-Challenge meeting 700g weight requirements. Solution– use alternative egg protection method and/or alter material of support rods (aluminum, wood, plastic)
Parts have been procured and machined
Dimensions finalized to fit in rocket bay
Mass budget concerns (underweight)

9. Fabrication Update Top Left: Side View with Aerobrake deployed
Top Right: Aerobrak cut-away with antenna
Bottom Left: Top View with aero-brake deployed
Presenter: Andrew Grant

10. Release Mechanism Prototype
Presenter: Andrew Grant

11. Sensor (Egg) Protection
Polystyrene beads chosen from experiment
1050 [kg/m3]
-Polystyrene beads chosen to protect egg
-Will be inserted in the bottom portion of the CanSat as seen in above image
Presenter: Andrew Grant

12. Integration of Electrical Components
Each sensor on separate circuit board
#2 & #1 screws used to attach to plastic platforms
Glue to secure
Rubber footpads used to separate components from platform
Holes will be drilled in platform to provide wire bundle channel
(not shown)
-Multi-Level Electronics Arrangement
-Permanently Affixed to Payload Half
-Rigid shelves made of plastic
Presenter: Samuel Rustan

13. Configuration of Telemetry Components
CanSat Onboard Electronics
To Antenna
USB
XBEE
Antenna
Ground Station
-Multi-Level Electronics Arrangement
-Permanently Affixed to Payload Half
-Rigid shelves made of plastic
Note: USB cables for programming only
Presenter: Samuel Rustan

14. Integration of Electrical Components
Accelerometer
Press/Temp
GPS Module
Microcontroller
-Multi-Level Electronics Arrangement
-Permanently Affixed to Payload Half
-Rigid shelves made of plastic
Battery
XBEE Radio
Presenter: Samuel Rustan

15. Communications: Range Tests
Packet Loss: 0%
10%
30%
50%
Lost
Ground Level
Distance [m]
Test 1-6: 45 65 80
110
115+
~3 [m] high
Tests 7-10 60
120
140
180
190+
Results
2.4 GHz, 60 mW
Insufficient Range
Improper Test
Link Margin: 20 [dB]
Receiver Sensitivity: 100 [dB]
Received Power: 80 [dB]
Link Margin = 100 – 80
Enough margin to maintain link (accord. To Digi RF Tech)
Proposed Solutions
Increase Gain of Receiver Ant
Digi Int’l RF Engineer
Proper range test (5 [m] above any obstacle)
Presenter: Samuel Rustan

16. Ground Control Software
Flight Software
Working “Beta” version
Migration is “so far good”
No noticeable difference between the Uno and Mini functionality
Ground Station Software
Version 5, working “alpha” version
Written in Python
Both Mac (shown) & PC versions
Not yet fully integrated with all subsystems
Presenter: Andrew Guerr

17. Flight Software Current Working “Beta” version
Transmits telemetry data packet
Integrated with altimeter and GPS
Errors reading GPS data
Needs
Integration with accelerometer, voltage divider, buzzer, and motor
Support for user entry of altitude correction data
Altitude smoothing
Presenter: Andrew Guerr

18. Updated Gantt

19. Total Procurement Expenditures
Funding / Project Budget
Revenue
Expenses
Funding Source
Funds Received
Procured
Expense Amount
ECE Department
$200.00
ECE Components (Telemetry)
300
Private Donation
$750.00
Mechanical & Structural 70
Dr. Shih $
Shipping
15.00
State Farm
$250.00
Total Funds Generated $
Total Procurement Expenditures
385
Total Available Funds Remaining $

20. Looking Forward Parachute attachment Complete fabrication of CanSat
Emphasis on Open House Display
Test separation mechanism and aero-braking deployment using altimeter
Complete microcontroller migration
Complete range testing
Demonstrate Telemetry with FSW & GCSW
Prepare User Manual
Present AIAA Critical Design Review (Mar 29th)
Prepare Open House Demonstration (April 18th)