1. Critical Design Review Presentation Jan. 20, 2011

2. Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach & Budget

3. Major Changes For greater stability the rocket was made shorter (2.8m instead of 3.12m) Acrylic window for the payload bay Mini-camera

4. Rocket Body Specs Dimensions: –Length: 2.8m –Diameter: 102mm –Empty Mass: 7.72kg –CG Location: 168cm –CP Location: 238cm Motor Specifications: –Motor: Aerotech K828FJ-6 –Length: 579 mm –Diameter: 54 mm –Impulse: 2157 Ns –Max Altitude: 1613 m –Max Velocity: 222 m/s

5. Rocket Body and Structure Body Recovery (Vehicle) Engine housing system Payload housing system

6. Static margin CG at 172cm CP at 238 cm Static margin: 66cm

7. CG on the launch pad Established using vendor information 13.6kg launch pad, 40cm tall CG with rocket mounted 65cm above ground (25cm above blast shield) “Gun turret” launch pad to be used

8. Payload integration feasibility Payload encapsulated in a removable easy-to- access body tube we call the payload bay o Can attach in different components directly to it Bulkheads located on both sides of the payload bay o Provide protection from the ejection blasts o Each has 2 M6 holes to allow more components to also be attached Before the bulkhead slides in, the coupler will first be put in place around the it. Then the coupler and bulkhead together slide into the payload bay and are screwed into place via 12 M4’s To make this process easier the bulkheads may be glued into place on the couplers.

9. Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach & Budget

10. Flight Simulations Simulation Results: Maximum acceleration: 132 m/s 2 Maximum velocity: 216 m/s Apogee: 1627 m Total flight time: 155 s

11. Rail exit velocity 16 m/s at 1m altitude (53 ft/s at 3.3 ft)

12. Thrust to Weight Ratio Initial mass: 9.0 kg Initial thrust: 1100 N Thrust to weight ratio: 12.5 (safe)

13. Parachute sizes and descent rates Drogue Chute SkyAngle 20 nylon d = 72.2 cm c D = 0.8 deployed at apogee (1627m / 1mi) descend at 20 m/s (65.6 ft/s) Main Chute SkyAngle 44 nylon d = 158.0 cm c D = 1.87 deployed at 245m (800ft) descend at 5.5 m/s (18 ft/s)

14. Ejection charge amount test Ejection charge tests currently scheduled for February 12 The test is composed of two stages: In the first stage we determine the size of the charge to be used o Initial size based on our previous rocket In the second stage we will test the interaction between the two independent sets of charges

15. Test plans and procedures Each component of rocket will be tested, individually where applicable Electronics bay subassembly will be tested as a whole

16. Safety Plan Review of planned test procedure before each test Review of MSDS safety information applicable to each test Check each other’s work (theoretical and in the field)

17. Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach & Budget

18. Payload Overview Processing - Arduino micro controllers Atmospheric Sensors - UV, irradiance, temperature, pressure, humidity Photo Sensors - camera feedback Imaging – CHDK camera, mini cam, orientation system Recovery (Electronics) - GPS transceiver, TeleMetrum and PerfectFlight

19. Payload Connection Diagram

20. Data storage from the Arduino to a SD Card Description The storage shield allows for data to be stored and read from a standard SD card. Advantages -An SD card allows for more memory storage, which is useful for more advanced projects. From a design standpoint, it is also easier to work with a memory card rather than using the on-board memory. -It uses a minimal number of pins on the Arduino so that they can be used to connect to sensors and other equipment. -Availability of sample code and libraries for interfacing with the SD card. Disadvantage -The only disadvantage is the task of having to assemble and interface with the software. Communication Ports 54 Digital I/O Ports 16 Analog Inputs 128k Flash Memory SD card shield for the Arduino Arduino UNO

21. Data Storage USB -Interfacing with USB can cause the disk to become unreadable if program is not written properly. -Also, information can be lost if the data is written too quickly. SD Card -A SD card shield is more desirable for saving sensor data. -It is simpler to interface with the SD memory card than the USB. -The SD card shield uses fewer pins on the Arduino and other shields can be added on. USB shield SD card shield

22. Humidity/Temp/Solar Sensor We will monitor humidity, temperature, and solar radiation with this device It will be the second device in our one-wire “MicroLAN” Will be powered by parasitic power from our Arduino Humidity is measured from 0%-100% with 2% accuracy Temperature is measured from-55 to 125 degrees Celsius with a.5 degree accuracy Solar detector detects light in the visible to infrared portion of the spectrum, with peak detection at 850nm and an acceptance angle of 150 degrees

23. Pressure Sensor Multiple sensors for detecting cabin pressure Redundant system for altimeters

24. UV Index Meter We will monitor UV light with this sensor One-wire device that we are able to interface with our Arduino by creating a “MicroLAN” The device reports a UV index from 0-16 with a precision to one decimal place This device will be powered through its RJ45 connection using parasitic power drawn from the Arduino

25. CHDK Canon A480 Canon Hacker Software Development Kit Automated scripts for time lapse imaging Autofocus parameters and extended exposure times Data save as raw Uses AA batteries High resolution Document our trip and experience with pictures and videos

26. Mini Cam Highlights: Multiple mini cams in various orientations Continuous video capture Inexpensive and lightweight

27. Camera Orientation Gimble Mount for Gravity- based orientation Servo feedback state diagram Photodiode Sensor Array

28. Perfectflite miniAlt/WD Testing

29. Dual deployment avionics test Primary altimeter will be Perfectflite MAWD with Altus Metrum Telemetrum as a backup Ground tests will be conducted for both altimeters by emulating pressure decreases on the ground that will be expected during flight LEDs will be placed at ejection charge terminals in place of ejection charges for preliminary testing. Lighting of LEDs will indicate success. Afterwards, actual ejection charges will be tested. Perfectflite MAWDAltus Metrum Telemetrum

30. Telemetrum GPS Tests Time taken until GPS lock will be measured GPS accuracy will be verified with known coordinates across campus Ability to maintain connection to ground computer at expected altitude will be observed Battery life will be measured AltOS interface

31. Scale model flight test Due to the delays with parts delivery we decided to upgrade our scale model flight test to a full scale flight test Full-scale flight tests planned for Feb 19-20, Mar 12-13, Mar 26-27

32. Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach & Budget

33. Activity Plan Engineering Open House o University of Illinois Engineering College sponsored event o Open to elementary through college students and the general public o Team Rocket will be discussing Moltres, past rockets built by ISS and model rocket basics o Also demonstrating the heat resistivity of a Space Shuttle tile and relate it to rocket reentry along with other exhibits Illinois Space Day o Illinois Space Society sponsored event o Open to junior and high school students throughout Illinois o Dedicated to getting students excited about math, science, and more specifically, space o Team Rocket will also be going over model rocket basics along with helping students build their own small rocket to launch later that day

34. Intended Schedule

35. Budget Incoming Funds SourceAmount NASA SMD$5,000 UIUC Design Council$2,145 Illinois Space Society$500 SORF$933* Total:$7,767 *UIUC Engineering Council (SORF) will pay for 75% of specific items totaling $933. The additional 25% ($311) will come from Illinois Space Society funds Current budget estimates predict $1,900 for team travel. Combined with an expected rocket cost of about $5,000, around $800 is left for testing, shipping, ground support and other expenses.

36. Questions?