Critical Design Review Presentation Jan. 20, 2011.
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Transcript of Critical Design Review Presentation Jan. 20, 2011.
![Page 1: Critical Design Review Presentation Jan. 20, 2011.](https://reader036.fdocuments.in/reader036/viewer/2022062518/56649eb45503460f94bbbe47/html5/thumbnails/1.jpg)
Critical Design Review Presentation
Jan. 20, 2011
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Outline Report
• Rocket Body and Structure • Flight Simulations
• Payload and Electronics Bay
• Educational Outreach
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Major Changes
• For greater stability the rocket was made shorter (2.80 m instead of 3.12 m)
• Acrylic window for the payload bay
• Mini-camera
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Rocket Body Specs
• Dimensions:– Length: 2.80 m
– Diameter: 102 mm
– Empty Mass: 7.72 kg
– CG Location: 1.68 m
– CP Location: 2.38 m
• Motor Specifications:– Motor: Aerotech K828FJ-6
– Length: 57.9 cm
– Diameter: 54 mm
– Impulse: 2157 Ns
– Max Altitude: 1625 m
– Max Velocity: 216 m/s (Mach 0.64)
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Rocket Body and Structure
Body
Recovery (Vehicle)Engine housing system Payload housing system
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Static margin
CG: at 1.72 m from noseconeCP: at 2.38 m from nosecone
Static margin: 0.66 m
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Payload integration feasibility• Payload encapsulated in a removable easy-to-access body tube we
call the payload bayo Can attach in different components directly to it
• Bulkheads located on both sides of the payload bayo Provide protection from the ejection blastso Each has two ½’’ holes to allow more components to also be attached. Steel
rods attach to these hole and travel the length of the payload.
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Payload integration feasibility• First the Payload tube slides over the electronics stack.
• Then the coupler and bulkhead together slide into the payload bay and are screwed into place via 12 M4s
• To make this process easier the bulkheads may be glued into place on the couplers.
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Outline Report
• Rocket Body and Structure • Flight Simulations
• Payload and Electronics Bay
• Educational Outreach
![Page 10: Critical Design Review Presentation Jan. 20, 2011.](https://reader036.fdocuments.in/reader036/viewer/2022062518/56649eb45503460f94bbbe47/html5/thumbnails/10.jpg)
Flight Simulations
Maximum acceleration: 135 m/s2
Maximum velocity: 216 m/sApogee: 1625 mTotal flight time: 130 s
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Rail exit velocity
16 m/s at 1 m altitude (53 ft/s at 3.3 ft)
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Thrust to Weight RatioInitial mass: 9.0 kgInitial thrust: 1100 N
Thrust to weight ratio: 12.5
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Parachute sizes and descent ratesDrogue Chute
SkyAngle 20nylond = 72.2 cmcD = 0.8deployed at apogee (1625 m / 1 mi)
descend at 20 m/s (65.6 ft/s)
Main ChuteSkyAngle 44nylond = 158.0 cmcD = 1.87deployed at 245m (800 ft)
descend at 5.5 m/s (18 ft/s)
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Test plans and procedures
• Each component of rocket will be tested, individually where applicable
• Electronics bay subassembly will be tested as a whole
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Ejection charge tests
Ejection charge tests currently scheduled for February 12
The test is composed of two stages:
• Determine size of the charge • Based on recommendations and past experience
• Live test• Particularly interested in the interaction between the two independent sets of
charges
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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 forFeb 19-20, Mar 12-13, Mar 26-27
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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)
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Outline Report
• Rocket Body and Structure • Flight Simulations
• Payload and Electronics Bay
• Educational Outreach
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Altimeters
Camera Mechanism
Sensors
Arduino
Acrylic window
Payload Bay
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Payload Overview• Processing - Arduino
microcontroller
• Atmospheric Sensors - temperature, pressure, humidity
• Optical Sensors – UV, Solar Irradiance
• Imaging – Camera mechanism
• Recovery (Electronics) – TeleMetrum and PerfectFlight Altimeters
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Sensors• 1-wire devices
- Humidity/Solar
- UV
• Temperature
• Pressure
• Difficulties in interfacing 1-wire devices UV Sensor
Humidity/Solar Sensor
Pressure
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Data storage
SD card shield for the Arduino
• SD card shield – quick, easy data collection
• Requires fewer pins
• USB vs. SD
- Simplicity
- Interfacing
- USB: Programming complications
vs.
USB shield
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Dual Deployment Avionics• PerfectFlite MAWD and Altus Metrum Telemetrum will be
mounted side by side
• Successful ground tests using LEDs for both altimeters by simulating launch
• LEDs were placed at ejection charge terminals in place of ejection charges
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Telemetrum GPS Tests• Time taken until GPS
lock will be measured
• Current Process - Verification
- GPS accuracy
- Range of connection to ground computer
- Battery life AltOS interface
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Recovery Electronics – Launch Process
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Camera Mechanism
Two Components:
• Camera
• Camera Mount / Positioning
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Camera
• The Camera takes pictures during the launch, descent, and landing of the Rocket
• Camera must be small enough to fit in Optical section of Payload
• Interfaced with storage unit to compress and save photos
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Camera Positioning
• Mechanism to position camera to take well oriented images
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Camera Positioning
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Positioning Vector
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Micro Camera
• Multiple micro cameras in various orientations
• Continuous video capture
• Inexpensive
• Lightweight
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Outline Report
• Rocket Body and Structure • Flight Simulations • Payload and Electronics Bay • Educational Outreach
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Engineering Open Houseo University event hosted by studentso Exhibitions to generate interest in engineeringo Elementary through college students, general publico Discussing our rocket, rocketry basicso Space Shuttle tile, rocket reentry
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o Illinois Space Society sponsored evento Middle and high school students from Illinois o Getting students interested in spaceo Demonstration discussing our rocketo Two rocket competitions
o Rocket kits for middle school studentso Junkyard rockets for high school students
Illinois Space Day
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Intended Schedule
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Change in Rocket Name
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Questions?