Critical Design Review Presentation Jan. 20, 2011

Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach

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

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)

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

Static margin CG: at 1.72 m from nosecone CP: at 2.38 m from nosecone Static margin: 0.66 m

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 two ½’’ holes to allow more components to also be attached. Steel rods attach to these hole and travel the length of the payload.

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.

Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach

Flight Simulations Maximum acceleration: 135 m/s 2 Maximum velocity: 216 m/s Apogee: 1625 m Total flight time: 130 s

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

Thrust to Weight Ratio Initial mass: 9.0 kg Initial thrust: 1100 N Thrust to weight ratio: 12.5

Parachute sizes and descent rates Drogue Chute SkyAngle 20 nylon d = 72.2 cm c D = 0.8 deployed at apogee (1625 m / 1 mi) descend at 20 m/s (65.6 ft/s) Main Chute SkyAngle 44 nylon d = cm c D = 1.87 deployed at 245m (800 ft) descend at 5.5 m/s (18 ft/s)

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

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

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

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)

Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach

Altimeters Camera Mechanism Sensors Arduino Acrylic window Payload Bay

Payload Overview Processing - Arduino microcontroller Atmospheric Sensors - temperature, pressure, humidity Optical Sensors – UV, Solar Irradiance Imaging – Camera mechanism Recovery (Electronics) – TeleMetrum and PerfectFlight Altimeters

Sensors 1-wire devices - Humidity/Solar - UV Temperature Pressure Difficulties in interfacing 1-wire devices UV Sensor Humidity/Solar Sensor Pressure

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

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

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

Recovery Electronics – Launch Process

Camera Mechanism Two Components: Camera Camera Mount / Positioning

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

Camera Positioning Mechanism to position camera to take well oriented images

Camera Positioning

Positioning Vector

Micro Camera Multiple micro cameras in various orientations Continuous video capture Inexpensive Lightweight

Outline Report Rocket Body and Structure Flight Simulations Payload and Electronics Bay Educational Outreach

Engineering Open House o University event hosted by students o Exhibitions to generate interest in engineering o Elementary through college students, general public o Discussing our rocket, rocketry basics o Space Shuttle tile, rocket reentry

o Illinois Space Society sponsored event o Middle and high school students from Illinois o Getting students interested in space o Demonstration discussing our rocket o Two rocket competitions o Rocket kits for middle school students o Junkyard rockets for high school students Illinois Space Day

Intended Schedule

Change in Rocket Name

Questions?