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Preliminary Design Review: 

Preliminary Design Review Yonas Alemu Tyler Welch Megan Christopher Jeremy Stromsoe Jeremy Bank Group 1, June 07 2007

Introduction: 

Introduction November 3, 1957 the Russians sent dog into orbit May 28, 1959 the United States launch two monkeys from Cape Canaveral Today NASA still uses animals in space to test the effects of microgravity on bodies Christopher

Introduction (continued): 

Introduction (continued) Australian Billionaire Michael Antolini’s plan First test flight in 1994 when Jeremy Stromsoe launched a lizard with ESTES Rising Star Rocket Testing stagnation temperature and pressure to prove the flight worthiness of the team Christopher

Test Predictions: 

Test Predictions Goal: To predict thrust, altitude, velocity, stagnation temperature, and stagnation pressure profiles Sources include laboratory measurements and assumptions made Thrust and mass profiles were collected from NowHybrids.com for the HT J motor and 300cc N2O tank Welch

Test Predictions (continued): 

Test Predictions (continued) Assumed mf = 2.794 kg Force Balance: Euler's method: Time to apogee = 12.488 s Max Height = 705.75 m Max Velocity = 113.38 m/s Welch

Test Predictions (continued): 

Test Predictions (continued) Incompressible, isentropic flow linear static temperature and static pressure profiles Welch

Low Pressure Measurement: 

Low Pressure Measurement Circuitry consists of: -48psi max pressure transducer: Consists of a micro-machined silicon diaphragm with piezoresistive strain gauges diffused into it, fused to a silicon or glass backplate. Pressure induced strain increases the value of the radial resistors, and decreases the value of the resistors transverse to the radius. -Texas Instruments Op-Amp, INA2126 Chip Feeds amplified micro amp signal from pressure transducer into the RDAS for recording. -Battery Pack 3 x 1.5 V AA Battery Pack provides a DC Current Source for the Op-Amp chip and the pressure transducer. Pressure Transducer Texas Instruments Op-Amp Stromsoe

Slide8: 

Pspice Schematic of Pressure Transducer Circuitry Stromsoe

Temperature Measurement: 

Temperature Measurement Circuitry Consists of: AD595AQ Monolithic Thermocouple Chip This provides an “ice” reference point from which to compare measurements as a pre-calibrated signal amplification. Type K Alumel(NiAl alloy)/Chromel (CrAl alloy) Wire Thermocouple When a conductive material is subjected to a thermal gradient, a small voltage is produced. This is also known as the Seebeck Effect (1821, the German-Estonian physicist Thomas Johann Seebeck) -RDAS Flight Data Recorder -Battery Pack AD595 Monolithic Thermocouple Chip Two Wire Thermocouple Stromsoe

Pspice Schematic of Thermocouple Circuitry: 

Pspice Schematic of Thermocouple Circuitry Stromsoe

Sensor Locations: 

Sensor Locations Pressure Transducer Thermocouple Wire Battery Pack Circuit Board Temperature Pitot Stromsoe

Instrument Calibration: 

Instrument Calibration Pressure Transducer: In laboratory, input pressures on the same scale expected by test predictions Discover linear psi/volt relationship Thermocouple: Pre-calibrated with a known ºC/volt relationship Verify and test at different voltage inputs Voltage divider: To compensate for battery power dissipation Welch

Instrument Testing: 

Instrument Testing Pressure Transducer: Place syringe on tip of transducer. Ensure pressure on gauge reads predicted calibrated psi/volt pressure Compare RDAS collected data to calibrated expected result. Thermocouple: Place thermocouple wire in water bath. Cool water with ice, record decrease in temperature using thermometer. Compare RDAS collected data to calibrated expected result. Stromsoe

PRE-FLIGHT REVIEW CHECKLIST: 

PRE-FLIGHT REVIEW CHECKLIST Check continuity of light bulb Check attachments to data recovery devices Check Center of Pressure and Center of Gravity Check airframe structures for firm attachment such as Fin, Nosecone Check the motor mount Alemu

Testing the GSE: 

Check the launch pad suitable for the rocket Check the launch lug, or rail guide suitable for the rocket Confirm the launch angle Testing the GSE Launch Stem; (GOX) line; Solenoid Assembly; GOX Assembly; Ignition module; Launch Controller; Alemu

Slide16: 

Confirm stripped igniter wire ends to the alligator clips of the ignition Confirm launch pad area is clear prior to checking the oxidizer fill system. Check fully open the Gaseous Oxygen and Nitrous oxide tank valve and verify that there are no leaks. Verify launch controller switches Safe/Arm key switch on Safe, rotary switch on Fill (top) position, and activate switch Off/On. LAUNCH Pre launch check lists Alemu

Primary Mission Failures: 

Primary Mission Failures Bank

Secondary Mission Failures: 

Secondary Mission Failures Bank

Conclusion: 

Conclusion Launch hybrid launch vehicle and test stagnation temperature and pressure to determine flight worthiness Proper planning and precautionary actions have been outlined to ensure a successful launch Bank

What Went Wrong?: 

What Went Wrong? Known Facts: Rocket successfully launched At launch the circuit was continuous The ejection charge did not deploy the parachute Post launch the flash bulb was not continuous and destroyed The RDAS chip was destroyed and we hope to recover the data on the flash memory drive in the future Christopher

Possible Causes: 

Possible Causes Alemu

Acceleration Testing: 

Acceleration Testing Jeremy Stromsoe

Slide23: 

Results of Acceleration Testing Drop Height = 1 inch Bulb fired after testing… Result: Flashbulbs still ignite after heavy acceleration loads (equivalent to those at liftoff). Acceleration eliminated as possible cause. Jeremy Stromsoe

Vibration Testing: 

Vibration Testing Welch

Possible Solutions: 

Possible Solutions Bank