Stephan Shurn 28 February 2008 Propulsion Thrust Vector Control

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Presentation transcript:

Stephan Shurn 28 February 2008 Propulsion Thrust Vector Control AAE 450 Spring 2008

Liquid Injection Thrust Vector Control (LITVC) Gimbaling more expensive due to manufacturing for Hybrid/Solid Liquid 90% H2O2 4 Injectors normal to centerline 4 Valves on each injector Signal from controller, relay to valve and inject Hardware on engine (valves and injectors) already in engine cost AAE 450 Spring 2008 Propulsion

LITVC Future Work Assumptions Code integration for LITVC prop. 0.8 Fs/Fp 0.09 ws/wp Prop. Injected for 1/3 of tb 1st Stage Tap off from main tank 10.26 kg of H2O2 Mp = 10.264 kg 2nd Stage Carry own fuel tank and nitrogen tank ~ 1.03 MPa Mp = 1.265 kg 3rd Stage No LITVC – Spin Stabilize Future Work Code integration for LITVC prop. Prop needed from duty cycle data AAE 450 Spring 2008 Propulsion

Backup AAE 450 Spring 2008 Propulsion

LITVC Calculation Input Calculations Thrust (vac) Mass Flow rate Stage Burn Time Calculations Side thrust = (0.8)*Thrust Side Mass Flow Rate = (0.9)*main mass flow rate Time of injection = (1/3)*tburn mprop = Side Mass Flow Rate * Time of injection AAE 450 Spring 2008

Force and Mass Flow Rate Chart Force ratio and mass flow ratio have linear relation Image courtesy E. Glenn Case IV1 AAE 450 Spring 2008

Sources Case IV, E. G., “Preliminary Design of a Hybrid Rocket Liquid Injection Thrust Vectore Control System," AIAA Paper, No. 2008-1420, January 2008 Broadwell, J., “Analysis of the Fluid Mechanics of Secondary Injection for Thrust Vector Control,” AIAA Journal, Vol. 1, No. 5, 1963, pp 1067-1075. Ciepluch, Carl, “Technology for Low Cost Solid Rocket Boosters,” NASA TM X-67912, November 1971. “Thrust Vector Control System Study Program,” Vol. I - Rep. TWR-4037-Vol. 1, Thiokol Chemical Corp. (NASA CR-72727), June 15, 1970. AAE 450 Spring 2008 Propulsion