An alternative attitude control strategy for SCRAMSPACE 1 experiment

Banerjee, Sanchito, Creagh, Michael and Boyce, Russell (2014). An alternative attitude control strategy for SCRAMSPACE 1 experiment. In: AIAA Guidance, Navigation, and Control Conference. AIAA Guidance, Navigation, and Control Conference 2014 - SciTech Forum and Exposition 2014, National Harbor, MD, United States, (1-17). 13-17 January 2014. doi:10.2514/6.2014-1475


Author Banerjee, Sanchito
Creagh, Michael
Boyce, Russell
Title of paper An alternative attitude control strategy for SCRAMSPACE 1 experiment
Conference name AIAA Guidance, Navigation, and Control Conference 2014 - SciTech Forum and Exposition 2014
Conference location National Harbor, MD, United States
Conference dates 13-17 January 2014
Convener American Institute of Aeronautics and Astronautics
Proceedings title AIAA Guidance, Navigation, and Control Conference
Journal name AIAA Guidance, Navigation, and Control Conference
Place of Publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2014
Sub-type Fully published paper
DOI 10.2514/6.2014-1475
Open Access Status
ISBN 9781600869624
Start page 1
End page 17
Total pages 17
Collection year 2015
Abstract/Summary The current reaction control strategy for SCRAMSPACE 1 involves an exo-atmospheric reorientation using attitude and rate feedback from the Inertial Navigation System. An alternative design methodology of an attitude control system is presented that only uses rate feedback. This eliminates the need for an attitude determination system altogether. This methodology is designed to re-orient the hypersonic experimental vehicle SCRAMSPACE 1 by using rate damping and natural aerodynamic moments. It is desired that the re-orientation produces a 2.5 degrees angle of attack at 32km altitude on the decent trajectory. This angle of attack is necessary in order to test the scramjet at Mach 8. The re-entry rate damping is initialized at an altitude of 55km on the descent trajectory. The worst case scenario angle of attack of 150 degrees is taken as the initial conditions at 200km altitude. For the worst case scenario, thrusters of size 10N, 15N, 20N, 25N and 30N are able to acquire the desired angle of attack. The final angles of attack for all the aforementioned thruster sizes are less than 1 deg. The mean of the angle of attack during the experimental window is under 0.5 degrees for all tested cases of thruster force, initial spin rate and initial angle of attack. However, when a sensible fuel restriction of 5kg is placed, the recommended thruster size is 20N.
Q-Index Code EX
Q-Index Status Confirmed Code
Institutional Status UQ

 
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Created: Tue, 11 Mar 2014, 00:37:38 EST by System User on behalf of School of Mechanical and Mining Engineering