Launch vehicle load relief algorithms are concerned with realizing a reduction of transient bending moments near maximum dynamic pressure. Traditional approaches to load relief typically use inner-loop acceleration feedback to reduce the wind-induced angle of attack. When implemented in the inner loop, load relief bandwidth is necessarily limited by the achievable stability margins, and when acceleration feedback is employed, by the uncertainty associated with structural modes that couple with the body-mounted accelerometer. The structure of innerloop load relief increases the dimensionality of the flight control gain and filter optimization problem. Most importantly, classical load relief laws do not take advantage of high-rate and high-accuracy GPS-aided inertial velocity data that is readily available from modern strapdown IMUs.
A MODERN LOAD RELIEF GUIDANCE SCHEME FOR SPACE LAUNCH VEHICLES
Proceedings of the 44th Annual American Astronautical Society Guidance, Navigation, and Control Conference, 2022 ; Chapter : 44 ; 755-774
2024-01-01
20 pages
Article/Chapter (Book)
Electronic Resource
English
LOAD RELIEF FOR LAUNCH VEHICLES USING AN ENGINE BIASING ECHNIQUE
SAE Technical Papers | 1989
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