TY - GEN
T1 - A Comparison of Partially and Fully Integrated Guidance and Flight Control Optimized with Reinforcement Meta-Learning
AU - Gaudet, Brian
AU - Furfaro, Roberto
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - We use reinforcement meta-learning to optimize and evaluate two integrated guidance and flight control systems, the first being fully integrated and the second being partially integrated. The fully integrated system maps navigation system outputs directly to commanded control surface deflections. In contrast, in the partially integrated system a guidance system maps navigation system outputs to a commanded acceleration, with the flight control system mapping this acceleration to commanded deflections. The latter approach is integrated in the sense that the flight control system consists of a single control loop, and is optimized for a particular guidance system. We optimize and evaluate the two approaches in an environment modeling a point defense interceptor defending against a hypersonic threat. We find that both systems adapt to a large flight envelope and off-nominal flight conditions that include perturbation of aerodynamic coefficient parameters and flexible body dynamics. Similarly, both systems are robust to the parasitic attitude loop induced by radome refraction and imperfect seeker stabilization. We then repeat the experiment by evaluating the two approaches in an air-to-air missile environment. Although our original hypothesis was that the fully integrated system would provide the highest performance, in both environments we found that the converse was true.
AB - We use reinforcement meta-learning to optimize and evaluate two integrated guidance and flight control systems, the first being fully integrated and the second being partially integrated. The fully integrated system maps navigation system outputs directly to commanded control surface deflections. In contrast, in the partially integrated system a guidance system maps navigation system outputs to a commanded acceleration, with the flight control system mapping this acceleration to commanded deflections. The latter approach is integrated in the sense that the flight control system consists of a single control loop, and is optimized for a particular guidance system. We optimize and evaluate the two approaches in an environment modeling a point defense interceptor defending against a hypersonic threat. We find that both systems adapt to a large flight envelope and off-nominal flight conditions that include perturbation of aerodynamic coefficient parameters and flexible body dynamics. Similarly, both systems are robust to the parasitic attitude loop induced by radome refraction and imperfect seeker stabilization. We then repeat the experiment by evaluating the two approaches in an air-to-air missile environment. Although our original hypothesis was that the fully integrated system would provide the highest performance, in both environments we found that the converse was true.
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U2 - 10.2514/6.2023-1628
DO - 10.2514/6.2023-1628
M3 - Conference contribution
AN - SCOPUS:85175598906
SN - 9781624106996
T3 - AIAA SciTech Forum and Exposition, 2023
BT - AIAA SciTech Forum and Exposition, 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2023
Y2 - 23 January 2023 through 27 January 2023
ER -