TY - GEN
T1 - Multi-Outer Loop Adaptive Control for a VTOL Free-Wing Aircraft
AU - Axten, Rachel M.
AU - Khamvilai, Thanakorn
AU - Johnson, Eric N.
N1 - Publisher Copyright:
© 2024 by Rachel Axten, Thanakorn Khamvilai, and Eric Johnson. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2024
Y1 - 2024
N2 - This work extends a typical series cascade control structure to a multi-outer loop system applicable to coupled rigid body systems, including a VTOL free-wing aircraft. In this case, there are now external command signals from multiple outer subsystems that are designed simultaneously for a single inner subsystem. In the scenario of a VTOL free-wing aircraft, which has similar pitch dynamics to an aircraft coupled with a short, heavy-slung load in hover, the conventional outer loop adjusts the wing pitch attitude command to achieve the desired position and velocity. Simultaneously, a “swing loop” introduced in this work has a separate desired wing pitch attitude to achieve fuselage pitch damping. A Lyapunov stability analysis is included for the proposed multi-outer loop dynamic inversion architecture with a neuro-adaptive element to capture modeling errors. The proposed architecture successfully stabilizes a VTOL free-wing aircraft with simulation and flight test results included to demonstrate achieved fuselage damping in flight around hover.
AB - This work extends a typical series cascade control structure to a multi-outer loop system applicable to coupled rigid body systems, including a VTOL free-wing aircraft. In this case, there are now external command signals from multiple outer subsystems that are designed simultaneously for a single inner subsystem. In the scenario of a VTOL free-wing aircraft, which has similar pitch dynamics to an aircraft coupled with a short, heavy-slung load in hover, the conventional outer loop adjusts the wing pitch attitude command to achieve the desired position and velocity. Simultaneously, a “swing loop” introduced in this work has a separate desired wing pitch attitude to achieve fuselage pitch damping. A Lyapunov stability analysis is included for the proposed multi-outer loop dynamic inversion architecture with a neuro-adaptive element to capture modeling errors. The proposed architecture successfully stabilizes a VTOL free-wing aircraft with simulation and flight test results included to demonstrate achieved fuselage damping in flight around hover.
UR - http://www.scopus.com/inward/record.url?scp=85192138549&partnerID=8YFLogxK
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U2 - 10.2514/6.2024-0726
DO - 10.2514/6.2024-0726
M3 - Conference contribution
AN - SCOPUS:85192138549
SN - 9781624107115
T3 - AIAA SciTech Forum and Exposition, 2024
BT - AIAA SciTech Forum and Exposition, 2024
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2024
Y2 - 8 January 2024 through 12 January 2024
ER -