Application of Generic Flight Controller Design Approach for A Delta Canard Fighter Aircraft -ADMIRE

Lathasree, P; Pashilkar, AA; Sundararajan, N.

doi:10.1109/icc47138.2019.9123201

Cited by 1 publication

(2 citation statements)

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“…The ADMIRE fighter jet and its development of a generic flight controller are presented in detail in [6,8]. However, for completeness, it is briefly described here so its baseline FCS interface with the IFC block added in an adaptive control configuration can be accurately described and presented.…”

Section: Admire Baseline Controller Descriptionmentioning

confidence: 99%

“…For the purposes of the roll axis control (the first column of B v2r matrix, virtual to real (v2r)), the differential canards (KR2), and differential elevons (KR4) are used. For the pitch axis control (second column of B v2r matrix, the symmetric canards (KP1) and symmetric elevons (KP3) are used (see [6,8] for background). Finally, for the yaw axis control (third column of B matrix), the differential canards (KY2), differential elevons (KY4), and rudder (KY5) are used.…”

Section: Admire Baseline Controller Descriptionmentioning

confidence: 99%

See 1 more Smart Citation

Perspective Chapter: Intelligent Adaptive Flight Control Augmentation of a Dynamic Inversion Autopilot

M. Lam,

J. Calise,

T. Nguyen

2024

Adaptive Control Theory and Applications

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High-speed UAV flight control is challenged by unknown external aerodynamic disturbances and internal system variations due to complex aerodynamic configuration, propellant consumption, the center of gravity movement, and possible actuator failures. Redundant aerodynamic control effectors and engine inlet control mechanisms are exploited/blended to maintain adequate force/moment control to satisfy flight control reliability requirements. A control allocation (CA) mixing matrix is an essential element of the redundancy design in addressing fault tolerance capabilities. This paper employs an Intelligent Flight Controller (IFC) implemented in an adaptive control augmentation fashion to assist the UAV’s primary Nonlinear Dynamic Inversion (NDI) controller in restoring aircraft stability and command following objective when subjected to effector performance degradation, including failures. Through a blended design between optimal control modification (OCM) and derivative-free model reference adaptive control (DF-MRAC), the IFC offers performance consistency in comparison to traditional MRAC. The proposed IFC framework has demonstrated its effectiveness in assisting the baseline NDI flight control system to maintain its mission subjected to actuator’s failures (via an implicit automatic CA ‘re-distributing’ action). Furthermore, the IFC also works well with any existing onboard CA algorithm in dealing with effector failures without requiring restructuring of the CA blending matrix. It therefore deserves consideration for application to future high Mach UAVs.

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Section: Admire Baseline Controller Descriptionmentioning

confidence: 99%

Section: Admire Baseline Controller Descriptionmentioning

confidence: 99%