Publication Date:
2019-07-13
Description:
An integrated flight/propulsion control system design is presented for the piloted longitudinal landing task with a modern, statically unstable, fighter aircraft. A centralized compensator based on the Linear Quadratic Gaussian/Loop Transfer Recovery methodology is first obtained to satisfy the feedback loop performance and robustness specificiations. This high-order centralized compensator is then partitioned into airframe and engine sub-controllers based on modal controllability/observability for the compensator modes. The order of the sub-controllers is then reduced using internally-balanced realization techniques and the sub-controllers are simplified by neglecting the insignificant feedbacks. These sub-controllers have the advantage that they can be implemented as separate controllers on the airframe and the engine while still retaining the important performance and stability characteristics of the full-order centralized compensator. Command prefilters are then designed for the closed-loop system with the simplified sub-controllers to obtain the desired system response to airframe and engine command inputs, and the overall system performance evaluation results are presented.
Keywords:
AIRCRAFT STABILITY AND CONTROL
Type:
NASA-TM-102137
,
E-4860
,
NAS 1.15:102137
,
AIAA PAPER 89-3520
,
Guidance, Navigation and Control Conference; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
Format:
application/pdf
