ABSTRACT
The paper addresses the precision missile guidance problem where the successful intercept criterion has been defined in terms of both minimizing the miss distance and controlling the missile body attitude with respect to the target at the terminal point. We show that the H 1 control theory when suitably modified provides as effective framework for the precision missile guidance problem. Existence of feedback controllers (guidance laws) is investigated for the case of finite horizon and non-zero initial conditions. Both state feedback and output feedback implementations are explored.
Keywords. Precision missile guidance, robust control, H 1 control, optimal control, Riccati equations
ABSTRACT
This paper deals with fault detection and identification (FDI) of sensor failures in an aircraft flight control system. The proposed FDI algorithm only weakly depends on a specific model of an aircraft. The advantage of such an FDI algorithm is the possible reduction in the flight control system complexity and cost due to the reduced number of redundant hardware components required to ensure safe flight operation in cases of failures. The non-mode] based approach is in particular attractive because it could provide an FDI algorithm suitable for implementation on a variety of aircraft with only minimal adjustments required when using it on a specific aircraft, thus reducing the development cost. The current paper focuses on non-distinctive sensor failures that are identified using dissimilar sensor information. The proposed FDI algorithm was favorably tested using a realistic simulation model of a small civil aircraft.
Key Words. Fault detection and identification, fault tolerant flight control, Neural Networks, Wavelet Transform.
ABSTRACT
The design goal of independent control of sideslip angle, roll angle and yaw angle of an aircraft is considered. To handle the issue the input-output decoupling technique is applied to the lateral motion dynamics of the aircraft. The conditions under which the problem is solvable via state feedback appears to be generically true. The general form of the static controllers, as well as the general form of the resulting decoupled closed loop system, are derived. The results has been illustrated by simulation to the data of 5th-order FPCC aircraft.
Key Words. I/O Decoupling, Flight Control, Linear System, Multvariable Control