Development of an integrated fire/flight control system for a high-performance fighter aircraft

1977 ◽  
Author(s):  
J. WATSON ◽  
G. KOMECHAK
Keyword(s):  
Control System ◽  
Flight Control ◽  
High Performance ◽  
Flight Control System ◽  
Fighter Aircraft

LQG-Based Robustifying Flight Control System

2003 ◽  
Author(s):  
D. Griffin ◽  
A. G. Kelkar
Keyword(s):  
Control System ◽  
Flight Control ◽  
Controller Design ◽  
Second Step ◽  
Flight Control System ◽  
Robust Controller ◽  
Fighter Aircraft ◽  
Stability Robustness ◽  
Uncertainty Model ◽  
The Stability

This paper presents a robust controller design for an automatic flight control system (AFCS) for a fighter aircraft model with eight inputs and seven outputs. The controller is designed based on McFarlane-Glover robustifying technique using a simple baseline LQG design. Controllers designed purely based on traditional LQG techniques are known to have no guaranteed robustness margins. The McFarlane-Glover technique can be used to enhance the stability robustness of the baseline LQG design using a two-step design process. In the first step, an LQG controller is designed which is optimized only for performance without any consideration to robustness. In the second step, the performance optimized LQG design is rendered robust using McFarlane-Glover procedure. The robustifying procedure uses a coprime factor uncertainty model and H∞ optimization. An important advantage of this procedure is that no problem dependent uncertainty modelling or weight selection is required in the second step of the process. The robustifying procedure also yields the quantitative estimate of the robustness.

scholarly journals Aircraft/Engine Integration for an Advanced Fighter Considering Mission Specifics

1986 ◽  
Author(s):  
G. Rauh ◽  
W. Anders
Keyword(s):  
Control System ◽  
Flight Control ◽  
System Integration ◽  
High Performance ◽  
Single Point ◽  
Aircraft Engine ◽  
Propulsion System ◽  
Normal Operation ◽  
Flight Control System ◽  
Engine Control System

In this paper propulsion system integration is considered for an advanced twin engined, high performance agile air to air fighter aircraft in view of its requirements for extreme flight conditions and maneuvers. The propulsion system mainly consists of air inlets, engines and nozzle/afterbody systems. The air inlet, a propulsion subsystem within the aircraft manufacturers responsibility, is physically well integrated with the aircraft flight control system, processing hardware being part of it. The engine itself, as the most complex propulsion subsystem and not within the aircraft manufacturers responsibility, is to have very simple and clearly defined interfaces with the aircraft. Its integration must therefore be on this basis i.e. functional. A central utility data bus allows for easy communication between the engine control system and all relevant aircraft systems through a single point interface in normal operation. This improved communication allows for better performance, operation and handling of the engine. A special feature of the propulsion system is the vectoring nozzle system with thrust deflection for maneuvers at high angles of attack beyond maximum lift. This system is also integrated with the flight control system.

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