Aircraft Arresting System Analysis And Control Research

Aircraft arresting system is a kind of important safeguard equipment for airports. It is used to arrest an aircraft going beyond the end of a runway at normal landing or by accident to provide safety for pilot and aircraft. The performance of the system designed will directly affect the overloading that an aircraft can bear, the safe overrunning length of runway as well as the changes of tensile force of belt and braking pressure of oil, and ultimately has influence on the arresting effects. So in the process of developing a system, we should study the system in order to define the optimal configuration parameters or more effective control methods. At present, the overseas development of arresting equipment is very fast and the corresponding research is also rather mature, but few documents can be obtained. The new type aircraft arresting system in China is under development and the corresponding research is at a premature stage. This dissertation does researches on the design of arresting force, the characteristics of the system, the control strategies and the deviation rectifying. Research results are used in the manufacturing of our new type aircraft arresting system, so the dissertation has significant value of practical application.The dissertation summarizes the application, development and study status quo of aircraft arresting system. The significance and background of the study are presented. The theories relating to nonlinear control systems are expounded. And a robust output tracking control unit of a class of multi-variable affine nonlinear systems with uncertain parameters is designed.As to the multiple-index restricted problem that overloading of aircraft, tensile force of belt, overrunning length and braking pressure cannot exceed the bounds of indexes, the dissertation analyzes it in detail. Energy method is proposed. The method of defining the arresting force law and tensile force law of belt in various engaging conditions is presented. Using this method, the possibility of indexes being met could be analyzed. If the indexes could be met, the relative ideal arresting force law that adapts to engaging condition could then be obtained.The mathematical model of new type aircraft arresting system is established in detail, and the unique solution of differential equation and the stability and the motion and control characteristics of the system are proved and analyzed. The dissertation also does a research on the control strategies of mechanical control parts. The theoretical expression among needle valve throttle area, cam-control valve throttle area and the equivalent throttle area of combining control is given, and the principle of combining control of the two valves is analyzed. The arresting control strategies under various engaging conditions are presented, namely the engaging condition of same overrunning length and same engaging speed but different weight, the engaging condition of same overrunning length and same weight but different speed as well as the engaging condition of same weight and same engaging speed but different overrunning length. The design technique and design model of cam curve law with multiple-index restrictions are given and a typical example is designed. The design result is simulated by means of system simulation model established. The simulation results confirm that every performance can meet the requirement of the indexes. Arresting processes with the changes of system parameters are also analyzed by simulation.Electro-hydraulic proportional control and nonlinear control methods for aircraft arresting system are discussed theoretically. The electro-hydraulic proportional control law is given. The laws of tracking control of displacement and speed of aircraft as well as tracking control of angle and angular speed of belt wheel are designed by means of statefeedback linearization and quadratic performance index linear optimal control method. The robustness of the designed systems is analyzed, and arresting processes are simulated. The simulation...