Multiobjective design for an integrated flight control system: a combination with model reduction approach

2004 ◽  
Author(s):  
H.H.T. Liu
Keyword(s):  
Control System ◽  
Model Reduction ◽  
Flight Control ◽  
Flight Control System ◽  
System A ◽  
Multiobjective Design ◽  
Reduction Approach

A Study on UCAV Flight Control System Based on Jamming Observer

2011 ◽  
Vol 268-270 ◽  
pp. 1411-1414
Author(s):  
Hai Wen Du ◽  
Xing Wei Weng ◽  
Yu Song Fu ◽  
Chuan Lin Tang ◽  
Li Xin Zhang
Keyword(s):  
Control System ◽  
Flight Control ◽  
System Stability ◽  
Good Stability ◽  
Restrictive Condition ◽  
Control Law ◽  
Flight Control System ◽  
System A ◽  
Adaptive Flight Control ◽  
Simulation Results

In order to study the uncertain nonlinear jamming problem in UCAV’s flight control system, a method using jamming observer to check the system’s jamming was designed. Based on jamming observer, a flight control law was constructed, which reduced the restrictive condition for the jamming. The simulation results show that the adaptive flight control law based on jamming observer, make UCAV’s flight control system have good stability and robustness, it’s a great convenience analyzing the system stability.

Design UCAV Flight Control Law Based on Jamming Observer

2011 ◽  
Vol 66-68 ◽  
pp. 27-30
Author(s):  
Hai Wen Du ◽  
Xing Wei Weng ◽  
Yu Song Fu ◽  
Chuan Lin Tang
Keyword(s):  
Control System ◽  
Flight Control ◽  
System Stability ◽  
Good Stability ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
System A ◽  
Simulation Results

In order to study the nonlinear jamming problem in UCAV’s flight control system, a method of using observer to check the system’s jamming was designed, constructed robust dynamic inversion control law based on jamming observer. The simulation results show that the robust dynamic inversion control law based on jamming observer, make UCAV’s flight control system have good stability and robustness, it’s a great convenience analyzing the system stability.

The Design of Mini Quad-Rotor Unmanned Aerial Vehicle Control System

2011 ◽  
Vol 383-390 ◽  
pp. 569-573
Author(s):  
Ying Zhao ◽  
Jian Xu Yang
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Program ◽  
Flight Control System ◽  
Helicopter Flight ◽  
System A ◽  
Model Aircraft ◽  
Aerial Vehicle ◽  
Avr Microcontroller ◽  
Hardware Circuit

In this paper we describe a small four-rotor UAV's autonomous flight control system. A comprehensive plan of flight control system was designed base on the remote control model aircraft for flight platform, and Completed with AVR microcontroller core flight control system software and hardware design. It including device type, hardware circuit design and software design. Preliminary study of the four rotor while the helicopter flight control program design, For the future to perform more complex tasks such as fixed-point flight, obstacle avoidance and coordination of multiple aircraft flying and so lay a foundation.

Study of Rapid Calibration Method of Angel of Attack Sensor and Error Impact on Flight Control System

2013 ◽  
Vol 655-657 ◽  
pp. 757-763
Author(s):  
Dao Li ◽  
Wei Yang ◽  
Zhao Xu Yang ◽  
Jian Ping Li
Keyword(s):  
Control System ◽  
Flight Control ◽  
Fault Tolerant ◽  
Calibration Method ◽  
Measure Data ◽  
Flight Control System ◽  
System A ◽  
Calibration Methods ◽  
Network Identification ◽  
Design Requirements

The current calibration methods of combat aircraft’s attarck angle sensors are too complex and have some insufficiencies. According to the detailed design requirements of flight control system，a method combined with linear fitting and neural network identification is proposed, which can calibrate the measure data of the attarck angle sensors qucikly and accurately. The method proposed avoids the disadvantages of traditional interplation method， improves the computating efficiency, and ensures the the flight control system’s fault-tolerant ability. A simulation on flight control system with this calibration method was carrid out, which validated the precision and dependability of the method. The method can also deal strong nonlinear data quickly.

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