Flight control system control law and the flying quality evaluation test

2021 ◽  
pp. 239-270
Author(s):  
Yakui Gao ◽  
Gang An ◽  
Chaoyou Zhi
Keyword(s):  
Control System ◽  
Flight Control ◽  
Quality Evaluation ◽  
Control Law ◽  
System Control ◽  
Flight Control System ◽  
Evaluation Test

Integrated Aircraft Modeling Research for Accurate Flight Control System Design

2013 ◽  
Vol 791-793 ◽  
pp. 658-662
Author(s):  
Chao Zhang ◽  
Yi Nan Liu ◽  
Jian Hui Xu
Keyword(s):  
Control System ◽  
System Design ◽  
Flight Control ◽  
Time Delays ◽  
Flight Dynamics ◽  
Control System Design ◽  
Control Law ◽  
Flight Control System ◽  
Aircraft Model ◽  
Simulation Results

In order to realize accurate flight control system design and simulation, an integrated scheme of aircraft model which consists of flight dynamics, fly-by-wire (FBW) platform and flight environment is proposed. Flight environment includes gravity, wind, and atmosphere. And the actuator and sensors such as gyroscope and accelerometer models are considered in the FBW platform. All parts of the integrated model are closely connected and interacted with each other. Simulation results confirm the effectiveness of the integrated aircraft model and also indicate that the (Flight Control Law) FCL must be designed with robustness to sensor noise and time delays with the FBW platform in addition to the required robustness to model uncertainty in flight dynamics.

scholarly journals Impacts of Deflection Nose on Ballistic Trajectory Control Law

2014 ◽  
Vol 2014 ◽  
pp. 1-6 ◽  
Author(s):  
Bo Zhang ◽  
Shushan Wang ◽  
Mengyu Cao ◽  
Yuxin Xu
Keyword(s):  
Control System ◽  
Motion Control ◽  
Flight Control ◽  
Calculation Model ◽  
Trajectory Control ◽  
Control Law ◽  
Flight Control System ◽  
Theory Of Motion ◽  
Ballistic Trajectory ◽  
Exterior Ballistics

The deflection of projectile nose is aimed at changing the motion of the projectile in flight with the theory of motion control and changing the exterior ballistics so as to change its range and increase its accuracy. The law of external ballistics with the deflectable nose is considered as the basis of the design of a flight control system and an important part in the process of projectile development. Based on the existing rigid external ballistic model, this paper establishes an external ballistic calculation model for deflectable nose projectile and further establishes the solving programs accordingly. Different angle of attack, velocity, coefficients of lift, resistance, and moment under the deflection can be obtained in this paper based on the previous experiments and emulation researches. In the end, the author pointed out the laws on the impaction of external ballistic trajectory by the deflection of nose of the missile.

scholarly journals Robust dynamic inversion control of flight control system based on L1 adaptive structure

2021 ◽  
Vol 39 (5) ◽  
pp. 995-1004
Author(s):  
Yu LI ◽  
Xiaoxiong LIU ◽  
Ruichen MING ◽  
Shaoshan SUN ◽  
Weiguo ZHANG
Keyword(s):  
Control System ◽  
Flight Control ◽  
Dynamic Performance ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
Parameter Uncertainties ◽  
Strong Robustness ◽  
Adaptive Structure ◽  
The Stability

Nonlinear Dynamic Inversion(NDI) control has excellent rapidity and decoupling ability, unfortunately it lacks the essential robustness to disturbance. From the perspective of enhancing the robustness, an adaptive NDI method based on L1 adaptive structure is proposed. The L1 adaptive structure is introduced into the NDI control to enhance its robustness, which also guarantees the stability and expected dynamic performance of the system suffering from the disturbance influence. Secondly, the flight control law of the advanced aircraft is designed based on the present method to improve the robustness and fault tolerance of the flight control system. Finally, the effectiveness of the flight control law based on the present approach is verified under the fault disturbance. The results showed that the flight control law based on L1 adaptive NDI has excellent dynamic performance and strong robustness to parameter uncertainties and disturbances.

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 and Implementation of a Dual-Redundant Flight Control System for a Miniature Autonomous Helicopter

2013 ◽  
Vol 278-280 ◽  
pp. 1723-1728
Author(s):  
Qiang Wang ◽  
Bing Zhu ◽  
Peng Liu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Design Procedure ◽  
Control Architecture ◽  
Control Law ◽  
Systematic Design ◽  
Flight Control System ◽  
Flight Tests ◽  
Design And Implementation ◽  
Autonomous Helicopter

This paper present the design and implementation of a dual-redundant flight control system for a miniature autonomous helicopter, named SRD-Heli. The systematic design procedure includes hardware integration, flight control law, exchange scheme, as well as experimental evaluation. A dual-redundant control architecture is adopted to construct the flight control system for the helicopter. The control architecture is composed by (1) an active flight control law designed for the active computer, which works in normal condition, (2) a standby flight control law to effectively control the helicopter by standby computer in fault condition. The result of actual flight tests shows that the flight control system is capable of achieving the desired performance.

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.

Suboptimal Control Theory for Vehicle Attitude Control System Design

2012 ◽  
Vol 466-467 ◽  
pp. 976-980
Author(s):  
Guo Long Fan ◽  
Xiao Geng Liang ◽  
Yong Hua Fan
Keyword(s):  
Control System ◽  
Lyapunov Stability ◽  
Flight Control ◽  
Attitude Control ◽  
Stability Theory ◽  
Deflection Angle ◽  
Lyapunov Stability Theory ◽  
Suboptimal Control ◽  
System Control ◽  
Flight Control System

Base on the Lyapunov stability theory, an improved suboptimal control system scheme is advanced in this paper. Aiming at hypersonic reentry vehicle nonlinear properties of the actuator deflection angle rate and the deflection angle were studied. First, the mathematical model of the control system is established according to the flight control system control scheme. Considering the project realize easy, the flight control system is designed based on suboptimal control of Lyapunov stability theory. In order to close to the optimal control, then the suboptimal control design is improved. Finally the controller is applied to the instances, by analyzing the results confirmed the method is correctly.

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