A Robust and Self-Scheduled Longitudinal Flight Control System: a Multi-Model and Structured H-infinity Approach

2014 ◽  
Author(s):  
Hugo Lhachemi ◽  
David Saussie ◽  
Guchuan Zhu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Control System ◽  
H Infinity ◽  
System A

Nonlinear H-infinity flight control system design for aircraft

1997 ◽  
Author(s):  
Ching-Fang Lin ◽  
Tie-Jun Yu ◽  
Jian-Hua Ge ◽  
Hsi-Han Yeh ◽  
Siva Banda ◽  
...  
Keyword(s):  
Control System ◽  
System Design ◽  
Flight Control ◽  
Control System Design ◽  
Flight Control System ◽  
H Infinity

scholarly journals Comparative Study of Different Algorithms for a Flight Control System Design and the Potentiality of Their Integration with a Sidestick

Aerospace ◽  
2021 ◽  
Vol 8 (10) ◽  
pp. 290
Author(s):  
Alexandr V. Efremov ◽  
Zoe Mbikayi ◽  
Eugene V. Efremov
Keyword(s):  
Control System ◽  
Flight Control ◽  
Inverse Dynamics ◽  
Synergetic Effect ◽  
Tracking Task ◽  
Modern Trend ◽  
Control Force ◽  
Flight Control System ◽  
H Infinity ◽  
Pitch Tracking

The modern trend of developing highly automated aircraft is characterized by a transition from traditional methods and technical solutions to innovative approaches in order to control the system, inceptor and display design. This paper deals with the development and comparison of flight control system algorithms based on inverse dynamics, H-infinity and traditional feedback methods. The integration of a controller based on inverse dynamics with a novel type of sidestick, shaping the pilot output signal such that it is proportional to the control force (force sensing control—FSC), is studied. The inverse dynamics-based controller is chosen, as it provides a variance of error that is up to 2.3 times less than that of the feedback gains and up to 1.5 times less than that of the H-infinity controller in a pitch tracking task. The synergetic effect arising from the proposed integration is also evaluated. The evaluation of the effectiveness of the methods is carried out through mathematical modeling of the pilot–aircraft system and ground-based simulations on a helicopter mathematical model in a pitch tracking task.

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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