scholarly journals Survey on Flight Control Technology for Large-Scale Helicopter

2017 ◽  
Vol 2017 ◽  
pp. 1-14 ◽  
Author(s):  
Jinshuo Hu ◽  
Hongbin Gu
Keyword(s):  
Flight Control ◽  
Large Scale ◽  
Control Technology ◽  
Flight Control System ◽  
Future Directions ◽  
Research Issues ◽  
Advantages And Disadvantages ◽  
Helicopter Flight ◽  
Challenging Research ◽  
Theoretical Developments

A literature review of flight control technology is presented for large-scale helicopter. Challenges of large-scale helicopter flight control system (FCS) design are illustrated. Following this, various flight control methodologies are described with respect to their engineering implementation and theoretical developments, whose advantages and disadvantages are also analyzed. Then, the challenging research issues on flight control technology are identified, and future directions are highlighted.

Second Paper: Failure-Survival Automatic Flight Control Systems for Aircraft with Particular Reference to a High Reliability Electrohydraulic Actuator

1965 ◽  
Vol 180 (1) ◽  
pp. 246-259
Author(s):  
R. Ruggles
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
High Reliability ◽  
Supply System ◽  
Design Criteria ◽  
Flight Control System ◽  
Advantages And Disadvantages ◽  
System Configurations ◽  
Very High

The author discusses some of the problems of failure-survival automatic flight control systems and suggests some basic ground rules as design criteria. The advantages and disadvantages of some of the main types of system are discussed: duplex, triplex, triple component, duplicate-monitored and quadruplex systems being covered. In particular, a quadruplex actuator is described which has been designed and developed mainly for automatic flight control system applications where a very high degrees of failure-survival capability is required. A detailed failure analysis of the various systems is carried out and the importance of the electrical and hydraulic supply system configurations and failure rates is brought out.

scholarly journals Analytical Predictor-Corrector Guidance Algorithm Based on Drag Modulation Flight Control System for Mars Aerocapture

2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Yu-ming Peng ◽  
Bo Xu ◽  
Bao-dong Fang ◽  
Han-lun Lei
Keyword(s):  
Control System ◽  
Flight Control ◽  
Large Scale ◽  
Piecewise Linear ◽  
Scale Space ◽  
Flight Control System ◽  
Initial State ◽  
Aerodynamic Parameter ◽  
Guidance Algorithm ◽  
Predictor Corrector

Aerocapture is one of the essential technologies for future large-scale space exploration missions, as it can significantly reduce the Δv and fuel requirement. The performance and robustness of two different aerocapture control methods are analyzed around Mars exploration, and then an analytic predictor-corrector guidance algorithm for drag modulation flight control system is proposed. A piecewise linear function between velocity and flight path angle is established by appropriate approximations and assumptions, and then the state at atmosphere interface can be predicted by an analytical method; therefore, aerocapture guidance can be realized by feedback control. Numerical simulation is used to evaluate performance and robustness of the algorithm. The simulation results show that the guidance algorithm is accurate and robust, which can effectively overcome the influence of atmospheric density error, aerodynamic parameter error, and initial state uncertainty.

A Self-Repairing Control for the Uncertain System of a Helicopter Using Adaptive Sliding Mode Technology

2012 ◽  
Vol 468-471 ◽  
pp. 529-533 ◽  
Author(s):  
Fu Yang Chen ◽  
Wen Li Luan ◽  
Rui Hou
Keyword(s):  
Control System ◽  
Flight Control ◽  
Sliding Mode ◽  
Nonlinear Function ◽  
Uncertain System ◽  
Flight Control System ◽  
Adaptive Technology ◽  
Helicopter Flight ◽  
Control Scheme ◽  
Adaptive Control Scheme

In this paper, an adaptive control scheme is proposed for the uncertain flight control system of the helicopter with fault in vertical flight. The controller is designed using sliding mode theory and adaptive technology. In the controller, the nonlinear function is brought in, which can enlarge the small errors, and saturate the large errors. And it can make sure the good transient performances and stability of the helicopter flight control system. Finally, the simulation results of the nonlinear helicopter flight system illustrate the effectiveness and feasibility of the proposed scheme in the paper.

Design, Flight Simulation, and Handling Qualities Evaluation of an LPV Gain-Scheduled Helicopter Flight Control System

2000 ◽  
Vol 6 (6) ◽  
pp. 553-566 ◽  
Author(s):  
Ian Postlethwaite ◽  
Ioannis K. Konstantopoulos ◽  
Xiao-Dong Sun ◽  
Daniel J. Walker ◽  
Adrian G. Alford
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Simulation ◽  
Flight Control System ◽  
Handling Qualities ◽  
Helicopter Flight ◽  
Gain Scheduled

Understanding the Effect of Rotor-to-Rotor Interference on CH-47D Helicopter Dynamics

2021 ◽  
Author(s):  
Feyyaz Guner ◽  
David G. Miller ◽  
J. V. R. Prasad
Keyword(s):  
Flight Control ◽  
Influence Factors ◽  
Flight Test ◽  
Flight Simulation ◽  
Flight Control System ◽  
Pressure Potential ◽  
Handling Qualities ◽  
Helicopter Flight ◽  
Lateral Inflow ◽  
Lateral Axis

During the development of the Boeing CH-47D helicopter flight simulation model, test pilots reported mismatch between the flight simulator results and flight test data of the hover and low-speed lateral axis handling qualities, especially for the case without the automatic flight control system. In addressing the observed mismatch, the gains of the longitudinal and lateral components of the inflow model were selected to be significantly higher than their theoretical values. In this study, a detailed understanding of the rotor-to-rotor inflow interference is pursued using a recently developed multi-rotor pressure potential superposition inflow model. It is shown that the coupling between the inflow gradients of individual rotors exists in a tandem rotor, which can be approximated by using higher values for the longitudinal and lateral inflow gains of individual rotors. Further, it is shown that the need for empirical tuning of aerodynamic hub moment influence factors can be eliminated by properly accounting for the rotor-to-rotor interference in the inflow model.

Highly Scalable Flight Control Architecture for Small Autonomous Helicopter Using PC104/ARM Technology

2013 ◽  
Vol 748 ◽  
pp. 718-722
Author(s):  
Shu Xun Zhou ◽  
Jie An ◽  
Jian Guo Yao ◽  
Fei Hu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Pid Control ◽  
Control Experiment ◽  
Measurement Data ◽  
Control System Design ◽  
Flight Control System ◽  
Helicopter Flight ◽  
Integration Architecture ◽  
Autonomous Helicopter

Autonomous helicopter flight presents challenges in flight control system design with scalability. In this paper, we present the integration architecture of hardware and software for the flight control system based TREX 600 helicopter. In order to enhance scalability, the flight control system uses the PC104 and the ARM which is exerted to process the measurement data, including the position, attitude, height etc. The flight control is developed based multi-loop decoupling PID control which is easy to be implemented. Finally, the flight control system is successfully verified in the actual autonomous flight control experiment.

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