scholarly journals Emergency Flight Control Based on the Fan Wing

2021 ◽  
Vol 2021 ◽  
pp. 1-9
Author(s):  
Lin Meng ◽  
Shuo Wang ◽  
Ye Chen ◽  
Yang Gao
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Method ◽  
Cross Flow ◽  
Flight Control System ◽  
Longitudinal Control ◽  
Emergency Control ◽  
Flight Mode ◽  
Pitch Moment ◽  
Cross Flow Fan

FanWing has been taken to the visual field because of its performance combination of fixed-wing aircraft and helicopter. Its flight mode is currently limited mainly by a remote control, while the research of automated flight control is on the rise. The fan wing could offer lift, thrust, and the additional pitch moment for longitudinal control. At the same time, the roll moment and the yaw moment can be generated by the differential rotation of the cross-flow fan to realize the lateral control. It provides the possibility for its emergency flight control when the aerodynamic control becomes inefficient at a low speed. The difficulties in designing the emergency control system in both the longitudinal and lateral controls are analyzed. And it emphasizes the importance of selecting its center of gravity and the emergency control method of longitudinal control in engineering. The simulation results show that as an emergency flight control system, fan wing control is feasible. The study of the fan wing control will provide a reference solution for its further engineering applications.

PID Control Based Missile Sub-Channel Simulation

2012 ◽  
Vol 433-440 ◽  
pp. 7011-7016 ◽  
Author(s):  
Chao Bo Chen ◽  
Bing Liu ◽  
Ning He ◽  
Song Gao ◽  
Quan Pan
Keyword(s):  
Control System ◽  
Real Time ◽  
Flight Control ◽  
Pid Control ◽  
Pid Controller ◽  
Channel Model ◽  
Control Method ◽  
Flight Control System ◽  
Aerodynamic Control ◽  
The Stability

The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.

scholarly journals Modified shuffled frog leaping algorithm optimized control for air-breathing hypersonic flight vehicle

2016 ◽  
Vol 13 (6) ◽  
pp. 172988141667813 ◽  
Author(s):  
Bingbing Liang ◽  
Ziyang Zhen ◽  
Ju Jiang
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Method ◽  
Hypersonic Vehicle ◽  
Pid Controllers ◽  
Flight Control System ◽  
Shuffled Frog Leaping Algorithm ◽  
Air Breathing ◽  
Nature Inspired Algorithm ◽  
Shuffled Frog Leaping

This article addresses the flight control problem of air-breathing hypersonic vehicles and proposes a novel intelligent algorithm optimized control method. To achieve the climbing, cruising and descending flight control of the air-breathing hypersonic vehicle, an engineering-oriented flight control system based on a Proportional Integral Derivative (PID) method is designed for the hypersonic vehicle, which including the height loop, the pitch angle loop and the velocity loop. Moreover, as a variant of nature-inspired algorithm, modified shuffled frog leaping algorithm is presented to optimize the flight control parameters and is characterized by better exploration and exploitation than the standard shuffled frog leaping algorithm. A nonlinear model of air-breathing hypersonic vehicle is used to verify the dynamic characteristics achieved by the intelligent flight control system. Simulation results demonstrate that the proposed swarm intelligence optimized PID controllers are effective in achieving better flight trajectory and velocity control performance than the traditional controllers.

Research on the Simulation Model for Longitudinal Control Channel of FCS Based on PC

2013 ◽  
Vol 756-759 ◽  
pp. 564-568
Author(s):  
Qing Li ◽  
Wei Yang ◽  
Zhao Xie Huang
Keyword(s):  
Control System ◽  
Simulation Model ◽  
Flight Control ◽  
Control Channel ◽  
Control Parameters ◽  
Flight Control System ◽  
Longitudinal Control ◽  
Control Structures ◽  
Control Rules ◽  
Classical Control

According to the analysis of control structures of the two typical control modes-pitch control and height control, the simplified control rules for the two special control systems are presented. Under the condition of enduring the real-time property and fidelity, the classical control theory is applied to study the control parameters selecting of the flight control system (FCS) based on PC modeling traits. The selecting process of control parameters of longitudinal control channel is analyzed and the simulation resources are simplified. The simulation model is achieved. The steps are summarized for the simulation modeling of longitudinal control channel of the flight control system, and the corresponding flow chart based on PC is also given.

Helicopter load alleviation using active control

2008 ◽  
Vol 112 (1137) ◽  
pp. 663-672
Author(s):  
M. Voskuijl ◽  
D. J. Walker ◽  
B. J. Manimala
Keyword(s):  
Control System ◽  
Flight Control ◽  
High Speed ◽  
Flight Control System ◽  
Order Model ◽  
Longitudinal Control ◽  
Handling Qualities ◽  
Control Techniques ◽  
Maneuvering Flight

Abstract This paper discusses how structural load objectives can be included in a rotorcraft flight control system design in an efficient and straightforward way using multivariable control techniques. Several research studies have indicated that pitch link loads for various rotorcraft types can reach high or even unacceptable values, both in steady state and maneuvering flight. This is especially the case for high-speed aggressive maneouvers. Pitch link loads at high-speed flight are therefore taken as a case study. A novel longitudinal control system is presented, designed to reduce helicopter pitch-link loads during high-speed longitudinal manoeuvres whilst providing a pitch attitude command attitude hold response type. The design is based on a high-order model of a helicopter representative of the UH-60 Black Hawk. New metrics are presented for the analysis of structural loads that can be used in combination with ADS-33 handling qualities requirements.

Control System Design and Implementation of a Quadrotor Unmanned Aerial Vehicle

2012 ◽  
Vol 466-467 ◽  
pp. 749-753
Author(s):  
De Xin Xu ◽  
Guang Chun Li ◽  
Lu Wang
Keyword(s):  
Control System ◽  
Embedded System ◽  
Flight Control ◽  
Control Method ◽  
Hybrid Control ◽  
Sliding Mode ◽  
Control Strategies ◽  
Flight Control System ◽  
Computational Performance ◽  
Aerial Vehicle

In this paper, a method of embedded system with multi-processor is proposed, so as to satisfy the requirement of strong real-time property, high computational performance and multi-task function of the flight control system. In addition, in order to solve the problems of unknown aerodynamic disturbance and weight uncertainties during flight, a hybrid control method based on sliding mode control (SMC) and model referenced adaptive control (MRAC) is proposed. Through the Lyapunov stability analysis, it’s proved that the controller is stable. Various simulations were performed and several experiments on the quadrotor UAV validate the control strategies.

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