Design of Air-Breathing Hypersonic Vehicle Control System

2015 ◽  
Vol 719-720 ◽  
pp. 324-329
Author(s):  
Zhu Bing Hu ◽  
Li Xin Deng ◽  
Bing Bing Li
Keyword(s):  
Control System ◽  
Flight Control ◽  
Feedback Linearization ◽  
Uncertainty Modeling ◽  
Taylor Series Expansion ◽  
Expansion Method ◽  
Hypersonic Vehicle ◽  
Model Parameters ◽  
Air Breathing ◽  
Lqr Controller

The focus of this paper is uncertainty modeling and controller designing of air-breathing hypersonic vehicle. First, the hypersonic vehicle longitudinal dynamics model is made on the base of the fitting of aerodynamic parameters. As to the uncertainty of model parameters, a linear model of the uncertain part is established and the LQR controller parameters are thereupon designed with state transition and a first-order Taylor series expansion method, based on feedback linearization of the system. The simulation results that the hypersonic flight control system stated in this paper can well realize the tracking of speed and trajectory angle input command under the situation of floating model parameters.

F-16/MATV; Optimal Position Controller Design using Robust and Discrete Linear Quadrature Gaussian [RLQG] Controller

2020 ◽  
Vol 8 (1) ◽  
pp. 70-77
Author(s):  
G. Kassahun Berisha ◽  
◽  
Parvendra Kumar
Keyword(s):  
Control System ◽  
State Space ◽  
Flight Control ◽  
Feedback Linearization ◽  
Position Control ◽  
Controller Design ◽  
Taylor Series Expansion ◽  
High Sensitivity ◽  
Optimal Position ◽  
Design Objective

This paper presents the robust controller design for nonlinear F-16/MATV (Multi–Axis – Thrust - Vectoring) position control system. The linearization of nonlinear flight position system is guaranteed by feedback linearization using Taylor series expansion and the optimal LQG controllers are designed to achieve the steady state flight condition. The comparison of the using continuous and discrete LQG is fully discussed for control system. First the continuous optimal LQG controller is designed for continuous time state space represented flight dynamic system based on separation principle. But the designed optimal LQG controller requires a very large controller gain to achieve the design objective, which lacks high sensitivity and leads to highly cost system. This leads to design a controller using discrete LQG controller for discrete time state space represented flight control system. After implementing this controller into the system in MATLAB Simulink environment, using singular value decomposition technique, it is founded that the performance and robustness of the design objective is satisfied.

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.

Exact Linearization Algorithm of Tight Coupling Nonlinear System Based on Differential Manifold

2013 ◽  
Vol 380-384 ◽  
pp. 686-691
Author(s):  
Hua Ming Qian ◽  
Zhen Duo Fu ◽  
Liang Chen ◽  
Xiu Li Ning
Keyword(s):  
Control System ◽  
Nonlinear System ◽  
Attitude Control ◽  
Taylor Series Expansion ◽  
Expansion Method ◽  
Exact Linearization ◽  
Tight Coupling ◽  
Attitude Control System ◽  
Application Range ◽  
Differential Manifold

Dealt with the short precision the traditional Taylor series expansion induced and shortage that the system mechanics is hard to match with the exact linearization conditions, a novel exact linearization algorithm of tight coupling nonlinear system based on differential manifold to the missile attitude control system is proposed. A dimension expansion method is proposed, the method solves the problem that the input and output dimensions can not meet the exact linearization conditions; the algorithm application range is widened. Using the principle of the differential manifold, the missile velocity and height information are selected as the measure output, the exact linearization of the missile attitude system is derived based on the diffeomorphism transformations. The simulations are performed on the missile attitude control system. Simulation results show that the effectiveness of the algorithm proposed.

Design of Composite Control System for an Air-Breathing Hypersonic Vehicle with Wing-Rudder Deflection

2015 ◽  
Vol 719-720 ◽  
pp. 365-368 ◽  
Author(s):  
Yong Hua Fan ◽  
Yun Feng Yu ◽  
Xin Li
Keyword(s):  
Control System ◽  
Control Algorithm ◽  
Hypersonic Vehicle ◽  
Linear Quadratic ◽  
Air Breathing ◽  
Composite Control ◽  
Flight Height ◽  
Simulation Results ◽  
Highly Correlated ◽  
Engine Power

The Scramjet performance of air-breathing hypersonic vehicle is highly correlated with flight height, Mach and angle of attack (AOA). The violent disturbance of the AOA can cause the engine power off. Consequently the maneuverability of hypersonic vehicle is strictly limited in the phase of cruise. A composite Control system for an air-breathing hypersonic vehicle is presented. The hypersonic vehicle has a configuration with tail control rudders and a set of deflectable wings installed nearby the center of gravity. During the phase of cruise, the precision of AOA is achieved by deflecting tail rudders, and the maneuverable acceleration command is tracked by deflecting wings. A linear quadratic (LQ) track control algorithm with integrator is used to design the composite control system. Simulation results demonstrate that the composite control system has good performance in tracking AOA and acceleration command by respective deflection in cruise.

Approximate Feedback Linearization of an Air-Breathing Hypersonic Vehicle

2006 ◽  
Author(s):  
Jason Parker ◽  
Andrea Serrani ◽  
Stephen Yurkovich ◽  
Michael Bolender ◽  
David Doman
Keyword(s):  
Feedback Linearization ◽  
Hypersonic Vehicle ◽  
Air Breathing

scholarly journals Parametric Schedulability Analysis of a Launcher Flight Control System under Reactivity Constraints*

2021 ◽  
Vol 182 (1) ◽  
pp. 31-67
Author(s):  
Étienne André ◽  
Emmanuel Coquard ◽  
Laurent Fribourg ◽  
Jawher Jerray ◽  
David Lesens
Keyword(s):  
Control System ◽  
Flight Control ◽  
Formal Model ◽  
Schedulability Analysis ◽  
Model Parameters ◽  
Space Systems ◽  
Model Checker ◽  
Development Cost ◽  
Flight Control System ◽  
Space Launcher

The next generation of space systems will have to achieve more and more complex missions. In order to master the development cost and duration of such systems, an alternative to a manual design is to automatically synthesize the main parameters of the system. In this paper, we present an approach for the specific case of the scheduling of the flight control of a space launcher. The approach requires two successive steps: (1) the formalization of the problem to be solved in a parametric formal model and (2) the synthesis of the model parameters with a tool. We first describe the problem of the scheduling of a launcher flight control, then we show how this problem can be formalized with parametric stopwatch automata; we then present the results computed by the parametric timed model checker IMITATOR. We enhance our model by taking into consideration the time for switching context, and we compare the results to those obtained by other tools classically used in scheduling.

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