Flight control for air-breathing hypersonic vehicles using linear quadratic regulator design based on stochastic robustness analysis

Purpose The purpose of this paper is to elaborate and develop an automatic system for automatic flight control system (AFCS) performance evaluation. Consequently, the developed AFCS algorithm is implemented and tested in a virtual environment on one of the mission task elements (MTEs) described in Aeronautical Design Standard 33 (ADS-33) performance specification. Design/methodology/approach Control algorithm is based on the Linear Quadratic Regulator (LQR) which is adopted to work as a controller in this case. Developed controller allows for automatic flight of the helicopter via desired three-dimensional trajectory by calculating iteratively deviations between desired and actual helicopter position and multiplying it by gains obtained from the LQR methodology. For the AFCS algorithm validation, the objective data analysis is done based on specified task accomplishment requirements, reference trajectory and actual flight parameters. Findings In the paper, a description of an automatic flight control algorithm for small helicopter and its evaluation methodology is presented. Necessary information about helicopter dynamic model is included. The test and algorithm analysis are performed on a slalom maneuver, on which the handling qualities are calculated. Practical implications Developed automatic flight control algorithm can be adapted and used in autopilot for a small helicopter. Methodology of evaluation of an AFCS performance can be used in different applications and cases. Originality/value In the paper, an automatic flight control algorithm for small helicopter and solution for the validation of developed AFCS algorithms are presented.

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Flight Control System Design for Propulsion-Controlled Aircraft

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1243/095441005x30289 ◽

2005 ◽

Vol 219 (4) ◽

pp. 329-340 ◽

Cited By ~ 3

Author(s):

Y Ochi

Keyword(s):

Flight Control ◽

Linear Models ◽

Control Method ◽

Linear Quadratic Regulator ◽

State Feedback Control ◽

Longitudinal Motion ◽

Linear Quadratic ◽

Engine Thrust ◽

Model Following Control ◽

Flight Controls

The loss of an aircraft's primary flight controls can lead to a fatal accident. However, if the engine thrust is available, controllability and safety can be retained. This article describes flight control using engine thrust only when an aircraft has lost all primary flight controls. This is a kind of flight control reconfiguration. For safe return, the aircraft must first descend to a landing area, decelerate to a landing speed, and then be capable of precise flight control for approach and landing. For these purposes, two kinds of controllers are required: a controller for descent and deceleration and a controller for approach and landing. The former controller is designed for longitudinal motion using a model-following control method, based on a linear quadratic regulator. The latter is designed by an H∞ state-feedback control method for both longitudinal and lateral-directional motions. Computer simulation is conducted using linear models of the Boeing 747. The results indicate that flight path control, including approach and landing, is possible using thrust only; however, speed control proves more difficult. However, if the horizontal stabilizer is available, the airspeed can be reduced to a safe landing speed.

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MIMO PID Controller Tuning Method for Quadrotor Based on LQR/LQG Theory

Robotics ◽

10.3390/robotics8020036 ◽

2019 ◽

Vol 8 (2) ◽

pp. 36 ◽

Cited By ~ 1

Author(s):

Rafael Guardeño ◽

Manuel J. López ◽

Víctor M. Sánchez

Keyword(s):

Pid Controller ◽

Controller Design ◽

Low Cost ◽

Robustness Analysis ◽

Linear Quadratic Regulator ◽

Linear Quadratic ◽

Estimation Errors ◽

Plant Model ◽

Bias Drift ◽

Noise Characteristics

In this work, a new pre-tuning multivariable PID (Proportional Integral Derivative) controllers method for quadrotors is put forward. A procedure based on LQR/LQG (Linear Quadratic Regulator/Gaussian) theory is proposed for attitude and altitude control, which suposes a considerable simplification of the design problem due to only one pretuning parameter being used. With the aim to analyze the performance and robustness of the proposed method, a non-linear mathematical model of the DJI-F450 quadrotor is employed, where rotors dynamics, together with sensors drift/bias properties and noise characteristics of low-cost commercial sensors typically used in this type of applications are considered. In order to estimate the state vector and compensate bias/drift effects in the measures, a combination of filtering and data fusion algorithms (Kalman filter and Madgwick algorithm for attitude estimation) are proposed and implemented. Performance and robustness analysis of the control system is carried out by employing numerical simulations, which take into account the presence of uncertainty in the plant model and external disturbances. The obtained results show the proposed controller design method for multivariable PID controller is robust with respect to: (a) parametric uncertainty in the plant model, (b) disturbances acting at the plant input, (c) sensors measurement and estimation errors.

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Flight Control of Air-Breathing Hypersonic Vehicles Based on Disturbance Rejection Scheme

IEEE Access ◽

10.1109/access.2019.2936232 ◽

2019 ◽

Vol 7 ◽

pp. 143392-143401

Author(s):

Dong Zhang ◽

Lin Cao

Keyword(s):

Flight Control ◽

Disturbance Rejection ◽

Hypersonic Vehicles ◽

Air Breathing

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SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight

International Journal of Robotics and Control Systems ◽

10.31763/ijrcs.v1i2.329 ◽

2021 ◽

Vol 1 (2) ◽

pp. 131-144

Author(s):

Guilherme P. Dos Santos ◽

Adriano Kossoski ◽

Jose M. Balthazar ◽

Angelo Marcelo Tusset

Keyword(s):

Nonlinear Model ◽

Flight Control ◽

High Performance ◽

Large Range ◽

Angle Of Attack ◽

Linear Quadratic Regulator ◽

Linear Quadratic ◽

State Dependent ◽

Stall Angle ◽

Difficult Situations

This paper presents the design of the LQR (Linear Quadratic Regulator) and SDRE (State-Dependent Riccati Equation) controllers for the flight control of the F-8 Crusader aircraft considering the nonlinear model of longitudinal movement of the aircraft. Numerical results and analysis demonstrate that the designed controllers can lead to significant improvements in the aircraft's performance, ensuring stability in a large range of attack angle situations. When applied in flight conditions with an angle of attack above the stall situation and influenced by the gust model, it was demonstrated that the LQR and SDRE controllers were able to smooth the flight response maintaining conditions in balance for an angle of attack up to 56% above stall angle. However, for even more difficult situations, with angles of attack up to 76% above the stall angle, only the SDRE controller proved to be efficient and reliable in recovering the aircraft to its stable flight configuration.

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H∞-Based LQR Control for Flexible Air-Breathing Hypersonic Vehicles with Pole Placement

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.787.938 ◽

2013 ◽

Vol 787 ◽

pp. 938-943

Author(s):

Xue Zhang ◽

Xiao Geng Liang

Keyword(s):

Linear Quadratic Regulator ◽

Pole Placement ◽

Control Law ◽

Linear Quadratic ◽

External Disturbances ◽

Air Breathing ◽

Lqr Control ◽

Flight Vehicles ◽

Quadratic Performance ◽

Linearized Model

Focusing on a nonlinear longitudinal dynamical model for air-breathing hypersonic flight vehicles (AHFV), we propose a state feedback linearized model on a nominal trim condition. To stabilize the flight of an AHFV in the presence of external disturbances, a newHbased Linear Quadratic Regulator (LQR) control law with pole placement is designed. Indexes forHperformance, quadratic performance and pole placement are considered together. As a result, the robustness of system is improved and the AHFV system is effectively stabilized. Numerical simulation shows that the controller can effectively stabilize the AHFV system with some disturbances and assign the poles into a desired region.

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Flight control law of unmanned aerial vehicles based on robust servo linear quadratic regulator and Kalman filtering

International Journal of Advanced Robotic Systems ◽

10.1177/1729881416686952 ◽

2017 ◽

Vol 14 (1) ◽

pp. 172988141668695 ◽

Cited By ~ 3

Author(s):

Yongfeng Zhi ◽

Gaoshang Li ◽

Qun Song ◽

Ke Yu ◽

Jun Zhang

Keyword(s):

Unmanned Aerial Vehicles ◽

Kalman Filtering ◽

Flight Control ◽

Pitch Angle ◽

Linear Quadratic Regulator ◽

Control Law ◽

Linear Quadratic ◽

Aerial Vehicles ◽

Simulation Results ◽

Influence Of Noise

A new flight control law for unmanned aerial vehicles based on robust servo linear quadratic regulator control and Kalman filtering is proposed. This flight control law has a simple structure with high dependability in engineering. The pitch angle controller, which is designed based on the robust servo linear quadratic regulator control, is given to show the flight control law. Simulation results show that the pitch angle controller works well under noise-free conditions. Finally, Kalman filtering is applied to the pitch angle controller under noisy conditions, and the simulation results show that the proposed method reduces the influence of noise.

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Design of Flight Control System for a Novel Tilt-Rotor UAV

Complexity ◽

10.1155/2020/4757381 ◽

2020 ◽

Vol 2020 ◽

pp. 1-14

Author(s):

Zaibin Chen ◽

Hongguang Jia

Keyword(s):

Mathematical Model ◽

Control System ◽

Flight Control ◽

Actuator Saturation ◽

High Reliability ◽

Linear Quadratic Regulator ◽

Control Law ◽

Linear Quadratic ◽

Tilt Rotor ◽

Configuration Scheme

This paper presents the control system design process of a novel tilt-rotor unmanned aerial vehicle (TRUAV). First, a new configuration scheme with the tilting rotors is designed. Then, the detailed nonlinear mathematical model is established, and the parameters are acquired from designed experiments and numerical analyses. For control design purposes, the dynamics equation is linearized around the hovering equilibrium point, and a control allocation method based on trim calculation is developed. To deal with the actuator saturation and uncertain disturbance problems for the novel TRUAV, an improved flight control law based on the combination of the robust servo linear quadratic regulator (RSLQR) optimal control and the extended state observer (ESO) is proposed. The designed flight control law has a simple structure with a high reliability in engineering. Simulations and hovering flight tests are carried out to verify the effectiveness of the mathematical model and the proposed control strategy.

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