A Coordinated Control Method of Thrust Vector and Aerodynamic Surfaces Based on Control Allocation Technology

Shi Jingping,Lv Yongxi,Qu Xiaobo,Shi Jing 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10

As one of the most important technologies of the advanced fighter, thrust vector technology can greatly increase the range of controlled angle of attack, and make the fighter easily realize the post stall maneuver. However currently thrust vector technology is achieved by manually manipulating the additional vector stick, which greatly increases the burden on pilots. Thus how to bring the thrust vector control into the automatic control system to reduce the pilot operation burden has become an important engineering problem to be solved. A dynamic inverse design method based on daisy chain allocation method is proposed, which integrates the thrust vector into the automatic control system, thus eliminating the thrust vector manipulating mechanism and reducing the pilot`s operating burden. In addition, the method maximizes the use of the control surface and reduces the use time of the thrust vector, thus effectively reducing the maintenance cost of the engine. The simulation results of vector cylinder maneuver shows that this method can effectively achieve the coordinated control of thrust vector.

Quantized Consensus Control for Multi-UAVs based on Prescribed Performance

Zhihui Du,Jingping Shi,Zhonghua Wu 제어·로봇·시스템학회 2022 International Journal of Control, Automation, and Vol.20 No.1

A distributed adaptive control approach based on a prescribed performance is proposed for multiple unmanned aerial vehicles (multi-UAVs) with disturbances and input quantization. The tracking error is converted into the consensus error by relying on the communication topology so that the distributed controller can be implemented. The radial basic function (RBF) neural network with composite learning is used to estimate the unknown nonlinear functions, and adaptive compensation terms are applied to compensate for the errors caused by filters and disturbances. A hysteretic quantizer is introduced to process the control input signal to relax the channel burden, and an estimator is implemented to solve the problem where the quantizer parameters are unknown. An improved Barrier Lyapunov function (BLF) is developed to ensure that the consensus error satisfies the prescribed performance requirements. Stability analysis proves that the tracking error and all signals in the closed-loop systems are bounded. Finally, all follower UAVs can track the virtual leader and maintain the given formation. A numerical simulation is provided to validate the effectiveness of the proposed control approach.

Adaptive Back-stepping Neural Control for an Embedded and Tiltable Vtail Morphing Aircraft

Fuxiang Qiao,Jingping Shi,Xiaobo Qu,Yongxi Lyu 제어·로봇·시스템학회 2022 International Journal of Control, Automation, and Vol.20 No.2

This paper presents an adaptive back-stepping neural control (ABNC) method for the coupled nonlinear model of a novel type of embedded surface morphing aircraft. Based on a large number of aerodynamic data for different V-tail configurations, the longitudinal and lateral aerodynamic characteristics of the aircraft are analyzed, and a nonlinear model with six degrees-of-freedom is established. To avoid the problem of “differential explosion,” the controller is designed using the traditional back-stepping control (TBC) method with a first-order filter. Radial basis function neural networks are introduced to estimate the uncertainty and external disturbance of the model, and a controller based on the ABNC method is designed. The stability of the proposed ABNC controller is proved using Lyapunov theory, and it is shown that the tracking error of the closed-loop system converges uniformly within specified bounds. Simulation results show that the ABNC controller works well, with better tracking performance and robustness than the TBC controller.

Finite-time Observer Based Predefined-time Aircraft Attitude Tracking Control

Yunhao Fu,Jingping Shi,Yongxi Lyu 제어·로봇·시스템학회 2023 International Journal of Control, Automation, and Vol.21 No.11

This paper investigates the attitude tracking issue of the fixed-wing unmanned aerial vehicle (UAV) with model uncertainty and external disturbance using contemporary predefined-time stability theory and disturbance observer. Firstly, by using a time-varying tuning function with the expected settling time, composite state tracking errors are introduced to the design process of dynamic surface control, which is named dynamic surface based predefined time control (DSPTC). Then, the lumped disturbances are estimated by finite time extended states observer (FTESO). It is proved that all of signals in the aircraft attitude system are globally uniformly ultimately bounded. Finally, a set of simulations is implemented to validate the availability of the proposed controller.

Reconfigurable Flight Control System Design for Blended Wing Body UAV Based on Control Allocation

Xiaobo Qu,Jingping Shi,Haijun Zhou,Ling Zuo,Yongxi Lyu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10

The aircraft control surface fault reconfigurable scheme based on control allocation is an active approach to achieve fault-tolerant in flight control. It has obvious advantages such as the structure and parameters of the control law does not need to be redesigned as deflector failures occurs. The attainable moment subset and allocation efficiency with typical control allocation algorithms are evaluated. A modular scheme reconfigurable flight control system (FCS) of a miniature tailless Blended Wing Body UAV is studied by utilizing weighted pseudo-inverse, direct control, and fixed-point control allocation methods. The performance of the reconfigurable FCS is tested and verified with the simulation including typical failure modes such as deflector floating, loss-of-effectiveness and lock-in-place. Results validate that the reconfigurable FCS based on control allocation has preferable ability to handle deflector failures, improve the safety and reliability of aircraft. And the modular scheme proposed in the article demonstrates a good application prospect in the field of aviation and aerospace engineering.

Maneuverable Aircraft Flight Control Using Nonlinear Dynamic Inversion

Qianlei Jia,Weiguo Zhang,Jingping Shi,Jiayue Hu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10

Feedback linearization is a mature and highly applied control method in aerospace and other industrial applications. The designed control inputs are used to cancel the nonlinear terms using negative feedback of these terms. This paper focuses on designing a fight simulation model for F-16 fighter jet in responding to diverse sharp maneuvers. F-16 model is expressed by fixed-mass rigid-body six-degree-of freedom (6-DOF) equations of motion, which include the detailed aerodynamic coefficients, the engine model and the actuator models that have lags and limits. The two-time scaled concept of dynamic inversion method divides the aircraft states into groups according to their rate of response. Dynamic Inversion (DI) control law is designed for the fast variables using the aerodynamic control surfaces as inputs. Next, DI is applied to the control of the slow states using the outputs of the fast loop as inputs. Simulation results for the nonlinear flight control system have proved the validity and rationality of the proposed technique .

Tracking Strategy of Unmanned Aerial Vehicle for Tracking Moving Target

Chuanjian Lin,Weiguo Zhang,Jingping Shi 제어·로봇·시스템학회 2021 International Journal of Control, Automation, and Vol.19 No.6

Unmanned aerial vehicles (UAVs) are prone to losing their targets when tracking moving objectives. A tracking strategy is proposed herein that enables the standoff tracking of a moving target using a vision system, which significantly reduces the occurrence of target loss. The strategy combines the Gimbal Control Algorithm based on Motion Compensation (GCAMC) with the Improved Reference Point Guidance Method (IRPGM). The GCAMC utilizes the attitude of the UAV and the deviation of the target from image center as the feedback. The target can be kept within the field-of-view (FOV) of the camera when the gimbal model is unknown. The IRPGM generates straight or circular paths according to the speed and potition of the target, while the UAV will continuously track the generated trajectory to achieve the objective of target tracking. To validate and demonstrate the tracking performance of the proposed strategy, a closed-loop visual simulation platform was devised and implemented to simulate the process of target tracking. The results of the simulation demonstrate that by using the proposed approach, the UAV can enter the desired trajectory quickly when its initial position and flight direction are arbitrary.

An Improved Method of Control Law Design at High Angle of Attack Based on Wind Tunnel Test Data

Yongxi Lyu,Yuyan Cao,Weiguo Zhang,Jingping Shi,Xiaobo Qu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10

This paper presents an improved dynamic inversion (DI) based method, which is further successfully applied to the high angle of attack flight control of the aircraft under the influence of unsteady aerodynamics. On the basis of large oscillation wind tunnel test data, the accurate unsteady aerodynamic model is established by the sequential minimal optimization - support vector regression (SMO-SVR) method. The nonlinear longitudinal aircraft model is created by considering engine model, atmospheric model, actuator model, and so on. In order to solve the problem of large control error and control delay caused by the unsteady aerodynamics, the improved DI method is proposed. The integral is added in the pitch angle rate control, and the control law of angle of attack is designed combining lag correction. The daisy chain allocation method is utilized to obtain the deflections of the control surfaces and the engine vector nozzle. Numerical simulation of Cobra maneuver is employed to demonstrate the advantages and potential practical application of the proposed improved control law design method.