WANG F , LI Y P , ZHOU C , et al. Composite practically fixed time controller design for a hypersonic vehicle with multisource uncertainty and actuator fault [J ] . IEEE Transactions on Aerospace and Electronic Systems , 2021 , 1 : 1 - 12 .

赵良玉 , 雍恩米 , 王波兰 . 反临近空间高超声速飞行器若干研究进展 [J ] . 宇航学报 , 2020 , 41 ( 10 ): 1239 - 1250 .

ZHAO L Y , YONG E M , WANG B L . Some achievements on interception of near space hypersonic vehicles [J ] . Journal of Astronautics , 2020 , 41 ( 10 ): 1239 - 1250 . (in Chinese)

KERR M , HAYA R , PENIN L F , et al. IXV re-entry guidance,control & DRS triggering: algorithm design and assessment [C ] // Proceedings of AIAA Guidance,Navigation and Control Conference.Minneapolis,MN, US:AIAA , 2012 : 13 - 16 .

BAIOCCO P , GUEDRON S , PLOTARD P , et al. The pre-X atmospheric reentry experimental lifting body:program status and system synthesis [J ] . Acta Astronautica , 2007 , 61 ( 1-6 ): 459 - 474 . DOI: 10.1016/j.actaastro.2007.01.053 http://doi.org/10.1016/j.actaastro.2007.01.053 https://linkinghub.elsevier.com/retrieve/pii/S0094576507000677 https://linkinghub.elsevier.com/retrieve/pii/S0094576507000677

AN H , GUO Z Y , WANG G , et al. Neural adaptive control of air-breathing hypersonic vehicles robust to actuator dynamics [J ] . ISA Transactions , 2021 , 116 : 17 - 29 . DOI: 10.1016/j.isatra.2021.01.017 http://doi.org/10.1016/j.isatra.2021.01.017 This paper investigates the neural adaptive control problem for air-breathing hypersonic vehicles. For the velocity subsystem, a radial basis function neural network (RBFNN)-based adaptive controller is first designed, which employs the auxiliary variable to compensate for the saturation nonlinearity of the scramjet control command. For the altitude subsystem, an RBFNN-based controller addresses actuator constraints and dynamics using the model predictive control, as well as counteracts uncertainties and disturbances using the neural adaptive mechanism. The effectiveness of the proposed control is verified by simulations.Copyright © 2021 ISA. Published by Elsevier Ltd. All rights reserved.

AN H , FIDAN B , WU Q Q , et al. Sliding mode differentiator based tracking control of uncertain nonlinear systems with application to hypersonic flight [J ] . Asian Journal of Control , 2019 , 21 ( 1 ): 143 - 155 . DOI: 10.1002/asjc.v21.1 http://doi.org/10.1002/asjc.v21.1 https://onlinelibrary.wiley.com/toc/19346093/21/1 https://onlinelibrary.wiley.com/toc/19346093/21/1

ZHANG D , TANG S , ZHU Q J , et al. Analysis of dynamic characteristics of the rigid body/elastic body coupling of air-breathing hypersonic vehicles [J ] . Aerospace Science and Technology , 2016 , 48 : 328 - 341 . DOI: 10.1016/j.ast.2015.11.027 http://doi.org/10.1016/j.ast.2015.11.027 https://linkinghub.elsevier.com/retrieve/pii/S1270963815003715 https://linkinghub.elsevier.com/retrieve/pii/S1270963815003715

SEO M G , LEE C H , TAHK M J , et al. Control input blending logic with aerodynamic control and reaction jet control [C ] // Proceedings of the 29th Congress of the International Council of the Aeronautical Sciences.St. Petersburg , Russia : International Council of the Aeronautical Sciences , 2014 : 7 - 12 .

SHOU Y X , XU B , LIANG X H , et al. Aerodynamic/ reaction-jet compound control of hypersonic reentry vehicle using sliding mode control and neural learning [J ] . Aerospace Science and Technology , 2021 , 111 : 1 - 20 .

AN H , WU Q Q , WANG G , et al. Adaptive compound control of air-breathing hypersonic vehicles [J ] . IEEE Transactions on Aerospace and Electronic Systems , 2020 , 56 ( 6 ): 4519 - 4532 . DOI: 10.1109/TAES.7 http://doi.org/10.1109/TAES.7 https://ieeexplore.ieee.org/xpl/RecentIssue.jsp?punumber=7 https://ieeexplore.ieee.org/xpl/RecentIssue.jsp?punumber=7

YUN Y H , TANG S J , GUO J , et al. Robust controller design for compound control missile with fixed bounded convergence time [J ] . Journal of Systems Engineering and Electronics , 2018 , 29 ( 1 ): 116 - 133 . DOI: 10.21629/JSEE http://doi.org/10.21629/JSEE http://www.jseepub.com/ http://www.jseepub.com/

赵明元 , 魏明英 , 何秋茹 . 基于有限时间稳定和Backstepping的直接力/气动力复合控制方法 [J ] . 宇航学报 , 2010 , 31 ( 9 ): 2157 - 2164 .

ZHAO M Y , WEI M Y , HE Q R . Research on method of lateral jet and aerodynamic fins compound control based on finite time stability and backstepping approach [J ] . Journal of Astronautics , 2010 , 31 ( 9 ): 2157 - 2164 . (in Chinese)

LIU K , HOU Z , SHE Z Y , et al. Reentry attitude tracking control for hypersonic vehicle with reaction control systems via improved model predictive control approach [J ] . Computer Modeling in Engineering & Science , 2020 , 122 ( 1 ): 131 - 148 .

DENG F , XIE F , QIN N , et al. Drag reduction investigation for hypersonic lifting-body vehicles with aerospike and long penetration mode counterflowing jet [J ] . Aerospace Science and Technology , 2018 , 76 : 361 - 373 . DOI: 10.1016/j.ast.2018.01.039 http://doi.org/10.1016/j.ast.2018.01.039 https://linkinghub.elsevier.com/retrieve/pii/S1270963817304315 https://linkinghub.elsevier.com/retrieve/pii/S1270963817304315

ZHAI R Y , QI R Y , ZHANG J R . Compound fault-tolerant attitude control for hypersonic vehicle with reaction control systems in reentry phase [J ] . ISA Transactions , 2019 , 90 : 123 - 137 . DOI: S0019-0578(19)30002-3 http://doi.org/S0019-0578(19)30002-3 In this paper, a novel compound fault-tolerant attitude control (FTC) scheme is proposed for reentry hypersonic vehicles with aerodynamic surfaces and reaction control systems (RCS) in the presence of parameter uncertainties, external disturbances and aerodynamic surfaces faults. Aerodynamic surfaces work as the primary actuators and RCS serve as auxiliary actuators. When aerodynamic surfaces cannot provide the required attitude control torque due to low dynamic pressure or faults, RCS are activated to assist aerodynamic surfaces to generate the residual torque. A nonlinear disturbance observer-based sliding mode controller is designed to calculate the required attitude control torque which can handle the parametric uncertainties and external disturbances together. The quadratic programming method is applied to obtain the optimal aerodynamic surfaces deflections from the required control torque. An innovative fuzzy rule-based decision-making system is design to solve the RCS control allocation problem, which is conceptually easy to understand and computationally efficiently compared with existing approaches. Based on quantized control theory, the closed-loop control system stability is rigorously analyzed. Simulation results are given to demonstrate the effectiveness and efficiency of developed FTC scheme.Copyright © 2019 ISA. Published by Elsevier Ltd. All rights reserved.

WANG Z , BAO W M , LI H F . Second order dynamic sliding mode control for nonminimum phase underactuated hypersonic vehicles [J ] . IEEE Transactions on Industrial Electronics , 2017 , 64 ( 4 ): 3105 - 3112 . DOI: 10.1109/TIE.2016.2633530 http://doi.org/10.1109/TIE.2016.2633530 http://ieeexplore.ieee.org/document/7763848/ http://ieeexplore.ieee.org/document/7763848/

LU B , FANG Y C . Gain-adapting coupling control for a class of underactuated mechanical systems [J ] . Automatica , 2021 , 125 : 109461 . DOI: 10.1016/j.automatica.2020.109461 http://doi.org/10.1016/j.automatica.2020.109461 https://linkinghub.elsevier.com/retrieve/pii/S0005109820306592 https://linkinghub.elsevier.com/retrieve/pii/S0005109820306592

WU Y M , SUN N , FANG Y C , et al. An increased nonlinear coupling motion controller for underactuated multi-TORA systems:theoretical design and hardware experimentation [J ] . IEEE Transactions on Systems,Man,and Cybernetics:Systems , 2017 , 49 ( 6 ): 1186 - 1193 .

LI J Q , CHEN S , LI C Y , et al. Adaptive control of underactuated flight vehicles with moving mass [J ] . Aerospace Science and Technology , 2019 , 85 : 75 - 84 . DOI: 10.1016/j.ast.2018.12.003 http://doi.org/10.1016/j.ast.2018.12.003 https://linkinghub.elsevier.com/retrieve/pii/S1270963818320777 https://linkinghub.elsevier.com/retrieve/pii/S1270963818320777

BELLLETER D , MAGHENEM M A , PALIOTTA C , et al. Observer based path following for underactuated marine vessels in the presence of ocean currents: a global approach [J ] . Automatica , 2019 , 100 : 123 - 134 . DOI: 10.1016/j.automatica.2018.11.008 http://doi.org/10.1016/j.automatica.2018.11.008 https://linkinghub.elsevier.com/retrieve/pii/S0005109818305405 https://linkinghub.elsevier.com/retrieve/pii/S0005109818305405

周荻 , 董金鲁 . 带襟翼的飞行器非线性控制系统分析和设计 [J ] . 兵工学报 , 2017 , 38 ( 7 ): 1322 - 1329 . DOI: 10.3969/j.issn.1000-1093.2017.07.010 http://doi.org/10.3969/j.issn.1000-1093.2017.07.010 以襟翼作为执行机构的面对称飞行器，研究其控制能力和自动驾驶仪设计。襟翼作为执行机构相比传统全动舵缺少方向舵，对缺少方向舵类型的控制方式，推导出此情况下的面对称飞行器动力学模型。基于该模型描述的非线性控制系统，采用微分几何方法进行能控性分析,证明该系统的弱能控性；应用求解状态依赖的Riccati方程方法，以襟翼为执行机构的面对称飞行器，设计非线性最优控制器。仿真结果表明，在系统弱能控性的基础上，设计的控制器能够在缺少方向舵的情况下，使得滚转角和纵向过载快速地跟踪指令。同时验证了飞行器双通道控制的可行性。

ZHOU D , DONG J L . Analysis and design of nonlinear control system for aircraft with flap [J ] . Acta Armamentarii , 2017 , 38 ( 7 ): 1322 - 1329 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2017.07.010 http://doi.org/10.3969/j.issn.1000-1093.2017.07.010 The design and controllability of autopilot of surface symmetric aircraft with flaps as actuators are studied. Compared with traditional aircrafts, such an aircraft lacks rudder in its yaw loop while using flaps as actuators. The motion dynamics model of such an aircraft is derived. The differential geometry method is used to analyze the controllability of the nonlinear control system described by this dynamics. This analysis has proved the controllability of the system. Based on the controllability analysis, a nonlinear optimal controller for the nonlinear coupled control system is designed using state-dependent Riccati equation method. Simulated results demonstrate that the roll angle and longitudinal overload can fast track the commands based on the system of weak controllability, and also testify the feasibility of two-channel control of aircraft. Key

DUPAS A , LOGSDON J M . Creating a productive international partnership in the vision for space exploration [J ] . Space Policy , 2007 , 23 ( 1 ): 24 - 28 . DOI: 10.1016/j.spacepol.2006.11.003 http://doi.org/10.1016/j.spacepol.2006.11.003 https://linkinghub.elsevier.com/retrieve/pii/S0265964606001056 https://linkinghub.elsevier.com/retrieve/pii/S0265964606001056

TIAN J , ZHANG S F , ZHANG Y H , et al. Active disturbance rejection control based robust output feedback autopilot design for airbreathing hypersonic vehicles [J ] . ISA Transactions , 2018 , 74 : 45 - 59 . DOI: S0019-0578(18)30002-8 http://doi.org/S0019-0578(18)30002-8 Since motion control plant (y=f(⋅)+d) was repeatedly used to exemplify how active disturbance rejection control (ADRC) works when it was proposed, the integral chain system subject to matched disturbances is always regarded as a canonical form and even misconstrued as the only form that ADRC is applicable to. In this paper, a systematic approach is first presented to apply ADRC to a generic nonlinear uncertain system with mismatched disturbances and a robust output feedback autopilot for an airbreathing hypersonic vehicle (AHV) is devised based on that. The key idea is to employ the feedback linearization (FL) and equivalent input disturbance (EID) technique to decouple nonlinear uncertain system into several subsystems in canonical form, thus it would be much easy to directly design classical/improved linear/nonlinear ADRC controller for each subsystem. It is noticed that all disturbances are taken into account when implementing FL rather than just omitting that in previous research, which greatly enhances controllers' robustness against external disturbances. For autopilot design, ADRC strategy enables precise tracking for velocity and altitude reference command in the presence of severe parametric perturbations and atmospheric disturbances only using measurable output information. Bounded-input-bounded-output (BIBO) stable is analyzed for closed-loop system. To illustrate the feasibility and superiority of this novel design, a series of comparative simulations with some prominent and representative methods are carried out on a benchmark longitudinal AHV model.Copyright © 2018 ISA. Published by Elsevier Ltd. All rights reserved.

XIAO D B , LIU M Y , LIU Y B , et al. Switching control of a hypersonic vehicle based on guardian maps [J ] . Asta Astronautica , 2016 , 122 : 294 - 306 .

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WU Y J , LIU X C , HUA Y Y . Super twisting disturbance observer-based fixed-time sliding mode backstepping control for air-breathing hypersonic vehicles [J ] . IEEE Access , 2020 , 8 : 17567 - 17583 . DOI: 10.1109/Access.6287639 http://doi.org/10.1109/Access.6287639 https://ieeexplore.ieee.org/xpl/RecentIssue.jsp?punumber=6287639 https://ieeexplore.ieee.org/xpl/RecentIssue.jsp?punumber=6287639

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YIN X M , WANG B , LIU L . Disturbance observer-based gain adaptation high-order sliding mode control of hypersonic vehicles [J ] . Aerospace Science and Technology , 2019 , 89 : 19 - 30 . DOI: 10.1016/j.ast.2019.03.030 http://doi.org/10.1016/j.ast.2019.03.030 https://linkinghub.elsevier.com/retrieve/pii/S1270963818304012 https://linkinghub.elsevier.com/retrieve/pii/S1270963818304012

CHEN S , HUO X , ZHAO H , et al. Active tilting flutter suppression of GyroWheel with composite-structured adaptive compensator [J ] . IEEE Transactions on Industrial Electronics , 2021 , 68 ( 7 ): 6227 - 6237 . DOI: 10.1109/TIE.2020.2994858 http://doi.org/10.1109/TIE.2020.2994858 https://ieeexplore.ieee.org/document/9097374/ https://ieeexplore.ieee.org/document/9097374/

GUO Y , GUO J H , LIU X , et al. Finite-time blended control for air-to-air missile with lateral thrusters and aerodynamic surfaces [J ] . Aerospace Science and Technology , 2020 , 97 : 105638 . DOI: 10.1016/j.ast.2019.105638 http://doi.org/10.1016/j.ast.2019.105638 https://linkinghub.elsevier.com/retrieve/pii/S1270963818309829 https://linkinghub.elsevier.com/retrieve/pii/S1270963818309829

JIAO J J , TRENTELMAN H L , CAMLIBEL M K . A suboptimality approach to distributed linear quadratic optimal control [J ] . IEEE Transactions on Automatic Control , 2019 , 65 ( 3 ): 1218 - 1225 . DOI: 10.1109/TAC.9 http://doi.org/10.1109/TAC.9 https://ieeexplore.ieee.org/xpl/RecentIssue.jsp?punumber=9 https://ieeexplore.ieee.org/xpl/RecentIssue.jsp?punumber=9

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