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Coupled dynamic model of state estimation for hypersonic glide vehicle

Journal of Systems Engineering and Electronics 2018年第6期29卷 1284-1292页

作者： ZHANG Kai XIONG Jiajun FU Tingting Department of Graduation Air Force Early Warning Academy Early Warning Intelligence Department Air Force Early Warning Academy

Aiming at handling complicated maneuvers or other unpredicted emergencies for hypersonic glide vehicle tracking,three coupled dynamic models of state estimation based on the priori information between guidance variables and aerodynamics are presented. Firstly, the aerodynamic acceleration acting on the target is analyzed to reveal the essence of the target’s *** three coupled structures for modeling aerodynamic parameters are developed by different ideas: the spiral model with a harmonic oscillator, the bank model with trigonometric functions of the bank angle and the guide model with the changing rule of guidance variables. Meanwhile, the comparison discussion is concluded to show the novelty and advantage of these ***, a performance assessment in different simulation cases is presented and detailed analysis is revealed. The results show that the proposed models perform excellent properties. Moreover, the guide model produces the best tracking performance and the bank model shows the second; however, the spiral model does not outperform the maneuvering reentry vehicle(MaRV) model markedly.

关键词： hypersonic glide vehicle state estimation dynamic model aerodynamic parameter guidance variable

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Robust Optimal Guidance for hypersonic glide vehicle with Hinge Moment Constraint

Robust Optimal Guidance for Hypersonic Glide Vehicle with Hi...

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第25届中国控制与决策会议

作者： CAI Wei-wei YANG Le-ping LIU Xin-jian ZHU Yan-wei College of Aerospace Science and Engineering National University of Defense Technology

ISBN: (纸本)9781467355339

The magnitude of hinge moment is a prominent problem for rapid dive maneuver of hypersonic glide vehicles. A robust optimal integrated guidance law considering constraints of hinge moment and terminal impact angle is proposed with excellent performance. Based on the analogy relationship of hinge moment and normal aerodynamic load, the constraint of hinge moment is transformed to normal load constraint;and the optimal guidance law under nominal conditions is derived utilizing optimal control theory. A terminal sliding mode control based guidance modification is designed to eliminate the inevitable departure brought by uncertainties in finite time;and the hyperbolic tangent function is introduced to reduce the high-frequency chatting. The theoretical analysis and simulation results are conducted to illustrate the capability of the proposed integrated guidance law for hypersonic glide vehicle.

关键词： hypersonic glide vehicle Integrated guidance Hinge moment Terminal sliding mode control

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Initial Descent Phase Guidance for hypersonic glide vehicle 36

Initial Descent Phase Guidance for Hypersonic Glide vehicle

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第36届中国控制会议

作者： Sun Jian-bo Pan Xing-hua Zhao Yu-shan School of Astronautics Beihang University Beijing Electro-mechanical Engineering Institute

ISBN: (纸本)9781538629185

A novel initial descent guidance law based on the transition function is proposed for the hypersonic glide vehicle without offline nominal angle of attack（AOA） design and online iteration *** the variation of the gravitational acceleration,a new transition condition between the initial descent phase and the quasi-equilibrium glide phase is ***,the initial descent phase is divided into two sub-phases noted as the open-loop guidance phase and the transition scheme *** guidance command during the transition scheme phase is generated by transition functions firstly proposed in this paper,which can smoothly adjust the AOA to satisfy the transition *** simulation results show that the proposed guidance law can satisfy the transition condition and the path constraints.

关键词： hypersonic glide vehicle quasi-equilibrium glide initial descent guidance transition function

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Tracking hypersonic glide vehicle Based on the MaRV Model with Multiple-model Approach

Tracking Hypersonic Glide Vehicle Based on the MaRV Model wi...

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第43届中国控制会议

作者： Liu Hao Liang Yongqi State Key Laboratory for Strength and Vibration of Mechanical Structures Xi'an Jiaotong University

In the research on hypersonic glide vehicle(HGV) tracking,the maneuvering reentry vehicle(Ma RV) model and multiple-model estimator have been widely ***,a systematic approach for model set design is ***,this paper analyzes MaRV model and its mode ***,the uniform model set is proposed,which is designed from an effective measurement approach for matching the uncertain model with the *** centered L2 discrepancy is applied to cover the uncertain mode of the target,and an in-depth analysis is ***,the mode space constructed based on the mode features of common aero vehicle(CAV) is *** interactive multiple model(IMM) estimator is employed for hybrid state ***,simulation results demonstrate that compared with Monte Carlo model sets,the proposed approach for MaRV model for HGV significantly improves the tracking accuracy.

关键词： hypersonic glide vehicle Maneuvering Target Tracking Uniform Set Mode Space Interactive Multiple Model Estimator

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Trajectory Tracking for hypersonic glide vehicles Based on Improved Sine-AIMM 36

Trajectory Tracking for Hypersonic Glide Vehicles Based on I...

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第36届中国控制会议

作者： Shan Feng Qingke Tan Qingdong Li Zhang Ren School of Automation Science and Electrical Engineering Science and Technology on Aircraft Control LaboratoryBeihang University

ISBN: (纸本)9781538629185

To obtain a better performance of trajectory tracking for hypersonic glide vehicles（HGVs）,this paper focuses on enhancing the accuracy of tracking model,an effective method with a modified tracking model is ***,according to the skip glide trajectory of HTV-2,a simplified trajectory model is established to describe the periodical characteristic of the ***,a modified tracking model based on Sine model for HGVs is ***,for better model matching performance,an adaptive method is proposed to update the probability transition matrix of ***,numerical simulation results are given to demonstrate that:interacting multiple model（IMM） algorithm based on the proposed Sine model is more accurate than that of Singer model,moreover,the adaptive IMM（AIMM） algorithm improves both the precision and the convergence rate of tracking for HGV.

关键词： maneuvering model target tracking hypersonic glide vehicle IMM Markov transition matrix

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Lateral-profile planning:Three-dimensional-profile-based optimal trajectory generation

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Science China(Technological Sciences) 2022年第12期65卷 3057-3068页

作者： ZHANG YuanLong XIE Yu BAO WeiMin College of Intelligence Science and Technology National University of Defense TechnologyChangsha 410073China Science and Technology Committee of China Aerospace Science and Technology Corporation Beijing 100048China

The conventional re-entry guidance method considerably limits the maneuverability of hypersonic glide vehicles under pre-given angle-of-attack *** address this issue,based on a previous three-dimensional(3D)profile guidance method,we propose a lateral-profile-first 3D profile optimization design strategy to solve the trajectory generation problem under complex conditions involving multiple *** the traditional method,which prioritizes the design of the longitudinal drag acceleration profiles,our method first converted the re-entry flight constraints into a lateral flight corridor,generated the initial lateral profile via parameterization,and solved the 3D profile using the coupling relationship between the longitudinal and lateral *** design of the 3D profile requires simultaneous consideration of waypoints,no-fly zones,and altitude profiles;hence,a new 3D profile optimization design model was constructed,and a customized sequential quadratic programming algorithm was employed to solve *** advantages of the proposed method were demonstrated based on landing footprint results obtained using the lateral profile-first ***,simulation results based on the common aero vehicle-high-performance model verified the feasibility and effectiveness of the strategy.

关键词： hypersonic glide vehicle three-dimensional profile lateral profile-first planning optimal trajectory footprint

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Analytical reentry guidance framework based on swarm intelligence optimization and altitude-energy profile

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Chinese Journal of Aeronautics 2023年第12期36卷 336-348页

作者： Hui XU Guangbin CAI Chaoxu MU Xin LI College of Missile Engineering Rocket Force University of EngineeringXi’an 710025China School of Electrical and Information Engineering Tianjin UniversityTianjin 300072China

Aimed at improving the real-time performance of guidance instruction generation,an analytical hypersonic reentry guidance framework is *** key steps of the novel guidance framework are the parameterization of reentry guidance problems and the optimization of ***,a quintic polynomial function of energy was designed to describe the altitude ***,according to the altitude-energy profile,the altitude,velocity,flight path angle,and bank angle were obtained analytically,which naturally met the terminal *** addition,the angle of the attack profile was determined using the velocity *** swarm intelligent optimization algorithms were used to optimize the *** path constraints were enforced by the penalty function ***,extensive simulations were carried out in both nominal and dispersed cases,and the simulation results showed that the proposed guidance framework was effective,high-precision,and robust in different scenarios.

关键词： Analytical solution hypersonic glide vehicle Improved swarm intelligent optimization Monte-Carlo simulation Reentry guidance method

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A New Sliding Mode Tracking Guidance Based on Three-dimensional Trajectory

A New Sliding Mode Tracking Guidance Based on Three-dimensio...

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第30届中国控制与决策会议

作者： Yuan-long Zhang Guo-jian Tang Wei-min Bao National University of Defense Technology China Aerospace Science and Technology Corporation

With multiple path constraints taken into consideration during hypersonic glide phase, a new sliding mode tracking guidance based on three-dimensional trajectory is proposed. Firstly, on the basis of entry vehicle dynamics and geometrical transformation, the dynamics formulation of crossrange parameter is derived. Therefore, a nonlinear guidance model composed of crossrange parameter and flight path angle is formed. Secondly, with the aid of feedback linearization technology, the nonlinear dynamics equations are converted into linear ones. Later, in order to track the reference states well, two sliding mode controllers are introduced based on the linear model and the stability of guidance system is proofed. At last, CAV-H model is utilized to validate the robustness of proposed guidance.

关键词： Crossrange Parameter Three-dimensional Tracking Guidance Sliding Mode Control hypersonic glide vehicle

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