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Infrared radiation characteristics of dagger-type hypersonic missile

第40届中国控制会议

作者： Haihong Chi Mingxin Zhou Harbin Engineering University

This paper discusses the problem of avoiding threats during the cruising flight of hypersonic vehicles（HV）.Considering the constraints on kinematics of HV and changing environments, this paper proposes two methods of trajectory planning that taking the overload or the rotational angular velocity of the ballistic deflection angle as actions of agent. Meanwhile,the agent’s policy is optimized with policy gradient method, and Proximal Policy Optimization（PPO） and Soft Actor-Critic（SAC） are used for comparison. Experimental results show that PPO and SAC have similar performance in penetration ***, in the complicated flight environment, the method of taking overload and exploration distance as actions has a higher penetration success ratio.

关键词： hypersonic vehicles Trajectory planning Reinforcement learning

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Chinese Journal of Aeronautics 2024年第4期37卷 137-150页

作者： Xubo DU Qingzhen YANG Haoqi YANG Jin BAI Yongqiang SHI School of Power and Energy Northwestern Polytechnical UniversityXi’an 710129China

hypersonic vehicles emit strong infrared radiation from their high-temperature exhaust plume and body, which is critical for infrared early warning, tracking, and guidance. In this work, a comprehensive analysis is conducted on the factors involved in air dissociation reaction within the shock layer of hypersonic missile heads, as well as the multi-component afterburning effect of the exhaust plume. A novel Reverse Monte Carlo Method(RMCM) is proposed for infrared radiation calculation, which utilizes two-dimensional Low-Discrepancy Sequences(LDS) to improve computational accuracy. The numerical calculations for a dagger-type missile show that afterburning reactions increase the temperature on the centerline of the outlet exhaust plume by about 1000 K. The total infrared radiation intensity of the missile is the highest in the 1–3 μm band, with the hightemperature wall of the nozzle being the primary source of solid radiation, and gas radiation primarily coming from H_(2)O. The radiation intensity of the missile exhaust plume in the 3–5 μm band is the highest, with radiation sources primarily coming from CO_(2), CO, and HCl. Afterburning reactions of the exhaust plume increase the total infrared radiation intensity of the missile by about 0.7times. These results can provide reference for the detection and guidance of hypersonic missiles.

关键词： hypersonic vehicles Infrared radiation Monte Carlo methods Low-discrepancy sequences Exhaust plume Afterburning

A novel evasion guidance for hypersonic morphing vehicle via intelligent maneuver strategy

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Chinese Journal of Aeronautics 2024年第5期37卷 441-461页

作者： Xun LI Xiaogang WANG Hongyu ZHOU Yu LI Department of Aerodynamics Harbin Institute of TechnologyHarbin 150001China Beijing Aerospace Technology Institute Beijing 100074China

This paper presents a novel evasion guidance law for hypersonic morphing vehicles,focusing on determining the optimized wing's unfolded angle to promote maneuverability based on an intelligent ***,the pursuit-evasion problem is modeled as a Markov decision *** the agent's action consists of maneuver overload and the unfolded angle of wings,which is different from the conventional evasion guidance designed for fixed-shape *** reward function is formulated to ensure that the miss distances satisfy the prescribed bounds while minimizing energy ***,to maximize the expected cumulative reward,a residual learning method is proposed based on proximal policy optimization,which integrates the optimal evasion for linear cases as the baseline and trains to optimize the performance for nonlinear engagement with multiple ***,offline training guarantees improvement of the constructed evasion guidance law over conventional ***,the guidance law for online implementation includes only analytical *** maps from the confrontation state to the expected angle of attack and the unfolded angle while retaining high computational *** show that the proposed evasion guidance law can utilize the change of unfolded angle to extend the maximum overload *** it surpasses conventional maneuver strategies by ensuring better evasion efficacy and higher energy efficiency.

关键词： hypersonic vehicles Variable-sweep wings Evasion guidance Reinforcement learning Pursuit-evasion problem

An unsupervised classification method of flight states for hypersonic targets based on hyperspectral features

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Chinese Journal of Aeronautics 2023年第5期36卷 434-446页

作者： Shurong YUAN Lei SHI Yutong ZHAI Bo YAO Fangyan LI Yuefan DU Key Laboratory of Equipment Efficiency in Extreme Environment Ministry of EducationXiDian UniversityXi’an 710071China School of Aerospace Science and Technology XiDian UniversityXi’an 710071China

In response to the challenges of aerospace defense caused by the rapid development of hypersonic targets in recent years,the research on the unsupervised classification of flight states for hypersonic targets is carried out in this paper,which is based on the Hyperspectral Features(HFs)of hypersonic targets covered with plasma sheath during high-speed ***,a new concept of the super node is defined to improve classification accuracy by alleviating the intraclass variability of ***,the frequency domain information of the curve of HFs is utilized to reduce the feature redundancy according to the prior theoretical knowledge that the fluctuation characteristics of HFs of the same flight states are ***,an unsupervised classification method based on the Density Peak Clustering(DPC)for HFs is designed to class flight states after eliminating the impact of intraclass variability and feature dimension *** proposal is compared with the traditional classification algorithms on simulated hyperspectral data sets of typical flight states of the hypersonic vehicle and an actual-observation hyperspectral data *** results indicate that the performance of our proposal has competitive advantages in terms of Overall Accuracy(OA),Average Accuracy(AA)and Kappa coefficient.

关键词： Classification Clustering algorithms hypersonic vehicles Hyperspectral Unsupervised

Review of control and guidance technology on hypersonic vehicle

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Chinese Journal of Aeronautics 2022年第7期35卷 1-18页

作者： Yibo DING Xiaokui YUE Guangshan CHEN Jiashun SI School of Astronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai Aerospace Control Technology Institute Shanghai 201109China Beijing Reserarch Institute of Automation for Machinery Industry Co. LTD.Beijing 100124China

Air-breathing hypersonic vehicle has great military and potential economic value due to its characteristics:high velocity,long range,quick ***,the development of hypersonic vehicle and its guidance and control technology are reviewed in this ***,the development and classification of hypersonic vehicles around the world are summarized,and the geometric configuration and mission profile of typical air-breathing hypersonic vehicle are ***,the control difficulties of air-breathing hypersonic vehicle are introduced,including integrated design of engine and fuselage,static instability,strong nonlinearity,uncertain aerodynamic parameters,*** to its control requirements,the control methods considering external disturbance,fault-tolerant control methods,anti-saturation methods,and prescribed performance control methods considering transient performance constraints are summarized *** classification and comparison of various control methods are given,and the frontiers of theoretical development are ***,considering the effects of composite disturbances,the design of terminal guidance law under multiple constraints is overviewed,including guidance law with angle constraint,velocity constraint,acceleration constraint and time ***,the classification of guidance law design methods under different constraints,their advantages as well as the future development trend and requirements are introduced.

关键词： Classification of hypersonic vehicles Control equipmentaerospace applications Flight profiles Guidance strategy hypersonic vehicles

Difference analysis in terahertz wave propagation in thermochemical nonequilibrium plasma sheath under different hypersonic vehicle shapes

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Chinese Journal of Aeronautics 2023年第10期36卷 137-151页

作者： Wenchong OUYANG Qi LIU Zhengwei WU School of Nuclear Science and Technology University of Science and Technology of ChinaHefei 230026China Joint Laboratory of Plasma Application Technology Institute of Advanced TechnologyUniversity of Science and Technology of ChinaHefei 230031China CAS Key Laboratory of Geospace Environment University of Science and Technology of ChinaHefei 230026China

Research on terahertz communication under different vehicles has important guiding significance for the design of future hypersonic vehicle and Radio Frequency(RF)*** this paper,a joint simulation model of plasma flow under thermochemical nonequilibrium state and terahertz transmission is developed to investigate the differences in terahertz wave transmission characteristics under different vehicle shapes and the related *** comparing the plasma sheath characteristics and terahertz transmission among HIFIRE-5b(hypersonic International Flight Research Experimentation-5b),RAM C(Radio Attenuation Measurement C)and ARD(Atmospheric Reentry Demonstrator)vehicles,it is found that the sheath thickness and electron density of ARD vehicles is significantly larger than that of HIFIRE-5b and RAM C vehicles,resulting in greater terahertz wave *** absorption plays a major role in the terahertz attenuation of vehicles,and the contribution of reflection effects is only observed in the ARD vehicle due to its larger plasma sheath thickness and spatial structure *** on the above comparison results,a shape design scheme of reducing the vehicle head and tail for mitigating RF blackout is proposed,and the scheme is proved by further analyzing the effects of different vehicle heads and tails on the terahertz *** the decrease of the head radius and tail width of hypersonic vehicle,the wave attenuation at the same terahertz frequency decreases,and the contribution of reflection effect to wave attenuation gradually ***,the shape design scheme of reducing the vehicle head and tail can effectively alleviate the RF blackout problem,which provides an important reference value for future hypersonic vehicle design.

关键词： hypersonic vehicles Plasma flow Plasma sheaths Shape optimization Terahertz waves Wave propagation

Particle swarm optimization applied to hypersonic reentry trajectories

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Chinese Journal of Aeronautics 2015年第3期28卷 822-831页

作者： Zhao Jiang Zhou Rui School of Automation Science and Electrical Engineering Beihang University

Abstract This paper presents the novel use of the particle swarm optimization （PSO） to generate the end-to-end trajectory for hypersonic reentry vehicles in a quite simple formulation. The velocity- dependent bank angle profile is developed to reduce the search space of unknown parameters based on the constrained PSO algorithm. The path constraints are enforced by setting the fitness function to be infinite on condition that the particles violate the maximum allowable values. The PSO algo- rithm also provides a much easier means to satisfy the terminal conditions by adding penalty terms to the fitness function. Furthermore, the approximate reentry landing footprint is fast constructed by incorporating an interpolation model into the standardized bank angle profiles. Numerical sim ulations demonstrate that the PSO method is a feasible and flexible tool to generate the end-to-end trajectory and landing footprint for hypersonic reentry vehicles.

关键词： Footprint hypersonic vehicles Particle swarm optimization(PSO) Reentry Trajectories

Flight Dynamic Analysis of hypersonic Vehicle Considering Liquid-Solid Coupling

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Transactions of Nanjing University of Aeronautics and Astronautics 2015年第1期32卷 81-88页

作者：徐晓东黄一敏蔡晓斌 College of Automation Engineering Nanjing University of Aeronautics and Astronautic Research Institute of UAV Nanjing University of Aeronautics and Astronautic 95835 PLA Troops

With the liquid propellant making up 60%—70% of the takeoff weight of the hypersonic vehicle,the dynamic load caused by great propellant sloshing interacts with the flexible structure of the ***,the dynamic model displays characteristics of strong coupling with structure/control and *** on the sloshing mass dynamic simplified as a spring-mass-damping model,a rigid-flexible-sloshing model is ***,the effect on the dynamic performance of the coupled model is analyzed with changing frequency and *** results show that propellant sloshing dynamics significantly affects the rigid body motion modes,especially flexible mode and short *** right half plane pole(RHP)moves far from the imaginary axis with the consumption of the *** flexible mode attenuates with the increase of the sloshing damping,and the coupling becomes stronger when sloshing frequency is close to the short mode frequency or the flexible frequency of the beam.

关键词： hypersonic vehicles liquid propellant sloshing coupling model structure vibration

Robust tracking control design for a flexible air-breathing hypersonic vehicle

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Journal of Central South University 2014年第1期21卷 130-139页

作者：张垚鲜斌刁琛赵勃郭建川 Institute of Robotics and Autonomous System Tianjin Key Laboratory of Process Measurement and ControlSchool of Electrical Engineering and AutomationTianjin University

A nonlinear robust controller was presented to improve the tracking control performance of a flexible air-breathing hypersonic vehicle(AHV) which is subjected to system parametric uncertainties and unknown additive time-varying *** longitudinal dynamic model for the flexible AHV was used for the control ***-gain observers were designed to compensate for the system uncertainties and additive *** gain theorem and Lyapunov based stability analysis were utilized to prove the stability of the closed loop *** uniformly ultimately bounded tracking of the vehicle's velocity,altitude and attack angle were achieved under aeroelastic effects,system parametric uncertainties and unknown additive ***/Simulink simulation results were provided to validate the robustness of the proposed control *** simulation results demonstrate that the tracking errors stay in a small region around zero.

关键词： hypersonic vehicles nonlinear robust control flexible mode small gain theorem Lyapunov