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Three-dimensional cooperative guidance law for multiple missiles with impact angle constraint

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Journal of Systems Engineering and Electronics 2020年第6期31卷 1286-1296页

作者： YANG Biao jing wuxing GAO Changsheng School of Astronautics Harbin Institute of TechnologyHarbin 150001China

This paper proposes a cooperative guidance law for attacking a ground target with the impact angle constraint based on the motion camouflage strategy in the line-of-sight(LOS)frame.A dynamic model with the impact angle constraint is established according to the relative motion between multiple missiles and the *** process of cooperative guidance law design is divided into two ***,based on the undirected graph theory,a new finite-time consensus protocol on the LOS direction is derived to guarantee relative distances reach *** the value of acceleration command is positive,which is beneficial for engineering ***,the acceleration command on the normal direction of the LOS is designed based on motion camouflage and finite-time convergence,which can ensure the missiles reach the target with the desired angle and satisfy the motion camouflage *** finitetime stability analysis is proved by the Lyapunov *** simulations for stationary and maneuver targets have demonstrated the effectiveness of the cooperative guidance law proposed.

关键词： cooperative guidance law motion camouflage impact angle constraint finite-time

Recorded recurrent deep reinforcement learning guidance laws for intercepting endoatmospheric maneuvering missiles

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Defence Technology（防务技术） 2024年第1期31卷 457-470页

作者： Xiaoqi Qiu Peng Lai Changsheng Gao wuxing jing Department of Aerospace Engineering Harbin Institute of TechnologyHarbin150001China Shanghai Electro-Mechanical Engineering Institute Shanghai Academy of Spaceflight TechnologyShanghai201100China

This work proposes a recorded recurrent twin delayed deep deterministic(RRTD3)policy gradient algorithm to solve the challenge of constructing guidance laws for intercepting endoatmospheric maneuvering missiles with uncertainties and observation *** attack-defense engagement scenario is modeled as a partially observable Markov decision process(POMDP).Given the benefits of recurrent neural networks(RNNs)in processing sequence information,an RNN layer is incorporated into the agent’s policy network to alleviate the bottleneck of traditional deep reinforcement learning methods while dealing with *** measurements from the interceptor’s seeker during each guidance cycle are combined into one sequence as the input to the policy network since the detection frequency of an interceptor is usually higher than its guidance *** training,the hidden states of the RNN layer in the policy network are recorded to overcome the partially observable problem that this RNN layer causes inside the *** training curves show that the proposed RRTD3 successfully enhances data efficiency,training speed,and training *** test results confirm the advantages of the RRTD3-based guidance laws over some conventional guidance laws.

关键词： Endoatmospheric interception Missile guidance Reinforcement learning Markov decision process Recurrent neural networks

An improved numerical method for constructing Halo/Lissajous orbits in a full solar system model

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Chinese Journal of Aeronautics 2018年第6期31卷 1362-1374页

作者： Yingjing QIAN Xiaodong YANG wuxing jing Wei ZHANG Beijing Key Laboratory of Nonlinear Vibrations and Strength of Mechanical Structures College of Mechanical Engineering Beijing University of Technology Department of Aerospace Engineering Harbin Institute of Technology

An improved numerical method that can construct Halo/Lissajous orbits in the vicinity of collinear libration points in a full solar system model is investigated. A full solar system gravitational model in the geocentric rotating coordinate system with a clear presentation of the angular velocity relative to the inertial coordinate system is proposed. An alternative way to determine patch points in the multiple shooting method is provided based on a dynamical analysis with Poincare′sections. By employing the new patch points and sequential quadratic programming, Halo orbits for L1, L2, and L3points as well as Lissajous orbits for L1and L2points in the EarthMoon system are generated with the proposed full solar system gravitational model to verify the effectiveness of the proposed method.

关键词： Full solar system model Halo orbit Libration motion Lissajous orbit Poincare section

Autonomous navigation to quasi-periodic orbits near translunar libration points

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Chinese Journal of Aeronautics 2013年第5期26卷 1259-1268页

作者： jing wuxing Qian Yingjing Gao Changsheng Li Jianqing Department of Aerospace Engineering Harbin Institute of Technology

Libration-point missions have been very useful and successful. Due to the unstable natures of most of these orbits, the long-time stationkeeping demands frequent maneuvers and precise orbit determinations. Earth-based tracking will have to undertake much more responsibilities with the increasing number of libration missions. An autonomous navigation system could offer a better way to decrease the need for Earth-based tracking. Nevertheless, when an autonomous navigation system is applied, there are three important factors affecting autonomous navigation accuracy, i.e., the accuracy of initial conditions, the accuracy of measurements, and the accuracy of onboard dynamics for propagation. This paper focuses on analyzing the influence from the third factor and finding an appropriate navigation dynamics, which can satisfy the requirement of estimation accuracy but not cause too much burden for onboard computation. When considering the restricted three-body model and the bicircular restricted four-body model as navigation dynamics, the astrin- gency is not shown during the simulations. Meanwhile, when considering the influences of the Sun＇s direct and indirect perturbations and the eccentricity of the Moon＇s orbit, a new navigation dynamic model with the standard ephemerides is proposed. The simulation shows the feasibility of the proposed model.

关键词： Autonomous navigation Extended Kalman filters Libration points Multi-body dynamics Quasi-periodic orbit

A novel adaptive lateral reentry guidance algorithm with complex distributed no-fly zones constraints

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Chinese Journal of Aeronautics 2022年第7期35卷 128-143页

作者： Yudong HU Changsheng GAO Junlong LI wuxing jing Wenxue CHEN School of Astronautics Harbin Institute of TechnologyHarbin 150001China Beijing Institute of Electronic System Engineering China Aerospace Science and Industry CorporationBeijing 100854China

Aimed at complex distributed no-fly zones avoidance problems,a novel adaptive lateral reentry guidance algorithm is ***,by introducing the improved attractive and repulsive potential fields,an improved artificial potential field method is *** with the proposed judgment criterion for whether a no-fly zone has been avoided,the proposed improved artificial potential field method effectively solves the reference heading angle determination problem under the constraints of complex distributed no-fly ***,based on the proposed no-fly zone’s threat quantitative evaluation method and the reference heading angle determined by the proposed improved artificial potential field method,the heading corridor is improved to increase its sensitivity to the threat changes of the no-fly ***,for satisfying the requirements of complex distributed no-fly zones avoidance,a novel guidance logic via improved heading corridor is proposed to update the reference heading corridor adaptively in real time according to the threat and constraint changes of the no-fly zones,and the bank reversal logic is employed to control the lateral *** simulation results for nominal and dispersed cases indicate that the proposed guidance algorithm has high robustness,stability,and applicability,and is feasible and effective to deal with the complex distributed no-fly zones avoidance problems.

关键词： Guidance strategy Heading corridor Hypersonic vehicles Improved artificial potential field Lateral reentry guidance Threat quantitative evaluation

Parametric modeling of hypersonic ballistic data based on time varying auto-regressive model

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Science China(Technological Sciences) 2020年第8期63卷 1396-1405页

作者： HU YuDong LI JunLong ZHANG Zhao jing wuxing GAO ChangSheng Department of Aerospace Engineering Harbin Institute of TechnologyHarbin 150001China China Aerospace Science and Industry Corporation Beijing 100854China

For describing target motion in hypersonic vehicle defense,a parametric analyzing and modeling method on ballistic data is proposed based on time varying auto-regressive *** data are regarded as non-stationary random signal,where the hidden internal law is ***,ballistic data are decomposed into smooth linear trend signal and non-stationary periodic skip signal with ensemble empirical mode decomposition method to avoid mutual interference between different modal ***,the linear trend signal and the periodic skip signal are modeled *** linear trend signal is approximated by power function regressive estimator and the periodic skip signal is modeled based on time varying auto-regressive *** order to determine optimal model orders,a novel method is presented based on information theoretic criteria and the criteria of minimizing the mean absolute ***,the consistency test is conducted by investigating the time-frequency spectrum characteristics and statistical properties of outputs of the parametric model established above and dynamics model under the same initial *** results demonstrate that the parametric model established by the proposed method shares a high consistency with the original dynamics model.

关键词： hypersonic vehicle parametric modeling ballistic data decomposition time varying auto-regressive periods drift

Application of PID controller to 2D differential geometric guidance problem

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控制理论与应用（英文版） 2007年第3期5卷 285-290页

作者： Chaoyong LI wuxing jing Department of Aerospace Engineering Harbin Institute of Technology Harbin Heilongjiang 150001 China

This paper presents the application of the proportional-integral-derivative （PID） controller to the flight control system （FCS） for two-dimensional （2D） differential geometric （DG） guidance and control problem. In particular, the performance of the designed FCS is investigated. To this end, the commanded angle-of-attack is firstly developed in the time domain using the classical DG formulations. Then, the classical PID controller is introduced to develop a FCS so as to form the 2D DG guidance and control system, and the PID controller parameters are determined by the Ziegler-Nichols method as well as the Routh-Hurwitz stability algorithm to guarantee the convergence of the system error. The results demonstrate that the designed controller yields a fast responding system, and the resulting DG guidance and control system is viable and effective in a realistic missile defense engagement.

关键词： Differential geometry Flight control system Missile guidance PID controller

Attitude Control for Spacecraft with Swinging Large-scale Payload

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Chinese Journal of Aeronautics 2011年第3期24卷 309-317页

作者： jing wuxing XIA Xiwang GAO Changsheng WEI Wenshu Department of Aerospace Engineering Harbin Institute of Technology Harbin 150001 China

The primary sensor of astronomy observation satellite （AOS） is mounted on a gimbal base which connects directly with the satellite platform and has two degrees of freedom. Attitude control for AOS with a swinging sensor will be highlighted in this paper. Due to the non-negligible mass and length of the sensor, the internal motion between the satellite and the sensor will change the attitude, the position of center of mass and moment of inertia of the SYSTEM （consists of the satellite and the sen- sor）. According to moment of momentum theorem, a rigid two-body dynamic model is derived, which can he used to determine the inertial tensor of the SYSTEM. Modulating the satellite＇s present and desired quaternions results in quasi-Euler angles and normalizing these resultant parameters can ensure that the channel corresponding to each quasi-Euler angle is in the charge of each component of the control torque. Based on the normalized quasi-Euler angles, a switching attitude control law is proposed. With the control law, the corresponding phase trajectory will slide along the switching surface to the origin （corresponding to the desired states）. Simulation results show that the satellite can be controlled perfectly by thrusters with the proposed control law, even in the case of structural asymmetry and serious coupling between the control channels.

关键词： rigid two-body relative motion modeling attitude control quasi-Euler angle switching control law

Multidisciplinary integrated design of long-range ballistic missile using PSO algorithm

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Journal of Systems Engineering and Electronics 2020年第2期31卷 335-349页

作者： ZHENG Xu GAO Yejun jingwuxing WANG Yongsheng Department of Aerospace Engineering Harbin Institute of TechnologyHarbin 150001China The 28th Research Institute of China Electronics Technology Group Corporation Nanjing 210007China Beijing Aerospace Long-march Flying Vehicle Institute Beijing 100076China Beijing Aerospace Technology Institute Beijing 100074China

In the case of the given design variables and constraint functions, this paper is concerned with the rapid overall parameters design of trajectory, propulsion and aerodynamics for long-range ballistic missiles based on the index of the minimum take-off *** contrast to the traditional subsystem independent design, this paper adopts the research idea of the combination of the subsystem independent design and the multisystem integration ***, the trajectory, propulsion and aerodynamics of the subsystem are separately designed by the engineering design, including the design of the minimum energy trajectory, the computation of propulsion system parameters, and the calculation of aerodynamic coefficient and dynamic derivative of the missile by employing the software of missile DATCOM. Then, the uniform design method is used to simplify the constraint conditions and the design variables through the integration design, and the accurate design of the optimized variables would be accomplished by adopting the uniform particle swarm optimization(PSO) algorithm. Finally, the automation design software is written for the three-stage solid ballistic missile. The take-off mass of 29 850 kg is derived by the subsystem independent design, and 20 constraints are reduced by employing the uniform design on the basis of 29 design variables and 32 constraints, and the take-off mass is dropped by 1 850 kg by applying the combination of the uniform design and PSO. The simulation results demonstrate the effectiveness and feasibility of the proposed hybrid optimization technique.

关键词： ballistic missile independent design multidisciplinary integrated design uniform design particle swarm optimization(PSO)