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Introduction of Aerospace Technology
Chinese Name:空天技术
English Name: Aerospace Technology
Publication cycle: Bimonthly
Language: Chinese
Director: China Aerospace Science and Industry Corporation Limited (CASIC)
Sponsor: Beijing HIWING Scientific and Technology Information Institute
Editor in chief: LIU Haifeng
Transient reconstruction of force-thermal coupling response of cabin based on surrogate model
Yan Yuehui;Qin Yuling;Fu Mengsi;Liu Yinxin;Chen Shuailong;Yu Chuanyun;Chen Qiang;Beijing Institute of Long March Spacecraft;To achieve the rapid solution and accurate prediction of full-field response of the bearing structure of high-speed aircraft under force-thermal coupling loads, a novel response reconstruction method based on multi-dimensional order reduction and deep learning is proposed. The sequential coupling method is adopted to reduce the computational complexity under the force-thermal coupling condition. The load-spacetime three-dimensional order reduction technique is adopted to complete the fundamental mode feature decomposition of the global transient response field, and the fundamental mode containing the characteristics of the vast majority of samples is truncated and selected to linearly fit all samples. A surrogate model is built through deep learning methods to establish the mapping relationship between the input parameters determining the force-thermal load and the fitting coefficients, thereby achieving rapid prediction of the global transient response field of the structure. The verification carried out for the three-dimensional cabin bearing structure shows that this method can accurately predict the global transient stress field and displacement field of the bearing structure of high-speed aircraft under the force-thermal coupling loads. The mean absolute error of the Mises stress field is 0.25 MPa, and the mean absolute error of the displacement field is 0.0144 mm. Moreover, the response reconstruction time for a single working condition can be controlled within 0.6 seconds, which is much lower than that of traditional numerical calculation methods. It is of great significance for the subsequent comprehensive evaluation and optimization design of the structural strength.
Design of deployment mechanisms of split rudders for hypersonic vehicles under constrained space and research on the dynamic characteristics
Li Guowang;Jin Liang;Split rudders, which can perform distinct functions by employing different deflection strategies, are widely utilized in modern aircraft. To address the challenges of compact structural layouts and limited motion space in hypersonic vehicles, which hinder the application of split rudders, a deployment mechanism based on fan-shaped wheel and sliding joint is proposed. Force analysis of the fan-shaped wheel during its motion demonstrates the feasibility of symmetric deployment under non-self-locking conditions. Multi-body dynamics simulation of the fan-shaped wheel's deployment process is conducted using the impact model in ADAMS, and the change of the thrust of the steering engine and the contact force of the sliding pin is obtained. The simulation results agree well with the theoretical analyses, proving the rationality of the impact model parameter settings and the feasibility of the deployment mechanism kinematical principles. The proposed design can be referenced for developing similar mechanisms in constrained space, while the simulation parameters can serve as a basis for other dynamics simulation.
Design of integrated control law for vehicle in wide speed range based on adaptive sliding mode
Zhao Chong;Wu Anping;Wang Nantian;Guo Huihui;In order to meet the requirements of wide-speed-range reusable aircraft for transonic flight, a guidance and control integrated strategy based on an adaptive sliding mode method is proposed, and the control systems across different flight phases are cooperatively designed to address the nonlinear variations of aerodynamic parameters and their derived issues during the Mach number transition from 3 to 8. The characteristics of the control system under different Mach numbers, as well as the differences between longperiod and short-period modes, are analyzed based on the aircraft's state-space model. Physical constraints are cooperatively handled by the integrated guidance and control strategy, and the conflict between control requirements for low-frequency stability in the long-period mode and high-frequency agility in the shortperiod mode is optimized. The interrelation between attitude angular velocity and acceleration is computed by integrating the dynamic equation concerning the center of mass, and a unified model is constructed in the ballistic coordinate system. A hyperbolic tangent saturation function is devised based on the sliding mode control approach to smoothly transit the sliding mode boundary layer, thus restraining chattering phenomena. The switching gain term is utilized to manage nonlinear aerodynamic parameter fluctuations across various speed ranges. The exponential reaching law is applied to adjust the convergence rate, while model uncertainties are offset via the adaptive law. The reliability of the introduced algorithm is verified by computational simulation. The results show that the proposed integrated control law is applicable to longitudinal and laterallongitudinal coupling control under different Mach numbers, can realize adaptive adjustment of control gains, and all variables are eventually in a stable state. Compared with the separate design method of guidance and control, it has smaller fluctuations and smoother control.
Multi-aircraft cooperative acquisition decision-making method based on double-layer optimization strategy
Liu Youxin;Guo Jie;Wang Haoning;Li Peilin;Tang Shengjing;Aiming at the problem of multi-aircraft cooperative interception of targets at the end of the shift time under the condition of limited target indication accuracy in long-range defense missions, a fast decision-making method of cooperative interception formation configuration based on double-layer optimization strategy is proposed. By analyzing the characteristics of satellite detection, a mathematical model of target indication area is established based on the least square method. According to the detection characteristics of the aircraft seeker, a mathematical model of multi-aircraft detection and search is established, and a simplified formation configuration optimization decision scenario is constructed. An area coverage algorithm based on Voronoi segmentation optimization is designed to optimize the formation configuration and an adaptive particle swarm optimization algorithm considering the optimization time is designed to complete the cooperative interception decision of the target indication area, which improves the decision-making efficiency. The simulation results show that the proposed double-layer optimization strategy can effectively solve the configuration decision-making problem of multi-aircraft cooperative interception formation for the mathematical model of target indication area and the mathematical model of aircraft detection and search established, and has good decision-making ability and fast response ability.
Online identification method for interceptor guidance parameter based on multi-model filtering
Li Huanyu;Guo Yang;Wang Shaobo;Zhang Shiyuan;Wang Jin;To address the problem that the guidance law of the opposing interceptor is unknown when the penetration vehicle faces interception by the interceptor, an identification method for the interceptor's guidance parameter law based on multi-model filtering is proposed. A linear time-varying guidance system is established under the small-angle assumption, and an optimal penetration method considering the maximization of zero-effort miss(ZEM) is designed based on the principle of optimal control. For the guidance strategies that the opponent's interceptor may adopt, a model set of typical guidance laws for the interceptor is designed. The guidance probabilities of each model are calculated based on the multi-model filtering method to identify the guidance law used by the opponent's interceptor. Simulation results show that under the objective function of maximizing the line-of-sight(LOS) angle rate, the designed optimal penetration guidance method satisfies the acceleration constraint conditions. When the model set is known, the guidance law of the interceptor can be quickly and accurately identified.
Intelligent evasion algorithm for aircraft in dynamic game scenario
Yu Hairan;Zhang Xiuyun;Liu Da;Zong Qun;Li Zhiyu;Zhang Ruilong;An online decision optimization method based on deep reinforcement learning (DRL) is proposed to solve the intelligent evasion problem for aircraft against multiple interceptors in highly dynamic game environment. Firstly， a dynamic adversarial evasion scenario is constructed using a 3-Degree-of-Freedom (3-DOF) mathematical model of the aircraft. Considering the constraints of dynamic pressure and overload， a dual-objective function is established to simultaneously address evasion interception and ensure arrival at the target point. The maximum entropy reinforcement learning algorithm is then designed to train the offline decision policy. Secondly， recognizing the potential mismatch between offline training conditions and actual online flight scenarios (e.g.， changes in interceptor tactics or positions)， a meta-learning-based online update algorithm is further developed， which utilizes small-sample data acquired from sensors to extract key information from new tasks， enabling rapid online parameter adjustment to guarantee successful evasion in real-time environments. Finally， a virtual simulation verification platform is developed using Unity3D， conducting comprehensive simulations and 3D visual demonstrations of the proposed intelligent aircraft evasion method. Experimental results demonstrate the effectiveness of the proposed approach.
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A lightweight cross-domain pose estimation network for non-cooperative spacecraft based on knowledge distillation
Yan Yuxiao;Li Yanyan;Chen Feiyu;Che Xueke;Zhou Siyin;To address the issues of domain gap， large parameter scale， and high computational cost faced by non-cooperative spacecraft pose estimation models in on-board hardware deployment， a lightweight improvement method based on knowledge distillation is proposed. By adding the ECA (Efficient Channel Attention) mechanism， optimizing the loss function， and designing dual distillation of feature loss and task loss， multi-dimensional knowledge transfer is achieved from the large-scale SPNv2 model. Focusing on the lightweight requirement for cross-domain non-cooperative spacecraft pose estimation， comparative experiments are conducted using the public SPEED+ dataset. Results show that while the target detection accuracy of the proposed method in complex backgrounds retains 81.6% of the original model， the parameter count is reduced by 35% and the computational complexity by 40.1%. It better meets the real-time deployment requirements of spacecraft embedded systems and provides a feasible solution for on-board real-time pose estimation.
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Intelligent Trajectory Prediction Algorithm for Reentry Glide Vehicles Based on Multi-Parameter Estimation
Zhou Chijun;Liu Yichen;Zhang Jinlin;Shao Lei;He Yangchao;Li Qingliang;To address the issues of error accumulation and insufficient prediction stability in traditional parameter estimation-based trajectory prediction methods， this paper proposes an intelligent trajectory prediction algorithm for reentry glide vehicles (RGVs) based on multi-parameter estimation. The method involves analytical modeling of aerodynamic acceleration， aerodynamic coefficients， control parameters， and maneuvering parameters. Using the minimum mean absolute error (MAE) of the trajectory as the optimization criterion， a Genetic Algorithm–Random Box Aggregation (GA-RBA) framework is constructed to deeply integrate function fitting theory with intelligent optimization algorithms. Innovatively， a sliding-time prediction mechanism is introduced to dynamically update the tracking and prediction windows， thereby blocking error propagation chains. This mechanism adaptively selects the optimal combination of functions to capture the variation patterns of key parameters in the motion model and generates high-precision predicted trajectories through numerical integration. Experimental results demonstrate that the proposed method maintains high prediction accuracy under medium and long-term trajectory prediction conditions. It overcomes the limitations of instability inherent in single-parameter and single-basis function predictions， breaks through the efficiency bottleneck caused by repeated function selection， and provides new theoretical support for high-precision rapid trajectory prediction of reentry glide vehicles.
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Research on Longitudinal Flight Control of Aerospace Vehicles Based on Linear Interpolation Variants
Ding Bingjia;Zhang Haochen;Geng Simao;Wen Jiawei;Chen Boyi;To address the control issues arising from the nonlinear changes in aerodynamic characteristics caused by configuration deformation during flight， this paper proposes incorporating deformation quantities into aerodynamic parameter modeling and adopts a method combining linear interpolation with Linear Quadratic Regulator (LQR). Taking the variable-configuration aircraft Horus as the research object， this study proceeds as follows: first， deformation quantities are introduced to establish the aerodynamic model of the morphing aircraft. Second， a longitudinal three-degree-of-freedom dynamic model integrating key aerodynamic deformation features is constructed， and the nonlinear functional relationship between longitudinal aerodynamic parameters and deformation quantities is derived. On this basis， an LQR control law is designed: control matrices are built respectively for the 0° and 30° configurations， and a time-varying control strategy based on linear interpolation is proposed. This strategy achieves smooth control transition during the deformation process and ensures the stability and dynamic consistency of the system throughout the entire deformation range. The results show that the LQR control strategy with linear interpolation exhibits excellent control performance during the time-varying process of aerodynamic parameters caused by aircraft deformation. This method not only ensures the dynamic stability and convergence of the five longitudinal state quantities， but also effectively overcomes the limitations of a single fixed controller in a time-varying environment.
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Separation optimization for TSTO aerospace vehicles based on energy climbing
Lai Jianqi;Hu Xingzhi;Zhao Bendong;Niu Huipeng;Chen Boyi;In response to the mission requirements for future high-efficiency aerospace transportation， this paper investigates the influence of staging conditions on takeoff mass for a two-stage-to-orbit (TSTO) aerospace vehicle， focusing on the optimization of initial takeoff mass based on overall parameters of the booster and orbiter stages. First， a preliminary configuration of the TSTO aerospace vehicle is introduced， along with modeling methods for mass and propulsion systems. Subsequently， building upon an energy-altitude climb approach， the required propellant mass fraction during the stage separation phase is derived， enabling the development of a parametric analytical model related to overall system parameters. Furthermore， by integrating the overall parameters of the TSTO system with energy-based analysis methods， and taking orbital insertion requirements of the upper stage as input parameters， an optimization model is established with the objective of minimizing the total takeoff mass. This model is then used to determine the optimal staging condition. Finally， the sensitivity of key design parameters on the total takeoff mass and staging conditions is analyzed.
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Chinese Library Classification
2022-03-24Beijing News Publication Bureau
2022-03-24Journal of Propulsion Technology
2021-11-25Tactical Missile Technology
2021-11-25Unmanned Systems Technology
2011-10-18Academic Misconduct Detection System
2011-10-18International Repository of Knowledge Resources
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