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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
Physics-informed neural networks with prospects for applications in aerospace vehicles
Ding Yixin;Yuan Ruizhe;Guo Zongyi;Cao Shiyuan;Guo Jianguo;Chang Jing;Aerospace vehicles have been recognized as a strategic focus globally due to their unique advantages of low cost and reusability. However, the dynamics involving complex multi-physics effects and wide flight conditions pose severe challenges to modeling and control design. Physics-Informed Neural Networks(PINNs), emerging as a method fusing data-driven approaches with physical constraints, provide a new pathway to address these challenges. The PINN method and its application prospects in aerospace research are systematically reviewed. The basic principles and frameworks are expounded, and the mainstream improved algorithms along with research progress are analyzed. Furthermore, the application potential and implementation paths in key sectors, including multi-physics modeling, aerodynamic identification, control system design, and fault diagnosis, are reviewed and prospected. The study provides valuable theoretical and engineering references for the development of intelligent technologies for aerospace vehicles.
A transfer surrogate approach based on Gaussian process regression for aerodynamic characteristics of morphing aerospace vehicles
Jia Jun;Chen Boyi;Liu Yanbin;Chen Jinbao;To address the problem of exponential sample data requirement in high-dimensional aerodynamic characteristic prediction modeling for morphing aerospace vehicles, this paper proposes a transfer surrogate method based on Gaussian process regression. A regularity regression model is constructed using data from reduced-dimension baseline configurations, and a multi-model fusion algorithm based on distribution characteristics is introduced. By integrating limited aerodynamic data from variable configurations, accurate global aerodynamic predictions are achieved. An intermediate-layer surrogate model for multifidelity data is established using Gaussian processes, identifying the heteroscedastic characteristics of latent noise and obtaining posterior distributions. The multi-model fusion is transformed into a predictive variance optimization problem based on the K-nearest neighbors method. Optimal weights are solved via spatial clustering, and spatial distribution features are adaptively adjusted through a sample density function to improve local modeling behavior. Numerical examples are used to compare and analyze the dependence of the proposed data transfer method and pure data-driven methods on sample size. Results show that the effectiveness of data transfer depends on the degree of morphing, specifically, the strength of nonlinearity between pre-morphing data and post-morphing data. For mechanical properties with higher linearity, the proposed data-transfer-based surrogate modeling can reduce the sample requirement for variable configuration models down to one; however, for moment characteristics exhibiting strong nonlinearity before and after deformation, the proposed method has certain limitations.
Hypersonic airframe-propulsion integrated control considering inlet constraints
Zeng Boyu;Wang Guan;Li Jiaxin;Yang Feng;Wu Guoqiang;Liu Kai;An integrated intelligent control method oriented toward performance requirements is proposed to address the flight-propulsion coupling control problem of hypersonic vehicles under engine-inlet constraints. An extended-dimension dynamic model that characterizes flight-propulsion coupling effects is established, and the fuel-air equivalence ratio is introduced as a key state variable for control design. Prescribed performance constraints are designed to optimize control parameters, and the inlet constraint is transformed into a performance boundary of angle-of-attack tracking error to ensure compliance with inlet operation limits. A multi-objective cost function with high weight penalty term is constructed to realize the intelligent adaptive configuration of the integrated control law parameters. Simulation results demonstrate that the proposed method significantly reduces the overshoot and settling time of the angle of attack, effectively balances rapid dynamic response with inlet constraints, and exhibits strong robustness under model uncertainty.
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.
Separation optimization for TSTO aerospace vehicles based on energy climbing
Lai Jianqi;Hu Xingzhi;Zhao Bendong;Niu Huipeng;Chen Boyi;Nanjing University of Aeronautics and Astronautics;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. The specific impulse at the mission stage has the greatest impact on the total takeoff mass, followed in order by the mission-stage structural mass ratio and the launch-vehicle-stage structural mass ratio. The optimal staging velocity exhibits a negative correlation with both the launch-vehicle-stage structural mass ratio and the mission-stage specific impulse, while showing a positive correlation with the launch-vehicle-stage specific impulse and the mission-stage structural mass ratio. The variation trend of staging altitude is consistent with that of staging velocity.
Investigation on the ground proximity separation of a parallel arrangement vehicle based on CFD/RBD coupled method
Luo Xingdong;Hou Zihao;Yuan Ya;Bo Jinglong;Zhai Maochun;Li Shaowei;Zhang Shenrong;To meet the safety analysis requirements for ground proximity separation of parallel configuration vehicles during maglev electromagnetic boost launch， a multi-body separation prediction method based on CFD/RBD coupling is established， a constrained separation strategy with auxiliary separation mechanism is developed， and the flow field structure， aerodynamic load and constrained load characteristics during constrained separation and free separation are explored. The effect of attitude control engine working time on the separation characteristics is also studied. The results show that the ground proximity shock wave interference structure is basically unchanged in the constrained separation stage， and the ground reflected shock wave of the head of the vehicle directly interferes with the vehicle wings in the free separation stage. With the vehicle's head up， the supersonic ground effect gradually weakens， the aerodynamic lift gradually approaches the free stream state， and the vertical constraint load decreases continuously. With the release of constraints and the free separation stage， the head reflected shock wave enhances the lift force and the nose-down moment of the vehicle. When the dimensionless working time of the attitude control engine is 280， the vertical displacement of the vehicle gravity center will meet the safety distance condition at the dimensionless time 1466， when the pitch Angle is 6.1° and the constraint time is just right， safe separation can be better realized.
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Chinese Library Classification
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