In order to solve the problem of high maneuverability and difficult trajectory prediction of hypersonic glide vehicle (HGV), an intelligent trajectory prediction method of HGV based on ensemble empirical mode decomposition and attention long short term memory network is proposed by selecting the aerodynamic acceleration as the prediction parameter. Firstly, the maneuvering characteristics and the aerodynamic variation law of HGV are analyzed based on the six degree of freedom motion equation. The dynamic tracking model is established to estimate the aerodynamic acceleration in real time. Secondly, the estimated aerodynamic acceleration is decomposed and reconstructed by using ensemble empirical mode decomposition to weaken the influence of noise and avoid interference to the prediction model. Finally, the denoised aerodynamic acceleration data used to train the attention long short term memory network. Then the future aerodynamic acceleration data predicted and the future trajectory of HGV is reconstructed to achieve online trajectory prediction. The simulation results show that the method can effectively predict the maneuver trajectory of HGV with high prediction accuracy and good stability.

Aiming at the difficulties of a class of hypersonic flight vehicle (HFV) involving variable configurations, the engineering application requirements are analyzed, and the research progress of several typical nonlinear control methods is summarized. Firstly, the sources and characteristics of several common research models of hypersonic flight vehicle are summarized. Secondly, based on the actual engineering requirements, the control difficulties and needs for the control system capability of such vehicle are analyzed. Furthermore, the current status of several typical nonlinear control methods and intelligent control methods for hypersonic flight vehicle are summarized, and the frameworks of various control schemes are given. Finally, some problems and directions for further research are discussed for the HFV control with diversified mission forms and complicated environment in the future.

Based on fuzzy clustering and LSTM network, a data driven anomaly analysis method of launch vehicle engine oxygen turbopump data is proposed. Firstly, fuzzy clustering is used to pre classify the data samples with complex working conditions and incomplete labels to obtain complete labels and analyze the feature contribution, which lays a foundation for feature screening and training of LSTM network. The LSTM network is used to predict the data of the oxygen turbopump, and the average error between the predicted results and the original data is calculated. Then the threshold criterion calculated by the non parametric threshold calculation method is used to determine whether the turbopump is abnormal. Finally, the fault detection and alarm driven by the oxygen turbopump data are realized, and the accuracy is improved by 7% compared with the red line threshold detection method.

The components and initial deployment of a space elevator system is briefly introduced in this work. On this basis, aiming at the complex dynamics and control problems existing both in the initial deployment and the follow up operation, the development status of dynamics and control of the space elevator system is analyzed and summarized from five aspects, including the dynamic modeling, stability, cable oscillation, cable oscillation caused by climber(s) motion and oscillation suppression, and initial deployment dynamics. Finally, further development of dynamics and control of the space elevator is summarized and prospected.

Aiming at the problem of intercepting endo atmospheric high speed maneuvering targets, a deep reinforcement learning guidance law is proposed based on the twin delayed deep deterministic policy gradient(TD3) algorithm. It directly maps the engagement information to the commanded acceleration of the interceptor, which is an end to-end, model free guidance strategy. Firstly, the engagement kinematic model of both sides is described as a Markov decision process suitable for deep reinforcement learning algorithms. After that, a complete deep reinforcement learning guidance algorithm is constructed by reasonably designing the engagement scenarios, action space, state space and network structure required for algorithm training. The reward shaping and random initialization are introduced to construct a complete algorithm. The simulation results show that, compared with the proportional guidance and augmented proportional guidance laws, the proposed guidance strategy can reduce the requirement for mid course guidance while having smaller miss distances. It has good robustness and generalization ability, with less computational burden that makes it eligible to run on missile borne computers.

The launch probability of the modular launch vehicle is too low due to the mismatch between the flight load and the bearing capacity. To solve this problem, a joint optimization control method for lunch vehicle’s flight load based on ballistic wind correction, engine throttling, active deloading and refining of transverse dynamic load is proposed. With the constraint of vehicle body bearing capacity, this method joints multiple load control technologies to design a launch vehicle reversely for the purpose of improving launch probability.Taking the first flight of the Long March 8 launch vehicle as an example, this technology has successfully increased the launch probability from 33% in the initial stage of development to 83%.

The importance of the on orbit artificial intelligence technology for imaging satellite and the current research status are analyzed in this paper. Restricted computing power, high real time requirements, lack of large scale data sets, and special space environment are main challenges faced by the on orbit intelligence. Then the intelligent algorithms, hardware platforms, and optimization techniques are systematically summarized. As for the object detection, the remote sensing image data set, model architecture, real time and other aspects are introduced in detail. Finally, the future development of on orbit artificial intelligence technology for imaging satellite are studied and discussed.

Guidance methods and integrated guidance and control(IGC) methods under terminal angle constraints of guided weapons are reviewed. Firstly, several typical definitions of terminal angle constraints are compared and analyzed, and the state space models of the guidance law and IGC method design oriented to terminal angle constraints are constructed for two and three dimensional engagement scenarios. Subsequently, the current approaches involving guidance and IGC methods under terminal angle constraints are classified, concluded and compared in detail. Thirdly, the problems of multi constraint impact angle control, guidance information extraction, impact angle range estimation and cooperative guidance in the guidance and IGC methods under terminal angle constraints are prospected.

The basic principles of three modes for moving mass control are summarized, including the extra moment of inertia despin control, mass moment attitude control, and stability regulation. The key control problems that the moving mass high speed vehicles would face are then analyzed in detail with four aspects, i.e. dynamic modeling, guidance & control, actuator implementation, and system simulation & evaluation. Finally, the development trend and potential research themes are pointed out for the moving mass high speed vehicles.

Aiming at the problems that the traditional passive suspension rover may have in the complex terrain movement of Mars, the inchworm like rover is designed, including subsidence and escape, hill climbing, bottom support and wheel lift design. The key parameters of the moving system of the inchworm like rover were identified, and the key parameter values of different lifting heights of the rover and the displacement value of one inchworm movement period are calculated. The results show that the inchworm like rover can solve the above problems of passive suspension rover. Ground tests and flight tests have been carried out on the designed inchworm like rover, and verified the ability of wheel sinkage and extrication, obstacle crossing and slope climbing. As an example of application of the imitated inchworm rover, the Mars rover Zhurong has successfully undergone flight tests, and its smooth operation on the surface of Mars shows that the design measures of the inchworm like rover are effective.

Centering on the structural mechanism technology in the on orbit construction of space optical telescope, this paper focuses on the basic concepts and technical characteristics of key technologies related to structure and mechanism, including topology optimization and module technology of space structure of large telescope, high precision deployment adjustment and locking technology of optical mechanical structure and mechanism, on orbit additive manufacturing technology of typical optical mechanical components. It also analyzes the technical connotation and advanced technical approaches of robot assisted autonomous precision assembly and control technology. Finally, the development trend of structure and mechanism technology in on orbit construction and some technical problems to be studied are prospected. This paper may provide a reference for evolution of space optical telescope.

Taking the moving platform aircraft cluster as the research object, cluster cooperative positioning and navigation countermeasures technology is analyzed, as well as the state of the art. By refining technical difficulties, the development trend of the technology is put forward, providing new ideas for future construction of autonomous spatio temporal reference system and navigation countermeasures of aircraft cluster in China.

In this paper, the acceleration technologies and basic theory of various types of electric propulsion, and the advantages and disadvantages of existing acceleration technologies are summarized. Then the development trend of acceleration technologies or the latest acceleration technologies both in China and abroad are introduced. On this basis, the next electric propulsion acceleration technology is prospected to provide reference for the research and development of new electric propulsion technology in China, and promote the further development of space propulsion technology.

This paper systematically reviews the types of parking orbits near the moon that can be used to deploy space station, and gives the definitions and main parameters of different types of orbits. The energy requirements, mission support, space environment and other characteristics of different types of orbits are analyzed through simulation calculation and comparison of domestic and foreign orbit research conclusions. The main considerations and basis for the selection of the deployment orbit for deep space Gateway are analyzed. Finally, this paper offers several suggestions on the application of various kinds of orbits, which can provide technical reference for the selection of the parking orbit for the future deployment of lunar space station.

Taking landing and roving exploration on the extraterrestrial bodies such as the Moon, the Mars and asteroids as the research background, the development status, application and future trend of autonomous intelligence technology are analyzed and studied. The current implementation of such landing and roving exploration missions in China and abroad is reviewed. The research status of autonomous intelligence technology in the above field is described from four aspects, including navigation positioning and environment sensing, trajectory optimization and guidance control, autonomous detection and path planning, and fault diagnosis and autonomous processing. Finally, the future development trend is prospected.

The development status, aerodynamic modeling, dynamic modeling and control methods of morphing vehicle are reviewed. Firstly, the definition and deformation requirements of morphing vehicle are described, and then the technical advantages are sorted out from four aspects. The characteristics and development status of various vehicle deformation technologies are analyzed and summarized in detail according to different wing deformation modes. The aerodynamic mechanism of the deformed vehicle and the fixed shape vehicle is compared and analyzed, and the dynamics modeling methods of the deformed vehicle are sorted out, and the characteristics of each method are summarized. The characteristics and difficulties of flight control are analyzed in combination with those of deformed vehicle, and the research progress of various kinds of deformed vehicle control is described in detail. Finally, the development trends of morphing vehicle are summarized: deepen basic theory and technology research, developing towards intelligent direction from all aspects of material, structure and control, and finally realizing engineering, autonomous and intelligent application of morphing vehicle.

The concept of cislunar exploration and exploitation is put forward firstly in this paper. The global development status and trends are summarized, and the development demands are described from perspectives of human civilization, the pattern of space, strategic security and sci tech/economy development. The architecture composition, functional requirements, technical difficulties are proposed. The development benefits are analyzed from three aspects of science, economy and engineering. Finally, the development roadmap is given. The research results can provide reference for large scale exploration and exploitation of cislunar space in the future.

Aiming at solving the problem of correcting injection parameters or terminal program angular correction after using classic iterative guidance method, an adaptive prediction compensation iterative guidance algorithm based on model reference is studied for the application of launch vehicle. Base on the classical iterative guidance algorithm, this algorithm compensates the parameters of shutdown points in time according to the reference model of the predicted iterative terminal program angle and flight acceleration. The flight trajectory is reconstructed according to the compensated terminal parameters, and then the guidance command satisfying the correction of the orbital parameters or terminal program angular deviation is obtained, so as to improve the correction ability of the adaptive prediction iterative guidance algorithm. In addition, the basic algorithm of classical iterative guidance is expounded, and the basic principle of adaptive predictive compensation iterative guidance algorithm is summarized. Taking the direct orbital injection scenario with large thrust, large deviation of terminal program angle and meeting the constraint of terminal program angle as examples, the iterative guidance algorithm of adaptive predictive compensation under corresponding working conditions is given. The simulation results show that the algorithm has a certain correction ability for the orbital parameters and terminal program angle deviation.

For initial values of co state variables guessing problem in the indirect optimization of the low thrust trajectory with variable specific impulse, a method based on machine learning is proposed to estimate the initial values of co state variables with high accuracy and efficiency. Firstly, based on the continuation of the nominal optimal trajectory, a data set generation method under the condition of high perturbation upper limit of the state variable boundary value is established and the influence of the upper limit of the perturbation on solving efficiency is analyzed. Then, an artificial neural network (ANN) mapping relationship based on the combined inputs of position, velocity, the orbital elements and the modified equinoctial elements is constructed. The neural network structure is analyzed and optimized. The proposed method is applied to the scenarios of low thrust transfers in deep space exploration. Simulation results indicate that the method effectively improves the solution convergence rate compared with the data set generation method with direct perturbation of nominal trajectory and the artificial neural network mapping method with a single form of states input, and it can efficiently and accurately estimate the initial values of co state variables to achieve fast trajectory optimization.

In view of the serious problems of aerodynamic heat concentration, accumulation and time dependence that faced by hypersonic vehicles, the heat dissipation technologies of passive thermal materials, structures and active ones, the heat transport technologies of high thermal conductivity materials, heat pipes and working fluid convection, and the heat conversion technologies of regeneration and thermoelectric conversion are discussed. For above technologies, the research status and application cases in hypersonic vehicles are presented, and the limitations in hypersonic aerodynamic heating are then pointed out. Finally, the development trend of aerodynamic heat dissipation, transport and conversion technologies for hypersonic vehicles is prospected.