Based on the platform definition principles of “Communication Bus+Hardware Redundancy+Structural+Software Architecture”, a new highly reliable rocket-borne integration electronic platform is proposed. Firstly, the Aerospace Time-Triggered Ethernet (ATTE) bus is used outside among multiple rocket-borne electronic equipments and the GLINK bus is used inside for high-speed interconnection within devices. Secondly, a “master-control three-redundant and execution two-redundant” hardware platform based on 6U-VPX modular is built and a rocket cloud real-time partition operating system is also established. Thirdly, the reliability of the new platform is improved by bus communication and control circuit. Fourthly, the integrated high power thermal design and mass mechanical design are proposed and a product prototype based on the new platform is developed. In the end, the superiority of the new platform is proved through performance analysis and test results presentation.

Regarding the significant impact of code generation techniques based on large language models （LLMs） on software productivity and their broad application prospects to the aerospace field，the latest research progress on this kind of technology is reviewed from three aspects: problem background and definition，typical technologies and their potential application scenarios in the aerospace domain，and application evaluation methods，with the aim of providing guidance and insights for related research on code generation techniques in the aerospace domain. Firstly，the basic capabilities of LLMs are discussed on code generation according to the features of code generation problem definition and LLMs structures. Then，the main methods for code generation are elaborated，including pre-training，instruction fine-tuning，prompt engineering and retrieval-augmented generation as well as their potential application scenarios to the aerospace field. Next，due to the perspectives of semantic similarity and validation datasets，the popular methods are reviewed for evaluating the results of LLM-based code generation techniques and their characteristics and limitations are analyzed. Finally，the challenges are presented and future improvements are proposed.

Under the background of the vigorous development of theory and application of embodied intelligence， in order to further improve the intelligence level of low altitude UAVs and expand their application boundaries， the development requirements of low altitude UAVs are focused on the context of low altitude economy， and the researches are implemented and systematically analyzed， regarding three domains in terms of the theoretical basis， key technology paths and application challenges. Firstly， the advantages and research value of embodied navigation compared with traditional navigation on semantic understanding， environment interaction and group collaboration are determined. Secondly， derived from the development of traditional simultaneous location and mapping（SLAM） to the technology evolution of visual language navigation（VLN） and visual language action（VLA） model， one special navigation technology framework for low altitude UAVs is established. Thirdly， through analysis of two typical application cases， the practical application trend of low altitude UAV in complex environment is discussed. Finally， future development directions of low altitude UAV embodied navigation are overviewed， the proposed achievement can serve as valuable references for theoretical research and industrial application to intelligent autonomous navigation.

Aiming at the stability control of a slender air defense missile under low elastic frequency and multiple constraints， a linear time-varying model predictive control method which is considered under elasticity and multiple constraints is proposed. Firstly， in order to ensure the amplitude attenuation in the mid-frequency band， the overload error integral output is used to augment the missile's linear state space equation. Under the model predictive control full state feedback strategy， the controller inherits the structure of the traditional three-loop control method. Then， a cost function is established， which is based on the criterion of ensuring the rapidity and smoothness of the missile's overload and attitude response， and the missile's stability control problem is transformed into a rolling optimization solution of model predictive control. Finally， in order to ensure the stability and elastic suppression capability of the system under elastic working conditions， a notch is inserted into series at the output end. The simulation results show that the proposed method has faster response speed， higher control accuracy and better elastic suppression ability， compared with the traditional three-loop control method.

The transfer strategies for multi-objective missions around the Earth-Moon Lagrange points are studied and a two-impulse transfer strategy that allows spacecraft to move between near-rectilinear halo orbits and distant retrograde orbits is designed. Firstly，the spacecraft's orbital dynamics model is established in the synodic frame. Then，the overall design of the transfer strategy is implemented，the relevant optimization variables are analyzed，the objective function and constraints are determined，and the transfer strategy design problem is transfered into a trajectory optimization problem. Furthermore，the feasibility of genetic algorithms and particle swarm optimization algorithms for this specific problem is verified for solving the transfer trajectory. A numerical method is presented through this research by applying genetic and particle swarm optimization algorithms to transfer strategies design of halo orbits，which focuses on recent interest in near-rectilinear halo orbits and distant retrograde orbits. The proposed optimization method has ability of effectively resolving the orbital transfer design problem without prior information and can be applied to various transfer scenarios.

The development of model-based systems engineering (MBSE) and its application in aerospace control are reviewed. Firstly, the definition and development process of MBSE are introduced, and the three pillars of MBSE are introduced, including modeling language, modeling method and modeling tool, and the characteristics of mainstream modeling tools are compared. Secondly, the existing researches on the application of MBSE in aerospace control are reviewed from three aspects: control system architecture design, control system reliability and safety analysis, and control system verification and validation. Finally, the application prospect of MBSE in aerospace control is presented by focusing on multi-domain co-simulation, control system digital twin and intelligent design and optimization of control system.

Based on the application of interactive sensing space teleoperation in space on-orbit service, the engineering cases of interactive teleoperation in space technology at home and abroad are firstly described, and the main technical components, core difficulties, current mainstream technology and research progress of interactive sensing space teleoperation robot are investigated. The necessity and urgency of interactive perception teleoperation are discussed, and the application of interactive perception teleoperation on-orbit service and the future research direction are discussed on the basis of that, and technical route based on the visual feedback, force feedback and local autonomous smart + auxiliary mechanical arm assembly+ path planning and motion planning is proposed.

Anomaly detection of spacecraft telemetry data by supervised machine learning is a challenging task due to the lack of priori knowledge. A spacecraft signal intelligent anomaly detection algorithm integrating with attention mechanism is proposed for solution. Firstly, the long-distance characteristics of spacecraft telemetry data are captured by attention mechanism, and an instruction is provided for anomaly tracing in the attention relationship matrix. Then, the stacked auto-encoder compresses the data dimension and reassembles the input signal to obtain the error reconstruction sequence. Furthermore, the anomaly indexes of the error reconstruction sequence are marked by the window threshold method to realize the anomaly detection of the spacecraft telemetry signal. Finally, the effectiveness of the proposed algorithm in terms of improving the anomaly detection performance and interpretability of spacecraft telemetry signals is verified by using a multi-channel spacecraft telemetry signal example.

A guidance law with variable control weight is proposed，which is based on the optimal control method for intercept different types of maneuvering targets by using air-defense missile. A state equation of relative motion between missile and target in the longitudinal plane is set up，and an indicator function based on variable control weight and line of sight angular velocity constraint is designed，furthermore，the optimal guidance law related to weight coefficients is derived by using the minimum numerical principle. Simulation experiments are implemented for different types of maneuvering targets，and the results indicate that the performance of the optimal guidance approach proposed in this paper is superior to traditional proportional guidance method. The line-of-sight angular velocity convergence is fairly quick，which can form preferable reverse orbit situation. Furthermore，regarding targets under different maneuvering modes，the weight of the optimal guidance law can be adjusted to match the optimal control parameters of each maneuvering target.

Aiming at the space mission scenarios in the complex space environment, space mission planning and control methods of small satellite swarm system are proposed. The space mission modes and main process of the small satellite swarm system are studied. Swarm intelligent command and decision methods based on different modes are introduced. By optimizing the transfer orbit and mission configuration, the consumption of orbit transfer can be reduced while the effectiveness of detecting targets is improved. The swarm individuals are enabled to cooperate in space missions by introducing automatic coordinated control, which improve the accuracy of target detection and maximize performance. The simulation results show that the space mission planning and control method of the small satellite swarm system can achieve multiple rounds of precision detection on space targets. It can also solve the problem of small satellite cluster space coordinated operations, and provide the theoretical foundation and technical support for the development of larger-scale swarm design.

According to the position and attitude control problem of quadrotor unmanned aerial vehicle （UAV） with external disturbances and time-varying loads，a parameter adaptive sliding mode control method is proposed，which is based on the parameter adaptive method and sliding mode control theory.The external disturbances and time-varying loads of quadrotor UAV are estimated and compensated by using parameter adaptive method so that the quadrotor UAV can be enabled to resist the disturbances caused by changes in time-varying loads and the capability of high-precision position and attitude control can be achieved. In the end，the Lyapunov stability theory and simulation results fully verify that the proposed method can effectively degrade the adverse effects of unknown disturbances and time-varying loads on the control system.

In this paper, the fault modes of liquid rocket engine are reviewed, and the latest achievements of liquid rocket engine fault diagnosis technology at home and abroad are analyzed in recent years, including the fault diagnosis based on the models, the signal analysis and the artificial intelligence. The application progress and the diagnosis effect of the different kinds of fault diagnosis methods are compared, and the future development tendency of fault diagnosis methods for liquid rocket engine is prospected.

The evolutionary trajectory of aerospace control technology is focused from classical control and modern control to agent-featured intelligent control technology 3.0. The agent-featured intelligent control technology 3.0 is represented and known as the key indicators of future aerospace control systems. The key attributes of control technology 3.0 labelled by "learning while flying"， "lifelong learning" and the "new-generation system architecture" are pointed to elucidate. The critical technologies of "intelligence empowerment"， "functional augmentation" and "information capability enhancement" are subjected to in-depth analysis. On this basis， the exploration of future aerospace intelligent control development is oriented to typical scenarios such as large model empowerment and software factories. Consequently， prospective thoughts on the development of advanced intelligent aerospace control are expanded upon the matter.

As a critical factor affecting safety-critical systems， it has been drawn increasingly attention to software safety issues. Based on engineering practices in aerospace embedded software testing and verification， the software safety requirements are taken as a clue and typical safety problems are focused in this paper. The two dimensions are introduced by the formal verification of source code safety properties and the automated testing of software safety requirements which analyze and summary key technologies， including special safety analysis， source code static analysis， source code model checking， fault-model-based safety testing and keyword-driven automated testing. A comprehensive technical solution for aerospace embedded software safety verification is proposed， and an independent controllable software assurance support platform and tools are developed to systematically enhance the trustworthy assurance capabilities of aerospace embedded software.

A controller design method is proposed for the attitude control of overactuated satellites under interference, reaction wheel fault, actuator misalignment and saturation. Firstly, the attitude equation of overactuated satellite is established and the mathematical descriptions of reaction wheel installation deviation, fault and saturation are introduced. Then, the sliding mode controller under external uncertain interference and reaction wheel actuator misalignment is designed, and the dynamic control allocation is applied for solving the reaction wheel fault of overactuated satellite. Finally, when the reaction wheel is saturated, the Null-space method is used to keep the reaction wheel torque command within the feasible range. The designed control method avoids the complex controller design process, and the controller is simpler, more adaptable, easier to understand and easier to be applied in engineering.

Aiming at the problem of instability of traditional Kalman filter under complex and high dynamic conditions, a Sage-Husa adaptive filtering algorithm based on improved adjustment factor is proposed. The GPS three-dimensional speed information of this algorithm is used to optimize the adjustment factors in the filter abnormality judgment conditions in real time, the noise covariance matrix is dynamically estimated and the adaptability of the integrated navigation system is improved. The simulation results show that the improved Sage-Husa adaptive filtering algorithm has a significantly reduction of calculation amount. By comparing with the traditional Kalman filter, it can maintain higher adaptability and significantly improves the positioning precision.

Regarding the stringent requirements of information confidentiality review in the aerospace field, current manual screening methods are suffering from high costs and insufficient accuracy of keyword matching. An enhanced review framework integrated with large language models is proposed to improve the efficiency and accuracy of confidential information screening. Initially, the characteristics of confidential information are analyzed in the aerospace sector, an architecture that enhances the auditing performance of large language models is introduced in this study, which is combined with dynamic domain-specific expert system prompts to enhance the granularity and accuracy of reviews among multiple perspectives including technical and business confidentiality. By introducing a dynamic system prompt mechanism, the framework is effectively combined the semantic understanding capabilities of large language models with the real-time updating of keywords. Additionally, in order to prevent excessive auditing by the large language model, a hybrid cross-training strategy is developed, which significantly improves the recall rate of confidential information that reaches by 96%. Experiments on a self-developed high quality test set of 1000 entries demonstrates that the proposed method outperforms global open-source large language models by 18% in aerospace classified information inspection tasks.

A method for designing appointed-time prescribed performance controller with extended state observer is proposed in this paper for the hypersonic flight vehicle longitudinal attitude systems with parameters perturbation and time-varying disturbance. Firstly, a novel appointed-time prescribed performance function is designed to limit the transient and steady-state performance of command tracking errors, and compared with the traditional function, the novel method can guarantee the errors convergence to the set stability precision at the appointed time. Furthermore, the error-transform function is applied to un-limited boundary transformed from the tracking errors which can ensure satisfaction of the constraint condition by means of controlling the transformed errors. Then, the virtual control law of attitude subsystem and the actual control law of angle velocity subsystem are designed, which are based on backstopping method, and the lumped disturbances are estimated by the finite-time extended state observer, the command filter is applied to avoiding the “explosion of terms” problem in the control law design process. Ultimately, the comparative simulations with parametric uncertainties and time-varying disturbance are performed to demonstrate that the performance constraints of tracking errors can be effectively satisfied by using the proposed method.

The requirements of the flexibility of aerospace control system are extensively analyzed in this paper，and the challenges are deeply discussed，which are concentrated on the system level and the device level. The design concept of the flexibility of the system level and the device level is proposed in innovation，and the key technical path of the flexibility of the system level and the device level is further elaborated，such as rapid assembly and interoperability management of system software and hardware，multi-level communication interconnection，flexible integrated conformal layout and analysis，and verification of the adaptability of flexible electronics to the aerospace environment，and the development trend of the flexibility of the aerospace control system is finally visioned in terms of integrating innovative technologies，strengthening cross domain cooperation，establishing standards and specifications，and expanding and deepening applications.

A design method for an active disturbance rejection controller based on complementary sliding mode is proposed to address the position and attitude control problem during the point cloud data collection process of quadrotor unmanned aerial vehicle （UAV） that carries a light detection and ranging （LiDAR） for power transmission lines. Regarding the problems of strong coupling，non-linearity，and external disturbance effects under the complex environment of quadrotor UAV，a finite time convergent extended state observer is adopted to estimate the state and lumped disturbances of the quadrotor UAV dynamic system，which introduces the observed lumped disturbances into the active disturbance rejection controller for feedforward compensation. At the same time，complementary sliding mode manifolds are established，and the exponential power function and the integral form of sign function are used to ensure the continuity of the active disturbance rejection controller. Finally，a rigorous proof of the asymptotic convergence of position and attitude tracking errors is provided，which is based on the Lyapunov analysis method，and the simulation results show that the proposed method has higher control precision and can effectively suppress different forms of external time-varying disturbances.

Aiming at the shortcomings of traditional artificial potential field (APF) for solving obstacle avoidance problems, such as local minimum value and unreachable target, an optimal consensus control method taking advantage of obstacle avoidance effect and combination with APF is proposed. Based on the double integrator UAVs formation model with fixed undirected communication topology, the optimal consensus control protocol with obstacle avoidance cost function is introduced to solve the limitation of APF obstacle avoidance. At the same time, the formation control of multiple UAVs is developed to make the consensus performance index, control consumption performance index and obstacle avoidance performance index of UAVs formation control system reach the optimal solution. In addition, by establishing a virtual repulsion potential field for each UAVs, the collisions among the UAVs during the obstacle avoidance process are prevented. The simulation results show that compared with the non-optimal consistency control of the improved APF, the optimal consistency control of the improved APF proposed can shorten the task time by 32 % and can greatly maintain the integrity of the formation and reduce the consistency consumption and control loss caused by obstacle avoidance.

A multi-channel and end-to-end attitude control method based on deep reinforcement learning is proposed for hypersonic morphing vehicle in the presence of situations by external disturbance and model uncertainty. Firstly, the attitude control model of hypersonic morphing vehicle is established. Secondly, the problem of vehicle attitude control is transformed into a Markov decision process. Furthermore, the training of the agent is implemented, which is based on the twin delayed deep deterministic policy gradient algorithm, and the end-to-end generated flight control instructions are deployed online. Finally, the proposed method's effectiveness and generalizability are confirmed through both basic performance and adaptive simulations.

The anti-peak circuit of the timing attitude control system of the launch vehicle adopts a "diode+resistor" circuit and a "resistor+diode+voltage regulator diode" circuit. MULTISIM is used for simulation and experimental verification. It is found that the theoretical solenoid valve shutdown time becomes shorter when anti-peak resistance grows larger，and the voltage regulator diode voltage goes larger，separately. Regarding the same electromagnetic valve shutdown time index requirements，a lower reverse voltage produced by using the method of increasing the voltage regulator than using the method of increasing the resistance； Due to the precisely controlling of the flows of fuel and gas that are ensured to be delivered to the engine in the predetermined ratio and time，the boost valve，relief valve and auxiliary power solenoid valve.play an important role of adjusting regulating pressure and protecting safety in the attitude control system，which maintain the stability of the launch vehicle's attitude and flight safety. Therefore，their shutdown time and anti-peak voltage need to be precisely controlled.

Regarding the ascent trajectory of horizontal take-off and landing reusable launch vehicles，a simplex-pseudospectral loop optimization algorithm is proposed. By optimizing the control parameters of the horizontal run section，the initial value of the ascent section is adaptively generated，and taking a certain horizontal take-off and landing reusable launch vehicle as an example，the trajectory optimization design simulation of the launch vehicle from taking off to climbing to the handover point is completed by using the simplex-pseudospectral double-loop optimization algorithm，which verifies the feasibility and effectiveness of the proposed method. On this basis，the influences of engine thrust and sensitive parameters of the flight trajectory on air-breathing mode flight profile and remaining mass are studied. At the same time，a design method of air-breathing mode power compensation is proposed. By comparing with the conventional design method，fuel consumption is further reduced and the carrying capacity of the reusable launch vehicle is improved.

By starting from the model of a three-loop overload pilot, a unified open-loop transmission function, closed-loop transmission function and closed-loop characteristic equation of the system are derived, and then the relationship between the system control gain and the closed-loop pole, open-loop cut-off frequency is determined according to the closed-loop transmission function. The objective function of minimizing the equivalent time constant of the closed-loop system is given by introducing the rudder yaw rate constraint, the open-loop cut-off frequency constraint, the stability margin index constraint and the high-frequency component constraint. The typical parameter optimization paradigm under constraint conditions is formed. Through using the optimal solution of the system, the precise design of the open-loop cut-off frequency and phase margin of the system is realized, and an engineering design method of pole placement is formed. The effectiveness of the method is verified by an example.

The navigation error of the GNSS/SINS integrated system can often rapidly be expanded due to the significant and time-varying errors inherent to the strapdown inertial navigation system (SINS) during the global navigation satellite system (GNSS) outages. In order to improve the navigation accuracy, a loosely coupled GNSS/SINS/GC/VL integrated navigation system is proposed, which is based on Kalman filtering (KF). New measurements are provided by the heading and speed information, and the SINS can be corrected finally. The simulation results show that the positioning error of the GNSS/SINS integrated navigation system assisted by a gyroscope and a vialog is smaller than that of the traditional GNSS/SINS loosely combination when the GNSS is temporarily disabled.

In order to achieve rapid and accurate recognition of combat intent in complex battlefield environments with fewer air combat data samples, a combat intent recognition model based on meta-metric learning framework is proposed.Regarding received small sample data during air combat intent recognition, a two-way gated recurrent unit network based on the air combat temporal data are developed to realize effective feature extraction, and the attention mechanism is introduced for promoting the network to fully extract the temporal core features of the air combat data when facing the small sample data are merely available for obtaining the inter-class differences which finally achieve a fairly higher recognition accuracy and recognition speed.Simulation results show that the model proposed in this paper has better accuracy and real-time performance for air combat target intent recognition, especially in the case of small sample data.

A hybrid control method combining feed-forward compensation with closed-loop feedback based on the target relative motion trajectory is proposed in this paper, which is aiming at significantly improving the satellite dynamic pointing tracking control precision. Firstly, the dynamic error coefficient method is adopted to analyze the attitude tracking errors, and power transfer function is established to analyze attitude angular velocity errors caused by sensor noise. Next, a feed-forward compensation control strategy calculating the desired line-of-sight angular velocity and angular acceleration by estimation of the target relative motion is proposed, which resolves the challenge of space-borne detection equipment that can only measure target pointing deviations and doesn’t directly perform hybrid control. Finally, the system stability and attitude tracking performance are validated through mathematical simulations, and ground-based air-bearing experiments are implemented to test the controller's tracking performance. This attitude controller reaches high-precision during dynamic tracking by different input commands without altering the closed-loop feedback bandwidth.

Aiming at the path optimization problem when the formation of multi-quadrotor UAV remains unchanged, the multi-quadrotor UAV formation is regarded as a virtual rigid body based on the graph theory method in the flight process, and the UAVs in the formation are treated as the constraints of the leader quadrotor UAV. In the optimization process, only the maximum turning radius constraints, formation transformation time constraints and transformed constraints of the leader quadrotor UAV are considered, and the minimum energy required for formation flight is taken as the optimization goal, the track optimization problem of multi quadrotor UAV formation arriving at the target at fixed time is resolved. In this paper, the flight path optimization of the leader quadrotor UAV is implemented based on Gauss pseudo spectrum method, which is transformed into a nonlinear programming problem. The simulation results show that a smooth flight path can be obtained by using the algorithm proposed in this paper, which meets the constraints of timing arrival at the destination, multi UAV performance and environment; the obstacles can be safely bypassed by using obtained track which can improve the survivability of UAV formation and has certain engineering application value.

A combined navigation positioning method based on improved radial basis function neural network （RBF） assisted volume Kalman filter （CKF） is proposed to resolve reduced precision of integrated navigation positioning caused by global navigation positioning system （GNSS） signal interruption in complex environments such as tunnels， urban roads and canyons. Firstly， the integrated navigation fusion data is preprocessed by using kernel principal component analysis （KPCA） combined with K-means++ clustering model to make its distribution representative； Secondly， the orthogonal least squares （OLS） method is used to determine the number and center values of hidden layer neurons in the RBF neural network， and the trust region constrained Gaussian-Newton （TR-CGN） algorithm is used to optimize its parameters； Finally， when the GNSS signal loses lock， the trained improved RBF neural network is used to assist in nonlinear CKF filtering for error compensation. The experimental results show that the average positioning error is reduced by 17.87% through application of this method without increasing hardware costs which is compared to the way of using the autonomous driving collaborative positioning system； Compared with the average positioning error assisted by KPCA-RBF， the reduction based on the proposed method takes advantage of 54.37%， which indicates that the adaptability and robustness of the integrated navigation positioning system are effectively enhanced within complex environments.

The algorithm of the integrated celestial navigation combined accelerometers with X-ray pulsar sensor is researched. Firstly，the inertial navigation algorithm is provided for spacecraft based on the heliocentric inertial reference frame，and the accelerometer drift is estimated by the phase difference of the inertial navigation and X-ray pulsar sensor in pulsar direction based on PI filter. Then，the algorithm of the integrated celestial navigation combined X-ray pulsar sensor with accelerometers based on the time of arrival （TOA） of the pulsar pulse is proved. Lastly，simulation results show that the algorithm of the integrated celestial navigation is effective.

In order to achieve formation flight for unpowered aerial vehicles and ensure the convergence of formation errors in three-dimensional space， a formation control method based on consensus theory is proposed. Firstly， by taking into account the formation group's characteristics of only having negative acceleration， the consensus theory is modified， and a longitudinal control method suitable for unpowered aerial vehicles is introduced. Next， a bank angle distribution and flipping strategy is involved， and under the condition that the lift is prioritized to satisfy high-directional control requirements， the bank angle flips by the lateral error corridor， thereby both high-directional and lateral errors are simultaneously reduced. Finally， simulations are conducted to verify the adaptability of the proposed method to various formation sizes and communication topologies. The simulation results demonstrate that， within the given range of initial conditions， the proposed method can effectively control the formation in different initial states. Moreover， the initial state of the cluster has significantly impacts on formation time and cluster speed loss and average formation time and lower average cluster speed have less loss while there are clusters with more directed edges in the topology structure.

Regarding the attitude tracking control of spacecraft,a second-order mathematical model of attitude control system based on error quaternion is established. Based on modern control theory,a state feedback controller based on error quaternion is designed to configure the poles of the attitude control system and realize the attitude stable tracking of spacecraft. The simulation results show that the state feedback controller can achieve high precision attitude tracking control of micro spacecraft.

A predictive control method for electromagnetic switching valve is proposed for attitude control of spacecraft. Based on the predicted control time and nozzle layout，the ignition logic of electromagnetic valve is designed and the force of the nozzle is utilized to cancel out each other，so that the control torque action time can be adjusted arbitrarily during the control cycle. The simulation analysis shows that compared with conventional pulse width modulation techniques，the predictive control method allows the solenoid valve to achieve precise attitude control without being limited to the minimum continuous opening time.

Multi-agent systems are widely used in many practical fields, including robotics, distributed control, and multiplayer games. Many complex tasks in these fields can not be solved by predefined agent behaviors, and communication based multi-agent reinforcement learning (MARL) technology is one of the effective methods to deal with these challenges. There are two core research issues in this field: 1) How to establish an effective multi-agent communication mechanism to improve the overall performance of the multi-agent system; 2) In the scenario under limited bandwidth, how to design an efficient communication schedule to compress redundant information in the communication process. The literature is summarized for dealing with these two core issues and some representative works are focused, then its application prospects in the aerospace field is presented, and finally the points of this research are shown.

The sequential convex optimization method applied to the powered vehicle entry trajectory optimization is researched in this paper. Firstly, in order to solve the problem of high coupling and non-linearity of control variables in the original optimization, the linear state equation about control variables is obtained by choosing new control variables due to the relationship between original and new control variables established. Secondly, the nonlinear dynamic equations, performance index and constraints on the path and control variables in the original optimization occurrence are relaxed and linearized. Next, aiming at ensuring the validity of relaxation and linearization, the trust-region constraint is applied to the state variables, and the integral term of velocity azimuth is added to the performance index. Furthermore, the original problem is converted to a convex optimization problem with discretization technique. Finally, the algorithm is proven to be effective by numerical simulation. Under the original nonlinear constraints satisfied, the proposed algorithm is proven to be reasonable with high solving accuracy for the powered vehicle entry trajectory optimization, and the optimized solution can be used as a feasible approach to the original problem in the range of defined precision.

Aiming at adapting to the digital and intelligent development of the electrical equipments of new generation launch vehicle, the multi-task design method of fly control software is introduced in this paper. The tasks are designed such as fly control task, data management task and correct cutoff task, and the corresponding execution priorities are set, and the synchronous operation method of fly control task in three redundant processors is proposed. The constraint requirement for multi-task sharing critical resource in one control cycle is proposed as a reliable margin index to control synchronization operation of fly control task in the three processors. The multi-tasks designed have been validated in flight experiments of the new medium launch vehicles.

Aiming at the problem of coordinated trajectory optimization between the boost and return sections of the RLV, a trajectory evaluation and decision-making program and a new optimized guidance law are proposed. Firstly, based on the numerical integration of ballistics and the mechanical energy, the carrying and return capability evaluation and decision-making plan for the thrust loss fault of the RLV booster stage are designed, and the trajectory decision interval with the best benefit is obtained. Then, PSO is used to optimize the ZEM/ZEV guidance law. After the thrust of the booster phase is reduced, the shutdown and landing time are optimized to promote the orbiting and return capabilities. After the payload and booster phases are separated, the secondary ignition height and the guidance law parameters are optimized to meet the maximum heat flow constraint. After the thrust is further reduced, the landing time and guidance parameters are finely optimized to achieve a precise soft landing. The simulation results show that the scheme proposed in this paper improves the RLV's orbiting and landing ability under the condition of engine thrust loss and the algorithm has benefits for simple structure and low burden computation.

Aiming at the problem of easily falling into local optimal solution by conventional particle swarm optimization algorithm, three-dimensional path planning of unmanned aerial vehicle (UAV) is developed by applying the quantum particle swarm optimization algorithm (QPSO). The flight performance constraint conditions of UAV are analyzed in detail. In order to reduce the computing complexity of algorithm and increase the plan efficiency, the height plan of three-dimensional path planning problem is adopted by the direct setting scheme, namely, the height of every waypoint is set between the maximum and the minimum. Thus, three-dimensional path planning problem is simplified as two-dimensional path planning problem. The linear increase adjustment scheme of compression-expansion factor, cost function and path planning flowchart are designed. The simulation experiments of three dimensional path planning of UAV are implemented by adopting respectively the quantum particle swarm optimization algorithm and the conventional particle swarm optimization algorithm. The contrast of simulation result shows that the designed QPSO algorithm has higher global search ability and search precision than the conventional particle swarm optimization algorithm.

On account of the issue that the communication network of multi-flight vehicles is vulnerable to be attacked by false data injection in the disturbance environment， a collaborative guidance strategy against high-speed targets that can autonomously identify and suppress the fault link is proposed. By designing the coordinated guidance method based on relative distance， when only the leader flight vehicle can get the target movement information， the flight vehicles can hit the maneuvering target at the specified time. The radial basis network is used to estimate the unknown items for the design of cooperative guidance law. The trust coefficient is introduced to identify the false data injection attacks on the communication network， which guarantees the information assurance for self-suppression of the multiple flight vehicle systems under the network attacks.The numerical simulation result indicates that the leader and followers multi-vehicle collaborative impact on the high-speed target simultaneously can be controlled and implemented by using the proposed method under the false data injection attacks.