Electromagnetic scattering data is essential for the recognition of targets. However， due to issues such as high cost and poor repeatability of experimental measurements， the quantity of measured electromagnetic scattering data of targets is very limited. A dynamic electromagnetic scattering data simulation method for air targets was studied based on the N-point model with hidden points removed and electromagnetic calculation data interpolation. Additionally， a dynamic electromagnetic scattering data simulation system for air targets was designed. This system integrated electromagnetic scattering simulation with actual flight scenes and supported scene definition and expansion of 3D models for air targets. Simulation data and imaging results of aircraft and cruise missiles were analyzed. The results show that the simulation method is correct， and the system is effective. The system can support the research on the recognition of air targets in actual scenes.

Training， testing， and evaluating radar intelligent recognition （RIR） methods usually require the construction of large datasets. Acquiring effective datasets efficiently is an urgent issue to be solved. The application scenarios of the RIR system for aerospace targets were analyzed first， and the construction idea of the RIR simulation system （RIRSS） for aerospace targets was given according to application demands. Then， the modular and component-based design methods were utilized to design the RIRSS framework for aerospace targets， and an intelligent recognition simulation system for aerospace targets was constructed， which could simulate the electromagnetic characteristics and dynamic echo of aerospace targets quickly and efficiently， with a scalable and reconfigurable capability. Simulation results and preliminary application show that this system can be used in the test and evaluation of the RIR method for aerospace targets in various scenarios.

As radar interference technology develops toward full polarization， it is crucial to clarify the mechanism of polarization jamming for the development of polarization jamming technology. This paper optimizes the multi-channel receiving and processing model of radar side-lobe cancellation by introducing a polarization matching coefficient. It also deduces the mathematical model of radar side-lobe interference cancellation ratio under variable polarization jamming conditions. In addition， partial mathematical simulation verification and actual test results are provided. The research contents can provide a theoretical reference for quantitatively analyzing the jamming mechanism of variable polarization interference on radar side-lobe cancellation.

In order to achieve high-precision trajectory tracking of hypersonic vehicles， a trajectory tracking algorithm for highly maneuverable targets combining moving horizon estimation and an interactive multi-model （IMM） algorithm was proposed. Firstly， the motion model and measurement model of the glide segment of the hypersonic vehicle under the half-velocity system were given. Then， the moving horizon estimation method was used to transform the state estimation problem into a constrained optimization problem， and the physical constraints of the glide segment of the flight vehicle were fully considered. On this basis， in order to cope with the different maneuver modes of the target， a model set was established to approximate it with the help of the IMM algorithm. Finally， the algorithm was verified under unchanged and mutated maneuver modes. The results show that the new algorithm adopts parallel estimation of multiple models， and the model probability is adjusted in real time for fusion output， which can effectively avoid the mismatch of the target tracking model and significantly improve the trajectory tracking accuracy of highly maneuverable targets such as hypersonic vehicles.

Due to factors such as the limited capabilities of the actuators， one needs to generally consider the effect of constraints on both attitude and angular velocity when addressing the attitude consensus control problem of multiple unmanned aerial vehicles （UAVs）. However， the constraints on both attitude and angular velocity pose a challenge to the design of effective attitude consensus controllers for multiple UAVs. To address such an issue， this paper introduces a finite-time attitude consensus controller for multiple UAVs under state constraints including the constraints on both attitude and angular velocity. Specifically， by using tools from nonsmooth analysis and algebraic graph theory， the paper develops a class of finite-time attitude consensus control strategies. In addition， combined with the barrier Lyapunov function （BLF） technique， it constructs a novel attitude consensus tracking controller. Theoretical analysis demonstrates that， under attitude and angular velocity constraints， the proposed controller enables the attitude of all UAVs to track the desired attitude within a finite time. Notably， the proposed method offers advantages such as simplicity of structure， adaptability to user-defined constraints， and fast convergence. Simulation results indicate that the proposed controller achieves finite-time consensus tracking of the desired attitude under constraints on attitude and angular velocity.

To address the drag acceleration profile design challenge during the gliding trajectory guidance of hypersonic vehicles， this paper proposes an improved method for designing the drag acceleration profile. To enhance the gliding range of the aircraft and improve flight state parameters， the paper designs a novel drag acceleration profile in the form of a quadratic function with the reciprocal of energy as the independent variable. The profile shape is adjusted by changing the drag acceleration values at the midpoint， satisfying various constraints of hypersonic flight. Simulation results indicate that， in comparison to the traditional quadratic drag acceleration profile， the proposed profile significantly increases the maximum gliding distance and improves flight state parameters， enabling the aircraft to complete flying missions around no-fly zones.

To address the cooperative guidance problem for multi-aircraft attacking maneuvering targets， this paper initially builds a relative model in the line-of-sight frame. Subsequently， the paper decomposes the cooperative guidance issue into two sub-issues： line-of-sight angle cooperation and impact time cooperation. Distributed cooperative guidance laws are developed based on extended state observers， strategically designed in both the line-of-sight and its normal direction. Consensus analysis is conducted to demonstrate the convergence of the proposed guidance laws under directed switching topologies. Numerical simulations are then employed to further substantiate the effectiveness of the guidance laws.

With the development of unmanned military technology， unmanned short-range air combat has attracted much attention from military powers in the world. Faced with the threat of high-speed and high-maneuverability attacker missiles， traditional passive defense measures such as throwing chaffs or releasing hot flame bombs fail to ensure the safe escape of target aircraft. It is a feasible method to implement active defense by launching defender missiles to coordinate the maneuvering of target aircraft. However， due to the strong maneuverability of the attacker missile and unknown acceleration information， it is difficult to design the guidance law of cooperative target aircraft-missile. An active defense line-of-sight （LOS） guidance law based on disturbance compensation was proposed in this paper. A nonlinear disturbance observer was designed to estimate the influence of the maneuverability from the attacker missile， which was compensated for in the design of active defense LOS guidance law for the cooperation of aircraft and missile. The results of the simulation indicate that the method used in this paper can effectively defend the attacker missile with unknown maneuverability. The study in this paper thus provides a reference for the three-body attack and defense problem.

A control strategy based on disturbance compensation is devised to address the issue of stabilizing trajectory tracking for quadcopter unmanned aerial vehicles （UAVs） with unknown external disturbances. Firstly， this paper designs a PID position controller for the quadcopter UAV’s position loop and compensates for external disturbances using a disturbance observer. Secondly， the desired attitude is obtained through attitude computation， and an incremental nonlinear dynamic inversion（INDI） attitude controller with strong robust performance is designed for the quadcopter UAV’s attitude loop. Finally， simulation and comparative experiments are conducted by Simulink. Experimental results indicate that this control strategy can achieve trajectory tracking capability for quadcopter UAVs under conditions of unknown external disturbances.

When flexible spacecraft operates， disturbances such as the swaying of liquid fuel and gravity gradients cause the spacecraft system to exhibit strong nonlinearity and coupling characteristics. Thus， controlling its attitude deflection has always been a challenging problem. To solve this issue， this paper designs a H_∞ state feedback controller. The integrated disturbance term in the dynamic model of the flexible spacecraft is redefined， and combined with the kinematic model， the mathematical expression of the flexible spacecraft is formulated. The mathematical model of the flexible spacecraft is transformed into an H_{\mathrm{\infty }} state feedback control mathematical model. The theoretical applicability of the controller is demonstrated by mathematical theory. The mathematical model of the flexible spacecraft under H_{\mathrm{\infty }} state feedback control is simulated by simulation software. The results show that the designed H_{\mathrm{\infty }} state feedback controller can effectively achieve attitude stabilization and vibration suppression of flexible spacecraft， showing practical value.

The notch filter is usually used to suppress the elastic vibration frequency of the missile body when the missile stability control is designed， so as to ensure the elastic stability of the missile body in the control system. The basic principle of the notch filter was introduced， and an improved pre-distortion bilinear transformation approach was proposed to address the frequency distortion problem caused by the discretization design of the notch filter. Compensation for the frequency distortion was achieved by adjusting the damping magnitude without changing the damping ratio of the notch filter. Compared with the traditional discretization method， the proposed method not only compensates for distortion frequency but also ensures that the notch width and phase characteristics are the same as those in the continuous domain， and the proposed method has the advantages of simple operation and strong adaptability.

Multi-agent reinforcement learning algorithms fail to form effective collaborative policy under partially observable conditions. In view of this problem， a policy transfer reinforcement learning method based on centralized training and decentralized execution （CTDE） paradigm was proposed. Firstly， under global observation， the teacher module was trained to explore good collaborative policy. Then， under partially observable conditions， the student module was trained online with the expectation of maximizing cumulative returns as the objective function， and at the same time， policy distillation techniques were used to transfer policy from the teacher module and adaptively adjust the proportion of teacher policy affecting student policy. Finally， the proposed method was verified by simulation in multiple map scenarios. The experimental results show that under partially observable conditions， the success rate of student modules is higher than that of the baseline algorithms. The research results can be applied to multi-agent collaborative tasks， improving the collaborative performance of agents in decentralized execution.

In view of the problem of multi-missile interception of atmospheric high-speed maneuvering targets， this paper proposed a multi-missile interception decision method based on footprint prediction. Firstly， based on the maneuvering ability analysis and curve fitting method of the interceptor， the analytical model of its footprint was established， and the boundary of the footprint of the interceptor was generated with the given launch point and predicted interception point. Secondly， combined with the fast footprint prediction method of the offensive， the multi-missile interception decision-making method of the high-speed maneuvering target was transformed into the optimization problem of the coverage of the offensive and defensive footprint， and the optimization algorithm was designed to solve the multi-missile interception strategy， which used the least interceptors to cover the maximum range of the footprint of the offensive. Finally， the effectiveness of the proposed method was verified by numerical simulation.

Directional warhead technology is a new killing technology that uses target miss direction information to change the blasting direction through the change of missile body or the logic control of warhead initiation to achieve the maximum damage effect. It is also one of the key promising technologies for the future new generation of air-defense missiles to achieve capability leaping. The overall design problems of the aimed killing air-defense missile equipped with a directional warhead are studied. Firstly， a prediction method of miss information that compensates the missile acceleration for aimed killing air-defense missiles is proposed. The demand for acquiring miss information in advance is met. Secondly， the distributing regularity of the predicted impacting point and the formation mechanism of fuzzy prediction are studied， which provides theoretical support for solving the fuzzy problem. Thirdly， the aiming accuracy improvement methods for small miss distance encounter cases are studied. Finally， the simulations taking a certain type of aimed killing air-defense missile as examples are conducted.

Aiming at the temperature control problem of the hypersonic vehicle transpiration cooling system， this paper proposes an active disturbance rejection controller （ADRC） to adjust the temperature of the porous medium on the vehicle wall based on the one-dimensional fixed boundary sweating cooling model， whose effectiveness and advantages are verified by a numerical simulation. The controller does not rely on the precise mathematical model of the temperature field of the porous medium. The heat flow disturbance is suppressed by extracting and compensating disturbance information from the input and output data of the system. The simulation results show that the ADRC designed for the transpiration cooling system can quickly track the reference temperature. Compared with the traditional PID control， the temperature response under ADRC has no overshoot. In addition， when external heat flow interference occurs， the ADRC has strong robustness and adaptability， which can provide a certain reference for the engineering application of transpiration cooling control systems.

There is a big difference between the turning control technology for four rocket pulse engines and other turning control technologies for vertical soft launched missiles. In view of this problem， the turning segment line motion equation， the attitude motion equation， and the turning information equation of the missile were established in this paper. The turning time sequence was designed， and a turning control strategy was designed by introducing the prediction model and the corresponding criterion. Based on the strategy， the parameter matching research was carried out. Finally， a large range of adjustment of the missile axis was realized by a simple device. A simulation example was given to verify the effectiveness of the proposed parameter matching relationship and the turning control strategy.

Miniature air launched decoys （MALD） can trick ground air defense radar into turning on and consume air defense ammunition， significantly reducing the effectiveness of air defense operations and improving aircraft formation penetration capability. After summarizing the development of MALDs， this paper analyzes the target characteristics of MALD and constructs typical operational scenarios. The influence of MALD on the detection and tracking performance and the interception efficiency of guidance radar is analyzed. The influence of long-range deception and closed jamming on guidance radar by MALD are studied through theoretical analysis and dynamic simulation. The influences of several factors on aircraft formation penetration efficiency are investigated based on queuing theory. The research conclusion can provide a theoretical reference for MALD operation.

Driven by the increasing intelligence of potential threats and the continuous progress of current intelligent technology， the air and space defense combat system of systems （SoS） is not a linear superposition and mechanical stacking of equipment and technology but a comprehensive intelligent agent that organically integrates， dynamically adapts， and continuously evolves various combat elements. On the basis of analyzing the characteristics of intelligent air and space defense combat SoS， this paper innovated the intelligent design paradigm and concept， proposed a SoS architecture design method based on intelligent agent networks， and explored the key technologies of intelligent empowerment architecture design from three aspects： force nodes， force relationships， and adaptive mechanisms. This method provides an intelligent method reference for the top-level design of air and space defense forces， which helps to improve the intelligence and networking level of the construction and application of air and space defense combat SoS.

Threats often have the characteristics of dynamic evolution with the development of bilateral confrontation. Traditional threat assessment methods are more based on static threats and lack of prediction of dynamic threats. To solve this problem， this paper proposes a threat assessment method for aerial targets under confrontational conditions. Setting the red side as the attacking side and the blueside as the defending side. The reinforcement learning model is established with the enemy target as the agent， and its state space， action space， transition function and reward function are designed. The threat assessment model is established， the threat element index is established， and the threat assessment method is designed. The model is trained， and the trained model can predict the enemy aerial target threat according to the confrontation situation. Through test and analysis， the method is more reasonable for threat assessment of enemy aerial targets under confrontation conditions.

The finite element analysis software ABAQUS is used to analyze the buckling of solid rocket motor shell under external pressure. By comparing the theoretical formula calculation results with the finite element calculation results， the error between the finite element calculation results and Mises formula calculation results is within 2.7% when the length-diameter ratio of the light shell is greater than 8， which verifies the accuracy of the finite element calculation method. The buckling performance of shells with different centering parts is analyzed by finite element method. It can be seen that compared with increasing the axial length of centering parts， increasing the thickness of centering parts can improve the buckling resistance of shells more obviously. The closer the centering position is to the middle of the shell， the better the buckling resistance of the shell is. In this paper， under the size constraint of centering parts， the critical instability pressure increases by 36.1% from one centering part in the middle to three centering parts uniformly distributed.

According to the high difficulty and risk in organizing the operational command training of carrier-based aircraft equipped with multiple arms， combined with the advantages of simulation training economy and safety， the carrier-based aircraft operational command training system is researched and designed，the overall frame structure of the carrier-based flight simulation training system is built， the technical principle is described，the function of each subsystem is introduced. The functions of "back to back" operational planning， multi-level force command and control， access to command information system， multi-dimensional situation display， confrontation effect evaluation and other auxiliary decision support are realized. Two application modes， "human-in-the-loop" and "human-out-of-the-loop"， are established， and the key technologies are analyzed， such as the use of injective extension technology to support the high-performance parallel simulation engine driver， the joint middleware technology based on interface programming and dynamic QoS， and the use of code reuse to achieve the integration of the engineering numerical model encapsulation.

Changing depth by strong movement to avoided torpedo terminal attack trajectory is one of the methods of submarine avoiding torpedo attack， and this method is also the final defense measure of submarine avoiding torpedo attack. The feasibility and effectiveness of this evasion method can provide reference for submarine commanders to scientifically and reasonably maneuver the submarine to evade torpedo attacks， which has very important theoretical research significance and military application value for improving the submarine's vitality and combat effectiveness. Based on the theoretical analysis of the basic principle of the strong maneuver evasion scheme and the effect of different maneuver modes， and the modeling simulation calculation of the relative motion situation of the submarine and the torpedo， the paper verifies the effect of the submarine's strong maneuver by changing depth to evade the torpedo attack. Simulation shows that， within a certain distance， the high-speed maneuvering submarine uses high-pressure air to blow away the water in the main ballast water tank， and at the same time adopts the upward floating large rudder horn to make the submarine large tail incline high-speed upward floating to the surface to avoid the torpedo end attack trajectory， and then quickly dives to the shallow water layer to complete the avoidance of torpedo attack， this tactical maneuvering evasion measures are theoretically feasible， but the timing of this program should be considered and analyzed fully.

Aiming at the problem that radar is easy to be damaged when being attacked by HPM weapons， this paper theoretically analyzes the relationship between the farthest protection boundary to antenna gain and receiving front-end limiter’s capability， and compares the capability of reflector radar and active phased array radar against front door coupling attack from the perspective of spatial filtering. The analysis shows that only when the HPM weapon is near the main lobe range of the reflector radar antenna， its front door coupling attack effect is stronger than that of the active phased array radar； on the contrary， it is weaker than active phased array radar. Because the main beam of the reflector antenna radar is very narrow， the attack time window is very short， so the reflector antenna radar has stronger protection ability when facing HPM weapons.

Aiming at the problems of single function， poor versatility， cumbersome loading operation process and long time in the process of missile transfer and loading， a technical scheme of multi-functional missile transport vehicle is proposed.The scheme takes the design concept of generalization and structural function integration， integrating the transport function and auxiliary erection function of the transport vehicle.The horizontal and vertical attitude conversion functions of the missile are integrated under the premise of meeting the road transportation functions of various types of missiles in Haitong.The limitation of the loading method of missile on the ship is broken.The problem of complicated lifting procedure in the process of missile loading on the ship is solved， the function of directly lifting the vertical missile-in-container on the transport vehicle is achieved， and the time of missile-in-container loading ship is shorten. The scheme simplifies the process of shipborne missile transfer and loading， and the efficiency of equipment use is improved.

Due to the mismatch between the tracking model and the real motion state of the target， the estimation accuracy of the high order motion feature of the target is poor in single-station radar.In this paper， the estimation accuracy of high order motion feature of the target is improved from the perspective of radar networking and radial velocity augmentation measurement. The sequential unscented Kalman filter algorithm is used to centrally fuse the asynchronous measurement information of multiple radars. The estimation effect of the high order motion feature of the target under different ranging， angular accuracy and radial velocity augmentation measurement is analyzed， and the influence of the radar station layout on the estimation effect of the high order motion feature of the target is analyzed by using the geometric accuracy factor of double sensors to optimize the radar station layout. Through simulation experiment， it is found that the radar ranging accuracy in this radar networking mode has a greater impact on the estimation effect of high order motion feature than the angle measurement accuracy. Radar station layout optimization combined with radial velocity augmentation measurement can effectively obtain high precision estimation of high order motion feature of target.

The spectral imaging provides important support for ballistic missile early warning by virtue of its abundant spatial and spectral information， and the compressive sensing provides a effective approach for spectral image data collecting and processing. Aiming at the existing compressed perceptual reconstruction mostly adopts the coding method of "spatial domain compressed sampling and inter-spectral traditional compression"， which still exists a certain waste of resources， a compressed perceptual reconstruction method based on tensor decomposition for spectral images is proposed. Taking use of the sparsity of spectral image data in three-dimensional space， a reconstruction model based on Tucker decomposition is built， and the solution algorithm based on orthogonal matching pursuit（OMP） is given. Moreover， an improved OMP algorithm which takes three-dimension tensors as dictionary atoms is proposed by expanding traditional OMP algorithm into three-dimensional space. The experimental results indicate that the proposed method can effectively reduce algorithm complexity and improve the performance of reconstruction.

Underwater target detection plays an important role in modern warfare. With the development of remote sensing， detecting and identifying underwater targets through images is one of the key research directions. The article briefly introduces hydrodynamic wake and thermal wake. According to the classification of remote sensing images， the characteristics and algorithms of wake detection from optical images， synthetic aperture radar （SAR） images， and thermal infrared images are analyzed. The preliminary concept of future development is put forward， and the key technological directions that should be paid attention to are sorted out and summarized， so as to provide reference for the development of underwater target detection．

Aiming at the problem of airspace configuration of AWACS in irregular polygonal responsibility area in air defense operations， based on the real-time detection area formed by the shortest direct flight distance and the smallest turning diameter of the AWACS patrol route， the AWACS responsibility subarea and the corresponding available airspace for AWACS patrol are determined through optimization algorithm. Based on the evaluation criteria of AWACS stability coverage， the airspace configuration is further optimized， and finally the optimization scheme of AWACS airspace configuration is obtained. The feasibility of this method in planning AWACS airspace configuration in irregular polygon responsibility area and the effectiveness of improving operational efficiency are verified by numerical simulation. The method has strong practical value and military value.

In order to realize the mosaic of C⁴ISR system construction mode， aiming at the construction of "meta element" data model of the system， driven by the software definition technology， the definable resource modeling principle is discussed， the resource modeling process is put forward， the resource concept is defined， and the resource classification framework based on multi perspectives is established. Around the control of resource information flows and the open sharing of capabilities， the model elements are proposed. According to the characteristics of 7 kinds of resources， the reference models are established. The applicability of the model to software-defined system construction is verified by instantiating the modelling of resources under typical cases.

Aiming at the problems of low observation efficiency and insufficient fuel in current space-based space observation tasks， this paper proposes a close orbit design method for space multi-target skimming observation based on particle swarm optimization algorithm and space multi-target observation model to achieve the close range skimming observation of specific multi-target under the condition of constant orbit. The space multi-target observation model is established by combining the distance calculation of two orbiting satellites with the conditions of sky light and earth shadow. The particle swarm optimization algorithm is used to optimize the number of six orbits of the observer to obtain the optimal orbit for the comprehensive closest distance observation of a specific multi-target. The periodic difference generated by the orbital height difference is used to offset the phase difference between the target and the position at the intersection in a way that consumes time to get the most fuel-efficient way， and the formula for the most fuel saving is obtained at the cost of time. Finally， the numerical method is used to illustrate the effectiveness of the orbit design method.