To satisfy lightweight requirements of thermal protection systems for hypersonic vehicles, a vacuum impregnation-assisted filtration process was proposed to prepare the phenolic resin pyrolysis carbon modified carbon fiber composites in response to the issues of high density and poor mechanical properties of the matrix of lightweight thermal protection materials developed by conventional schemes. The effective adjustment of process parameters has achieved a significant improvement in mechanical properties of the composites under maintaining low-density requirements. Compared with the material prepared by the non-filtering method at a similar density, the material obtained by filtration with a density of less than 0.37 g/cm3 showed an increase in compressive strength of 47.6~83.9 % and bending strength of 23.7~40.8 %. The introduction of the filtration process effectively solved the problems of the traditional vacuum impregnation scheme with high density and poor mechanical properties, and provided an effective technical way towards developing a new generation hypersonic vehicle large-area thermal protection material for China.

In order to achieve effective defense against high supersonic targets such as near space flight vehicles, the midcourse guidance together with terminal phase guidance is used to intercept the targets. First, the design of midcourse guidance is described as an optimization problem with terminal constraints. The problem is discretized and converted into a form of nonlinear programming (NLP) using the Gauss pseudo-spectral method (GPM). The NLP problem is solved online and the optimal guidance law is implemented in a closed-loop in a receding horizon architecture. The algorithm ensures the applicability under the condition of guidance information missing for a short time. Then, the terminal guidance law with target maneuver compensation is designed to reduce the requirement of overload on the interceptor, and the terminal guidance law is implemented based on guidance information estimation. Finally, the stability of the closed-loop guidance system is analyzed theoretically, and the effectiveness of the proposed interception strategy is verified by numerical simulation of the interception against a typical high supersonic target.

Aiming at the problem of ground air defense force deployment, a mathematical model of air defense force deployment is constructed, and an exponential function is introduced into the objective function to avoid the problem of excessive air defense firepower in order to fit the actual combat scenario; a genetic strategy-based air defense force deployment algorithm is proposed, using real number coding. Through simulation examples, the validity and rationality of the models and methods are verified, which provides support for the realization of automatic decision-making for air defense operations and the improvement of the response speed of combat defense.

To evaluate the survival effectiveness of one special surface-to-air missile system, a new method based on remaining operational capability was established. Firstly, the mathematic model of operational capability was established, which could change the capabilities of centralized command and control, ammunition reloading and self-synergy to a uniform form, typical factors were given, too. And then, survival effectiveness indicator system was established, and the survival effectiveness was defined as ratio of remaining operational capability and initial operational capability, and the calculation method was given, too. At last, one typical supression of enemy air defenses (SEAD) was given to verify the method.

In view of the development needs of the new generation of missiles with high speed and large maneuverability, as well as the shortcomings of traditional air control method in response time, maneuverability and stability, the attitude control problem of the missile with defectable nose in supersonic and large maneuvering flight conditions is studied, and an attitude stability control method based on backstepping sliding mode is proposed .First, the dynamic model of the missile with defectable nose was established，and then the aerodynamic characteristics of the missile with defectable nose were analyzed. The variation law of its main aerodynamic parameters with the change of aerodynamic configuration is studied. The attitude control system of the missile with defectable nose was designed by using the backstepping sliding mode control method, and the extended state observer is used to observe and compensate the "total disturbance" of the system including model uncertainty and external disturbance. Finally, the effectiveness of the attitude control algorithm is verified by simulation. The simulation results show that the missile attitude control system based on backstepping sliding mode can track the attitude commands quickly.

Aiming at the terminal guidance problem of interceptor with terminal attack angle, a double closed-loop guidance law is proposed. The relative motion model of missile and target is established, and the inner loop is designed to control the line of sight angular velocity and eliminate the target velocity disturbance; The outer loop controls the line of sight angle to realize line of sight angle tracking. The controller parameters compensate the nonlinear parameters of the model and simplify it to a linear system to realize line of sight tracking. Finally, this guidance law is simulated and compared with proportional guidance law and optimal guidance law to analyze the interception effect for different speed targets. The simulation results show that the guidance law can realize the line of sight angle constraint, the terminal trajectory is smoother than the proportion guidance law. For high-speed targets, the guidance law can still preserve good interception effect and angle constraint effect.

In order to solve the problem that conventional control strategy is difficult to effectively correct the handover error of midcourse and terminal guidance, a new control strategy is proposed in this paper. Firstly, the mathematical model of compound control system with lateral thrust and aerodynamic is established, then the common orbital control strategies of near space target interceptors are analyzed, and through simulation comparison, the orbital control strategies with the best control performance is selected. On this basis, combined with the work requirements of near space target interceptors, an orbital control strategy based on zero-effort miss and overload error is proposed. The simulation results show that the new control strategy can reduce fuel consumption over 40% on the premise of ensuring hitting precision, which is more conducive to hitting targets with larger position error.

Multi-beam antenna can generate multiple independent and uncorrelated high gain narrow beams through the feed, which can not only solve the problem of high loss and signal interference of millimeter wave in free space, but also dynamically control the beam direction, achieve beam switching and expand the signal coverage. Based on Butler matrix and multi-beam antenna theory, a Ka-band multi-beam antenna subsystem is designed in this paper. Three basic units of broadband quadrature coupler, phase shifter and cross junction are designed by copper based micro-coaxial process to achieve 4 × 4 Butler matrix, using Vivaldi antenna1 × 4 antenna array is designed with Butler matrix as its feed phase network. Using copper based micro coaxial flip chip packaging technology, the heterogeneous integration of copper based micro coaxial and active chip is realized. The input port of Butler matrix is integrated with switch chip, and the output port of Butler matrix is integrated with amplifier chip. Finally, Ka-band Butler matrix feed of 1 × 4 multi beam antenna subsystem is simulated and designed. In the frequency band of 28 ~ 35 GHz, the gain of the multi beam antenna can reach 14.47 dBi, and the maximum beam coverage can reach ±32°, which is conducive to improving the signal-to-noise ratio, communication capacity, anti-interference ability and signal coverage of the millimeter wave communication system.

Aiming at the problem that the limitation and blindness of adopting the empirical design method to carry out the lightweight design of the launching box structure leads to a serious impact on the overall design and R&D efficiency, taking the ANSYS Workbench as the software platform, combined with the parametric modeling and response surface analysis technology, a process for weight reduction optimization of the box is designed and implemented. By reasonably simplifying the launching box structure into a stiffened cylindrical shell structure, a simple and fast parametric modeling is realized. The test points are selected and the response surface is fitted and checked by using the best filled space design method and the Kriging interpolation algorithm. On this basis, the genetic algorithm is used to optimize the design points. The weight reduction optimization design of the missile launching box verifies the effectiveness of the proposed method. At the same time, the scheme proposed in this study has low technical threshold and strong scalability, which can be extended to the optimization design of various boxes or other structures.

In this paper, a fast simulation method based on non-uniform mesh model and high-frequency method is proposed to deal with the scattering of super electrically-large composite scenes. The composite scattering is departed into complex target scattering, rough background scattering and coupling scattering. For the scattering of targets, physical optics method and equivalent edge current method are used. For the scattering of background, the two-scale method modified scattering center model is utilized. For coupling scattering, the meshes which can produce coupling effect on target surface are encrypted, and the coupling scattering is solved with modified four-path model. Then the composite scattering features of a cube-sea model and complex tank-sand model are calculated. The results are compared with those from multi-layer fast multi-pole, the average error of radar cross section can be as good as 2.4 dB, and the efficiency is improved 104 times. The proposed method is helpful to break through the calculation bottleneck of super electrically large composite scene.

With the development of radar jamming technology in electronic warfare, multi-false target jamming has become an important jamming style against radar. This paper uses Zedboard-based FPGA hardware platform to realize false target jamming signal. This method can be used in the processing of radar signal interference modulation part of DRFM system. DRFM system can achieve high-fidelity replication of radar signal. At the same time, for the characteristics of radar signal such as large bandwidth, variable modulation patterns, the method of intermittently sampling and transmitting jamming based on delay superposition is adopted to design and realize false target jamming signal, which can quickly and accurately generate jamming signal and greatly reduce the requirements of the hardware system. The verification results show that this method can realize false target jamming to radar signal.

Many problems of reliability and application would arise through the first operation cycle after the equipment is in service. The pattern of the conventional overhaul aims at fault repair, which is deficient in considerations to meet the battlefield conditions. The technology upgrade activity could improve reliability and performance of weapon equipments. Therefore, this paper explores the feasibility of applying technology upgrade to the major repair in order to enhance the readiness and modernization of air defense missile weapons. Advanced and applicable mature technologies are used to modernize the air defense missile weapon during the major repair process. This method could solve revealed issues of quality and sustainment during the operation and support to improve the weapon's reliability and technical performance, and enhance the operational effectiveness of equipment.

The automatic loading system is system of loading and unloading missile-in-container or missile-in-tube between vehicles through the mechanical arm and matching attitude detection equipment. As one of the key technologies of automatic loading, the image processing technology based on machine vision is used to precisely locate the target during loading and unloading. In order to solve the problem of accurate target location in automatic loading,a highly targeted feature points detection alggorithm is proposed for target image features,which can quickly recognize image feature points. By analyzing the experimental processing results, this feature point detection algorithm can effectively improve the locating speed and accuracy, and improve the loading efficiency to a certain extent.

In view of the current operational background of the development of air attack system towards the integration of sky, ground, sea, network and electronic, and the expansion of operational airspace to near space, outer space and network electronic space, the paper points out the connotation and core content of the integrated air defense cooperative networking operation, analyzes the current situation at home and aboard, proposes the composition of integrated air defense cooperative networking operation, studies the technical approach of adaptive networking architecture, integrated fire control network, distributed command and control system, operational component, discusses its combat capability, combat style, typical scenario and operational process. The operation technology can provide a useful reference for realizing the cross domain networking operation of interconnection and interoperability between different types defense equipment and establishing the integrated aerospace defense system.

In recent years, the U.S.army has vigorously promoted the rapid acquisition of new weapon equipment in order to quickly form a "System Cluster" of weapon equipment form, counter potential opponents, and consolidate its military leading advantage. This paper introduces the new adaptive acquisition framework of defense, fast acquisition approaches and the implementation of related projects, and then judges the situation that fast acquisition can actively adapt to the future battlefield and accelerate the forming of weapon equipment system. Finally, it gives some suggestions for the development of our army's acquisition and weapon equipment system.