With the wide application of cognitive technology in the military field, cognitive Electronic Warfare (EW) has become the inevitable trend of future military war. Given the development of EW combat object in the cognitive direction leading to a decline in the operational effectiveness of traditional EW, an in-depth exploration and analysis of key technologies in cognitive electronic warfare are conducted, including cognitive reconnaissance, cognitive jamming, jamming evaluation, and dynamic knowledge base. Moreover, the basic concepts of cognitive EW are sorted out, by analyzing the numerous challenges to traditional EW. Then, the system architecture and composition of cognitive EW are studied. On this foundation, the key technologies of cognitive EW are summarized. Finally, based on the characteristics of cognitive EW, the development direction of cognitive EW has been prospected.

Aerodynamic configuration design is an important technology for hypersonic vehicles. Combined with other relative specialties, it is the key to obtain good flight performance and ensure essential flight quality. As a fundamental research area of modern hypersonic vehicles, air-breathing vehicle has become an indispensable way to realize the sustainable hypersonic flight. The typical hypersonic air-breathing vehicles are focused on and the design concept of configurations is investigated. Proposed from the perspective of combined-cycle propulsion systems, the relationship between propulsion systems and aerodynamic configuration is studied which provides a reference for the aerodynamic configuration design work.

The missile cabin structure is used to form the shape, connect and install the subsystems, and bear various loads. The loads that the missile needs to bear in the flight stage mainly includes shear load, bending moment, axial load, external pressure, thermal load, ect. In order to verify the structural stability and strength performance of the missile cabin structure under multi-load cooperation, it is necessary to carry out the research on the structural strength test. The equivalent treatment method of test load and the design of coupled loading scheme are focused on. The study of structural strength test method of a certain missile cabin under multi-load is carried out, which provides a reliable test basis for the calculation, optimization and modification of the cabin structural strength.

The nodes of the unmanned aircraft are fast maneuvering and confronting fiercely in the complex environment. There are bad conditions such as position change and link interference suppression. The robust routing technology adapted to wireless network is studied in order to solve the problem of network resource management caused by the frequent change of wireless network topology and the sharp increase of management and control cost, and realize the goal of tenacious, timely and accurate service carrying of wireless communication service in the specific environment. A lightweight hybrid routing scheme with layered management and control is constructed, and topology awareness and fault detection technologies are used to detect network changes quickly and accurately. The damaged residual network is quickly optimized scheduling and compensation through layered route construction, intra-segment route repair and inter-segment route repair, and the communication service capability of the damaged network is improved.

Aiming at the problem of rapid repair of the debonding defect between the solid rocket motor insulation layer and the case in the battlefield environment, a comparative performance analysis of the bonding materials required for the rapid repair of the debonding between the nitrile rubber insulation layer and the steel case is carried out through experiments, and the adhesives suitable for the corresponding conditions and performance requirements are screened out. Firstly, combined with the requirements for the rapid repair of the debonding between the solid rocket motor insulation layer and the case, the curing conditions and performance indicators required for the adhesives used for rapid repair are analyzed. Further, mechanical property and ablation tests of 11 kinds of adhesives from three major categories, namely acrylate, epoxy resin, and silicone, are conducted. Finally, a grouting machine for rapid repair is designed and a fluidity test is carried out. The test results show that the X701-1 adhesive can meet the curing conditions and performance requirements for the rapid repair of the debonding between the nitrile rubber insulation layer and the steel case.

To control the position of the windward side along the vehicle for reducing the impact of harsh re-entry force and thermal environment on the vehicle, an active continuous roll control method based on the aerodynamic coefficient fitting model is proposed. Firstly, an aerodynamic coefficient fitting model combining quadratic term and negative exponential term model is established, and the aerodynamic coefficients are fitted using the least squares method. Secondly, based on the coordinate system transformation relationship, the windward angle model and the windward error angle model are proposed to describe the trajectory of the windward side along the cone of the vehicle. Then, based on the BTT/STT composite control method, linear roll control commands are designed, and the effect of different roll control commands on the flight process is compared and analyzed. Furthermore, nonlinear rolling control commands are created based on the loads to ensure that the roll rate is consistent with the trend of the loads. Finally, the proposed roll control commands are verified to generate excellent roll control effect through six degrees of freedom simulation, and can make the windward side evenly distributed along the vehicle. The standard deviation of the load on each meridian of the vehicle in rolling condition is 20% of that without rolling.

For higher reliability, higher efficiency and easier maintenance, three TVC actuators for a hydrolox launch vehicle block are studied comparatively, in aspects of designs, models and testing performances, namely, a Servo-Valve Controlled Electro-Hydraulic Actuator (SHA), an Electro-Mechanical Actuator (EMA) and an Electro-Hydrostatic Actuator (EHA), each outputting a peak power of 3 kW. A fully packaged duplex EHA design is proposed, lightweight and compact by means of innovating indepth integrations in the actuator, Electro-Hydrostatic Module (EHM), Servo Motor Pumps (SMPs) and Electronic Control Units (ECUs). The weight of a TVC system with four EHAs is 85 kg, reduced by 37%, compared to the SHA counterpart of 135 kg. The dynamic capability of three TVC actuators is almost on a par, with the first-order frequency bandwidth of greater than 30 rad/s. As to the overall efficiency of energy conversion, it is one order of magnitude higher for an EMA or an EHA than a SHA. In an operation profile on ground with a duration of 1 200 s, the efficiency is lowest for an SHA, less than 1%, and heated quickly, with the temperature reaching over 100 ℃ at the hydraulic pump. In contrast, as to the EMA and EHA,the efficiency is remarkably upgraded to over 20%, with the temperature only slightly increasing by 5 ℃ at the pump or the electric motor. It demonstrates that an EHA embodies both the heavy loading, high reliability of a SHA, and the high efficiency, good maintenance of an EMA, at the same time overcoming the weak points in dynamics, power density, oil sealing, etc., providing an intriguing option for highly reliable and secure launch vehicles. The EHA has finished its maiden flight as the first one for launch vehicles.

Aiming at the problem of difficulty in quickly and accurately estimating the pose of non-cooperative structures of satellites during the operation of space robotic arms, a neural radiation field based method for estimating and tracking the pose of non-cooperative key structures of satellites is proposed. This method first obtains the scene point cloud online through an RGBD camera, segments the point cloud to obtain satellite key structures, and then uses neural radiation fields to automatically establish a three-dimensional model of the key structures. Finally, based on the initial pose generation network and pose evaluation network, accurate pose estimation is obtained. An experimental platform consisting of an RGBD depth camera, a robotic arm, and a satellite model is constructed to conduct pose estimation experiments on key structures of satellites with different poses. The experimental results show that the algorithm proposed can automatically construct a 3D model of non-cooperative targets online without the need for human preparation of target data in advance. At the same time, it can effectively deal with target object occlusion and motion situations, thus achieving true non cooperative target pose estimation and tracking in spatial operations.

At present, with the complex and changeable game environment, deep learning models such as deep convolutional neural networks are introduced to assist in improving personnel's cognition and decision-making level of the game situation. However, when deep learning is introduced into game situation understanding, it also introduces data uncertainty and cognitive uncertainty in artificial intelligence, which leads to problems such as divergence of artificial intelligence prediction results. Key elements of uncertainty in the measurement process of game situation understanding are decomposed, extracted and measurement modeling constructed based on the measurement uncertainty evaluation method. The experimental results show that the physical measurement method based on GUM can effectively measure and evaluate the cognitive uncertainty of game situation accurately and efficiently. Finally, based on Monte Carlo method, the proposed new qualitative measurement method of game situation cognition uncertainty is verified, which shows the accuracy and applicability of the proposed method.

Composite materials used in engineering design often exhibit different properties in tension and compression in addition to anisotropy. The tensile and compressive anisotropy of constitutive behavior can affect the stress and strain distribution of composite structures under operating conditions, further consideration of the difference between tension strength and compression strength may have an impact on the strength analysis results of the structure. This article takes the carbon-carbon composite material air rudder shaft as the research object, implements secondary development through ABAQUS' USDFLD interface, compares and analyzes the changes in rudder shaft stress before and after considering tensile and compressive anisotropy. Then, considering the tensile, compressive and in-plane shear strength of the material, corresponding stiffness reduction models are introduced to analyze the failure process of the rudder shaft under bending and shear loads. The analysis results indicate that different properties in tension and compression will have a significant impact on the stress distribution of composite structures, and this analysis method can achieve more accurate simulation of the failure process of the rudder shaft.