Firstly, the connotation and application of artificial intelligence and military intelligence technology are introduced, and the profound changes of military intelligence technology to naval warfare form, operational concept and style are studied. Moreover, the basic features of future intelligence naval warfare are summarized. Then, the development status of military intelligence technology at home and abroad is analyzed. Finally, the intelligent idea and suggestion of naval warfare equipment are put forward.

Intelligence-based distributed cooperative operation (IBDCO) is characterized by high integration, self-organization, self-decision, and high cost effectiveness. Therefore, it will be a new type of warfare in the future with good performance. Based on the core thoughts of combat theory, the components of the system structure, and its outstanding features, the definition and concept of IBDCO are discussed in this paper. Some advanced projects of IBDCO system are introduced, and the development purposes and characteristics of these corresponding projects are emphatically summarized. Then, some crucial technologies which improve the development of IBDCO are analyzed in details, including situation awareness and cognition, information fusion and target tracking, distributed cooperative mission planning, and coordinated guidance law design. Finally, according to the analysis results of the related projects and achievements, some suggestions are proposed from the equipment design and its technical features of IBDCO system. The development trend of IBDCO system is introduced to provide useful reference for architecture design and tackling key problems of our army’s intelligent and cooperative operational systems.

In order to more accurately study dynamic separation law of canisterized-missile of one-side pulling launching system under conditions of complex contact force and gas force and provide basis for exterior trajectory design, a direct coupling method between launching gas dynamics and multi-body dynamics is proposed to study fluid-structure coupling dynamic performance of one-side pulling launching system. Its launching gas dynamic model and rigid-flexible coupling dynamic model are built respectively using computational fluid dynamics and multi-body dynamics. Based on the built fluid-structure coupling co-simulation environment, fluid-structure coupling co-simulation of the one-side pulling launching system is realized with alternately solving the rigid-flexible coupling dynamics and launching gas dynamics. Fluid-structure coupling dynamic performance of the one-side pulling launching system is evaluated. The research results show that the reasonable guide rail gas unloading hole can effectively control the pitching moment on the missile body, so as to control the pitching angular velocity of the missile body. The research results have important engineering value for the optimization design of one-side pulling launching system.

A computation program was developed based on Method of Characteristic (MOC), with which the supersonic inlet compression surface was designed according to the prescribed parameter change law along the compression surface. The influence of pressure gradient and Mach number gradient on inlet performance was studied and compression surface was designed overall considering the two laws of compression. It was showed that efficiency of the design of supersonic inlet compression surface was greatly increased with the use of the MOC method. Strategy design was conducted, through which the compression surface with high capability was obtained. The pressure gradient in the rear section was greatly decreased and the outlet parameter distribution was more even if the compression law of Mach number cubic curve was adopted, the pressure gradient would also be reduced and better compression results would be gained. 

This paper makes analysis of the characteristics of high speed maneuvering target with large diving angle and the disadvantages of interception of this kind of targets by the missile using traditional proportional guidance. It suggests a real-time prediction measure for this kind of targets and introduces a guidance method of quasi-counter trajectory interception. Simulation tests have also been carried out to verify the effectiveness of this method.

A bias calibration scheme for MEMS gyroscope on optical axis by using the onboard strapdown high precision gyroscope is proposed, and the Kalman filter algorithm with zero deviation value between onboard strapdown high precision gyroscope and MEMS gyroscope is designed. Through the static base and dynamic base simulation verification, the gyro bias calibration technology is reasonable, feasible and robust, meeting the needs of engineering application.

The terminal guidance law for space kill vehicle in high-speed encounter was studied. Firstly, dynamic models of space kill vechicle were established. Then the variable structure guidance law was designed adopting exponential approach law based on the relative motion equation, and chattering was weakened through smoothing. Lastly, pulse width modulation was conducted for guidance command by Schmitt Trigger. The simulation results showed that the guidance law against space target presented in this paper was effective, which had the merits: strong robustness, small miss distance, and low fuel consumption.

With reference of fighter maneuverability and agility in geophysical domain space, the fighter agility in beyond-visual-range (BVR) air combat and maneuver counter of electromagnetic information are discussed. Using the principle of air combat OODA loop, the OODA loop of the fighter BVR air combat and the OODA loop of counter of electromagnetic information are analysed. The BVR air combat scenario, the attack and defense process of maneuver counter of electromagnetic information between F-22 and F/A-18 or EA-18G are discussed. The relationship between the maneuverability of electromagnetic information and the agility of the BVR air combat, and the advantage of the BVR air combat are discussed. By the analysis and study in this paper, it shows that the counter of electromagnetic information is the key of battle effectiveness, and the maneuver counter of electromagnetic information and agility in the air combat are very important to capture the advantage of the BVR air combat.

Three methods such as zero across and FFT and correlation analysis are introduced to measure phase difference for the test of missile automatic pilot. The virtual instrument based on LabView is used to realize the three methods. The advantage and disadvantage for these three methods are analyzed through simulation. The phase difference measurement by correlation analysis has the advantages of high precision and strong anti-jamming， so this paper emphasis on correlation analysis. Correlation analysis arithmetic is optimized and realized in low SNR. Through simulation， the ameliorated method of correlation can improve the test accuracy of phase difference efficiently. The algorithm has been applied to a missile automatic pilot testing system， the results has shown the validity of the algorithm.

According to the design requirements of the product for the local oscillator source, several schemes are elaborated and analyzed. A DDS-based frequency multiplication phase-locking scheme is selected to design. The design of frequency band, accuracy, phase noise and spurs is introduced in detail. The achievable indicators are calculated and simulated. Finally, the effectiveness of the design is verified by product testing.

The cable on missile is the transmission path of all the information on the missile, and also the main coupling channel of electromagnetic interference. The interference between the cables on the missile and interference of external electromagnetic pulse radiation on cables are simulated in the paper. Influence of cable arrangement factors on mutual interference between cables, interference of electromagnetic pulse with different polarization modes and incidence angle on the cables are analyzed. The simulation analysis of the electromagnetic compatibility of cables on missile can be used to quickly observe the disturbance of each device and provide a reliable basis for the design of missile anti-jamming.

This paper analyses the gray characteristic of the infrared dim target under complex background, and proposes a new target detection method. Firstly, an improved detection template is introduced based on the analysis of the gray distribution characteristic in different structure of an infrared image. The adopted detection template has eight different directions and three levels, which can filter out some parts belonging to the background. Secondly, a pretreatment process based on mean filter is adopted to save detection time consumption and a new improved algorithm based on gray characteristic is proposed. Finally, experimental results reveal that the proposed method can effectively detect small and dim targets, which builds a basis for improving the detection and tracking efficiency of missiles. 

In view of the shortcomings of present integrated support design of weapon equipment, and the demand of integrated support design of weapon equipment, a big data system oriented integrated support design of weapon equipment is researched in this paper. Through the study of the overall architecture of big data system of integrated support design, big data integration and storage of integrated support for life cycle, and big data mining of integrated support, a general frame plan including big data integration and storage, big data mining, network infrastructure support environment is formed. The research can guide the construction of big data system.