Joint surface stiffness parameter identification of complex structure of aircraft using optimization method is proposed in this article. The least square of the modal test mode of vibration and calculation mode is used as the objective function. The modal frequency is used as the constraint. The joint surface stiffness is used as the optimized parameter. This method is simple and feasible, and the joint surface stiffness can be identified more accurately with parameter identification. The modal calculation accuracy can be significantly improved and a more accurate model can be provided for the subsequent dynamic modeling and vibration analysis.

According to the characteristics of multiple fire units deployment in modern area air-defense, the key fire resources assignment under the constraint conditions is researched to make full use of the operational efficiency of weapon system and cause maximum damage to enemy targets. The description of air-defense fire resources assignment is presented, an optimal model of the airdefense missile fire assignment is established, and an improved adaptive genetic algorithm is put forward to solve the satisfied solution. The optimal model and genetic algorithm in this paper are simulated, and simulation results demonstrate that the method is quick and effective. It can offer support to aided decision making for air-defense operation command.

MICA is an air-to-air missile which is developed by Matra (France) for both interception and combat. MICA has special aerodynamic characteristics due to adopting normal aerodynamic configuration fitted with long wings with small rectangular strakes and L-shaped rudders on the missile body. Different aerodynamic configurations are built using components combination method and all the configurations are evaluated in terms of controllability, stability, overload and trim capability using CFD (computational fluid dynamic) technique. Through comparisons, the functions of aerodynamic components of MICA missile and design ideas are analyzed. Research shows that small strakes at the nose of MICA missile can increase the overload of the missile while decreasing the trim deflection angle of rudder. Compared with the intact trapeziform rudder, L-shaped rudder has obvious advantages: it can not only provide the same overload, but also decrease the trim deflection angle of rudder and hinge moment.

The transmission distance of the traditional data link applied on the medium-long-range air-to-air missile is limited. Hence, a novel operational mode of the medium-long-range air-to-air missile which uses the short message data link is proposed in this paper. This mode can not only realize the over-the-horizon attack and multi-missile coordinated operations, but also support the network operations for the 5th generation of air-to-air missiles. At the same time, there is the disadvantage of the low success rate when the short message data link is applied on the missile since the beam direction of the BD satellites is fixed. Therefore, the research on the beam alignment is carried out in this paper to solve the disadvantage. In this research, the joint alignment method with the rolling angle control and the beam-forming is proposed to align the antenna normal vector of short message and the beam direction of the BD satellites in real time based on the missile position. Finally, this beam alignment method is proved to be effective by the simulation experiment since it can build a reliable short message link in the whole process of the missile flight and provide technical support for short message data link, which has engineering application value.

Spoilers are widely used by submarine-launched tactical missiles to realize thrust vector control. However, they lack control over rolling moments, which constrains the partial missile parameters design and hinders the underwater maneuver performance. In this paper, a kind of water-exit control commands are put forward as solution to the rolling disturbance, which enables missiles with spoilers to follow the planned trajectory and successfully complete water-exit  and lateral evasive maneuver.

To solve the problem caused by multi-target interference in the terminal guidance phase, which affects stable target tracking and results in the final miss, the influence of multitarget interference on the seeker’s angle tracking is analyzed, and multi-target interference compensation methodology using multiple output angle error equations with different detection frequencies at single sensing period to extract the unknown parameters of multi-target interference based on the orthogonal multicarrier technique is proposed in this paper. The method is verified reasonable and feasible through the simulation analysis, and the analysis result can be applied to improve the tracking precision of the seeker’s terminal guidance phase.

With the development of detection technology of radar and the need of information war, modern military equipments are facing the higher demand of performance. And ground radar is becoming larger with more units and with better maneuverability and stability. However, automatic docking technology for radar antenna units restricts the maneuverability of ground radar. In this paper, in light of the automatic docking experience of large components and the actual requirements of ground radar for references, the characteristics of radar antenna automatic docking technology are analyzed. 3 key technologies are introduced, namely, automatic pose adjustment system, large-scale metrology and compliant docking technology. Meanwhile, research progress of these three technologies is introduced in detail. Finally, the development of automatic docking technology for radar antenna is summarized and its prospect is given.

A noise-spectrum reduction algorithm for wideband digital receiver is presented based on the deterministic characteristics of noise power spectrum. This method can reduce the background noise. This paper also discusses the methods of noise frame acquisition and updating based on spectral entropy, trace smoothing, optimal de-noise system model and so on. The experimental results show that the proposed noise-spectrum reduction algorithm can significantly reduce the background noise of the wideband digital receiver and greatly improve the detection ability of weak signals without reducing the useful signal power under the condition of simultaneous multi-signal reception.

Compared with other simulation systems, the warfare simulation system has the features of multilevel, multifactor, uncertainty, illposed, model granularity diversity and lacking of actual data. These features bring difficulties for the warfare simulation system credibility evaluation. The credibility evaluation must go throughout the whole process of system modeling and simulation. A scheme of warfare simulation credibility evaluation is proposed based on the evaluation process, evaluation object, index system and so on, which provides theoretical support for warfare simulation credibility evaluation.

An approximate energy conservation algorithm for nonlinear dynamic analysis of triangular flat shells based on co-rotational formulation finite element is derived from Generalized-α method. The numerical stability of this algorithm is satisfied by predictor-corrector iterative procedure of dynamics balance equation in each time step. Combined with computational fluid dynamics (CFD) and loose coupling algorithm, a nonlinear aeroelastic analysis process for thin shell structures is developed. The transient response of a Prandtl plane joined wing is investigated in two different flight conditions (two different dynamic pressure) based on this method. It is found that there are three balance positions in the transient response when the angle of attack is positive and dynamic pressure is large, and when static aeroelastic balance is achieved, the joined wing twists down in chord direction and bends down in span direction; when the angle of attack is positive and dynamic pressure is small, the transient response has only one balance position during vibration and the joined wing twists down in chord direction and bends up in span direction. The simulation results show that the aeroelastic transient response of joined wing is much more complicated than the monoplane, so the high-fidelity analyses should be used for the aeroelastic analysis of joined wing in the process of structure design.

Firstly, a method of infrared scene generation and correction was proposed in this paper, and a transformation model and a correction model of infrared scene were established based on the measured data obtained in the test range. Secondly, the measured data were transformed into the driving image of the scene simulator by the transformation model, and the driving image was iteratively corrected through the correction model, so that the simulated scene, which was projected by the scene simulator with the driving image as its input, was highly consistent with the test range scene corresponding to the measured data. Finally, the similarity evaluation between the simulated scene and the measured scene was carried out based on the sensitive features of the seeker. The conclusion showed that the transformation model and correction model had an efficient use of the measured data, eliminated the complex process of the target characteristics modeling and scene rending in the infrared imaging simulation, and provided a feasible approach to simulating the infrared scene with the same radiation characteristics as the test range. 

This paper presents the concept of the unmanned aerial vehicle swarm （UAVS）, and focuses on the current situation of UAVS launch and recovery technology development. After introduction and analysis of the five key technologies, the advices for Chinese UAVS launch and recovery technology development are provided finally.