雷达组网区域性防御区优化部署

对雷达网的费效比、数量、类型方面的优化部署进行了讨论。针对自卫压制式干扰或随队压制式干扰,给出一种采用不同频率的雷达利用不同位置进行优化部署的方法,并利用数据融合技术对这种部署方法进行讨论。     

基于公共燃气排导结构的共架发射系统武器选择与布局方法

公共燃气排导结构和同心筒结构的共架发射系统由于燃气排导机理不同,其对武器发射的影响及在武器选择、布局等方面均存在较大差异.针对公共燃气排导结构的共架发射系统分析了公共燃气排导对武器发射的影响,提出了武器选择与布局方法,通过算例进行了验证并得出结论:公共燃气排导结构的共架发射系统武器布局上应采取分散布局,武器选择上应优先选择“无发射活动、对应武器数量较多、烧蚀值较小”的模块,且按照模块编号依次交替在不同模块进行武器发射.     

战区一体化装备保障组织形式

针对未来信息化条件下作战中如何科学合理地组织战区装备保障力量的问题,借鉴外军经验,立足我军实际,从整体保障效能目标出发,区分诸军兵种一体、各层次各专业一体、军民一体3个层面,分别提出了三军联合保障、纵横联动保障、军地综合保障3类一体化装备保障组织形式。研究结果可为构建具有我军特色的＂大保障＂体制,加快提升战区部队体系保障能力提供理论指导。     

Supercritical carbon dioxide as a new working medium for pneumatic launch: A theoretical study

Compared with the conventionally gaseous or liquid working media, the specific internal energy of supercritical carbon dioxide (SCD) is higher at the same temperature and pressure, and the critical temperature of carbon dioxide is close to room temperature, making SCD a potential new working medium for pneumatic launch. To analyze the feasibility of this conception, an analytical model of a pneumatic catapult is established on basis of the conservations of mass and energy. The model consists of a high-pressure chamber and a low-pressure chamber connected by multiple valves, and there is a movable piston in the low-pressure chamber that can push an aircraft to accelerate. The effects of the launch readiness state of SCD in the high-pressure chamber, the initial volume of the low-pressure chamber and the valve control on the movement of the aircraft are analyzed. It is found that there is a restrictive relation between the temperature and pressure of the launch readiness state of SCD, i.e., there is a maximum allowable launch readiness pressure when the launch readiness temperature is fixed. If this restrictive relation is not satisfied, the working medium in the low-pressure chamber will drop to its triple point within a few milliseconds, leading to a launch failure. Owing to this restrictive relation, there is an optimal launch readiness state of SCD with the highest working capacity for any allowable launch readiness temperature. The pressure of the low-pressure chamber will decrease significantly as the initial volume increases, leading to a decreased acceleration of the aircraft. The ac-celeration can be controlled below a critical value by a designed sequential blasting technique of multiple valves. The calculated results show that a 500 kg aircraft can be accelerated from 0 to 58 m/s in 0.9 s with 36 kg of carbon dioxide. This research provides a new technique for the controllable cold launch of an aircraft.     

A novel launch dynamics measurement system for multiple launch rocket system and comparative analysis with numerical simulations

In this paper,a novel launch dynamics measurement system based on the photoelectric sensor pair is built.The actual muzzle time(i.e.a time duration that originates from the initial movement to the rocket's departure from the muzzle)and the muzzle velocity are measured.Compared with the classical methods,the actual muzzle time is obtained by eliminating the ignition delay.The comparative analysis method is proposed with numerical simulations established by the transfer matrix method for multibody systems.The experiment results indicate that the proposed measurement system can effectively measure the actual muzzle time and reduce the error of classical methods,which match well with the simulation results showing the launch dynamics model is reliable and helpful for further analysis and design of the MLRS.