基于多智能体联盟的多机协同空战任务分配

基于多智能体联盟形成理论,分析了网络化条件下多平台多目标攻击任务分配问题。将协同任务分配的过程视为复杂联盟的生成过程,首先将对目标总体的打击任务分解为一系列子任务,各子任务再进一步分解为单个平台能够完成的任务单元;再根据联盟特征函数的定义分别建立联盟报酬、能力成本、通信开销模型,以联盟特征函数作为空战任务分配目标函数;最后引入离散粒子群优化算法进行联盟生成,采用二进制矩阵编码形式,设计粒子可行性检查策略。仿真实验验证了本方法在协同制导条件下空战任务分配的合理性与有效性。     

超视距空战中多机协同制导方法

对空空导弹制导权交接的任务分配问题,根据己方飞机与制导权需交接的导弹的态势建立了对导弹的态势优势模型;根据己方飞机对该导弹攻击目标的态势建立了对目标的探测能力模型;根据敌方飞机对己方飞机的态势建立了己方飞机受到的威胁度模型;根据敌我双方飞机的空战能力建立了空战效能优势模型.在这4种模型的基础上建立了己方飞机对导弹的总的制导优势模型.在总的制导优势的基础上建立了协同制导任务分配模型,并采用遗传算法对协同制导任务分配问题进行优化求解.仿真结果表明,该方法能够实时地计算制导优势和进行任务分配,有效地完成多机协同制导.     

导弹自主编队综合作战效能评估方法

针对导弹自主编队协同制导与控制技术的综合作战效能评估问题,引入了协同制导与控制能力等级(CGCL)的概念,并结合层次分析法(AHP)和ADC效能评估模型建立了导弹自主编队综合作战效能的分析模型,分析了导弹自主编队典型作战想定下导弹编队成员的协同突防概率、交班成功率、命中概率和毁伤概率,分析过程充分考虑了导弹自主编队作战的能力和特点,并在搭建的导弹自主编队攻防对抗综合仿真验证系统上分析和验证了其有效性,为定量地分析导弹自主编队的综合作战效能提供了快速可靠的计算方法。     

孔型对多孔平板气膜冷却效果的数值研究

本文从加强气膜孔内的换热量和热侧的气膜覆盖两个角度来提高气膜孔壁的冷却效果,数值计算结果表明收缩进气可以强化孔内的对流换热,一般可以使换热量提高0.7倍左右;扩张出气可以使冷气出口的速度降低,气膜覆盖面更广,提高气膜的覆盖效果。     

结冰模拟对运七飞机横向特性及舵面效率的影响

继研究结冰模拟对Y-7飞机纵向特性影响之后,本文又介绍了结冰模拟对Y-7飞机横向特性及舵面效率的影响。在讨论其试验条件及结果之基础上得出的结论对结冰条件下的飞行具有重要意义。     

雷达隐身和机载电子攻击组合增强的飞机作战生存力评估

作战生存力是新型军用飞机发展中要考虑的一个关键要素,雷达隐身和机载电子攻击是两个减缩飞机敏感性的主要技术.本文给出一个攻击任务的战术设定,研究了雷达散射截面和机载雷达干扰机对威胁雷达探测概率的影响,确定了雷达制导地空导弹和防空炮火在目标雷达散射截面减缩或/和干扰机辐射功率干扰下的制导精度,计算了飞机单发击毁概率,最后给出一架攻击机在一个假设敌对威胁环境中的出击架次生存力,说明综合使用雷达隐身和机载电子攻击技术使作战飞机的生存力得到增强,评估方法有效实用.     

基于多指标综合评判法的空中加油机作战效能评估

针对空中加油机作战效能评估问题,构建了空中加油机作战效能评估指标体系,并对空中加油机的作战效能指标数据进行挖掘,利用信息熵概念求得各指标属性的重要度,并归一化处理为各效能指标的权重系数,克服了传统权重系数确定方法的主观性;然后,建立了基于理性解法的空中加油机作战效能多指标综合评价模型;最后,通过实例,对几种现役典型的空中加油机作战效能进行了评估,并得到了计算结果,同时验证了该模型的有效性。     

源项不准确加载对源项法模型仿真精度的影响

针对平板多孔气膜冷却结构开展了真实模型和源项法模型数值仿真,在同实验数据对比取得较高精度的基础上探究了源项不准确加载对源项法模型仿真精度的影响,分析了加载方式、流量系数、网格参数等影响因素。结果表明:源项法模型可以代替建立带气膜孔真实模型对气膜冷却结构进行数值计算。网格准确定位的源项加载方式在粗细网格条件下均能取得较高的精度,点源项加载方式对网格较为敏感。因流量系数公式不准确导致的流量计算误差会影响源项法模型的计算精度,低吹风比下影响更为显著。气膜孔进出口处网格面密度应不少于4个/mm2,第一层网格高度的选取应符合所选用的湍流模型,以保证较高的计算精度。     

Experiments on film cooling with sonic injection into a supersonic flow

Film cooling experiments with sonic injection were conducted to investigate the effects of the number of the injection holes, the mass flow ratio, and the hole spacing on the film cooling effectiveness. The mainstream was obtained by the hydrogen-oxygen combustion, entering the experimental section at a Mach number of 2.0. The nitrogen with ambient temperature was injected into the experimental section at a sonic speed. The measured mainstream recovery temperature was approximately 910K. The mass flow ratio was regulated by varying the nitrogen injection pressure. The experimental results show that for the investigated cooling surface, the cooling effectiveness increases with the increase in the number of the injection holes with other parameters held constant. For a fixed cooling configuration, the cooling effectiveness increases with the increase in the mass flow ratio. Different from the subsonic film cooling, the optimal mass flow ratio is not observed. When the hole spacing is less than 4, no obvious difference is observed on the cooling effectiveness and lateral uniformity. With the mass flow ratio increasing further, this difference becomes much smaller. The shock wave also has an effect on the cooling effectiveness. Downstream the incident point of the shock wave, the cooling effectiveness is lower than that in the case without the shock wave.     

Adaptive double chain quantum genetic algorithm for constrained optimization problems

Optimization problems are often highly constrained and evolutionary algorithms(EAs)are effective methods to tackle this kind of problems. To further improve search efficiency and convergence rate of EAs, this paper presents an adaptive double chain quantum genetic algorithm(ADCQGA) for solving constrained optimization problems. ADCQGA makes use of doubleindividuals to represent solutions that are classified as feasible and infeasible solutions. Fitness(or evaluation) functions are defined for both types of solutions. Based on the fitness function, three types of step evolution(SE) are defined and utilized for judging evolutionary individuals. An adaptive rotation is proposed and used to facilitate updating individuals in different solutions.To further improve the search capability and convergence rate, ADCQGA utilizes an adaptive evolution process(AEP), adaptive mutation and replacement techniques. ADCQGA was first tested on a widely used benchmark function to illustrate the relationship between initial parameter values and the convergence rate/search capability. Then the proposed ADCQGA is successfully applied to solve other twelve benchmark functions and five well-known constrained engineering design problems. Multi-aircraft cooperative target allocation problem is a typical constrained optimization problem and requires efficient methods to tackle. Finally, ADCQGA is successfully applied to solving the target allocation problem.