高超声速飞行器一体化构型部件的初步设计与性能评价

分析了高超声速巡航飞行器机体/发动机一体化构型的特点,进行了一体化构型的部件划分。系统地研究了一体化构型各部件的设计条件、设计内容、设计要求和设计参数,提出了一体化构型各个部件的性能评价方法。论文的方法可用于高超声速巡航飞行器机体/发动机一体化构型的快速初步设计与性能评价。     

无人机飞行训练资源配置效率的AHP-Arena综合评价方法

为降低传统层次分析法(analytic hierarchy process,AHP)赋权过程主观片面性影响,提出了一种综合AHP与Arena仿真建模技术的无人机训练资源配置效率评价方法。基于飞行训练流程分析,确定了训练资源配置效率影响因素和效率评价指标,建立了层次型综合评价体系,概括了AHP-Arena综合评价步骤。利用Arena建模软件构建训练流程动态仿真系统并验证有效性,采用单变量数值仿真法、均方差决策法完成了影响因素客观赋权,通过线性加权综合法得出综合评价系数,实现资源配置效率评价与方案优选。实例应用说明了该方法的有效性,同时,该方法可推广至其他类似的训练过程中,亦可为其他多因素、多指标评价决策过程提供借鉴。     

密集环境中无人机协同机动飞行运动规划方法综述

从单无人机机动飞行向多机协同扩展的通用规划框架出发,介绍了其中各模块相关研究的基本原理、代表性方法和前沿研究,主要包括用于环境障碍感知的实时导航地图构建、离散空间的路径规划、连续空间的轨迹规划、基于离散连续混合空间的规划、多航迹或轨迹的协同规划。综合无人机通用规划框架的关键技术,提出了无人机协同机动规划下一步需要重点研究的方向。     

运载火箭随机振动环境试验条件的变带宽设计方法

针对运载火箭随机振动环境试验条件提出了基于能量等效思想的变带宽设计方法,通过采用分数倍频程数据处理方法,并确保各个频带内的均方根值与原随机振动环境的均方根值相同,有效解决传统的等带宽随机振动环境试验条件总均方根过高的问题。为了验证所提方法的有效性,通过典型管路产品进行了随机振动响应计算。结果表明,该方法既能够有效地对产品进行考核,又不至于对产品造成过考核。所提变带宽设计方法可为运载火箭随机振动环境条件的合理设计与分析提供有效手段。     

围压下固体推进剂的破坏机理分析

贴壁浇筑的固体发动机推进剂药柱在点火状态下处于三向围压状态,而环向承受拉应变,亟待对围压下推进剂的破坏机理展开研究。基于自研的围压加载试验系统,通过开展推进剂在不同围压、温度和应变率下的单轴拉伸试验来研究围压、温度和应变率的耦合作用对推进剂力学行为的影响。针对围压下推进剂的力学响应特征,通过细观力学仿真进一步研究围压下推进剂的破坏形式,同时借助电镜扫描试验分析推进剂试样断面的形貌特征,通过试验和仿真相结合的手段分析了围压下推进剂的破坏机理。研究结果表明,围压下推进剂的损伤界面显著减少,且随着围压载荷的逐渐增加,推进剂的损伤形式从以颗粒脱湿为主转变为以颗粒破碎为主。     

Autonomous maneuver decision-making for a UCAV in short-range aerial combat based on an MS-DDQN algorithm

To solve the problem of realizing autonomous aerial combat decision-making for unmanned combat aerial vehicles (UCAVs) rapidly and accurately in an uncertain environment, this paper proposes a decision-making method based on an improved deep reinforcement learning (DRL) algorithm: the multi-step double deep Q-network (MS-DDQN) algorithm. First, a six-degree-of-freedom UCAV model based on an aircraft control system is established on a simulation platform, and the situation assessment functions of the UCAV and its target are established by considering their angles, altitudes, environments, missile attack performances, and UCAV performance. By controlling the flight path angle, roll angle, and flight velocity, 27 common basic actions are designed. On this basis, aiming to overcome the defects of traditional DRL in terms of training speed and convergence speed, the improved MS-DDQN method is introduced to incorporate the final return value into the previous steps. Finally, the pre-training learning model is used as the starting point for the second learning model to simulate the UCAV aerial combat decision-making process based on the basic training method, which helps to shorten the training time and improve the learning efficiency. The improved DRL algorithm significantly accelerates the training speed and estimates the target value more accurately during training, and it can be applied to aerial combat decision-making.     

Controllable combustion behaviors of the laser-controlled solid propellant

Microsatellites have been widely applied in the fields of communication,remote sensing,navigation and science exploration due to its characteristics of low cost,flexible launch mode and short development period.However,conventional solid-propellant have difficulties in starting and interrupting combustion because combustion is autonomously sustained after ignition.Herein,we proposed a new type of solid-propellant named laser-controlled solid propellant,which is sensitive to laser irradiation and can be started or interrupted by switching on/off the continuous wave laser.To demonstrate the feasibility and investigate the controllable combustion behaviors under different laser on/off conditions,the combus-tion parameters including burning rate,ignition delay time and platform pressure were tested using pressure sensor,high-speed camera and thermographic camera.The results showed that the increase of laser-on or laser-off duration both will lead to the decrease of propellant combustion performance during re-ignition and re-combustion process.This is mainly attributed to the laser attenuation caused by the accumulation of combustion residue and the change of chamber ambient temperature.Simultaneously,the multiple ignition tests revealed that the increased chamber ambient temperature after combustion can make up for the energy loss of laser attenuation and expansion of chamber cavity.However,the laser-controlled combustion performance of solid propellant displayed a decrease trend with the addi-tion of ignition times.Nevertheless,the results still exhibited good laser-controlled agility of laser-controlled solid propellant and manifested its inspiring potential in many aspects of space missions.     

扭曲尾翼飞行器的气动特性

为研究扭曲尾翼对飞行器气动特性的影响,引入扭曲率与平均攻角来表示尾翼的几何特征,通过求解旋转坐标系下的定常状态N-S方程,对十字型布局扭曲尾翼飞行器气动特性进行了数值仿真。结果表明:扭曲尾翼可以增加飞行器的滚转力矩和平衡转速,其平衡转速与扭曲率呈正比关系;随着扭曲率的增大,扭曲尾翼飞行器未转动时的阻力系数增大、平衡转速时阻力系数减小;在临界扭曲率以内,随着扭曲率的增加,飞行器平衡转速时翼面压力分布得到了有效改善,研究结果对于飞行器的气动构型设计及其飞行稳定性分析具有参考价值。     

车辆运动数学模型辅助的动基座对准方法

针对车载捷联惯导(SINS)在外部传感器失效时无法实现动基座对准的问题,提出了基于车辆运动模型辅助的动基座对准方法。与传统方法不同的是,该方法利用车辆在路面上的运动特性,利用车辆运动模型测得的虚拟观测量来提供辅助信息,从而实现SINS的动基座对准,仿真结果表明:对于中等精度惯导,在外部传感器失效时,利用车辆运动模型提供的辅助信息,水平对准精度为0.37°,方位对准精度为5.86°,对准时间小于150 s,依然能够快速有效地实现动基座对准。     

弹道计算格斗导弹攻击区的一种快速模拟计算法

以某型近距格斗导弹为例,在考虑了导弹制导控制延迟基础上,建立了导弹跟踪目标的质点运动模型,并根据判断导弹与目标交汇条件,给出了一种导弹攻击区和有利攻击区快速模拟计算方法。仿真结果表明,利用本方法计算结果与资料给出的包线基本重合,模拟计算在数值上和变化趋势上都与资料基本一致,本算法是可行的。