跨大气层飞行器

net的网络化监测诊断系统的方案和实现方法，并围绕国家863项目&可重复使用跨大气层飞行器健康监测与故障诊断技术，以地面远程监测和诊断的实际应用为对象，对基于。

This system is developed for a national 863 project , RLV ( Reusable Launch Vehicle ) Healthy Monitor and Diagnose Technology Research .

跨大气层飞行器RCS干扰数值模拟研究

The numerical study on RCS interaction for trans-atmospheric vehicle

本文主要研究了可重复使用跨大气层飞行器（RLV）健康管理系统（HMS）总体框架及其关键系统之一&有效载荷释放和回收系统的健康监控原理。

In this paper , the scheme of RLV 's health manages and the theories of health monitoring of one sysem of RLV are researched .

本文主要针对我国串联两级重复使用跨大气层飞行器设计方案，建立其动力学虚拟样机，并使用该样机对串联两级RLV的上升段进行仿真计算。

The thesis aims at setting up the dynamic virtual prototype for contacting series two stages of RLV system and simulating flight at ascent stage .

进一步对两种制导方法进行了比较分析研究，研究认为标准轨道制导与轨道预测制导都是可行的RLV再入制导方案，其有机结合是未来可重复使用跨大气层飞行器再入制导的发展趋势。

Comparisons between the two guidance schemes were performed , and simulation results show that the two guidance methods are feasible , which indicates that the integration of reference-trajectory entry guidance and predictor-corrector entry guidance is a promising entry guidance scheme for future RLVs .

跨大气层飞行器爬升段纵向飞行控制律和制导律设计

Longitudinal Flight Control and Guidance Law Design for Trans-aerosphere Vehicle During Climbing Phase

跨大气层飞行器爬升段飞行控制律方案研究

Conceptual Study on Flight Control Laws for a Trans-Aerosphere Vehicle in Climbing Phase

本文的研究成果对跨大气层飞行器的总体设计以及飞行规划具有重要的参考价值，所提出的方法及分析结论将为跨大气层飞行器气动防热和弹道综合优化设计提供分析与论证方法。

The methods and conclusions can provide analysis and demonstrating methods for aerodynamic heat-resist and trajectory synthesized optimization .

本文研究成果已经成功应用于某跨大气层飞行器任务仿真课题并取得了预期的效果。

The application of our results in the project that is about the task simulation for a sub-orbit spacecraft is successful , and reaches our expectations .

针对跨大气层飞行器外形，开展了超声速流动中的侧向喷流干扰问题研究。数值模拟了一定高度和飞行马赫数条件下不同喷流控制形式的干扰现象。

Lateral jet interaction in supersonic flow for trans-atmospheric vehicle is studied by numerical method in this paper , and different control methods by jet at different flow conditions are investigated numerically .

针对跨大气层飞行器的飞行特点，提出了四种纵向控制律初步方案，分析研究了这四种控制律设计方案的特点及存在问题，为具体的控制律方案设计提供了初步基础。

Based on the flight characteristics of the trans-aerosphere vehicle , the preliminary schemes for control systems were presented . A better one was selected by analyzing several inner and outer loops projects .

采用控制增益参数随动压变化进行调参的方法，对爬升段飞行轨迹进行了数字仿真，结果表明设计的控制增益参数及控制律，满足了跨大气层飞行器爬升段的预定目标要求。

The method for controlling gains scheduled by the pressure is used to digitally simulate the flight path . Simulation results show that the designing gain parameters are reasonable and meet the TAV scheduled climbing goal .

根据跨大气层飞行器再入大气的气动加热环境和C/SiC复合材料构件的应用特点，要求C/SiC陶瓷基复合材料具有优异的应力氧化烧蚀性能，以满足防热结构一体化构件重复使的要求；

According to aerodynamic heating environment of re-entry atmosphere and specialties of C / SiC components , C / SiC ceramic matrix composite has excellent stressed oxidation and ablation resistance for the reuse of thermo-structure components .

跨大气层飞行器在爬升过程中重量、重心、高度和速度等参数变化剧烈，因而飞行器的操纵稳定特性也变化急剧，与常规飞行器相比其飞行控制律设计有它的特殊性。

During the climbing phase , the parameters , such as weight , center of weight , altitude and velocity of a trans-aerosphere vehicle changed so much so that its control and stability also change so much .

高超声速飞行器是一种基于助推-滑翔概念的超声速跨大气层飞行器，是一种非常规弹道、能突破防御系统或航空母舰战斗群防线的精确制导武器。

Hypersonic glide spacecraft is one type of supersonic stride aerosphere vehicle that based on supersonic volplane trajectory conception , is a type of unconventionality trajectory , breaking through contravallation or aircraft carrier battle group line of defense precision-guided weapon .

跨大气层和空间区域飞行器的液体推进剂管理

Research on Liquid Propellant Management for Cross Atmospheric Layer and Space Vehicle

高超声速飞行器在大气中通常以5倍Ma数以上的速度飞行，包括弹道导弹、巡航导弹、再入飞行器、跨大气层式的空天飞行器等。

Hypersonic vehicles including ballistic missiles , cruise missiles , re-entry vehicles , trans-atmosphere aerospace aircrafts , etc. usually cruise in the atmosphere at a Mach number higher than 5 .