提出了一种针对可重复使用运载器的再入制导算法。
A new reentry guidance algorithm for RLV (reusable launching vehicle) is presented.
新一代可重复使用运载器对再入制导提出了更高地要求。
The new generation of Reusable Launch Vehicles (RLVs) demands improvements to the current entry guidance capability.
建立了可重复使用运载器金属热防护系统瞬态热分析的并联一维模型。
A parallel one-dimensional model for transient thermal analysis of the metallic thermal protection system (MTPS) for reusable launch vehicle (RLV) is established.
热防护系统是航天飞行器 ，特别是重复使用运载器的关键技术之一。
Thermal protection system (TPS) is one of the key technologies for space vehicle, especially for reusable launch vehicles (RLV).
基于非线性动态逆理论，设计了亚轨道可重复使用运载器（SRLV）的再入控制律。
The objective of this paper is to design the reentry flight control laws for the Suborbital Reusable Launch Vehicle(SRLV) based on nonlinear dynamic-inversion.
指出金属热防护系统仍是下一代重复使用运载器大面积表面热防护系统的优选方案之一。
It is indicated that the metal lic TPS is the one of top priority blue prints of the acreage TPS for the next generation reusable launch vehicle.
可重复使用运载器的防热瓦故障会使航天器的局部结构产生热源，并在结构中形成温度场。
The malfunction of thermal protection system on reusable launch vehicle will generate a heat source on the part of vehicle.
为了研究重复使用运载器末端能量管理段的下滑轨迹线设计，给出了基于高度和动压的质点动力学的设计方法。
To research the trajectory design method for terminal area energy management(TAEM) of reusable launch vehicle(RLV), the method basing on nonlinear equations of motion is designed.
基于古典控制理论和BTT倾斜转弯控制技术，设计了可重复使用运载器(RLV)的大气层内姿态稳定控制系统。
Focused on the problem of reusable launch vehicle (RLV) attitude control, an engineering attitude control system based on the classical control theory and BTT technology was designed.
本文对可重复使用运载器的自适应逆姿态控制进行了研究，以航天飞机轨道器为模型，建立了自适应逆姿态控制的数学模型，设计了自适应逆姿态控制方案。
In this paper, adaptive inverse attitude control of RLV (reusable launch vehicle) is studied. The mathematical model of the orbiter is built and adaptive inverse attitude controller is designed.
本文对可重复使用运载器的自适应逆姿态控制进行了研究，以航天飞机轨道器为模型，建立了自适应逆姿态控制的数学模型，设计了自适应逆姿态控制方案。
In this paper, adaptive inverse attitude control of RLV (reusable launch vehicle) is studied. The mathematical model of the orbiter is built and adaptive inverse attitude controller is designed.
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