A new reentry guidance algorithm for RLV (reusable launching vehicle) is presented.
提出了一种针对可重复使用运载器的再入制导算法。
Thermal protection system (TPS) is one of the key technologies for space vehicle, especially for reusable launch vehicles (RLV).
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。
A parallel one-dimensional model for transient thermal analysis of the metallic thermal protection system (MTPS) for reusable launch vehicle (RLV) is established.
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。
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.
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。
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.
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。
The guidance, navigation and control(GNC) system, the brain system, is the one of the key systems of RLV. In this paper the mission requirements and system structure are first studied.
再入飞行是RLV飞行任务的重要阶段，而制导、导航与控制（GNC）系统则是RLV的核心系统之一，是RLV再入飞行的“脑系统”。
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.
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。
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