This paper is major in the preliminary wing design for the Reusable Launch Vehicle(RLV) ( RLV ). 本文研究可重复使用运载器机翼外形的初步设计和优化方法。
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。
Engineering Attitude Control System Design of Reusable Launch Vehicle(RLV) 可重复使用运载器的工程化姿态控制系统设计
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。
The objective of this paper is to design the reentry flight control laws for the Suborbital Reusable Launch Vehicle(RLV) ( SRLV ) based on nonlinear dynamic-inversion. 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。