可重复使用运载器再入数学建模  

RLV Reentry Mathematical Modeling

作　　者：余光学 李昭莹[1] 林平[1,2] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]北京航天自动控制研究所,北京100854

出　　处：《中国空间科学技术》2014年第3期23-31,共9页Chinese Space Science and Technology

基　　金：国家自然科学基金(61174221)资助项目

摘　　要：针对可重复使用运载器(RLV)方案论证和初步设计阶段对模型的需求,提出了一种RLV再入概念设计,进行了数学建模研究。RLV采用翼身组合体的气动布局,包括左右升降副翼、方向舵和机体襟翼。对其无动力再入返回姿态控制,建立了反作用控制系统/气动舵复合控制数学模型。再入过程要经历自由分子流区、稀薄大气过渡流区和连续流区,基于气动力的工程计算方法建立了这三个流区的RLV气动模型。控制特性分析与六自由度再入仿真表明,所设计的RLV控制模型具有与航天飞机轨道器一致的再入飞行特性,证明了数学建模的有效性,能够进一步用于RLV姿态控制的研究。A reusable launch vehicle （RLV） reentry conceptual design and control modeling research were presented for scheme analysis in the preliminary design stage.The RLV aerodynamic configuration was a wing-body combination with two elevons at the wing trailing edge,a rudder on the vertical tail and a flap at the end of the body.The RCS/Aerosurfaces compound control mathematical model was developed for attitude control.In order to rapidly accomplish the preliminary aerodynamic databases,the engineering prediction method was applied to calculate the aerodynamic forces and moments.The aerodynamic regions implemented was rarefied flow,transitional flow,and hypersonic continuum flow.The control analysis supported the evolution of the design to provide an optimal design.A six degrees of freedom reentry simulation shows that the RLV aerodynamic and control model has the same flight performances as the space shuttle orbiter.

关 键 词：可重复使用运载器 再入 姿态控制 建模 反作用控制系统 

分 类 号：V475[航空宇航科学与技术—飞行器设计]