快船式飞行器参数化建模及高超声速气动计算  

Parametric Geometric Modeling and Hypersonic Aerodynamics Characteristics Calculation for Kliper Vehicle

作　　者：赵彪[1] 崔乃刚[1] 郭继峰[1] 黄盘兴 王平[2] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]中国空间技术研究院,北京100094

出　　处：《宇航学报》2013年第8期1040-1046,共7页Journal of Astronautics

基　　金：哈工大航空宇航博士点人才培养与创新研究专项基金(2010B918022)

摘　　要：针对快船式飞行器概念研究和总体设计的需要,将已知几何构型截面划分为三个形状控制函数,并基于圆锥曲线拼接的思想将其封闭为统一的参数化截面形状函数。通过动态调整形状函数的少量控制参数,可获得一簇连续的形状截面,实现了飞行器几何外形的快速参数化建模。基于三角面元划分,进行了高超声速气动特性工程计算,并给出了数据的4阶多项式拟合公式。设计了一种中长航程任务,采用全数值预测校正再入制导算法对快船式飞行器和阿波罗飞船进行了相同条件的再入仿真。仿真表明,相比传统飞船,快船式飞行器升阻比增大,机动性增强,过载环境改善,着陆精度更高。In response to the need of overall design of a Kliper class vehicle, the cross-section of a specific configuration is divided into three shape control function. Based on the splicing conic concept, those functions are closed as a uniform cross-sectional shape function, and a cluster of continuous shape cross-sections is obtained by dynamically adjusting the small number of control parameters of the shape function. The hypersonic aerodynamic characteristics of the Kliper vehicle is calculated by using engineering method based on the triangular face element, and the resulting data is fitted into a fourth-order polynomial, thus reducing one interpolation dimension. Reentry simulation of the Kliper and the Apollo is performed in the same long range task scenario by use of a numerical prediction-correction reentry guidance algorithm. The reentry trajectory characteristics metrics of Kliper are significantly better than traditional vehicles.

关 键 词：快船飞行器 参数化几何建模 高超声速气动计算 总体设计 

分 类 号：V221[航空宇航科学与技术—飞行器设计]