摘要
为获取火星探测器升力-弹道式进入火星大气层的气动特性,以火星科学实验室探测器(MSL)为研究对象,开展基于有效比热比方法的高超声速流动的数值模拟研究,并建立探测器进入过程的气动性能分析方法。计算分析表明,探测器绕流流场因有效比热比较小而具有很薄的激波层,物面气动力与文献值吻合良好;气动分析表明,对特定飞行状态,质心位置决定配平升阻比和俯仰静稳定度,合理的质心法向偏移和纵向移动可满足探测器的升阻特性和静稳定性,同时给定的配平特性和静稳定性要求也可指导质心位置调整,进而为探测器的气动布局设计和舱内设备布置提供建议。
Complex lifting entry is selected for precise landing performance during the mars science laboratory （MSL） entry. This study aims to numerically simulate the hypersonic Martian flow by using the effective specific heat ratio method and to ascertain the capsule aerodynamic characteristics. Numerical computation results show that the shock layer is thin because of lower effective specific heat ratio and that both surface pressure and shear stress agree well with the reference. Aerodynamic performance analysis shows that CG location determines trim characteristics and pitch statical stability, and reasonable radial and axial shift of the CG location can alter the capsule lifting entry performance, which is of vital significance for the aerodynamic configuration design and inner instrument layout of the Mars entry capsule.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2015年第4期383-389,共7页
Journal of Astronautics
基金
国家自然科学基金重大项目(91216204)
关键词
火星探测器
气动分析
计算流体力学
高超声速流
Mars entry capsule
Aerodynamics analysis
Computational fluid dynamics
Hypersonic flow
