An optimization-based procedure for self-generation of Re-entry Vehicles shape
A Viviani, L Iuspa, A Aprovitola - Aerospace Science and Technology, 2017 - Elsevier
In the present paper a multidisciplinary optimization procedure for the self-generation of re-
entry vehicle shapes has been developed. The procedure relies on a novel parametric …
entry vehicle shapes has been developed. The procedure relies on a novel parametric …
Aerodynamics and Aerothermodynamics of undulated re-entry vehicles
K Kaushikh, S Arunvinthan, SN Pillai - Acta Astronautica, 2018 - Elsevier
Aerodynamic and aerothermodynamic analysis is a fundamental basis for the design of a
hypersonic vehicle. In this work, aerodynamic and aerothermodynamic analyses of a blunt …
hypersonic vehicle. In this work, aerodynamic and aerothermodynamic analyses of a blunt …
[PDF][PDF] 火星进入减速器技术综述与展望
李爽， 江秀强 - 航空学报, 2015 - researchgate.net
随着火星着陆探测任务的不断推进, 火星采样返回, 载人登火星和火星基地等任务要求能将更大,
更重的探测器着陆到火星表面, 这就需要在火星大气进入阶段进行高效减速 …
更重的探测器着陆到火星表面, 这就需要在火星大气进入阶段进行高效减速 …
火星大气模型参数对MSL 气动特性的影响
吕俊明， 苗文博， 程晓丽， 王强 - 空间科学学报, 2014 - cjss.ac.cn
火星大气与地球大气截然不同, 飞行器在进入火星时气动特性不同于地球再入.
大气模型的差异主要表现为气体组份, 密度和温度等物理参数. 针对火星进入器MSL 在进入-下降 …
大气模型的差异主要表现为气体组份, 密度和温度等物理参数. 针对火星进入器MSL 在进入-下降 …
A thermochemical nonequilibrium model of CO2 plasma for studying flow-field properties of the spacecraft Mars Pathfinder
M Yu, Z Hu - Physics of Fluids, 2024 - pubs.aip.org
Thermochemical nonequilibrium phenomena are key factors affecting the numerical
simulation results of flow fields of Mars rover. In order to make clear the flow field properties …
simulation results of flow fields of Mars rover. In order to make clear the flow field properties …
Hypersonic static aerodynamics for Mars science laboratory entry capsule
Abstract The Mars Science Laboratory (MSL) entry capsule has been designed as a lifting
entry for sufficient deceleration and precise landing performance. This paper presents the …
entry for sufficient deceleration and precise landing performance. This paper presents the …
火星科学实验室气动特性数值分析
吕俊明， 程晓丽， 王强 - 力学与实践, 2013 - lxsj.cstam.org.cn
针对火星着陆探测器进入-下降-着陆过程的高超声速进入阶段, 求解三维流体动力学Navier-
Stokes 方程与化学反应动力学模型, 分析火星科学实验室进入火星大气时的化学非平衡效应 …
Stokes 方程与化学反应动力学模型, 分析火星科学实验室进入火星大气时的化学非平衡效应 …
火星进入的气动力特性预测模型分析
吕俊明， 苗文博， 黄飞， 程晓丽 - 空间科学学报, 2016 - cjss.ac.cn
火星大气环境对飞行器进入带来了新的挑战, 气动力预测是首先需要解决的问题.
针对火星探测器的高超声速进入问题, 利用三维并行程序求解流体力学Navier-Stokes 方程 …
针对火星探测器的高超声速进入问题, 利用三维并行程序求解流体力学Navier-Stokes 方程 …
Impact of Martian atmosphere model parameters on aerodynamic characteristics of Mars Science Laboratory
L Junming, M Wenbo, C Xiaoli, W Qiang - 空间科学学报, 2014 - cjss.ac.cn
The difference between Martian atmosphere and Earth atmosphere results in the different
flow field and property around the entry vehicles, and the possible change of aerodynamic …
flow field and property around the entry vehicles, and the possible change of aerodynamic …
飞行器进入火星大气的流场预测
吕俊明， 程晓丽， 王强 - 空间科学学报, 2013 - cjss.ac.cn
针对火星着陆探测器进入-下降-着陆过程的高超声速进入阶段, 利用三维并行程序求解流体动力
学Navier-Stokes 方程与化学反应动力学模型, 分析火星科学实验室进入火星大气时探测器周围 …
学Navier-Stokes 方程与化学反应动力学模型, 分析火星科学实验室进入火星大气时探测器周围 …