Aerodynamic Heating In Atmospheric Entry of Space Transportation
太空运输进入大气层时的气动加热
基本信息
- 批准号:63550058
- 负责人:
- 金额:$ 1.41万
- 依托单位:
- 依托单位国家:日本
- 项目类别:Grant-in-Aid for General Scientific Research (C)
- 财政年份:1988
- 资助国家:日本
- 起止时间:1988 至 1989
- 项目状态:已结题
- 来源:
- 关键词:
项目摘要
One of the most serious problems which space transportation system "HOPE" encounters is aerodynamic heating during atmospheric entry. In order to predict the magnitude of the aerodynamic heating, the detailed flow structure around HOPE is required. According to HOPE's descent flight trajectory at the altitudes from 120km to 70km, the flight Mach number is larger than 20. For such ultimately high Mach numbers, the air temperature in the shock layer of the nose is highly increased, so that not only vibrational excitation of nitrogen and oxygen molecules but also their dissociations possibly take place. These processes will be generated as nonequilibrium process at high altitudes due to insufficient molecular collisions. Thus, the shock layer flows at high altitudes should be considered to be chemically out of equilibrium. For such nonequilibrium state, the flow field was numerically calculated with viscous shock layer method using 2 temperature model (translational-rotational temperature and vibrational temperature). The equations were formulated for a multicomponent the gas flow with thermal and chemical nonequilibrium. Although the temperatures to be considered are translational, rotational, vibrational and electron-translational temperatures, at high altitudes vibrational temperature deviates from translational temperature due to slow equilibration of vibrational energy with translational energy because of insufficient energy exchange. Therefore the vibrational energy equation is needed to determine the vibrational temperature. At moderate altitudes (60km to 50km), thermodynamic state will be in equilibrium, and therefore chemical and thermal equilibrium calculation was carried out and 1 temperature model was used. The model used here is a axisymmetric nyperboloid. In addition, experiments of heat flux to the wall using a few of TPS were performed in an arc-heated low density plasma wind tunnel.
航天运输系统“希望”遇到的最严重问题之一就是进入大气层时的气动加热问题。为了预测气动加热的大小,需要得到HOPE周围详细的流动结构。根据HOPE在120-70公里高度的下降飞行轨迹,飞行马赫数大于20。对于如此高的最终马赫数,机头激波层的空气温度大大增加,因此不仅可能发生氮和氧分子的振动激发,而且可能发生它们的解离。由于分子碰撞不足,这些过程将在高海拔地区以非平衡过程的形式产生。因此,高空激波层流动应该被认为是化学上不平衡的。针对这种非平衡态,采用粘性激波层法,采用平动-转动温度和振动温度两种温度模型对流场进行了数值计算。建立了具有热和化学非平衡的多组分气体流动方程。虽然要考虑的温度是平移、转动、振动和电子平移温度,但在高海拔,由于能量交换不足,振动能与平动能平衡缓慢,导致振动温度偏离平移温度。因此,需要用振动能量方程来确定振动温度。在中等高度(60~50公里),热力学状态处于平衡状态,因此进行了化学平衡和热平衡计算,并采用1温度模型。这里使用的模型是轴对称的抛物面。此外,还在低密度等离子体风洞中进行了少量TPS对壁面热流的实验研究。
项目成果
期刊论文数量(12)
专著数量(0)
科研奖励数量(0)
会议论文数量(0)
专利数量(0)
M. Nishida and Y. Skamura: "Hypersonic Flows with Air Chemistry over a Reentry Vehicle at High Altitudes" Proceedings of the 17th Int. Symp. Space Technology and Sciences, 1990.
M. Nishida 和 Y. Skamura:“高空再入飞行器上空空气化学的高超音速流动”第 17 届国际会议论文集。
- DOI:
- 发表时间:
- 期刊:
- 影响因子:0
- 作者:
- 通讯作者:
西田迪雄: "極超音速流" 日本機械学会誌. 92. 982-986 (1989)
Michio Nishida:“高超音速流动”日本机械工程师学会杂志 92. 982-986 (1989)。
- DOI:
- 发表时间:
- 期刊:
- 影响因子:0
- 作者:
- 通讯作者:
西田迪雄・渡辺泰夫: 日本航空宇宙学会誌. 36. 480-486 (1988)
Michio Nishida 和 Yasuo Watanabe:日本航空航天学会杂志 36. 480-486 (1988)。
- DOI:
- 发表时间:
- 期刊:
- 影响因子:0
- 作者:
- 通讯作者:
M.Nishida,K.Teshima,K.Ueno & S.Tanak: "Shock waves Generated by an Opposing Jet" Proceedings of the 17th International Symposium on Shock Tubes and waves. (1990)
西田先生、丰岛先生、上野先生
- DOI:
- 发表时间:
- 期刊:
- 影响因子:0
- 作者:
- 通讯作者:
M. Nishida, K. Teshima, K. Ueno and S. Tanaka: "Shock Waves Generated by an Opposing Jet" Proceedings of the 17th Int. Symp. on Shock Tubes and Waves, 1990.
M. Nishida、K. Teshima、K. Ueno 和 S. Tanaka:“反向射流产生的冲击波”第 17 届国际会议论文集。
- DOI:
- 发表时间:
- 期刊:
- 影响因子:0
- 作者:
- 通讯作者:
{{
item.title }}
{{ item.translation_title }}
- DOI:
{{ item.doi }} - 发表时间:
{{ item.publish_year }} - 期刊:
- 影响因子:{{ item.factor }}
- 作者:
{{ item.authors }} - 通讯作者:
{{ item.author }}
数据更新时间:{{ journalArticles.updateTime }}
{{ item.title }}
- 作者:
{{ item.author }}
数据更新时间:{{ monograph.updateTime }}
{{ item.title }}
- 作者:
{{ item.author }}
数据更新时间:{{ sciAawards.updateTime }}
{{ item.title }}
- 作者:
{{ item.author }}
数据更新时间:{{ conferencePapers.updateTime }}
{{ item.title }}
- 作者:
{{ item.author }}
数据更新时间:{{ patent.updateTime }}
NISHIDA Michio其他文献
NISHIDA Michio的其他文献
{{
item.title }}
{{ item.translation_title }}
- DOI:
{{ item.doi }} - 发表时间:
{{ item.publish_year }} - 期刊:
- 影响因子:{{ item.factor }}
- 作者:
{{ item.authors }} - 通讯作者:
{{ item.author }}
{{ truncateString('NISHIDA Michio', 18)}}的其他基金
Fundamental Research of Spallation Phenomena
散裂现象的基础研究
- 批准号:
17560702 - 财政年份:2005
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for Scientific Research (C)
Nonequilibrium Aerodynamics for a Super-orbital Reentry
超轨道再入的非平衡空气动力学
- 批准号:
11694165 - 财政年份:1999
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for Scientific Research (B)
NONEEQUILIBRIUM PHNOMENA OF LOW-DENSITY JETS IN SPACE
太空低密度射流的非平衡现象
- 批准号:
08044155 - 财政年份:1996
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for international Scientific Research
Investigation of Radiation-cooled Arc Heater
辐射冷却电弧加热器的研究
- 批准号:
07555607 - 财政年份:1995
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for Scientific Research (A)
EFFECT OF NONEQUILIBRIUM BEHIND A STRONG SHOCK UPON RE-ENTRY AERODYNAMIC HEATING
再入气动加热强冲击背后的非平衡效应
- 批准号:
05452305 - 财政年份:1993
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for General Scientific Research (B)
相似海外基金
Development of Non-Ablative Lightweight Thermal Protection System for Planetary Exploration and Crew Space Transportation System
行星探测和载人航天运输系统非烧蚀轻质热防护系统的研制
- 批准号:
24560982 - 财政年份:2012
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for Scientific Research (C)
Feasibility Study on Morphing Space Transportation System with Global Access on Earth from Space
从太空到地球全球访问的变形空间运输系统的可行性研究
- 批准号:
24656520 - 财政年份:2012
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for Challenging Exploratory Research
A guidance and control system design for reliability improvement of the next space transportation system
提高下一代空间运输系统可靠性的制导与控制系统设计
- 批准号:
20760549 - 财政年份:2008
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for Young Scientists (B)
Thermal Protection System Structures for the Space Transportation System
航天运输系统热防护系统结构
- 批准号:
02452091 - 财政年份:1990
- 资助金额:
$ 1.41万 - 项目类别:
Grant-in-Aid for General Scientific Research (B)