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气球型深空探测器技术研究进展 总被引:1,自引:1,他引:0
气球型深空探测器能够大大提高深空探测的机动能力,它不仅可以获取区域范围内的高分辨率观测数据,而且还可实现不同高度大气的原位测量。文章针对气球型深空探测器按技术特征进行了分类,并简述了各类气球探测器的原理和特点,重点总结了各类气球探测器在金星、火星和土卫六上应用的研究现状。针对我国未来的气球型深空探测器技术发展,提出首先以火星热气球为发展方向,与地球临近空间浮空器技术的发展彼此借鉴,促进关键技术领域的技术突破等建议,可为我国未来深空探测提供参考。 相似文献
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低空环境中浮空器的热数值模拟与实验研究 总被引:2,自引:1,他引:1
浮空器在通信等领域有着广阔的应用前景。温度控制是浮空器应用中涉及的关键技术之一,因此有必要对浮空器进行热分析和实验研究。本文针对低空环境与平流层的不同,考虑太阳直接辐射、天空散射辐射、地表反射的太阳辐射、大气辐射、地表辐射以及外部对流换热等因素,建立了浮空器在地面的热分析理论模型,利用CFD软件对浮空器进行了热数值模拟,并初步进行了实验研究。通过数值模拟结果与实验数据的对比,证明了理论模型具有一定的合理性。本文也为研究浮空器升空过程提供了数学物理模型。
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欧洲的海因斯行星际探测器目前正在为其7年的旅程进行最后的准备。这种着陆探测装置的探测目标将是上星最大的一颗卫星上卫六。它将对这颗卫星上古老的冰冷世界进行细致的观察,采集那里的大气和土壤样本,从而有望揭示太阳系演化初期可能存在过的生命的基本要素。海因斯是欧洲第一颗行星际探测器。它将和美国航字局的卡西尼轨道器一起飞往土星,并在ZOO4年年底在土卫六上着陆。它可望向地球发回土卫六的照片,从而增加人们对该卫星形成情况的认识。这项欧美联合计划还有望取得有关土卫六组成、大气化学活动能源。云物理、风和温度的关键… 相似文献
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广 《中国航天(英文版)》2000,(7)
形状颇像南瓜的一个大气球穿越土卫六大气橘红色的、朦胧的雾霾,向这颗土星卫星的表面降去。吊挂在气球下方很远处的有效载荷上,一台台探测器正不停地对着土卫六的表面拍照。一个探头从有效载荷上伸了出去,接着从土卫六的烃类化合物海洋中舀取了“沧海一粟”。完成预定任务后,不载人的这个大气球又穿过冰冷、稠密、以氮分子为主的大气层向上飘去,并在太空边缘处把采到的样品交给在轨道上运 相似文献
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为实现临近空间浮空器的持久区域驻留和机动飞行,文章所研究的一种利用自然能飞行的临近空间浮空器利用自然界的热能和风能,通过简易可行的技术手段实现飞行高度和轨迹的控制,有望解决临近空间浮空器面临的能源问题和热问题。文章介绍了该新型浮空器的系统组成和主要特点,分析了该新型浮空器在设计最大运行高度处的浮重平衡,进行了系统设计参数的分析。该新型浮空器由超热空气和氦气提供浮力,计算结果表明氦气囊所占比例越大,所需的浮空器半径越小,且随着设计最大运行高度的升高及超热值的减小,所需的浮空器半径增大。 相似文献
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利用浮空器提高临近空间的探测预警能力 总被引:3,自引:0,他引:3
概述了浮空器在临近空间探测预警上的作用,在此基础上,重点阐述了浮空器作为临近空间探测平台的优势,并与卫星和预警飞机进行了比较分析。主要针对美国对于浮空器的军事应用和进展,如利用浮空器对巡航导弹的探测应用等进行了介绍,最后得出结论。 相似文献
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Antoni K. Jakubowski 《Acta Astronautica》1980,7(2):169-181
The paper presents a preliminary conceptual design of a 2kW(e) autonomous power system consisting of a radioisotopic heat source, free-piston Stirling engine, reciprocating induction generator and a space radiator. The proposed design features a direct thermal interfacing of the Pu-238 heat source with the Stirling engine head, low heat losses during normal operation, and provides an auxiliary/emergency cooling system in the case of the engine failure of stopping. The Stirling engine is of the free-displacer, free-piston type invented by Beale and uses helium as the working fluid. The engine piston is integrated with the armature of a simple linear alternator which is used for electric generation. Waste heat is rejected by a four-finned space radiator sized for a geosynchronous orbit. Specific power and efficiency of the Stirling isotope power system are compared with the present and predicted performance of other power conversion systems suitable for the same power range. 相似文献
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小推力发动机膜冷却工程算法研究 总被引:1,自引:0,他引:1
为满足工程上对推力室内部传热流动分析的要求,应用分层流动理论,结合半经验传热和化学反应平衡模型,建立了分析小型液体火箭发动机推力室膜冷却的传热模型。以气氧/煤油发动机为例,初步实现了对定常情况下膜冷却过程的模拟。计算表明,冷却剂的质量分数,燃气的流动状态,喷注器尺寸等因素对冷却效果和发动机总体性能有重要影响。研究结果可为新一代小型液体火箭发动机的研制提供参考。 相似文献
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复合预冷吸气式火箭发动机热力循环分析 总被引:1,自引:0,他引:1
采用热力学第一定律分析法分析了复合预冷吸气式火箭发动机(SABRE)的基本热力过程,得出了吸气模式和火箭模式下的理想循环功和热效率表达式,确定了影响发动机理想热力循环性能的特征参数。结果表明:吸气模式下SABRE核心机采用布雷顿循环,压气机的增压比和循环增温比是影响理想热力循环性能的关键参数;火箭模式下SABRE采用火箭发动机循环,喷管降压比和出口排气速度是影响理想热力循环性能的关键参数。氦气仅仅在发动机内通过换热器换热实现能量在各循环子系统之间的输运,而其本身并无变化,不对发动机的理想循环功和热效率产生影响。 相似文献
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One of the biggest challenges of the exploration of the Moon is the survival of the crew and the lunar assets during the lunar night. The environmental conditions on the lunar surface and its cycle, with long periods of darkness, make any long mission in need of specific amounts of heat and electricity to be successful. We have analyzed two different systems to produce heat and electricity on the Moon's surface. The first system consists of Thermal Wadis, sources of thermal power that can be used to supply heat to protect the exploration systems from the extreme cold during periods of darkness. Previous results showed that Wadis can supply enough heat to keep lunar devices such as rovers above their minimum operating temperature (approximately 243 K). The second system studied here is the Thermal Energy Storage (TES), which is able to run a heat engine during the lunar night to produce electricity. When the Sun is shining on the Moon's surface, the system can run the engine directly using the solar power and simultaneously heat a thermal mass. This thermal mass is used as a high temperature source to run the heat engine during the night. We present analytical and numerical calculations for the determination of an appropriate thermal mass for the TES system. 相似文献
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连续爆轰发动机的研究进展 总被引:3,自引:0,他引:3
连续爆轰发动机是一种基于爆轰波将推进剂的化学能转化成热能的新概念发动机,近年来受到世界各主要国家的高度关注。现已成功获得多种燃料长时间稳定的连续爆轰,较深入地认识了连续爆轰流场结构,初步测得推力和比冲,验证了连续爆轰发动机的性能优势并在火箭模态、冲压模态以及涡轮模态下都实现了稳定连续爆轰。对连续爆轰发动机的工作原理,以及近年来世界各主要国家在连续爆轰发动机的基础研究和应用研究方面取得的代表性成果进行了综述,并给出尚待解决的问题,为其进一步工程化应用提供参考。 相似文献
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《Acta Astronautica》1986,13(1):1-7
This paper discusses the feasibility of the high pressure LOX/LH2 expander cycle engine which delivers 147 kN of thrust at 9.8 MPa of chamber pressure with a new concept combustion chamber.The expander cycle has the advantages of high performance and system simplicity, but it has not been applied for high pressure engine due to the existence of an upper limit in the chamber pressure to be achieved.In the expander cycle engine, the maximum chamber pressure is dominated by the amount of heat absorbed by the regenerative coolant. The larger amount of heat exchange requires the longer combustion chamber under the usual idea, which causes a decrease of performance because of reducing expansion ratio under the given engine envelope or increasing vehicle length. In order to achieve the higher chamber pressure without any decrease in performance, higher heat exchangability in the chamber is necessary.We propose the new concept combustion chamber in which higher heat exchangeability is realized by having the additional heat exchanger installed within it.Preliminary tests for the internal heat exchanger and for the expander cycle engine will by carried out in 1985 by ISAS. 相似文献
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真空羽流试验设备用于发动机真空羽流效应试验研究,同时兼顾卫星等热真空试验,对液氮系统有特殊要求。针对低至70 K液氮温度需求,设计一种全新的负压液氮系统,即利用液氮在负压下具有比常压液氮更低的饱和温度,来获得比常压液氮系统更低的液氮温度。该负压液氮系统主要由液氮输送子系统、常压过冷器子系统、负压抽气子系统、液氮泵子系统、热沉子系统及排放子系统组成,其中常压过冷器子系统和负压抽气子系统构成"负压过冷器",具有常压过冷器功能,供液温度可调,可为热沉提供70~77 K液氮制冷,满足发动机羽流及卫星热真空试验需求。 相似文献
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空气预冷发动机及微小通道流动传热研究综述 总被引:1,自引:0,他引:1
首先针对发动机空气预冷系统的特点,将现有的预冷机制分为四种类型,包括燃料预冷、质量喷注预压缩冷却、燃料预冷和质量喷注预压缩冷却组合预冷以及其他流体预冷,并分别介绍了每种预冷机制的代表性发动机循环以及技术特点。调研发现,微小通道结构的预冷器具有很高的散热能力和紧凑度,优势显著。英国Skylon空天飞机的预冷却组合循环发动机(SABRE)其微通道结构预冷器具有极高换热能力。对SABRE的预冷器及相关研究进行详细分析,强调微小通道强化换热对提高发动机性能的重要作用。通过对微小通道中单相气态流动换热研究的调研发现,微尺度流动传热机理仍存在诸多分歧,理论发展不完善,需要深入开展微小通道强化传热研究,尤其对于高速高内外温差条件下微小尺度复杂结构空间内流动传热机理需要深入探索。 相似文献
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Test results of the air turbo ramjet for a future space plane 总被引:1,自引:0,他引:1
The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 1/4-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition. 相似文献