共查询到17条相似文献,搜索用时 207 毫秒
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深空探测任务要求太阳能电推进系统具有大推力、高比冲特性,同时随着航天器离开太阳距离的增加,太阳能效率快速降低,要求电推进系统具备功率宽范围高效工作能力。为了研究兰州空间技术物理研究所研制的40cm离子推力器功率宽范围工作能力,从实验角度研究了1~10k W 40cm离子推力器的工作性能及其变化规律。通过对离子推力器工作参数和性能的分析与计算,依据功率调节方法确定了40cm离子推力器1~10k W多模式工作点电参数;通过阴极流率优化和放电损耗优化实验确定了多模式工作点最佳供气参数。在设计确定的电参数和实验确定的供气参数下,开展了1~10k W调节实验,获取了40cm离子推力器的工作性能及其变化规律。实验结果表明:40cm离子推力器可在1~10k W内稳定工作,推力42~336m N,比冲2174~4389s,效率41%~72%;随功率增加效率增高,当功率大于2.5k W时效率大于63%。 相似文献
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为了促进国内电推进技术的发展,简要介绍了国际上主要电推力器的种类和特点,并结合国外电推进技术的研究及在轨应用情况,介绍了中国电推进技术发展过程和应用现状,总结了国内外电推进技术的发展趋势。在此基础上,根据国内深空探测、商业航天、重力场测量、引力波探测等空间任务对推进器的高比冲、长寿命、宽调节范围、低成本、高精度等需求,提出了国内电推进技术应该将小型离子推力器、大型霍尔推力器、脉冲等离子体推力器以及无拖曳控制推力器作为重点发展方向的建议。 相似文献
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为了发展基于电推进的大功率空间运输系统,需要开发和验证功率达数十千瓦的电推进系统,深空任务电推进系统优化的比冲要求高达105s。凯尔迪什研究中心(KeRC)正在开发这样的电推进部件。本文概述了 35kW离子推力器 IT-500及其流动单元FCU-500的验证现状。作为其验证的一部分,完成了IT-500 和 FCU-500的2000h寿命试验。其中,离子推力器大部分验证条件是:输入功率17.8kW,使用了40kg氙,2018h寿命试验。本文介绍了磁场和离子光学以及石墨格栅开发现状。 相似文献
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有人参与深空探测任务面临的风险和技术挑战 总被引:1,自引:0,他引:1
《载人航天》2016,(2)
有人参与的深空探测工程是无人深空探测工程和载人航天工程的有机结合,是未来航天技术发展的一个重要方向。与无人深空探测工程相比,有人参与的深空探测系统更加复杂、难度更大、要求更高。经过系统梳理,提出了4个方面面临的风险和技术挑战,即保障人员精确可靠到达、着陆地外天体并安全起飞返回地球,保障人员在长期飞行及长期驻留任务时的居住及生活环境,保障人员在地外天体的大范围机动作业,保障人员长期任务中的健康和安全。解决上述技术问题可为后续开展有人参与的深空探测任务指明方向。 相似文献
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JPL实现标准化TT&C客户支持的发展计划 总被引:1,自引:0,他引:1
JPL通信与任务操作管理局(TMOD)为各种深空任务的实施提供跟踪、遥测与指令遥控业务。这些业务系统正在被重新设计成TMOD深空任务系统(DSMS)中的端到端业务。DSMS TT&C地面系统包括来自深空网(DSN)的数据业务单元和来自高级多任务操作系统(AMMOS)的任务业务单元。地面系统提供跟踪数据(至航天器的距离和载波多普勒测量值)、航天器遥测数据和上行指令业务。DSN通信系统 相似文献
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航天器姿态控制一直是地面飞控的核心,尤其对于有精确轨道控制要求的航天器,姿态控制的策略选择直接关系任务成败。探月三期月地高速再入返回任务对再入角有着严格要求,为了实现返回器高精度再入,在系统介绍服务舱的姿态控制模式、控制方法和控制流程的基础上,提出了利用修改相平面参数和轮控调姿,以建立轨控姿态,从而减少姿控喷气,并提高轨控精度的方法。飞行结果表明,中途修正的控制精度从最初的分米量级提高至0.009m/s。高精度轨道控制使得提前32h再入角控制精度达到0.024°,较设计指标提高1个数量级。文中提及的轮控调姿方法可作为未来深空探测任务姿态控制的设计参考。 相似文献
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Valerie C. Thomas Joseph M. Makowski G. Mark Brown John F. McCarthy Dominick Bruno J. Christopher Cardoso W. Michael Chiville Thomas F. Meyer Kenneth E. Nelson Betina E. Pavri David A. Termohlen Michael D. Violet Jeffrey B. Williams 《Space Science Reviews》2011,163(1-4):175-249
The Dawn spacecraft is designed to travel to and operate in orbit around the two largest main belt asteroids, Vesta and Ceres. Developed to meet a ten-year life and fully redundant, the spacecraft accommodates an ion propulsion system, including three ion engines and xenon propellant tank, utilizes large solar arrays to power the engines, carries the science instrument payload, and hosts the hardware and software required to successfully collect and transmit the scientific data back to Earth. The launch of the Dawn spacecraft in September 2007 from Cape Canaveral Air Force Station was the culmination of nearly five years of design, development, integration and testing of this unique system, one of the very few scientific spacecraft to rely on ion propulsion. The Dawn spacecraft arrived at its first destination, Vesta, in July 2011, where it will conduct science operations for twelve months before departing for Ceres. 相似文献
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《Aerospace and Electronic Systems Magazine, IEEE》2003,18(2):28-35
Exploration of the planets beyond Mars and their surroundings is already planned. Astronomy researchers are citing important information that can be obtained with instrumented spacecraft that fly beyond the planets of our solar system. Spacecraft flying these missions need power for performing their functions and communicating with Earth stations. Sunlight in these zones is so weak that alternative energy sources are needed. An alternative power source for deep-space missions is radioisotope heated energy converters.. The choice of heat-to-electric power conversion is narrowing to: 1) the Stirling engine; and 2) a combined cycle with thermionic and alkali-metal thermoelectric (AMTEC) heat-to-electricity conversion. For propulsion into deep space, a nuclear-reactor-heated AMTEC energy converter that powers ion engines can become the best alternative to hoisting tons of rockets into Earth orbit. 相似文献
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为满足设定的太阳能飞机多日连续飞行条件,依据飞行过程中当前时刻的飞行高度、光伏输出功率、动力电池组余量等系统状态参数,研究如何分配动力电池组充放电和电推进系统输入等功率。所用策略立足于实时功率平衡,充分利用正午前后的光伏峰值功率用于飞机爬升及充电,在午后下滑过程中利用全部光伏输出,以最大化利用光伏资源;在光伏有效输出不足时则以一定的维持功率下滑,使能量的综合损失最小。方法能够提高以预定夜间飞行高度连续多日续航的成功率,提升飞行高度、纬度、季节范围或搭载能力,或者拓展这几种飞行条件的组合域,优化太阳能飞机的适用性。 相似文献
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《Aerospace Science and Technology》2007,11(2-3):211-221
The present investigation points out the potential of continuously propelled spacecraft for piloted Mars missions and compares them to impulsive propulsion (chemical and nuclear thermal) and ballistic trajectories. Although the results are related to piloted Mars missions, the stated issues raised hold true for a broad range of space missions. It is demonstrated that the use of impulsive propulsion leads to inflexible missions and may result in long total mission durations. Meanwhile, the use of continuous electric propulsion not only guarantees short total mission durations of Mars missions with moderate masses but also results in highly flexible missions. These criteria can be met with a continuous electric propulsion system that provides a thrust level of 100 N and 3000 s of specific impulse. Great potential lies in electric hybrid thrusters. The high-power, two-stage hybrid plasma thruster TIHTUS is currently being developed at the Institute of Space Systems (IRS). Its technology including preliminary laboratory testing results are presented. 相似文献
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James C. Leary Richard F. Conde George Dakermanji Carl S. Engelbrecht Carl J. Ercol Karl B. Fielhauer David G. Grant Theodore J. Hartka Tracy A. Hill Stephen E. Jaskulek Mary A. Mirantes Larry E. Mosher Michael V. Paul David F. Persons Elliot H. Rodberg Dipak K. Srinivasan Robin M. Vaughan Samuel R. Wiley 《Space Science Reviews》2007,131(1-4):187-217
The MErcury Surface, Space ENvironment, GEochemistry, and Ranging (MESSENGER) spacecraft was designed and constructed to withstand the harsh environments associated with achieving and operating in Mercury
orbit. The system can be divided into eight subsystems: structures and mechanisms (e.g., the composite core structure, aluminum
launch vehicle adapter, and deployables), propulsion (e.g., the state-of-the-art titanium fuel tanks, thruster modules, and
associated plumbing), thermal (e.g., the ceramic-cloth sunshade, heaters, and radiators), power (e.g., solar arrays, battery,
and controlling electronics), avionics (e.g., the processors, solid-state recorder, and data handling electronics), software
(e.g., processor-supported code that performs commanding, data handling, and spacecraft control), guidance and control (e.g.,
attitude sensors including star cameras and Sun sensors integrated with controllers including reaction wheels), radio frequency
telecommunications (e.g., the spacecraft antenna suites and supporting electronics), and payload (e.g., the science instruments
and supporting processors). This system architecture went through an extensive (nearly four-year) development and testing
effort that provided the team with confidence that all mission goals will be achieved.
Larry E. Mosher passed away during the preparation of this paper. 相似文献