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Health scorecard of spacecraft platforms: Track record of on-orbit anomalies and failures and preliminary comparative analysis 总被引:1,自引:0,他引:1
Choosing the “right” satellite platform for a given market and mission requirements is a major investment decision for a satellite operator. With a variety of platforms available on the market from different manufacturers, and multiple offerings from the same manufacturer, the down-selection process can be quite involved. In addition, because data for on-obit failures and anomalies per platform is unavailable, incomplete, or fragmented, it is difficult to compare options and make an informed choice with respect to the critical attribute of field reliability of different platforms. In this work, we first survey a large number of geosynchronous satellite platforms by the major satellite manufacturers, and we provide a brief overview of their technical characteristics, timeline of introduction, and number of units launched. We then analyze an extensive database of satellite failures and anomalies, and develop for each platform a “health scorecard” that includes all the minor and major anomalies, and complete failures—that is failure events of different severities—observed on-orbit for each platform. We identify the subsystems that drive these failure events and how much each subsystem contributes to these events for each platform. In addition, we provide the percentage of units in each platform which have experienced failure events, and, after calculating the total number of years logged on-orbit by each platform, we compute its corresponding average failure and anomaly rate. We conclude this work with a preliminary comparative analysis of the health scorecards of different platforms.The concept of a “health scorecard” here introduced provides a useful snapshot of the failure and anomaly track record of a spacecraft platform on orbit. As such, it constitutes a useful and transparent benchmark that can be used by satellite operators to inform their acquisition choices (“inform” not “base” as other considerations are factored in when comparing different spacecraft platforms), and by satellite manufacturers to guide their testing and reliability improvement programs. Finally, it is important to keep in mind that these health scorecards should be considered dynamic documents to be updated on a regular basis if they are to remain accurate and relevant for comparative analysis purposes, as new information will impact their content. 相似文献
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《Acta Astronautica》1987,15(8):583-586
On-orbit servicing of spacecraft and payloads is one of the most viable economic justification for a permanent, manned space station. Services include the changeout of Orbital Replaceable Units (ORU's), the replenishment of consumables, general maintenance, on-orbit assembly and repair of failures. Among economic and operational advantages are: longer spacecraft operational lifetime; lower acquisition cost of satellites; improved spacecraft performance. A comparison is made between space station and shuttle-based servicing. 相似文献
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The Small Explorer (SMEX) Project at NASA Goddard Space Flight Center (GSFC) has accumulated nearly a decade of experience building missions with the underlying philosophy of “Faster, Better, Cheaper” (FBC). Five satellites are now successfully operating on-orbit with only one serious instrument anomaly. Together this Project has accumulated 14.6 years of on-orbit experience without a spacecraft bus failure. Additionally, this project, under the Explorer Technology Infusion effort, has developed a protoflight version of a 21st Century FBC spacecraft bus that has just completed environmental qualification and has been selected at the base spacecraft for NASA's Triana mission. Design and production of these six high performance spacecraft, in just ten years time, has provided a unique base of experience from which to draw lessons learned. This paper will discuss the fundamental practices that have been used by the SMEX Project in achieving this record of success. 相似文献
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The Voyager Interstellar Mission 总被引:1,自引:0,他引:1
The Voyager Interstellar Mission began on January 1, 1990, with the primary objective being to characterize the interplanetary medium beyond Neptune and to search for the transition region between the interplanetary medium and the interstellar medium. At the start of this mission, the two Voyager spacecraft had already been in flight for over twelve years, having successfully returned a wealth of scientific information about the planetary systems of Jupiter, Saturn, Uranus, and Neptune, and the interplanetary medium between Earth and Neptune. The two spacecraft have the potential to continue returning science data until around the year 2020. With this extended operating lifetime, there is a high likelihood of one of the two spacecraft penetrating the termination shock and possibly the heliopause boundary, and entering interstellar space before that time. This paper describes the Voyager Interstellar Mission--the mission objectives, the spacecraft and science payload, the mission operations system used to support operations, and the mission operations strategy being used to maximize science data return even in the event of certain potential spacecraft subsystem failures. The implementation of automated analysis tools to offset and enable reduced flight team staffing levels is also discussed. 相似文献
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航天器在轨寿命预测与可靠性评价 总被引:2,自引:1,他引:1
文章重点分析了航天器在轨寿命和可靠性的影响因素,提出了航天器在轨寿命预测和可靠性评价的基本研究思路并分析了研究的内容,提出了航天器基础在轨寿命的概念。 相似文献
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卫星太阳电池阵在轨故障统计及分析 总被引:1,自引:0,他引:1
文章针对2000年1月至2012年9月期间79颗在轨卫星发生的114次太阳电池阵故障事件进行了分类统计分析,并利用Kaplan-Meier估计量分析方法对这些在轨故障进行了可靠性分析。结果表明:太阳电池阵的故障多发生在卫星在轨第一年,其中电子类故障发生率较高;不同卫星平台的系统缺陷或设计共性问题也与太阳电池阵故障紧密相关。最后,结合我国卫星太阳电池阵设计及制造工艺技术,提出了加强出厂前的测试和试验验证、加强仿真建模、加强冗余设计等建议。 相似文献
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《Acta Astronautica》2003,52(2-6):371-379
Under constrained budgets and rigid schedules, NASA and industry have greatly increased their utilization of small satellites to conduct low-cost planetary investigations. Recent failed small planetary science spacecraft such as Mars Polar Lander (MPL) and Mars Climate Orbiter (MCO), and impaired missions such as Mars Global Surveyor (MGS) have fueled the ongoing debate on whether NASA's “Faster, Better, Cheaper” (FBC) approach is working. Several noteworthy failures of earth-orbiting missions have occurred as well including Lewis and the Wide-field Infrared Experiment (WIRE). While recent studies have observed that FBC has resulted in lower costs and shorter development times, these benefits may have been achieved at the expense of lowering probability of success. One question remaining to be answered is when is a mission “too fast and too cheap” that it is prone to failure? This paper assesses NASA FBC missions in terms of a complexity index measured against development time and spacecraft cost. A comparison of relative failure rates of recent planetary and earth-orbiting missions are presented, and conclusions regarding dependence on system complexity are drawn. 相似文献
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归因于空间环境的航天器故障与异常 总被引:1,自引:0,他引:1
天然空间环境对航天器设计、研制和运行的影响是NASA马歇尔空间飞行中心系统分析和集成实验室电磁与航空宇宙环境部组织编写的一系列NASA RP报告的主题.其中,NASA RP-1390详细概述了天然空间环境7个主要环境因素,包括它们的简单定义、相关的型号计划事项以及对各种航天器分系统的影响.该报告提供100多个从1974... 相似文献
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《Acta Astronautica》2003,52(2-6):253-258
A Europa Lander mission has been assigned high priority for the post-2005 time frame in NASA's Space Science Enterprise Strategic Plan. Europa is one of the most scientifically interesting objects in the solar system because of the strong possibility that a liquid water ocean exists underneath its ice-covered surface. The primary scientific goals of the proposed Europa Lander mission are to characterize the surface material from a recent outflow and look for evidence of pre-biotic and possibly biotic chemistry. The baseline mission concept involves landing a single spacecraft on the surface of Europa with the capability to acquire samples of material, perform detailed chemical analysis of the samples, and transmit the results to Earth. This paper provides a discussion of the benefits and status of the key spacecraft and instrument technologies needed to accomplish the science objectives. Also described are variations on the baseline concept including the addition of small auxiliary probes and an experimental ice penetration probe. 相似文献
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The paper provides a survey of novel mission concepts for continuous, hemispheric polar observation and direct-link polar telecommunications. It is well known that these services cannot be provided by traditional platforms: geostationary satellites do not cover high-latitude regions, while low- and medium-orbit Sun-synchronous spacecraft only cover a narrow swath of the Earth at each passage. Concepts that are proposed in the literature are described, including the pole-sitter concept (in which a spacecraft is stationary above the pole), spacecraft in artificial equilibrium points in the Sun–Earth system and non-Keplerian polar Molniya orbits. Additionally, novel displaced eight-shaped orbits at Lagrangian points are presented. For many of these concepts, a continuous acceleration is required and propulsion systems include solar electric propulsion, solar sail and a hybridisation of the two. Advantages and drawbacks of each mission concept are assessed, and a comparison in terms of high-latitude coverage and distance, spacecraft mass, payload and lifetime is presented. Finally, the paper will describe a number of potential applications enabled by these concepts, focusing on polar Earth observation and telecommunications. 相似文献
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Failure of a single component on-board a spacecraft can compromise the integrity of the whole system and put its entire capability and value at risk. Part of this fragility is intrinsic to the current dominant design of space systems, which is mainly a single, large, monolithic system. The space industry has therefore recently proposed a new architectural concept termed fractionation, or co-located space-based network (SBN). By physically distributing functions in multiple orbiting modules wirelessly connected, this architecture allows the sharing of resources on-orbit (e.g., data processing, downlinks). It has been argued that SBNs could offer significant advantages over the traditional monolithic architecture as a result of the network structure and the separation of sources of risk in the spacecraft. Careful quantitative analyses are still required to identify the conditions under which SBNs can “outperform” monolithic spacecraft. In this work, we develop Markov models of module failures and replacement to quantitatively compare the lifecycle cost and utility of both architectures. We run Monte-Carlo simulations of the models, and discuss important trends and invariants. We then investigate the impact of our model parameters on the existence of regions in the design space in which SBNs “outperform” the monolith spacecraft on a cost, utility, and utility per unit cost basis. Beyond the life of one single spacecraft, this paper compares the cost and utility implications of maintaining each architecture type through successive replacements. 相似文献