航速和海风仪表的故障保护设计

M. B. Bennett, J.F. Smith, W. Wilkinson
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引用次数: 0

摘要

quickscat和SeaWinds仪器是雷达散射计仪器,将用于测量海洋表面风。QuikScat仪器将于1998年11月在专用航天器上发射,海风仪器将于2000年夏天在日本的ADEOS-II航天器上发射。该仪器被设计为在几乎整个三年的任务中持续以风观测模式运行。然而,一些故障和外部条件可能会发生,这将中断仪器的连续风观测。这些类型的故障包括雷达单元的TWTA故障,与航天器的通信错误,仪器三个子系统之间的通信错误,计算机子系统中的软件错误,以及宇宙射线或太阳引起的仪器计算机中单一事件干扰的可能影响。一般来说,仪器自动故障响应的原理是执行不同级别的复位,以清除导致特定类型问题的故障。一般来说,仪器试图从故障中恢复,使仪器在没有地面干预的情况下恢复正常运行。但是,如果仪器中的自主算法无法通过合理的努力清除故障,仪器将自己置于安全待机模式并等待地面交互。在任何情况下,仪器都不会试图通过切换冗余单元来恢复故障。冗余单元的切换只能在地面的指挥和控制下进行。本文描述了航天器中设计的故障保护机制,以便对仪器中的某些故障和故障作出反应。此外,本文还解释了这些机制在初始响应未清除故障时如何升级其响应。此外,这篇文章还描述了在航天器故障需要关闭仪器的情况下,航天器将代表仪器采取的行动。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Fault protection design of the quikscat and seawinds instruments
The QuikScat and SeaWinds instruments are radar scatterometer instruments that will be used to measure ocean surface winds. The QuikScat instrument will be launched on dedicated spacecraft in November 1998, and the SeaWinds instrument will be launched on the Japanese ADEOS-II spacecraft in the summer of 2000. The instrument is designed to continuously operate in a wind observation mode for nearly the entire three year mission. However, a number of fault and external conditions can occur that will interrupt the instrument's continuous wind observations. These types of faults include the failures in the radar unit's TWTA, communication errors with the spacecraft, communication errors between the instrument's three subsystems, software errors in the computer subsystem, and possible effects of cosmic ray or solar induced single event upsets in the instrument's computers. In general, the philosophy of the instrument's autonomous fault response is to perform different levels of resets in order to clear a fault that is causing a particular type of problem. In general, the instrument attempts to recover from the fault in a manner that will allow the instrument to resume normal operations without ground intervention. However, if the fault does not clear with a reasonable level of effort by the autonomous algorithms in the instrument, the instrument places itself into a safe standby mode and waits for ground interaction. In no case does the instrument attempt to recover from faults by switching redundant units. The switching of redundant units is to only be performed under command and control from the ground. This paper describes the fault protection mechanisms that have been designed into the spacecraft, in order to react to certain faults and failures in the instrument. In addition, it explains how these mechanisms escalate their response when a fault is not cleared by their initial response. Also, this write-up describes the actions that the spacecraft will take on behalf of the instrument in the case of a spacecraft failure that will require the shutdown of the instrument.
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