REG NASA-LLIS-0436--1996 Lessons Learned - Receiver 1 Power Converter Failure on Voyager 2 (1978).pdf
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1、Lessons Learned Entry: 0436Lesson Info:a71 Lesson Number: 0436a71 Lesson Date: 1996-07-17a71 Submitting Organization: JPLa71 Submitted by: J.A. RobertsSubject: Receiver 1 Power Converter Failure on Voyager 2 (1978) Abstract: A Voyager telemetry failure was attributed to over-length screws that cause
2、d conductive end-caps to contact areas not sufficiently coated by conformal coating. The lesson provides recommendations for design of captivated inserts, QA monitoring of assembly, application of conformal coatings, and planning of ground activities.Description of Driving Event: (Relevant Historica
3、l Lesson(s) Learned)Voyager 2 Receiver 1 operated normally from launch until an inadvertent activation of the on-board command loss routine switched it out and put Receiver 2 into use. Receiver 2 would not lock to the uplink to receive a command to stop the loss routine, and it later was found to ha
4、ve a shorted loop capacitor. Twelve hours later, the routine again selected Receiver 1. The Voyager flight team, knowing the spacecraft was already on the High-Gain Antenna (HGA), transmitted a series of HGA select commands to stop the routine without having any other effect on the spacecraft. The f
5、irst command of the series was received and stopped the routine. Several receiver telemetry channels began changing unexpectedly between two subsequent HGA select commands, and within 11 seconds the receiver power converter had failed; this was one-half hour after Receiver 1 had been turned back on.
6、 Anomalous telemetry data occurred in other subsystems during the receiver failure, with several indications in the photopolarimeter and an in crease in radio frequency noise in one channel of the harmonic radiation experiment of the planetary radio astronomy instrument.The Voyager document, “Voyage
7、r 2 Command Receiver 1 Failure Analysis,“ details the telemetered failure indications and measurements from the other subsystems sent at the same time. It also hypothesizes a failure model fitting all the observations and based on confirming laboratory testing Provided by IHSNot for ResaleNo reprodu
8、ction or networking permitted without license from IHS-,-,-of Voyager assemblies, subsystems, and instruments.Additional Keyword(s): Surveillance, Captive Inserts, Conformal Coatings, Mission OperationsReference(s):1. Project Document 618-817, “Voyager 2 Command Receiver 1 Failure Analysis,“ Arthur
9、G. Gussner, Oct. 19792. Voyager Incident Surprise Anomaly (ISA) 1783, and Voyager P/FR 41029Receiver Failure Model:The hypothesized failure model asserts that a resistive short from the 30-volt return line to chassis existed somewhere in the spacecraft at the time of the receiver failure. This first
10、 short had no effect on operation by itself and could not be detected by telemetry. Then a short to chassis occurred in the receiver, intermittent during the first three seconds and then continuous. This second short completed the short circuit and caused the receiver fuses to open. The location of
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