1、Lessons Learned Entry: 0400Lesson Info:a71 Lesson Number: 0400a71 Lesson Date: 1995-06-08a71 Submitting Organization: JPLa71 Submitted by: J. LangmaierSubject: Spacecraft Structure Dynamical Interaction with Attitude Control Abstract: As Mariner 10 approached Venus encounter, an uncontrolled oscilla
2、tion occurred due to spacecraft structural interaction with the Attitude Control Subsystem. The result was a severe consumption of control gas that would have caused failure of the mission had it continued. The recommendations center on design and operational measures to cope with subtle and complex
3、 dynamical interactions between the spacecraft structure and the ACS.Description of Driving Event: As Mariner 10 (MVM73) was nearing encounter with Venus, an uncontrolled oscillation occurred due to spacecraft structural interaction with the Attitude Control Subsystem. The problem was first detected
4、 during a platform calibration sequence, which required a series of roll turns using roll gyroscope inertial control, and science scan platform motion. The result was a severe consumption of control gas which would have caused failure of the mission had it continued.The oscillation was due to a cont
5、rol instability exciting a structural mode of the spacecraft. The primary cause of the resonance was attributed to the flexibility of the solar panels.Additional Keyword(s): Flexible Body AnalysisReference(s): PFR #5024.Lesson(s) Learned: Spacecraft structural dynamical interactions with the Attitud
6、e Control Subsystem can be very subtle and complex.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Recommendation(s): 1. During the spacecraft design phase, consideration should be given to: a. Increasing the amount of analysis on and simulation of s
7、tructural / control interactions.b. Placing additional or tighter controls on key parameters at interfaces between structures and attitude control.c. Establishing procedures for communicating key parameter data between subsystem engineers and analysts, initially and when changed.2. In situations whe
8、re there is significant uncertainty in simulations, models, or analysis results, the spacecraft subsystem software should be designed so as to accommodate changes late in the development, test, and post-launch periods. Techniques such as modular design and parameter tables vs. hard coding should be
9、considered.3. The capability to cope with this type of anomaly, by analysis and simulation, should be maintained throughout the mission.Evidence of Recurrence Control Effectiveness: N/ADocuments Related to Lesson: N/AMission Directorate(s): N/AAdditional Key Phrase(s): a71 Flight Equipmenta71 Hardwa
10、rea71 Softwarea71 SpacecraftAdditional Info: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Approval Info: a71 Approval Date: 1987-07-16a71 Approval Name: Carol Dumaina71 Approval Organization: 125-204a71 Approval Phone Number: 818-354-8242Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
