本文關鍵詞： 軸系組件 固體潤滑角接觸球軸承 故障模式與影響分析 失效模型 等效試驗理論 加速壽命試驗　出處：《北華航天工業(yè)學院》2015年碩士論文　論文類型：學位論文

【摘要】：隨著北斗二代導航衛(wèi)星向著服務型開始轉變,導航衛(wèi)星上的驅動機構就要求向長壽命、高精度、高可靠性技術方向發(fā)展,軸系組件作為導航星間鏈路驅動機構的關鍵執(zhí)行組件,其性能下降或故障會導致整個導航衛(wèi)星驅動機構的失效,進而造成整個衛(wèi)星的指向精度的降低甚至失效。在軌階段期間,軸系組件需長時間間歇往復運轉上百萬次,這就對軸系組件的長壽命、高可靠性提出了極高的要求,因此需要進行一定樣本軸系組件的可靠性試驗來驗軸系組件的可靠性及壽命。由于傳統(tǒng)壽命試驗不能實現(xiàn)航天任務時間節(jié)點的要求,而且浪費了大量的資金和人力,有必要對驅動機構軸系組件通過加速壽命試驗,以期驗證機構的設計壽命和可靠性是否能夠滿足衛(wèi)星要求�；诖�,本研究項目主要開展了如下研究工作:對軸系組件進行了故障模式與影響分析,并最終確定固體潤滑角接觸球軸承作為影響軸系組件性能和壽命的關鍵部件和薄弱環(huán)節(jié)。研究了加速壽命試驗的等效理論,采用完全壽命試驗,并以軸系組件的摩擦力矩和旋轉精度作為失效判據(jù)。完成了軸系組件加速壽命試驗技術總體的規(guī)劃,基于軸系組件物理的失效機理和失效模型,以速度和軸向預緊力作為加速應力開展了雙應力加速壽命試驗,采用恒定應力的加速壽命試驗方法。對軸系組件加速壽命試驗裝置設備進行了設計和開發(fā),實現(xiàn)了判據(jù)數(shù)據(jù)的實時監(jiān)測和采集處理,實現(xiàn)軸系的運行情況的監(jiān)測和壽命判斷。本文在加速壽命試驗數(shù)據(jù)的基礎上,分析軸系組件的性能參數(shù)的退化情況以及通過加速壽命數(shù)據(jù)得到的軸系組件偽壽命推出正常工況下的壽命,驗證軸系組件的壽命符合設計要求,并對不同預緊力的軸系壽命進行分析,最后對軸系組件施加適當預緊力提供實驗數(shù)據(jù)支持。
[Abstract]:With the change of Beidou second generation navigation satellite to service type, the driving mechanism of navigation satellite needs to develop towards long life, high precision and high reliability technology. As the key executive component of the navigation intersatellite link driving mechanism, the shaft system performance degradation or failure will lead to the failure of the whole navigation satellite driving mechanism. During the orbit phase, the shafting module needs a long time intermittent reciprocating operation millions of times, which is the long life of the shafting module. High reliability puts forward very high requirements. Therefore, the reliability test of a certain sample shafting assembly is needed to verify the reliability and life of the shaft assembly. Because the traditional life test can not meet the requirements of the spaceflight mission time node. And wasted a lot of money and manpower, it is necessary to the driving mechanism shafting components through accelerated life test, in order to verify that the design life and reliability of the mechanism can meet the requirements of the satellite. The main work of this research project is as follows: the failure mode and influence analysis of shafting components are carried out. Finally, the solid lubricated angular contact ball bearing is determined as the key component and weak link to affect the performance and life of the shafting assembly. The equivalent theory of accelerated life test is studied, and the complete life test is adopted. Taking the friction moment and rotation precision of the shafting assembly as the failure criterion, the overall planning of the accelerated life test technology of the shafting assembly is completed, based on the physical failure mechanism and failure model of the shafting assembly. Double stress accelerated life test was carried out with speed and axial preload as acceleration stress. The accelerated life test equipment of shafting assembly was designed and developed by using constant stress accelerated life test method. The real-time monitoring and processing of the criterion data and the monitoring and life judgement of the shaft system are realized. This paper is based on the accelerated life test data. The degradation of the performance parameters of the shafting assembly is analyzed and the pseudo-life of the shafting component obtained from the accelerated life data is derived under normal working conditions to verify that the life of the shafting assembly meets the design requirements. The service life of shafting with different pretightening forces is analyzed, and the experimental data are provided to support the shafting components with proper pretightening forces.
【學位授予單位】：北華航天工業(yè)學院
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V416

【引證文獻】

相關會議論文 前1條

1 上官愛紅;穆猷;李治國;劉朝暉;王振宇;;空間二維轉動機構的熱真空準加速壽命試驗設計[A];中國空間科學學會2013年空間光學與機電技術研討會會議論文集[C];2013年

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本文編號：1480671