An efficient method for preliminary launcher/satellite coupled loads analysis by satellite developers using launcher user’s manual data

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• 作者：Constantinos Stavrinidis ; Sebastiaan Fransen
• 关键词：Satellite design loads ; Launcher user’s manual ; Launcher/satellite coupled loads analysis ; Sine vibrations ; Notching
• 刊名：CEAS Space Journal
• 出版年：2016
• 出版时间：March 2016
• 年：2016
• 卷：8
• 期：1
• 页码：13-21
• 全文大小：2,518 KB
• 参考文献：1.Stavrinidis, C.: Dynamic flight load charts for spacecraft design. In: Proc. of Presentation on Spacecraft Structure Design Verification. ESTEC, Noordwijk, The Netherlands. ESA
  2.Stavrinidis, C., Newerla, A.: Generation of Simplified Spacecraft Mathematical Models with Equivalent Dynamic Characteristics. AIAA J. Spacecr. Rockets 32(1), 117–125 (1995)CrossRef
  3.Fransen, S.: Methodologies for launcher-payload coupled dynamic analysis. Doctoral Thesis, European Space Agency, Noordwijk, The Netherlands (2005)
  4.Fransen, S.: Methodologies for Launcher-Payload Coupled Dynamic Analysis. CEAS Space J. 3, 13–25 (2012)CrossRef
  5.Arianespace: VEGA user’s manual issue 3 revision 0. In: Technical Report, ArianeSpace, Boulevard De L’Europe BP177, Evry-Courcouronnes, France (2006)
  6.Fransen S.: VEGA coupled loads analysis report–lisa path finder. In: Technical Report TEC-MSS/2013/409/ln/BF, ESA, The Netherlands (2013)
  7.Fischer, H.: VEGA coupled loads analysis report–Sentinel-2. In: Technical Report TEC-MSS/2014/507/ln/HF, ESA, The Netherlands (2014)
  8.Arianespace: ARIANE 5 user’s manual issue 5 revision 1. In: Technical Report, ArianeSpace, Boulevard De L’Europe BP177, Evry-Courcouronnes, France (2011)
  
• 作者单位：Constantinos Stavrinidis (1)
  Sebastiaan Fransen (1)
  
  1. TEC-M, European Space Agency, ESTEC, Keplerlaan 1, 2201 AZ, Noordwijk, The Netherlands
  
• 刊物类别：Engineering
• 出版者：Springer Wien
• ISSN：1868-2510

文摘

This paper presents a method used over the years by the authors in performing preliminary launcher/satellite coupled loads analysis (CLA) using in an innovative manner the quasi-static design loads defined in the launcher user’s manual (LUM). The rationale and the value of the approach are addressed first. Subsequently the use of the method is presented, and the results derived by satellite developers using the proposed preliminary launcher/satellite CLA are compared with preliminary or full CLA results performed by launcher authorities for a number of industrial satellite applications. Keywords Satellite design loads Launcher user’s manual Launcher/satellite coupled loads analysis Sine vibrations Notching