Estimation of Separation Shock of the Marman Clamp System by Using a Simple Band-Mass Model

Access this Article

Search this Article

Author(s)

Abstract

To prevent satellite failure during inter stage separation, the magnitude of separation shock must be estimated. The Marman Clamp System is a separation joint often used to mount satellites on a launch vehicle. This paper proposes a method of estimating separation shock for the Marman Clamp System. First, experimental results are discussed and the dominant parameters of separation shock are identified for the system. Next, a simple band-mass model is proposed to estimate the system’s separation shock. The differences between the model and experimental results are discussed. Radial and axial, but not tangential, separation shocks were estimated well by this method.

Journal

  • TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 45(147), 53-60, 2002-05-04

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

References:  6

Cited by:  1

Codes

  • NII Article ID (NAID)
    10008210779
  • NII NACSIS-CAT ID (NCID)
    AA0086707X
  • Text Lang
    ENG
  • Article Type
    Journal Article
  • ISSN
    05493811
  • NDL Article ID
    6170604
  • NDL Source Classification
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL Call No.
    Z53-M236
  • Data Source
    CJP  CJPref  NDL  J-STAGE 
Page Top