Analysis of parameter sensitivity on dynamics of satellite separation

Abstract Dynamic characteristics of satellite separation are synthetical results of various influencing factors. However, there have been few quantitative investigations on impact evaluation of crucial parameters on dynamics of satellite separation. In this paper, an improved dynamic simulation model of the typical satellite separation system considering the flexibility of interface rings is established based on the authors׳ previous work. The dynamic-envelope radius of seventh V-segment and the shock response amplitude in horizontal section of SRS curves are, respectively, taken as evaluation index to perform the analyses of parameter sensitivity. Subsequently, an improved Response Surface Methodology (RSM) for analyzing parameter sensitivity of dynamics of satellite separation is proposed. Finally, the impact evaluations of different parameters are carried out, respectively, by performing the sensitivity analysis on dynamic-envelope of clamp band and satellite separation shock responses to determine the most important parameters that significantly influence the dynamic characteristics. It is revealed from the studies that the parameter which has the most prominent effect on the dynamic-envelope of clamp band is the stiffness of lateral-restraining spring. While for the axial and radial separation shock responses, the preload of clamp band and the density of V-segments are respectively the most influential parameters. The research results in the paper can provide a reference for the initial engineering design of the clamp band joint of satellite separation systems to guarantee a secure and reliable separation event.

[1]  Sang Hyo Kim,et al.  Response surface method using vector projected sampling points , 1997 .

[2]  Ramana V. Grandhi,et al.  Studies on optimization of metal forming processes using sensitivity analysis methods , 2004 .

[3]  H. Binabaji,et al.  Sensitivity analysis of flexible joint nonholonomic wheeled mobile manipulator in singular configuration , 2012 .

[4]  Shaoze Yan,et al.  Dynamic analysis of clamp band joint system subjected to axial vibration , 2010 .

[5]  J Singaravelu,et al.  Reliability and Safety Assessments of the Satellite Separation Process of a Typical Launch Vehicle , 2012 .

[6]  Qingbin Zhang,et al.  Dynamics and transient perturbation analysis of satellite separation systems , 2013 .

[7]  Marco B. Quadrelli,et al.  Sensitivity studies of the deployment of a square inflatable solar sail with vanes , 2009 .

[8]  Shaoze Yan,et al.  Dynamic-Envelope Analysis of Clamp-Band Joint Considering Pyroshock of Satellite Separation , 2014 .

[9]  Bertrand Iooss,et al.  Response surfaces and sensitivity analyses for an environmental model of dose calculations , 2006, Reliab. Eng. Syst. Saf..

[10]  Shigemasa Ando,et al.  Simplified SRS Prediction Method for Pyroshock Source of V-band Clamp Separation Devices , 2007 .

[11]  Takashi Iwasa,et al.  Calculation Method for Flight Limit Load of V-band Clamp Separation Shock , 2010 .

[12]  Javier Domínguez-Hernández,et al.  The use of response surface methodology to improve the thermal transmittance of lightweight concrete hollow bricks by FEM , 2014 .

[13]  Shaoze Yan,et al.  Dynamic characteristics of launch vehicle and spacecraft connected by clamp band , 2011 .

[14]  Yan Shaoze.  Dynamic simulations and failure analysis of a clamp band system for spacecraft , 2010 .

[15]  Jonsson Martin.  Development of a shock test facility for qualification of space equipment , 2012 .

[16]  Takashi Iwasa,et al.  Simplified Estimating Method for Shock Response Spectrum Envelope of V-Band Clamp Separation Shock , 2008 .

[17]  Shinsuke Takeuchi,et al.  Estimation of Separation Shock of the Marman Clamp System by Using a Simple Band-Mass Model , 2002 .

[18]  Jun Lan Li,et al.  Modeling and Simulation of Clamp Band Dynamic Envelope in a LV/SC Separation System , 2011 .

[19]  Shaoze Yan,et al.  Analysis of parameter sensitivity of space manipulator with harmonic drive based on the revised response surface method , 2014 .

[20]  Jae-Hung Han,et al.  Ornithopter flight simulation based on flexible multi-body dynamics , 2010 .

[21]  Yong Zhao,et al.  Optimization design of satellite separation systems based on Multi-Island Genetic Algorithm , 2014 .

[22]  Soo-Chang Kang,et al.  An efficient response surface method using moving least squares approximation for structural reliability analysis , 2010 .

[23]  C. Bucher,et al.  A fast and efficient response surface approach for structural reliability problems , 1990 .

[24]  Yan Shaoze.  Axial Stiffness Analysis of Clamp Band System , 2009 .

[25]  Massimiliano Vasile,et al.  Contingency and recovery options for the European Student Moon Orbiter , 2014 .

[26]  Shaoze Yan,et al.  Finite element analysis of the clamp band joint , 2012 .

[27]  B. Nageswara Rao,et al.  Dynamics of satellite separation system , 2006 .

[28]  K. K. Biswas,et al.  Rigid body separation dynamics for space launch vehicles , 2006, The Aeronautical Journal (1968).

[29]  Shaoze Yan,et al.  Influence of clamp band joint on dynamic behavior of launching system in ascent flight , 2014 .