Hostname: page-component-cd9895bd7-dzt6s Total loading time: 0 Render date: 2024-12-27T06:07:25.121Z Has data issue: false hasContentIssue false
  • English
  • Français

Parametric analysis of ply properties on composite cylinder design for spacecrafts

Published online by Cambridge University Press:  10 May 2006

Vijayakumar Sahadevan
Vijayakumar Sahadevan*
Affiliation:
Laboratoire d'Ingénierie des Systèmes Mécaniques et des Matériaux, Institut Supérieur de Mécanique de Paris, 3 rue Fernand Hainaut, 93407 Saint Ouen Cedex 01, France
*
vijay.koumar@gmail.com
Get access

Abstract

This paper presents the parametric analysis of ply properties on composite cylinder design for satellites. The composite cylinder is modelled as a sandwich construction type with honeycomb as a core and a multi-layer laminate composed of CFRP (Carbon Fiber Reinforced Plastics) plies as a skin. A design algorithm is developed with the help of C programs interfaced with IDEAS EDS for finite element analysis. During simulation, the different subsystems and panels are idealised as a mass load applied at their centre of gravities. Different parameters such as aspect ratio, ply orientation and number of plies have been analysed for arriving optimum design satisfying the static and frequency constraints. This approach is well implemented in the design and development of composite cylinder for different satellites and their validation with tests are under development.

Keywords

Finite elementssatellitesstructural analysiscompositesIDEASÉlément finissatellitescalcul de structurecompositesIDEAS
Type
Research Article
Information
Mechanics & Industry , Volume 7 , Issue 1 , January 2006 , pp. 57 - 62
Copyright
© AFM, EDP Sciences, 2006

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

T.P. Sarafin, Spacecraft structures and mechanisms from concept to launch, Microcosm Inc, USA, 1995
H. Baeir, T. Puhlofer, Approaches for further rationalization in mechanical architecture and structural design of satellites, Proceeding of 54th International Astronautical Congress, Bremen, Germany, IAC-03-I 102, 2003
D.R. Mulville, Load analysis of spacecraft and payloads, NASA-STD-5002, 1996
H.R. Goldberg, B.T. Cesul, B.E. Gilchrist, The ICARUS student satellite – A fully autonomous student built small satellite for NASA, Proc. of 16th annual AIAA/USU Conference on Small Satellites, SSC02-I-7, 2002
Skullney, W.E., Kreitz, H.M., Harold, M.J., Vernon, S.R., Betenbaugh, T.M., Hartka, T.J., Persons, D.F., Schafer, E.D., Structural design of the MSX spacecraft, John Hopkins APL Technical Digest 17 (1996) 59–76
Simplified, W. Sodel equations and solutions for the vibration of orthotropic cylindrical shells, J. Sound Vibration 87 (1983) 555–566
Sharma, C.B., Darvizeh, M., Darvizeh, A., Free vibration response of multilayered orthotropic fluid-filled circular cylindrical shells, Composite structures 34 (1996) 349–355 CrossRef
S.W. Tsai, H.A.T. Hahn, Introduction to composite materials, Technomic, USA, 1980
J.R. Vinson, The behavior of structures composed of composite materials, Martinus Nijhoff, USA, 1986
Reese, C.D., Bert, C.W., Simplified design equations for buckling of axially compressed sandwich cylinders with orthotropic facings and core, J. Aircraft 6 (1999) 515–519
S. Vijayakumar, S.K. Basha, R.K. Srinivasan, Design details of CFRP honeycomb sandwich cylinder for I-3000 bus, Structures Group, ISRO, India, 2002
Vijayakumar, S., Parametric based design CFRP honeycomb sandwich cylinder for a spacecraft, Composite Structures 65 (2004) 7–12 CrossRef
Scharton, T.D., Vibration and acoustic testing of spacecraft, J. Sound and Vibration 6 (2002) 1–5
IDEAS User's manual, SDRC, USA, 2000