structural analysis of propulsion system components of an indigenous cryogenic rocket engine
- Paper number
IAC-08.C4.1.5
- Author
Mr. A.K. Asraff, Indian Space Research Organization, India
- Year
2008
- Abstract
The Indian Space Research Organisation has indigenously designed and is in the process of development of a cryogenic stage and engine for a future satellite launch vehicle. The engine which works using LOX/LH2 propellants is based on the gas generator cycle. The thrust chamber and gas generator of this engine are regeneratively cooled and of double walled construction. Regenerative cooling is achieved by passing liquid hydrogen through rectangular coolant passages milled on outer surface of the inner wall. The coolant channels of the gas generator are axial whereas that for the thrust chamber are of helical pattern for up to an area ratio of 10 after which they are kept straight. Number of coolant passages also varies along the length of the chamber. This paper deals with the three dimensional structural analysis of major liquid propulsion systems of the above liquid rocket engine viz. thrust chamber, gas generator, LH2 turbo-pump, LOX turbo-pump and hot gas ducts. Stress analysis of ground facilities for hot testing of GG and TP’s are also discussed. Material, geometric and contact nonlinearities are considered in the analysis. Double walled regions of the thrust chamber and gas generator are idealized using layered shell elements whereas for other zones, uni-layered shell elements are employed. Figure 1 shows the configuration of the thrust chamber having an area ratio of 100. Ground test facility ducts, supports, bellows, flexible hoses etc. are idealized using pipe, beam and spring elements. Both thermal and pressure loads are accounted for in the analysis. High temperature mechanical properties of the engine materials available from in-house testing as well as literature are input for analysis. Analysis has been carried out for engine subsystems in their ground test as well as flight configurations. Stress analysis of the fully integrated engine required high computing power since a large number of shell elements are involved. ANSYS (Revision 11) FEA software package implemented in a Pentium 4 based workstation is used for modeling and analysis. In this paper, various modeling, stress analysis and design techniques for the propulsions systems and components of the engine are discussed. Results are presented in tabular and graphical forms and conclusions are drawn.
- Abstract document
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