Numerical Analysis of Reverse Jet Effect on the aerodynamic characteristics of SSTO configuration with an Aerospike Nozzle in Landing Phase

Paper number

IAC-05-D2.5.02

Author

Ms. Harumi Tsukada, Yokohama National University, Japan

Coauthor

Mr. Keiichiro Fujimoto, University of Tokyo, Japan

Coauthor

Dr. Koji Miyaji, Yokohama National University, Japan

Coauthor

Prof. Kozo Fujii, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan

Year

2005

Abstract

Fully reusable, single-stage-to-orbit (SSTO) launch vehicle system has potential to fulfill the requirements of space transportation systems in the next generation such as low launching costs and high reliability and flexibility. At Institute of Space and Astronautical Science / Japan Aerospace Explanation Agency (ISAS/JAXA) in Japan, ground and flight tests of a vertical takeoff and vertical landing (VTVL) SSTO rocket system are presently conducted for the establishment of basic technologies. Technology of soft landing with opposing jet is one of the key issues for the realization of the VTVL-SSTO rocket system. Therefore understanding of the effects of the interactions between the external flow and the jet is important.
In this paper, flow fields around conical SSTO vehicle configurations with aerospike nozzle, which has better performance than conventional bell-shaped nozzle from the sea level to the high altitude as it adjusts the jet boundary to the ambient pressure, are computationally investigated using the Reynolds-averaged Navier-Stokes simulations. The exhausted jet from the aerospike nozzle is simulated and the interactions between the external flow and the jet are investigated. The computational results showed that circulation regions are generated near the ramp base and between the free-stream and the flows induced by jet. In all cases with the jet, the pressure level between the nose and the edge of the conical body is larger than that of without jet case because the large-scale separation is suppressed by circulation regions generated by the interaction between the free-stream and the reverse jet. Pressure level of the ramp base also changes due to the circulation region as the thrust of the jet changes. The computation turned out that experiments or CFD analyses are necessary to estimate the axial force of the entire body because the aerodynamic force on both nose region and ramp region change. So that means it is impossible to estimate the axial force of the entire body by a linear summation of the thrust of each case with the jet and the aerodynamic force of without jet case. In addition, the computational results indicate that exhausted jet results in decrease of axial force for deceleration under a certain thrust condition.

Abstract document

IAC-05-D2.5.02.pdf

Manuscript document

IAC-05-D2.5.02.pdf (🔒 authorized access only).

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