Supersonic flight separation simulation for TSTO launch vehicles considering shock wave interaction reduction

Taro Uematsu, Shigeru Aso, Yasuhiro Tani

Research output: Contribution to conferencePaper

Abstract

This paper shows a study on separation simulation of T ST O system in hypersonic flow .The booster has three types cross-section configuration, square, triangle and circle. The orbiter is a wing-body configuration and a hemispherical cylinder . Results of wind tunnel experiments show that the orbiter being relatively small to the booster is afected by shock wave interference. Especially , The orbiter pitching moment have diferent inclination for changing clearance length. Results of the numerical calculations show the lift of the booster decrease and the pitching moment increase with increasing the length. Increasing pressure rise area causes the lift of the booster decreasing with increasing the length. Also, both of the results show that the triangle cross-section configuration of the booster shows significant reduction effect against shock wave interference.

Original languageEnglish
DOIs
Publication statusPublished - Dec 1 2012
Event50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition - Nashville, TN, United States
Duration: Jan 9 2012Jan 12 2012

Other

Other50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
CountryUnited States
CityNashville, TN
Period1/9/121/12/12

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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    Uematsu, T., Aso, S., & Tani, Y. (2012). Supersonic flight separation simulation for TSTO launch vehicles considering shock wave interaction reduction. Paper presented at 50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Nashville, TN, United States. https://doi.org/10.2514/6.2012-253