정상 해석 기반의 데이터베이스를 이용한 TSTO 비행체의 분리 궤도 예측

다국어 초록 (Multilingual Abstract)

In this paper, prediction of separation trajectory for Two-stage-To-Orbit space launch vehicle has been numerically simulated by using an aerodynamic database based on steady state analysis. Aerodynamic database were obtained for matrix of longitudinal and vertical positions. The steady flow simulations around the launch vehicle have been made by using a 3-D RANS flow solver based on unstructured meshes. For this purpose, a vertex-centered finite-volume method was adopted to discretize inviscid and viscous fluxes. Roe’s finite difference splitting was utilized to discretize the inviscid fluxes, and the viscous fluxes were computed based on central differencing. To validate this flow solver, calculations were made for the wind-tunnel experiment model of the LGBB TSTO vehicle configuration on steady state conditions. Aerodynamic database was constructed by using flow simulations based on test matrix from the wind-tunnel experiment. ANN(Artificial Neural Network) was applied to construct interpolation function among aerodynamic variables. Separation trajectory for TSTO launch vehicle was predicted from 6-DOF equation of motion based on the interpolated function. The result of present separation trajectory calculation was compared with the trajectory using experimental database. The predicted results for the separation trajectory shows fair agreement with reference[4] solution.

참고문헌 (Reference)

1 Decker. J.P., "Technology and methodology of separating two similer size aerospace vehicles within the atmosphere" AIAA

2 Bordelon, W.J., "Stage Separation Wind Tunnel tests of a Generic Two-Stage-to-Orbit Launch Vehicle" AIAA 2003

3 Pamadi, B.N., "Simulation and analyses of Staging Maneuvers of Next Generation Reusable Launch Vehicles" AIAA 2004

4 Pamadi. B.N, "Simulation and Analyses of Stage Separation of Two-Stage Reusable Launch Vehicles" 44 : 2007

5 Broomhead, D.S, "Radial Basis Functions, Multi-variable Functional Interpolation and Adaptive Networks" Royal Signals and Radar Establishment 1988

6 Murphy. K.J, "Overview of transonic to hypersonic stage separation tool development for multi-stage-to-orbit concepts" AIAA

7 Murphy, K.J., "Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-to-Orbit concepts" AIAA 2004

8 Venkatakrishnan, V., "On the Accuracy of Limiters and Convergence to Steady State Solutions" AIAA 1993

9 Murphy K.J, "Experiment stage separation development in Langley’s Unitary Plan Wind Tunnel" AIAA

10 Buning, P.G, "CFD Approaches for simulation of Wing-Body Stage Separation" AIAA 2004

11 Pamadi B.N., "Ascent, stage separation and glideback performance of a partially reusable small launch vehicle" AIAA

12 Pamadi, B.N., "Ascent, Stage Separation and Glideback Performance of a Partially Reusable Small Launch Vehicle" AIAA 2004

13 Roe, P.L., "Approximate Riemann Solvers, Parameter Vectors and Difference Scheme" 43 : 357-372, 1981

14 Spalart, P.R., "A One-Equation Turbulence Model for Aerodynamic flows" AIAA 1992

15 McCulloch, W.S., "A Logical Calculus of Ideas Immanent in Nervous Activity" 5 : 115-133, 1943