An integrated optimization for conceptual designs of airbreathing launch TSTO vehicle

Abstract

This paper presents the application of an optimization method to conceptual designs of fully reusable TSTO (Two-Stage-To-Orbit) spaceplanes. TSTO spaceplane is under consideration for the future space transportation vehicle Japan aims to develop and realize in the near future. Technical fields for vehicle designs in this paper are aerodynamic analysis, engine analysis, weight analysis, and trajectory analysis, which are integrated and optimized simultaneously by an optimization method proposed herein. A payload weight is defined as an index of the feasibility of spaceplanes, and the best shape and trajectories maximizing the payload weight are indicated. The results show the effectiveness of the proposed numerical methods and necessity of the further weight reduction to realize future space transportation vehicles.

Wind Tunnel Test of Mach 5 Class Hypersonic Airplane

“…In the simple aerodynamic analysis 7) , we used PAN AIR for the subsonic flow, which was considered to be an isentropic flow in a non-viscous fluid. Furthermore, we used the Local Surface Inclination method 8,9) for the supersonic flow, and the estimation was performed using the Prandtl-Meyer expansion flow theory for the expansion side and the Tangent Cone/Wedge method for the compression side.…”

Staging of Two-Stage-to-Orbit Aerospace Plane

“…Studies have been conducted on the TSTO of factors such as the aerodynamic interaction between the first-stage and the second-stage vehicles 1,2) and the conceptual design of vehicles and flight trajectory. [3][4][5][6][7][8][9] At staging, the first-stage vehicle releases the secondstage vehicle, and the mass of the vehicle decreases by about 50% due to disconnection of the second-stage vehicle. Thus, gravity acting on the first-stage vehicle decreases.…”