Multidisciplinary Optimization of Space Transportation Systems
- Paper number
IAC-05-D1.3.04
- Author
Dr. Naoshi Kuratani, Japan Aerospace Exploration Agency (ISTA/JAXA), Japan
- Coauthor
Mr. Hirokazu SUZUKI, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr.-Ing. Robert Goehlich, Japan Aerospace Exploration Agency (JAXA), Germany
- Year
2005
- Abstract
In this paper, a summary of a concept study program for a multidisciplinary optimization of space transportation systems developed by JAXA and results of optimal design for several types of reusable space transportation systems will be introduced. The program helps to design the optimal transportation system based on technical data base and analytical methods. The objective is to formulate strategies for future investigation in reusable space transportation systems. The program is composed by an inner loop and an outer loop. The former is used to calculate an approximate solution while the later one is used to perform a more precise analysis. The inner loop has six subroutines: aerodynamics, propulsion, weight estimation, flight analysis, thermal protec-tion system design and cost evaluation. Aerodynamic characteristics are estimated based on Panel method, Tangent Cone / Wedge method and Newtonian method. Aerodynamic heating on the surface of body is estimated by Fay-Riddell, equation of Cunningham-Haney and Eckert’s Reference temperature method. Performances and weight of four types of rocket propulsion (Staged-Combustion, Gas-Generator, Expander and Expander-Bleed) and five types of turbo propulsion (Turbojet, Ramjet, PCTJ, ATREX and Gas-Generator ATR) are calculated by the propulsion sub-routine. Weight of the vehicle is estimated by HASA, WAATS and analytical method. Flight analysis optimizes ascent and re-entry trajectories and vehicle size. Thermal protection system is de-signed based on aerodynamic heating. Life-cycle costs are estimated by using TRANSCOST 7.1. Seven types of transportation systems are designed optimally using this concept study program. A reference mission of a 1 Mg payload into Low Earth Orbit with 0 degree inclination angle, vehicles take off from Equator and 200 km altitude is set. Take-off weight is selected as performance index. Vehicle size, flight time and time histories of angle of attack and throttle are determined to minimize take-off weight.
- Abstract document
- Manuscript document
IAC-05-D1.3.04.pdf (🔒 authorized access only).
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