TY - JOUR
T1 - Integrated optimization for single-stage-to-orbit using a pulse detonation engine
AU - Yoshida, Hiroaki
AU - Micci, Michael M.
AU - Nakane, Masakatsu
AU - Yamaguchi, Katsuhito
AU - Ishikawa, Yoshio
N1 - Funding Information:
This work was supported by Nihon University, and it was performed at the Pennsylvania State University. The first author thanks Robert Melton of the Pennsylvania State University, who provided the opportunity to conduct this study. The authors extend their deepest gratitude to all individuals who assisted in this study.
Publisher Copyright:
Copyright © 2019 by DLR e.V. (German Aerospace Center). Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2019
Y1 - 2019
N2 - A new optimization method, called the stochastic process optimization technique, was developed. The integrated optimization of single-stage-to-orbit vehicles with two different engines systems was achieved. Although the performances of the two engine types were different, similar airframe configurations and flight paths were obtained. Additionally, different flight paths for similar airframe configurations were obtained as temporary optimal solutions during the optimization process. This transition of the optimal solution reveals the relationships between the engine performance, the airframe configuration, and the flight path, on which the integrated optimization is based. It was also found that improving the specific impulse at low Mach numbers may improve the feasibility of single-stage-to-orbit vehicles.
AB - A new optimization method, called the stochastic process optimization technique, was developed. The integrated optimization of single-stage-to-orbit vehicles with two different engines systems was achieved. Although the performances of the two engine types were different, similar airframe configurations and flight paths were obtained. Additionally, different flight paths for similar airframe configurations were obtained as temporary optimal solutions during the optimization process. This transition of the optimal solution reveals the relationships between the engine performance, the airframe configuration, and the flight path, on which the integrated optimization is based. It was also found that improving the specific impulse at low Mach numbers may improve the feasibility of single-stage-to-orbit vehicles.
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U2 - 10.2514/1.A34341
DO - 10.2514/1.A34341
M3 - Article
AN - SCOPUS:85069789280
VL - 56
SP - 983
EP - 989
JO - Journal of Spacecraft and Rockets
JF - Journal of Spacecraft and Rockets
SN - 0022-4650
IS - 4
ER -