Abstract
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.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 983-989 |
| Number of pages | 7 |
| Journal | Journal of Spacecraft and Rockets |
| Volume | 56 |
| Issue number | 4 |
| DOIs | |
| State | Published - Jan 1 2019 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science
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Integrated optimization for single-stage-to-orbit using a pulse detonation engine. / Yoshida, Hiroaki; Micci, Michael M.; Nakane, Masakatsu; Yamaguchi, Katsuhito; Ishikawa, Yoshio.
In: Journal of Spacecraft and Rockets, Vol. 56, No. 4, 01.01.2019, p. 983-989.Research output: Contribution to journal › Article
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
PY - 2019/1/1
Y1 - 2019/1/1
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.
UR - http://www.scopus.com/inward/record.url?scp=85069789280&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85069789280&partnerID=8YFLogxK
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 -