| タイトル | Analysis of a New Rocket-Based Combined-Cycle Engine Concept at Low Speed |
| 本文（外部サイト） | http://hdl.handle.net/2060/19990081112 |
| 著者（英） | Yungster, S.; Trefny, C. J. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 1999-09-01 |
| 言語 | eng |
| 内容記述 | An analysis of the Independent Ramjet Stream (IRS) cycle is presented. The IRS cycle is a variation of the conventional ejector-Ramjet, and is used at low speed in a rocket-based combined-cycle (RBCC) propulsion system. In this new cycle, complete mixing between the rocket and ramjet streams is not required, and a single rocket chamber can be used without a long mixing duct. Furthermore, this concept allows flexibility in controlling the thermal choke process. The resulting propulsion system is intended to be simpler, more robust, and lighter than an ejector-ramjet. The performance characteristics of the IRS cycle are analyzed for a new single-stage-to-orbit (SSTO) launch vehicle concept, known as "Trailblazer." The study is based on a quasi-one-dimensional model of the rocket and air streams at speeds ranging from lift-off to Mach 3. The numerical formulation is described in detail. A performance comparison between the IRS and ejector-ramjet cycles is also presented. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | NASA/TM-1999-209393
NAS 1.15:209393
AIAA Paper 99-2393
E-11824
ICOMP-99-05 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/95885 |
