Experimental Demonstration of the Vacuum Specific Impulse of a Hybrid Rocket Engine

被引：8

作者：

Lestrade, Jean-Yves ^{[1
]}

Anthoine, Jerome ^{[2
,6
]}

Verberne, Onno ^{[3
,6
]}

Boiron, Adrien J. ^{[4
,6
]}

Khimeche, Gael ^{[5
]}

Figus, Christophe ^{[5
]}

机构：

[1] Off Natl Etud & Rech Aerosp, Aerodynam & Energet Modeling Dept, F-31410 Mauzac, France

[2] Off Natl Etud & Rech Aerosp, Aerodynam & Energet Modeling Dept, Prop Lab, F-31410 Mauzac, France

[3] Nammo AS, Technol & Business Dev, N-2830 Raufoss, Norway

[4] Nammo AS, N-2830 Raufoss, Norway

[5] Airbus Def & Space, F-31402 Toulouse, France

[6] AIAA, Reston, VA USA

来源：

JOURNAL OF SPACECRAFT AND ROCKETS | 2017年 / 54卷 / 01期

关键词：

D O I：

10.2514/1.A33467

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper presents the experimental results of a hybrid rocket engine fired both at ambient pressure and under low-pressure conditions. The hybrid engine includes a catalyst bed and a vortex injector, and it is fitted with ultrasound sensors to measure the instantaneous fuel regression rate. These tests have enabled demonstration of the experimentally achievable specific impulse of the hybrid rocket technology under low-pressure conditions and validated the extrapolation of experimental results at ambient pressure to vacuum pressure conditions. The demonstrated combustion efficiency is above 98%, and the specific impulse is experimentally proven to be above 270s for a conical nozzle with an expansion ratio of 50.

引用

页码：101 / 108

页数：8

共 19 条

[1] Anthoine J., 2010, 61 INT ASTR C
[2] Anthoine J., 2011, 4 EUR C AER SCI
[3] Barrere M., 1967, INT SCI TECHNOLO AUG, P64
[4] Calabro M., 2007, 58 INT ASTR C
[5] Dupont C., 2006, 42 AIAAASMESAEASEE J
[6] Evans B., 2004, 40 AIAA JOINT PROP C
[7] Hijlkema J., 2012, 4 INT S PROP SPAC TR
[8] Karabeyoglu M. A., 2003, 41 AIAA AER SCI M EX
[9] Kuentzmann P., 1991, S LAUNCH PROP YEAR 2, P159
[10] Lengelle G., 2002, 6 INT S PROP SPAC TR

← 1 2 →