Investigation on Tri-propellant Hybrid Rocket Performance

2016 ◽  
Author(s):  
Yen-Sen Chen ◽  
Alfred Lai ◽  
Jhe-Wei Lin ◽  
Shih-Sin Wei ◽  
Tzu-Hao Chou ◽  
...  
Keyword(s):  
Hybrid Rocket ◽  
Rocket Performance

Influence of a Conical Axial Injector on Hybrid Rocket Performance

2006 ◽  
Vol 22 (5) ◽  
pp. 984-995 ◽  
Author(s):  
C. Carmicino ◽  
A. Russo Sorge
Keyword(s):  
Hybrid Rocket ◽  
Rocket Performance

Numerical Investigation of a N2O/HTPB Hybrid Rocket Motor with a Dual-Vortical-Flow (DVF) Design

2017 ◽  
Vol 33 (6) ◽  
pp. 853-862 ◽  
Author(s):  
A. Lai ◽  
Y. C. Lin ◽  
S. S. Wei ◽  
T. H. Chou ◽  
J. W. Lin ◽  
...  
Keyword(s):  
Specific Impulse ◽  
Rocket Motor ◽  
Vortical Flow ◽  
Reacting Flow ◽  
Hybrid Rocket ◽  
Rocket Motors ◽  
Roll Control ◽  
Hybrid Rocket Motor ◽  
Fluid Properties ◽  
Rocket Performance

AbstractA compact hybrid rocket motor design that incorporates a dual-vortical-flow (DVF) concept is proposed. The oxidizer (nitrous oxide, N2O) is injected circumferentially into various sections of the rocket motor, which are sectored by several solid fuel “rings” (made of hydroxyl-terminated polybutadiene, HTPB) that are installed along the central axis of the motor. The proposed configuration not only increases the residence time of the oxidizer flow, it also implies an inherent “roll control” capability of the motor. Based on a DVF motor geometry with a designed thrust level of 11.6 kN, the characteristics of the turbulent reacting flow within the motor and its rocket performance were analyzed with a comprehensive numerical model that implements both real-fluid properties and finite-rate chemistry. Data indicate that the vacuum specific impulse (Isp) of the DVF motor could reach 278 s. The result from a preliminary ground test of a lab-scale DVF hybrid rocket motor (with a designed thrust level of 3,000 N) also shows promising performance. The proposed DVF concept is expected to partly resolve the issue of scalability, which remains challenging for hybrid rocket motors development.

An Italian network to improve hybrid rocket performance: Strategy and results

2014 ◽  
Vol 96 ◽  
pp. 246-260 ◽  
Author(s):  
L. Galfetti ◽  
F. Nasuti ◽  
D. Pastrone ◽  
A.M. Russo
Keyword(s):  
Hybrid Rocket ◽  
Rocket Performance

DEVELOPMENT OF A DIRECT INJECTION GAS-HYBRID ROCKET SYSTEM USING GLYCIDYL AZIDE POLYMER

2019 ◽  
Vol 18 (2) ◽  
pp. 157-170
Author(s):  
Yutaka Wada ◽  
S. Hatano ◽  
Ayana Banno ◽  
Yo Kawabata ◽  
Hiroshi Hasegawa ◽  
...  
Keyword(s):  
Direct Injection ◽  
Hybrid Rocket ◽  
Glycidyl Azide Polymer ◽  
Rocket System ◽  
Glycidyl Azide

EVALUATION OF A LABORATORY-SCALE HYBRID ROCKET ENGINE'S PERFORMANCE

2014 ◽  
Vol 13 (2) ◽  
pp. 123-139
Author(s):  
V. Brahmbhatt ◽  
David R. Greatrix ◽  
J. Karpynczyk ◽  
A. P. Trumpour
Keyword(s):  
Laboratory Scale ◽  
Hybrid Rocket
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