Effect of Aft Chamber Volume on Hybrid Rocket Combustion Efficiency

2019 ◽  
Author(s):  
Lisa Kageyama ◽  
Landon T. Kamps ◽  
Harunori Nagata
Keyword(s):  
Combustion Efficiency ◽  
Hybrid Rocket ◽  
Chamber Volume ◽  
Hybrid Rocket Combustion

Model of Hybrid Rocket Combustion in Classical Hybrid Rocket Motors

2013 ◽  
Author(s):  
Takakazu Morita ◽  
Saburo Yuasa ◽  
Toru Shimada ◽  
Shigeru Yamaguchi
Keyword(s):  
Hybrid Rocket ◽  
Rocket Motors ◽  
Hybrid Rocket Combustion

Dynamic Modeling of Hybrid Rocket Combustion

1999 ◽  
Vol 15 (4) ◽  
pp. 562-571 ◽  
Author(s):  
M. Arif Karabeyoglu ◽  
D. Altman
Keyword(s):  
Dynamic Modeling ◽  
Hybrid Rocket ◽  
Hybrid Rocket Combustion

Vortex Shedding Influence on Hybrid Rocket Pressure Oscillations and Combustion Efficiency

2016 ◽  
Vol 32 (6) ◽  
pp. 1386-1394 ◽  
Author(s):  
Jérôme Messineo ◽  
Jean-Yves Lestrade ◽  
Jouke Hijlkema ◽  
Jérôme Anthoine
Keyword(s):  
Vortex Shedding ◽  
Combustion Efficiency ◽  
Hybrid Rocket ◽  
Pressure Oscillations

Conceptual Regenerative Nozzle Cooling Design for a Hydroxyl-Terminated Polybutadiene and Oxygen Hybrid Rocket Engine

2017 ◽  
Author(s):  
Luis R. Robles ◽  
Johnny Ho ◽  
Bao Nguyen ◽  
Geoffrey Wagner ◽  
Jeremy Surmi ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
High Temperatures ◽  
Cooling System ◽  
Rocket Engine ◽  
Combustion Efficiency ◽  
Rocket Engines ◽  
Hybrid Rocket ◽  
Gaseous Oxygen ◽  
Rocket Nozzle ◽  
Regenerative Cycle

Regenerative rocket nozzle cooling technology is well developed for liquid fueled rocket engines, but the technology has yet to be widely applied to hybrid rockets. Liquid engines use fuel as coolant, and while the oxidizers typically used in hybrids are not as efficient at conducting heat, the increased renewability of a rocket using regenerative cycle should still make the technology attractive. Due to the high temperatures that permeate throughout a rocket nozzle, most nozzles are predisposed to ablation, supporting the need to implement a nozzle cooling system. This paper presents a proof-of-concept regenerative cooling system for a hybrid engine which uses hydroxyl-terminated polybutadiene (HTPB) as its solid fuel and gaseous oxygen (O2) as its oxidizer, whereby a portion of gaseous oxygen is injected directly into the combustion chamber and another portion is routed up through grooves on the exterior of a copper-chromium nozzle and, afterwards, injected into the combustion chamber. Using O2 as a coolant will significantly lower the temperature of the nozzle which will prevent ablation due to the high temperatures produced by the exhaust. Additional advantages are an increase in combustion efficiency due to the heated O2 being used for combustion and an increased overall efficiency from the regenerative cycle. A computational model is presented, and several experiments are performed using computational fluid dynamics (CFD).

Effect of energetic fuel additives on the temperature of hybrid rocket combustion

1999 ◽  
Author(s):  
W. Teague ◽  
A. Wright ◽  
D. Balkanli ◽  
L. Hybl ◽  
M. Hudson
Keyword(s):  
Fuel Additives ◽  
Hybrid Rocket ◽  
Hybrid Rocket Combustion
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