New Concept of Laser-Augmented Chemical Propulsion

Towards an optimal concept for numerical codes simulating thrust chamber processes in high pressure chemical propulsion systems

Aerospace Science and Technology ◽

10.1016/s1270-9638(97)90031-6 ◽

1997 ◽

Vol 1 (3) ◽

pp. 203-213 ◽

Cited By ~ 4

Author(s):

C.-A. Schley ◽

G. Hagemann ◽

G. Krülle

Keyword(s):

High Pressure ◽

Propulsion Systems ◽

Thrust Chamber ◽

Pressure Chemical ◽

Chemical Propulsion

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Nuclear Electric Propulsion / Chemical Propulsion Hybrid Human Mars Exploration Campaign: From Start to Steady-State

10.2514/6.2021-4013 ◽

2021 ◽

Author(s):

Timothy S. Kokan ◽

James F. Horton ◽

Claude R. Joyner ◽

Daniel J. Levack ◽

Dennis E. Morris ◽

...

Keyword(s):

Steady State ◽

Electric Propulsion ◽

Mars Exploration ◽

Chemical Propulsion

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Development of Chemical Propulsion System for a Versatile Lander Demonstrator Platform

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference ◽

10.2514/6.2013-4163 ◽

2013 ◽

Author(s):

Daniel Fiot ◽

Vincent Coipeau ◽

Philip Martin ◽

Louis Souverein

Keyword(s):

Propulsion System ◽

Chemical Propulsion

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An analytical and experimental study of a hybrid rocket motor

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410013519432 ◽

2014 ◽

Vol 228 (13) ◽

pp. 2475-2486 ◽

Cited By ~ 1

Author(s):

Hadi Rezaei ◽

Mohammad Reza Soltani

Keyword(s):

Flow Rate ◽

Low Cost ◽

Specific Impulse ◽

Combustion Products ◽

Rocket Motor ◽

Chamber Pressure ◽

Hybrid Rocket ◽

Hybrid Rocket Motor ◽

Chemical Propulsion ◽

Rate Case

The hybrid rocket motor is a kind of chemical propulsion system that has been recently given serious attention by various industries and research centers. The relative simplicity, safety and low cost of this motor, in comparison with other chemical propulsion motors, are the most important reasons for such interest. Moreover, throttle-ability and thrust variability on demand are additional advantages of this type of motor. In this paper, the result of an internal ballistic simulation of hybrid rocket motor in a zero-dimensional form is presented. Further to validate the code, an experimental setup was designed and manufactured. The simulation results are compared with the experimental data and good agreement is achieved. The effect of various parameters on the motor performance and on the combustion products is also investigated. It is found that increasing the oxidizer flow rate, increases the pressure and specific impulse of the motor; however, the slope of the specific impulse for the high flow rate case reduces. In addition, by increasing the combustion chamber pressure, the specific impulse is increased considerably. The initial diameter of the fuel port does not have significant effect on the pressure chamber and on the specific impulse. Addition of a percentage of an oxidizer like ammonium perchlorate to the fuel increases the specific impulse linearly.

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