scholarly journals Experimental Study of the Swirling Oxidizer Flow in HTPB/N2O Hybrid Rocket Motor

2017 ◽  
Vol 2017 ◽  
pp. 1-10 ◽  
Author(s):  
Mohammad Mahdi Heydari ◽  
Nooredin Ghadiri Massoom
Keyword(s):  
Specific Impulse ◽  
Axial Flow ◽  
Combustion Efficiency ◽  
Swirl Flow ◽  
Rocket Motor ◽  
Outer Diameter ◽  
Hybrid Rocket ◽  
Feed System ◽  
Regression Rate ◽  
Hybrid Rocket Motor

Effects of swirling oxidizer flow on the performance of a HTPB/N2O Hybrid rocket motor were studied. A hybrid propulsion laboratory has been developed, to characterize internal ballistics characteristics of swirl flow hybrid motors and to define the operating parameters, like fuel regression rate, specific impulse, and characteristics velocity and combustion efficiency. Primitive variables, like pressure, thrust, temperature, and the oxidizer mass flow rate, were logged. A modular motor with 70 mm outer diameter and variable chamber length is designed for experimental analysis. The injector module has four tangential injectors and one axial injector. Liquid nitrous oxide (N2O) as an oxidizer is injected at the head of combustion chamber into the motor. The feed system uses pressurized air as the pressurant. Two sets of tests have been performed. Some tests with axial and tangential oxidizer injection and a test with axial oxidizer injection were done. The test results show that the fuel grain regression rate has been improved by applying tangential oxidizer injection at the head of the motor. Besides, it was seen that combustion efficiency of motors with the swirl flow was about 10 percent more than motors with axial flow.

An analytical and experimental study of a hybrid rocket motor

2014 ◽  
Vol 228 (13) ◽  
pp. 2475-2486 ◽  
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.

Dynamic characteristics study of regression rate in variable thrust hybrid rocket motor

2022 ◽  
Author(s):  
Tian Hui ◽  
Meng Xiangyu ◽  
Zhu Hao ◽  
Li Chengen ◽  
Yu Ruipeng ◽  
...  
Keyword(s):  
Dynamic Characteristics ◽  
Rocket Motor ◽  
Hybrid Rocket ◽  
Regression Rate ◽  
Hybrid Rocket Motor

scholarly journals Modified Regression Rate Formula of PMMA Combustion by a Single Plane Impinging Jet

2017 ◽  
Vol 2017 ◽  
pp. 1-9
Author(s):  
Tsuneyoshi Matsuoka ◽  
Kyohei Kamei ◽  
Yuji Nakamura ◽  
Harunori Nagata
Keyword(s):  
Control Volume ◽  
Rocket Motor ◽  
Displacement Sensor ◽  
Pure Oxygen ◽  
Hybrid Rocket ◽  
Single Plane ◽  
Regression Rate ◽  
Fuel Surface ◽  
Hybrid Rocket Motor ◽  
Quenching Distance

A modified regression rate formula for the uppermost stage of CAMUI-type hybrid rocket motor is proposed in this study. Assuming a quasi-steady, one-dimensional, an energy balance against a control volume near the fuel surface is considered. Accordingly, the regression rate formula which can calculate the local regression rate by the quenching distance between the flame and the regression surface is derived. An experimental setup which simulates the combustion phenomenon involved in the uppermost stage of a CAMUI-type hybrid rocket motor was constructed and the burning tests with various flow velocities and impinging distances were performed. A PMMA slab of 20 mm height, 60 mm width, and 20 mm thickness was chosen as a sample specimen and pure oxygen and O2/N2mixture (50/50 vol.%) were employed as the oxidizers. The time-averaged regression rate along the fuel surface was measured by a laser displacement sensor. The quenching distance during the combustion event was also identified from the observation. The comparison between the purely experimental and calculated values showed good agreement, although a large systematic error was expected due to the difficulty in accurately identifying the quenching distance.

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