Nitrous Oxide Hybrid Rocket Motor Fuel Regression Rate Characterization

2007 ◽  
Author(s):  
Eric Doran ◽  
Jonny Dyer ◽  
Kevin Lohner ◽  
Zach Dunn ◽  
Brian Cantwell ◽  
...  
Keyword(s):  
Nitrous Oxide ◽  
Motor Fuel ◽  
Rocket Motor ◽  
Hybrid Rocket ◽  
Regression Rate ◽  
Hybrid Rocket Motor

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.

Restartable Hybrid Rocket Motor using Nitrous Oxide

2006 ◽  
Author(s):  
Vadim Zakirov ◽  
Ke Wan ◽  
Fan-li Shan ◽  
Hai-yun Zhang ◽  
Lu-ming Li
Keyword(s):  
Nitrous Oxide ◽  
Rocket Motor ◽  
Hybrid Rocket ◽  
Hybrid Rocket Motor
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