Abstract
Thrust measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. The PDRE uses three types of gases, oxidizer, fuel, and purge gas to generate detonation wave intermittently and produces thrust. A rotary valve attached coaxially to a motor for supplying these three gases intermittently was used. The mechanism of the rotary valve is very simple. It is built up with a top cover, a rotating disk, and a casing, and has advantage to enable high mass flow rate and high frequency operation. In this study, pulse detonation rocket (PDR) for flight tests was developed. Thrust measurement experiment by grand test was carried out to check the performance of the this PDR. The oxidizer was N<inf>2</inf>O, the fuel was C<inf>2</inf>H<inf>4</inf>, and the purge gas was He. In the operation time for 1500 msec with C<inf>2</inf>H<inf>4</inf>-N<inf>2</inf>O propellant, we achieved time-averaged thrust of 256 N and specific impulse of 130.8 sec.
| Original language | English |
|---|---|
| Title of host publication | 52nd Aerospace Sciences Meeting |
| Publisher | American Institute of Aeronautics and Astronautics Inc. |
| ISBN (Print) | 9781624102561 |
| Publication status | Published - 2014 |
| Event | 52nd Aerospace Sciences Meeting 2014 - National Harbor, United States Duration: 2014 Jan 13 → 2014 Jan 17 |
Other
| Other | 52nd Aerospace Sciences Meeting 2014 |
|---|---|
| Country/Territory | United States |
| City | National Harbor |
| Period | 14/1/13 → 14/1/17 |
ASJC Scopus subject areas
- Aerospace Engineering