Experimental studies on rotary valves for single-tube pulse detonation rocket engines

Abstract

Two types of rotary valve were designed and fabricated for single-tube pulse detonation rocket engines. According to their driving components, they were named as gear-driven and cam-driven rotary valve, respectively. Preliminary experimental investigations were carried out to test their feasibility for supply of the single-tube pulse detonation rocket engine. Based on the gear-driven rotary valve, the single-tube pulse detonation rocket engine operated at 10 Hz stably. When operating frequency was increased to 15 Hz, inconsecutive detonations happened which was due to signal output block in the encoder. It was found that optimal ignition timing needed to be adjusted to obtain stable operation in the gear-driven rotary-valved pulse detonation rocket engine. Discussion on this was conducted. Operations of the cam-driven rotary-valved pulse detonation rocket engine were also performed. Fully developed and successive detonations at 40 Hz were successfully obtained although an explosion happened in initial tests. Experimental results showed that these two types of rotary valve were able to realize supply control of single-tube pulse detonation rocket engines effectively.

Keywords

Rotary valve detonation rocket engine frequency ignition

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References

Nicholls

Wilkinson

Morrison

. Intermittent detonation as a thrust producing mechanism. Jet Propul 1957; 27: 534–541.

Bussing

Pappas

. Pulse detonation engine theory and concepts. 32nd AIAA Aerospace Sciences Meeting and Exhibit, 10–13 January 1994, Reno, NevadaAIAA Paper 1994-0263.

Nikitin

Dushin

Phylippov

. Pulse detonation engines: technical approaches. Acta Astronaut 2009; 64: 281–287.

Fan

Yan

Huang

. Experimental investigation on two-phase pulse detonation engine. Combust Flame 2003; 133: 441–450.

Cooper

Jackson

Austin

. Direct experimental impulse measurements for detonations and deflagrations. J Propul Power 2002; 18: 1033–1041.

Kasahara

Hirano

Matsuo

. Thrust measurement of a multicycle partially filled pulse detonation rocket engine. J Propul Power 2009; 25: 1281–1290.

New

Panicker

. Experimental investigation on DDT enhancements by Shchelkin spirals in a PDE. 44th AIAA Aerospace Sciences Meeting and Exhibit, 9–12 January 2006, Reno, NevadaAIAA Paper 2006-552.

Sato

Matsuo

Endo

. Numerical studies on specific impulse of partially filled pulse detonation rocket engine. J Propul Power 2006; 22: 64–69.

Gamezo

Ogawa

Oran

. Deflagration to detonation transition in H2-air mixtures: effect of blockage ratio. 47th AIAA Aerospace Sciences Meeting and Exhibit, Orlando, FloridaAIAA Paper 2009-440, 2009.

10.

Ebrahimi

Malo-Molina

. Numerical investigation of 2-D and 3-D multitube pulse detonation using H2 and JP8 fuel. 42nd AIAA Aerospace Sciences Meeting and Exhibit, 5–9 January 2004, Reno, NevadaAIAA Paper 2004-0465.

11.

Wintenberger

Austin

Cooper

. An analytical model for the impulse of a single-cycle pulse detonation engine. J Propul Power 2003; 19: 22–38.

12.

Tangirala

Dean

. Performance estimations of a pulse detonation engine with exit nozzle. 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 2006, Sacramento, CAAIAA Paper 2006-4792.

13.

Heiser

Pratt

. Thermodynamic cycle analysis of pulse detonation engines. J Propul Power 2002; 18: 68–76.

14.

Fan

Chen

. Propulsive performance of a liquid kerosene/oxygen pulse detonation engine. Exp Ther Fluid Sci 2011; 35: 265–271.

15.

New

Panicker

Chui

. Experimental study on deflagration to detonation transition enhancement methods in a PDE. 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, 6–9 November 2006, Canberra, AustraliaAIAA Paper 2006-7958.

16.

Kailasanath

. Research on pulse detonation combustion systems – a status report. 47th AIAA Aerospace Sciences Meeting, Orlando, FLAIAA Paper 2009-631.

17.

Brophy

Netzer

. Effects of ignition characteristics and geometry on the performance of a JP-10/O2 fueled pulse detonation engine. 35th AIAA Joint Propulsion Conference, 20–24 June 1999, Los Angeles, CAAIAA Paper 99-2635.

18.

Panicker

. Development of a compact liquid fueled pulsed detonation engine with pre-detonator. 45th AIAA Aerospace Sciences Meeting and Exhibit, 8–11 January 2007, Reno, NevadaAIAA Paper 2007-237.

19.

Hinley

Henderson

Bussing

. Operation of a flight-scale rotary-valved, multiple-combustor pulse detonation engine (RVMPDE). AIAA Paper 1998-3881, 1998.

20.

Meyers

Wilson

. Experimental study of a propane-fueled pulsed detonation rocket. AIAA Paper 2003-6974, 2003.

21.

Matsuoka

Esumi

Kasahara

. Study on valve systems for pulse detonation engines. 46th Joint Propulsion Conference and Exhibit, 25–28 July 2010, Nashville, USAAIAA Paper 2010-6672.

22.

Gordon S and McBride BJ. Computer program for calculation of complex chemical equilibrium compositions and: analysis. NASA Technical Report RP1311. 1994.

23.

McBride BJ and Gordon S. Computer program for calculation of complex chemical equilibrium compositions and applications: user manual and program description. NASA Technical Report RP1311. 1996.

24.

Kailasanath

. Liquid-fueled detonations in tubes. J Propul Power 2006; 22: 1261–1268.