Deflagration-to-detonation transition in an annular combustor with hypergolic propellants

被引：0

作者：

Nair, Anil P. ^{[1
]}

Keller, Alex R. ^{[2
]}

Lima, Alexander B. ^{[3
]}

Spearrin, R. Mitchell ^{[1
]}

机构：

[1] Univ Calif Los Angeles, Mech & Aerosp Engn Dept, Los Angeles, CA 90095 USA

[2] Univ Calif Los Angeles, Los Angeles, CA 90095 USA

[3] Univ Calif Los Angeles, Mech & Aerosp Engn, Los Angeles, CA 90095 USA

来源：

AIAA SCITECH 2022 FORUM | 2022年

基金：

美国国家航空航天局;

关键词：

ROTATING DETONATION; ENERGY;

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Timescales associated with the spontaneous transition from a deflagration to a detonation combustion mode for hypergolic space-storable propellants (MMH, NTO) were experimentally assessed in an annular combustor. The presence of periodic detonation waves is detected using high-speed videography, engine audio frequencies, and oscillatory pressure measurements. Preliminary results suggest that detonation waves form on the order of tens to hundreds of milliseconds after ignition. Knowledge of these timescales aids in the design of in-space detonation-based propulsion systems with short burn durations.

引用

页数：7

共 16 条

[1]

Anderson W. S., 2018, 2018 AIAA AER SCI M, DOI [10.2514/6.2018-0635, DOI 10.2514/6.2018-0635]

[2] Experimental Study of a Hypergolically Ignited Liquid Bipropellant Rotating Detonation Rocket Engine [J].

Anderson, Wesly S. ;

Heister, Stephen D. ;

Kan, Brandon ;

Hartsfied, Carl .

JOURNAL OF PROPULSION AND POWER, 2020, 36 (06) :851-861

[3] Continuous spin detonations [J].

Bykovskii, Fedor A. ;

Zhdan, Sergey A. ;

Vedernikov, Evgenii F. .

JOURNAL OF PROPULSION AND POWER, 2006, 22 (06) :1204-1216

[4] Visualization of Pulse Firing Mode in Hypergolic Bipropellant Thruster [J].

Fujii, Go ;

Daimon, Yu ;

Inoue, Chihiro ;

Shiraiwa, Daijiro ;

Tanaka, Nobuhiko ;

Furukawa, Katsumi .

JOURNAL OF PROPULSION AND POWER, 2020, 36 (05) :677-684

[5]

Hargus WilliamA., 2018 JOINT PROPULSIO, DOI [10.2514/6.2018-4876, DOI 10.2514/6.2018-4876]

[6] Chemical Mechanism of MMH/NTO and Simulation in a Small Liquid Rocket Engine [J].

Hou, Lingyun ;

Fu, Pengfei ;

Ba, Yantao .

COMBUSTION SCIENCE AND TECHNOLOGY, 2019, 191 (12) :2208-2225

[7] Deflagration-to-detonation transition in highly reactive combustible mixtures [J].

Liberman, M. A. ;

Ivanov, M. F. ;

Kiverin, A. D. ;

Kuznetsov, M. S. ;

Chukalovsky, A. A. ;

Rakhimova, T. V. .

ACTA ASTRONAUTICA, 2010, 67 (7-8) :688-701

[8] Predicting deflagration to detonation transition in hydrogen explosions [J].

Middha, Prankul ;

Hansen, Olav R. .

PROCESS SAFETY PROGRESS, 2008, 27 (03) :192-204

[9]

Nair A. P., 2021, AIAA PROPULSION ENER, DOI [10.2514/6.2021, DOI 10.2514/6.2021-3648]

[10] PULSE PERFORMANCE ANALYSIS FOR SMALL HYPERGOLIC-PROPELLANT ROCKET ENGINES [J].

SMITH, GW ;

SFORZINI, RH .

JOURNAL OF SPACECRAFT AND ROCKETS, 1972, 9 (09) :627-&

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