Experimental Study of Performance of a 500-N Liquid-Propellant Rocket Engine using Kerosene and High-Concentration Hydrogen Peroxide

Experimental studies of the low-thrust liquid-propellant rocket engine using ecologically pure propellant components (kerosene and high-concentration hydrogen peroxide) are performed. The presented brief review of works, devoted to development of a low-thrust liquid-propellant rocket engine on high-concentration hydrogen peroxide and kerosene, has shown the lack of experimental studies of curtain cooling of a combustion chamber wall. To solve this problem, an experimental engine with a thrust of500 N was developed at "Rocket Engines" department of the Moscow Aviation Institute. The engine has undergone a cycle of firing tests. A description of the test bench for firing tests, its capabilities and peculiarities are given. Results of firing experiments are described and analyzed; they have shown the reliable ignition of components and the satisfactory nonstationary thermal state of combustion chamber walls during the engine operation in different regimes.

References

[1] Vorob’ev A.G., Borovik I.N., Kha S. Development low-thrust liquid-propellant rocket engine using components: kerosene and hydrogen peroxide. Vestn. Sibirskogo Gos. Aerokosmicheskogo Un. im. akad. M.F. Reshetneva [Bull. Reshetnev Siberian State Aerospace Uni.], Krasnoyarsk, 2011, no. 4 (37), pp. 121-126 (in Russ.).

[2] Kozlov A.A., Bazanova I.A., Borovik I.N. Razrabotka sistemy vosplameneniya ZhRDMT na komponentakh vysokokontsentrirovannaya perekis’ vodoroda i kerosin [Development the ignition system of the low-thrust liquid-propellant rocket engine using components: high-concentration hydrogen peroxide and kerosene]. All-Russian sc.-tech. conf. "Rocket-Space Propulsion" Moscow, MGTU im. N.E. Baumana Publ., 2008. 80 p.

[3] Vorob’ev A.G. Mathematical model of the thermal state for low-thrust liquid-propellant rocket engine. Vestn. Moskovskogo aviatsionnogo inst. [Bull. Moscow Aviation Inst.], 2007, vol. 14, no. 4, pp. 42-49 (in Russ.).

[4] Vorob’ev A.G. Eksperimental’no-teoreticheskaya model’ teplovogo sostoyaniya zhidkostnykh raketnykh dvigateley malykh tyag [Experimental and theoretical model of the thermal state of the low-thrust liquid-propellant rocket engines]. M., 2008. 21 p.

[5] Love J.E., Stillwell W.H. The Hydrogen Peroxide Rocket Reaction Control System for the X-1B Research Airplane. NASA TN-185, 1959.

[6] Takashashi K., Ikuta T., Dan Y., Nagayama K., Kishida M. Catalytic Porous Microchannel for Hydrogen Peroxide MEMS Thruster. Proc. 23rd Sensor Symposium on Sensors, Micromachines, and Applied Systems, 2006, pp. 513-516.

[7] Kim B., Lee Y., Kim G., Go Y., Kim Y., Kim S. A Study on Design and Combustion Characteristics of a H2O2/Kerosene Uni-injector Rocket Engine. Proc. 34th Spring Conf. of the Korean Society of Propulsion Engineers, 2010.

[8] Jo S., An S., Kim J., Yoon H., Kwon S. Performance Characteristics of Hydrogen Peroxide / Kerosene Staged-Bipropellant Engine with Axial Fuel Injector. AIAA J. Propulsion and Power, 2011, vol. 27. no. 3, pp. 684-691.

[9] Ventura M.C., Mullens P. The Use of Hydrogen Peroxide for Propulsion and Power. 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conf., June 20-24, 1999, Los Angeles, CA, AIAA-99-2880.

[10] Ventura M.C., Wernimont E., Heister S.D., Yuan S. Rocket Grade Hydrogen Peroxide (RGHP) for Use in Propulsion and Power Devices. Historical Discussion of Hazards, 2007, AIAA-2007-5468.

[11] Coxhill I., Richardson G., Sweeting, M. An Investigation of a Low Cost HTP/Kerosene 40 N Thruster for Small Satellite. 38th AIAA/ASME/SAE/ASEE. Joint Propulsion Conference and Exhibit. Indianapolis, IN, 2002, AIAA Paper 20024155.

[12] Vasil’ev A.P., Kudryavtsev V.M., Kuznetsov V.A., Kurpatenkov V.D., Obel’nitskiy A.M., Polyaev V.M., Poluyan B.Ya. Osnovy teorii i rascheta ZhRD [Fundamentals of the theory and calculation of liquid-propellant rocket engine]. Moscow, Vysshaya Shkola Publ., 1993. 656 p.

[13] Dobrovol’skiy M.V. Zhidkostnye raketnye dvigateli [Liquid-propellant rocket engine]. Moscow, MGTU im. N.E. Baumana Publ., 2006. 488 p.

[14] Kozlov A.A., Abashev V.M. Raschet i proektirovanie zhidkostnogo raketnogo dvigatelya maloy tyagi Calculation and design of low-thrust liquid-propellant rocket engine. Moscow. MAI Publ., 2003. 36 p.

[15] Vorob’ev A.G., Borovik I.N., Khokhlov A.N. Modernization of the firing tests for research working processes in low-thrust liquid-propellant rocket engine using ecologically pure propellant components. Vestn. Moskovskogo aviatsionnogo inst. [Bull. Moscow Aviation Inst.], 2010, vol. 1, no. 17, pp. 97-103 (in Russ.).

[16] Gurkin N.K., Kazennov I.S., Lizunevich M.M., Khokhlov A.N. Development and modernization of hydro pneumatic system, measurement and control systems for stand testing of low-thrust liquid-propellant rocket engine. Tr. 2-y Obshcherossiyskoy molodezhnoy nauchno-tekhn. konf. "Molodezh’. Tekhnika. Kosmos". Voenmekh. Vestnik BGTU [Proc. 2nd All-Russian youth scientific and technical. conf. "Youth. Tech. Space". Military Mech. Bull. Belarusian State Tech. Uni], SPb., 2010, pp. 5254 (in Russ.).

[17] Vorob’ev A.G., Borovik I.N., Khokhlov A.N., Zarankevich I.A. Software package for test automation of low-thrust liquid-propellant rocket engine using ecologically pure propellant components: high-concentration hydrogen peroxide and kerosene. The certificate on state registration of the computer program. No. 2012615618, 2004 (in Russ.).

[18] Bogacheva D.Yu., Borovik I.N. Automatic processing and analysis data of fire tests low-thrust liquid-propellant rocket engine. The certificate on state registration of the computer program. No. 201261461, 2012 (in Russ.).