Preliminary Development of a Hydrogen Peroxide Thruster
Green propellants used for satellite-level propulsion
system become attractive in recent years because the non-toxicity and
lower requirements of safety protection. One of the green propellants,
high-concentration hydrogen peroxide H2O2 solution (≥70% w/w,
weight concentration percentage), often known as high-test peroxide
(HTP), is considered because it is ITAR-free, easy to manufacture and
the operating temperature is lower than traditional monopropellant
propulsion. To establish satellite propulsion technology, the National
Space Organization (NSPO) in Taiwan has initialized a long-term
cooperation project with the National Cheng Kung University to
develop compatible tank and thruster. An experimental propulsion
payload has been allocated for the future self-reliant satellite to
perform orbit transfer and maintenance operations. In the present
research, an 1-Newton thruster prototype is designed and the thrusting
force is measured by a pendulum-type platform. The preliminary
hot-firing test at ambient environment showed the generated thrust and
the specific impulse are about 0.7 Newton and 102 seconds,
respectively.
<p>[1] W. J. Larson and J. R. Wertz, Space Mission Analysis and Design,
Second Edition, Microcosm, Inc., 1992.
[2] G. P. Sutton, Rocket Propulsion Elements, John Wiley & Sons, Inc.,
1992.
[3] R. W. Humble, G. N. Henry, and W. J. Larson, Space Propulsion Analysis
and Design, The McGraw-Hill Companies, Inc., Primis Custom
Publishing, 1995.
[4] M. Tajmar, Advanced Space Propulsion Systems, Springer, 2003.
[5] W. C. Schumb, C. N. Satterfield, and R. L. Wentworth, Hydrogen
Peroxide, Reinhold Publishing Company, New York, 1955.
[6] D. Andrews, “The Industrial History of the Ansty Rocket Department,
1946 to 1971,” July 26, 1998
[7] L. E. James and W. H. Stillwell, “The Hydrogen-Peroxide Rocket
Reaction-Control System for the X-1B Research Airplane,” NASA
Technical Note TN D-158, Flight Research Center, Edwards, CA, Dec.
1959.
[8] J. F. Runckel, C. M. Willis, L. B. Salters Jr., “Investigation of Catalyst
Beds for 98-Percent-Concentration Hydrogen Peroxide,” NASA TN
D-1808, Langley Research Center, Hampton, Virginia, 1963.
[9] W. E. Armstrong, C. Z. Morgan, L. B. Ryland, and H. H. Voge,
"Development of Catalysts for Monopropellant Hydrazine
Decomposition,'' Shell Development Company Report No. S-13947,
Contract NAS 7-97, 1964.
[10] J. Clark, Ignition - An Informal History of Liquid Rocket Propellants,
Rutgers University Press, New Brunswick, 1972.
[11] E. Wernimont and P. Mullens, “Recent Developments in Hydrogen
Peroxide Monopropellant Devices,” AIAA-99-2741, General Kinetics,
LLC, Aliso Viejo, CA
[12] D. L. Hitt, C. M. Zakrzwski, and M. A. Thomas, "MEMS-based satellite
micropropulsion via catalyzed hydrogen peroxide decomposition, Smart
Mater. Struct., vol. 10, pp. 1163–1175, 2001.
[13] J. Ponzo, “Small Envelope, High Flux 90% Hydrogen Peroxide Catalyst
Bed,” 39th AIAA/ASME/SAE/ASE Joint Propulsion Conference and
Exhibit, Huntsville, Alabama, 20-23 July 2003,
[14] C. Scharlemann, M. Schiebl, R. Amsüss, and M. Tajmar, “Development
of Miniaturized Green Propellant Based Mono- and Bipropellant
Thrusters,” 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
& Exhibit, AIAA 2007-5580, Cincinnati, OH, 8 - 11 July 2007.
[15] A. Pasini, L. Torre, L. Romeo, A. Cervone, L. d’Agostino, A. J. Musker,
and G. Saccoccia, “Experimental Characterization of a 5 N Hydrogen
Peroxide Monopropellant Thruster Prototype,” 43rd
AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit,
AIAA-2007-5465, Cincinnati, OH, 8 - 11 July 2007
[16] S. L. Lee and C. W. Lee, “Performance characteristics of silver catalyst
bed for hydrogen peroxide,” Aerospace Science and Technology, vol. 13,
no. 1, pp. 12–17, 2009.
[17] L. Pirault-Roy, C. Kappenstein, M. Guèrin, R. Eloirdi, and N. Pillet,
“Hydrogen Peroxide Decomposition on Various Supported Catalysts
Effect of Stabilizers,” Journal of Propulsion and Power, vol. 18, no. 6,
2002, pp. 1235–1241.
[18] Y. A. Chan, H. W. Hsu, and Y. C. Chao, “Development of a HTP
Mono-propellant Thruster by Using Composite Silver Catalyst,” 44th
AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San
Deigo, CA, 31 July - 3 August, 2011.</p>
<p>[1] W. J. Larson and J. R. Wertz, Space Mission Analysis and Design,
Second Edition, Microcosm, Inc., 1992.
[2] G. P. Sutton, Rocket Propulsion Elements, John Wiley & Sons, Inc.,
1992.
[3] R. W. Humble, G. N. Henry, and W. J. Larson, Space Propulsion Analysis
and Design, The McGraw-Hill Companies, Inc., Primis Custom
Publishing, 1995.
[4] M. Tajmar, Advanced Space Propulsion Systems, Springer, 2003.
[5] W. C. Schumb, C. N. Satterfield, and R. L. Wentworth, Hydrogen
Peroxide, Reinhold Publishing Company, New York, 1955.
[6] D. Andrews, “The Industrial History of the Ansty Rocket Department,
1946 to 1971,” July 26, 1998
[7] L. E. James and W. H. Stillwell, “The Hydrogen-Peroxide Rocket
Reaction-Control System for the X-1B Research Airplane,” NASA
Technical Note TN D-158, Flight Research Center, Edwards, CA, Dec.
1959.
[8] J. F. Runckel, C. M. Willis, L. B. Salters Jr., “Investigation of Catalyst
Beds for 98-Percent-Concentration Hydrogen Peroxide,” NASA TN
D-1808, Langley Research Center, Hampton, Virginia, 1963.
[9] W. E. Armstrong, C. Z. Morgan, L. B. Ryland, and H. H. Voge,
"Development of Catalysts for Monopropellant Hydrazine
Decomposition,'' Shell Development Company Report No. S-13947,
Contract NAS 7-97, 1964.
[10] J. Clark, Ignition - An Informal History of Liquid Rocket Propellants,
Rutgers University Press, New Brunswick, 1972.
[11] E. Wernimont and P. Mullens, “Recent Developments in Hydrogen
Peroxide Monopropellant Devices,” AIAA-99-2741, General Kinetics,
LLC, Aliso Viejo, CA
[12] D. L. Hitt, C. M. Zakrzwski, and M. A. Thomas, "MEMS-based satellite
micropropulsion via catalyzed hydrogen peroxide decomposition, Smart
Mater. Struct., vol. 10, pp. 1163–1175, 2001.
[13] J. Ponzo, “Small Envelope, High Flux 90% Hydrogen Peroxide Catalyst
Bed,” 39th AIAA/ASME/SAE/ASE Joint Propulsion Conference and
Exhibit, Huntsville, Alabama, 20-23 July 2003,
[14] C. Scharlemann, M. Schiebl, R. Amsüss, and M. Tajmar, “Development
of Miniaturized Green Propellant Based Mono- and Bipropellant
Thrusters,” 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
& Exhibit, AIAA 2007-5580, Cincinnati, OH, 8 - 11 July 2007.
[15] A. Pasini, L. Torre, L. Romeo, A. Cervone, L. d’Agostino, A. J. Musker,
and G. Saccoccia, “Experimental Characterization of a 5 N Hydrogen
Peroxide Monopropellant Thruster Prototype,” 43rd
AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit,
AIAA-2007-5465, Cincinnati, OH, 8 - 11 July 2007
[16] S. L. Lee and C. W. Lee, “Performance characteristics of silver catalyst
bed for hydrogen peroxide,” Aerospace Science and Technology, vol. 13,
no. 1, pp. 12–17, 2009.
[17] L. Pirault-Roy, C. Kappenstein, M. Guèrin, R. Eloirdi, and N. Pillet,
“Hydrogen Peroxide Decomposition on Various Supported Catalysts
Effect of Stabilizers,” Journal of Propulsion and Power, vol. 18, no. 6,
2002, pp. 1235–1241.
[18] Y. A. Chan, H. W. Hsu, and Y. C. Chao, “Development of a HTP
Mono-propellant Thruster by Using Composite Silver Catalyst,” 44th
AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San
Deigo, CA, 31 July - 3 August, 2011.</p>
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:51492", author = "Y. A. Chan and H. J. Liu and K. C. Tseng and T. C. Kuo", title = "Preliminary Development of a Hydrogen Peroxide Thruster", abstract = "Green propellants used for satellite-level propulsion
system become attractive in recent years because the non-toxicity and
lower requirements of safety protection. One of the green propellants,
high-concentration hydrogen peroxide H2O2 solution (≥70% w/w,
weight concentration percentage), often known as high-test peroxide
(HTP), is considered because it is ITAR-free, easy to manufacture and
the operating temperature is lower than traditional monopropellant
propulsion. To establish satellite propulsion technology, the National
Space Organization (NSPO) in Taiwan has initialized a long-term
cooperation project with the National Cheng Kung University to
develop compatible tank and thruster. An experimental propulsion
payload has been allocated for the future self-reliant satellite to
perform orbit transfer and maintenance operations. In the present
research, an 1-Newton thruster prototype is designed and the thrusting
force is measured by a pendulum-type platform. The preliminary
hot-firing test at ambient environment showed the generated thrust and
the specific impulse are about 0.7 Newton and 102 seconds,
respectively.
", keywords = "Hydrogen peroxide, propulsion, RCS, satellite.", volume = "7", number = "7", pages = "1375-8", }
