Performance Analysis of Bipropellant Propulsion System on Special Working Conditions

Zhen Lin; Yong Li

doi:10.4028/www.scientific.net/AMM.390.296

Paper Titles

Off Design Behavior of a 100kW Turbec T100P Micro Gas Turbine
p.275

Lightweight Battery Electric Vehicle for Educational Purposes
p.281

UV-Visible Emission Spectroscopy of the Combustion Process in a Common Rail Cl Engine Fulled with N-Butanol - Diesel Blends
p.286

Technical Characteristics and Applicationconcept of RBCC Engine
p.291

Performance Analysis of Bipropellant Propulsion System on Special Working Conditions
p.296

An Analytical and Experimental Study on Coolant Flow and Temperature Distribution within Pem Fuel Cell Stack
p.301

Numerical Calculation of Air Mass Flow in a Dual-Rotor Piston Engine
p.306

Air Pollution by the Exhaust Emissions from Construction Machinery under Actual Operating Conditions
p.313

Premixed Combustion of a Fine AP/HTPB Composite Propellant Based on Detailed Chemical Kinetics
p.320

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 390Performance Analysis of Bipropellant Propulsion...

Performance Analysis of Bipropellant Propulsion System on Special Working Conditions

Abstract:

At the end of a test satellite, oxidant of the propulsion system was exhausted ahead of fuel. Long-term monopropellant working condition without combustion, cool gas flow working condition and interim working condition were experienced, which trouble the de-orbit control of the satellite. In order to evaluate the performance of the propulsion system on the special working conditions during the satellite de-orbit, theoretic analysis of the specific thrusters is introduced. And effective calculation method is built. Based on the method and obtained remote data, the thrust and specific impulse of the propulsion system on monopropellant working condition and cool gas flow working condition are calculated. It is indicated that, on monopropellant working condition, the thrust of 10N thruster declines 83%, the specific impulse declines about 82%. On cool gas flow working condition, the thrust of the 10N thrusters is less than 0.12N, and declines with the decrease of the tank pressure. The specific impulse is less than 146s. These results can be consulted by other satellites confronting similar conditions.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Applied Mechanics and Materials (Volume 390)

Pages:

296-300

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.390.296

Citation:

Cite this paper

Online since:

August 2013

Authors:

Zhen Lin, Yong Li

Keywords:

Bipropellant Propulsion System, De-Orbit, Performance Analysis, Special Working Conditions

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

References

[1] Zhang Jun, Zhang Xiaoting: Fluid Power Transmission and Control Vol. 47(2011), pp.24-27.

Google Scholar

[2] Hu Changqing, Gu Zuo: The 2nd Chinese Symposium about Space debris(2003).

Google Scholar

[3] Zhou Weiyong, Zhang Yulin: Journal of Astronautic Vol. 31, No. 1(2010), pp.173-178.

Google Scholar

[4] Tang Fei, Ye xiongying, Zhou Zhaoying: Micronanoelectronic Technology Vol. 7-8(2003), pp.441-444.

Google Scholar

[5] Grossmann I, Jones IR, Lee D H: Auxiliary Propulsion Survey, Part III: Survey of Secondary Propulsion and Passive Attitude Control System for Spacecraft, AFAPL–T–68–67， Part III.

Google Scholar