Theoretical analysis on thermosoakback of monopropellant thruster

Bing Sun; Guobiao Cai; Quan Chen; Bingxiu Bian

Theoretical analysis on thermosoakback of monopropellant thruster

Bing Sun^*
, Guobiao Cai
, Quan Chen
, Bingxiu Bian

^*Corresponding author for this work

School of Astronautics

Beihang University

Research output: Contribution to journal › Article › peer-review

3 Scopus citations

Abstract

The thermosoakback of the attitude and orbit control thrusters on satellite was simulated by finite element method. The computation shows that the heat after the working of combustor dissipates mainly through supporting sticks by thermosoakback and radiation. The simulating results also show that the capillary tube used for transferring liquid fuel can effectively prevent the heat from transferring in the solenoid valve.

Original language	English
Pages (from-to)	40-44
Number of pages	5
Journal	Tuijin Jishu/Journal of Propulsion Technology
Volume	18
Issue number	3
State	Published - Jun 1997

Cite this

@article{328390a81f25493ab00c3d0206e7c2b9,

title = "Theoretical analysis on thermosoakback of monopropellant thruster",

abstract = "The thermosoakback of the attitude and orbit control thrusters on satellite was simulated by finite element method. The computation shows that the heat after the working of combustor dissipates mainly through supporting sticks by thermosoakback and radiation. The simulating results also show that the capillary tube used for transferring liquid fuel can effectively prevent the heat from transferring in the solenoid valve.",

author = "Bing Sun and Guobiao Cai and Quan Chen and Bingxiu Bian",

year = "1997",

month = jun,

language = "英语",

volume = "18",

pages = "40--44",

journal = "Tuijin Jishu/Journal of Propulsion Technology",

issn = "1001-4055",

publisher = "China Aerospace Science and Industry Corp",

number = "3",

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TY - JOUR

T1 - Theoretical analysis on thermosoakback of monopropellant thruster

AU - Sun, Bing

AU - Cai, Guobiao

AU - Chen, Quan

AU - Bian, Bingxiu

PY - 1997/6

Y1 - 1997/6

N2 - The thermosoakback of the attitude and orbit control thrusters on satellite was simulated by finite element method. The computation shows that the heat after the working of combustor dissipates mainly through supporting sticks by thermosoakback and radiation. The simulating results also show that the capillary tube used for transferring liquid fuel can effectively prevent the heat from transferring in the solenoid valve.

AB - The thermosoakback of the attitude and orbit control thrusters on satellite was simulated by finite element method. The computation shows that the heat after the working of combustor dissipates mainly through supporting sticks by thermosoakback and radiation. The simulating results also show that the capillary tube used for transferring liquid fuel can effectively prevent the heat from transferring in the solenoid valve.

UR - https://www.scopus.com/pages/publications/0031152423

M3 - 文章

AN - SCOPUS:0031152423

SN - 1001-4055

VL - 18

SP - 40

EP - 44

JO - Tuijin Jishu/Journal of Propulsion Technology

JF - Tuijin Jishu/Journal of Propulsion Technology

IS - 3

ER -

Theoretical analysis on thermosoakback of monopropellant thruster

Abstract

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