|Table of Contents|

Experimental investigations on non-rated condition performance of a 10 N thruster with bi-centrifugal swirl injector(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2020年01期
Page:
52-58
Research Field:
研究与设计
Publishing date:

Info

Title:
Experimental investigations on non-rated condition performance of a 10 N thruster with bi-centrifugal swirl injector
Author(s):
ZHAO Ting1; 2;  LIU Changguo1; 2;  WU Lingfeng1; 2;  NI Weigen1; 2
(1.Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China)
Keywords:
10 N thruster;  bi-centrifugal swirl injector;  non-rated condition
PACS:
V434.3文献标识码:A 文章编号:1672-9374(2020)01-0052-07
DOI:
-
Abstract:
According to the development experience of 10 N bi-propellant thrusters at home and abroad, the range of inlet pressure is from 0.8 MPa to 2.2 MPa.The deviation of inlet pressure will cause great changes in thruster performance such as vacuum specific impulse and gas temperature.To investigate the performance of a 10 N bi-propellant thruster at different supply pressures from 0.8 MPa to 2.2 MPa,experiments were conducted on the discharge device with two-dimensional particle dynamic analyzer,as well as with the 42 km-high-altitude simulation test facility.It has successfully undergone all qualification tests recommended for bipropellant blowdown propulsion system.The results show that the 10 N bi-propellant thruster can fit the supply pressures from 0.6 MPa to 2.5 MPa,the nominal specific impulse of the thruster is greater than 2 881 N·s/kg when the inlet pressure is 1.58 MPa.When the inlet pressure changes from 0.6 MPa to 2.5 MPa, the corresponding vacuum thrust increases from 4.7N to 14 N and the pressure drop-down ratio is 3.As inlet pressure increases, the specific impulse also increases, when the inlet pressure is 0.6 MPa, the vacuum specific impulse is 2 600 N·s/kg; and when the inlet pressure is 2.5 MPa, the vacuum specific impulse is 2 956 N·s/kg.Within the range, the combustion chamber temperature of the thruster is lower than the allowable temperature of the material, reflecting the excellent design of the thruster, which can meet the performance demands of bipropellant blowdown propulsion system for attitude control.

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Last Update: 2020-02-25