Direct measurement of 1-mN-class thrust and 100-s-class specific impulse for a CubeSat propulsion system

被引：16

作者：

Asakawa, J. ^{[1
]}

Nishii, K. ^{[2
]}

Nakagawa, Y. ^{[2
]}

Koizumi, H. ^{[1
]}

Komurasaki, K. ^{[2
]}

机构：

[1] Univ Tokyo, Dept Adv Energy, 5-1-5 Kashiwanoha, Kashiwa, Chiba 2778561, Japan

[2] Univ Tokyo, Dept Aeronaut & Astronaut, Bunkyo Ku, 7-3-1 Hongo, Tokyo 1138656, Japan

来源：

REVIEW OF SCIENTIFIC INSTRUMENTS | 2020年 / 91卷 / 03期

基金：

日本学术振兴会;

关键词：

PERFORMANCE; STAND; BALANCE;

D O I：

10.1063/1.5121411

中图分类号：

TH7 [仪器、仪表];

学科分类号：

0804 ; 080401 ; 081102 ;

摘要：

This paper presents the development of a thrust stand to enable direct measurement of thrust and specific impulse for a CubeSat propulsion system during firing. The thrust stand is an inverted pendulum and incorporates a mass balance for direct in situ mass measurement. The proposed calibration procedure allows precise performance characterization and achieves a resolution of 80 mu N thrust and 0.01 g mass loss, by taking into account the drift of the thrust-stand zero caused by propellant consumption. The performance of a water micro-resistojet propulsion system for CubeSats was directly characterized as a proof of concept of the thrust stand. Continuous profiles of thrust, specific impulse, and mass consumption were acquired under various conditions in a single firing test. A thrust from 1 mN to 10 mN and a specific impulse from 45 s to 100 s with a maximum measurement uncertainty of +/- 15.3% were measured for the throat Reynolds number in the range 100-400.

引用

页数：10