Asakawa J, Nishii K, Nakagawa Y, Koizumi H, Komurasaki K
Department of Advanced Energy, University of Tokyo, 5-1-5 Kashiwanoha, Kashiwa-shi, Chiba 277-8561, Japan.
Department of Aeronautics and Astronautics, University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, Japan.
Rev Sci Instrum. 2020 Mar 1;91(3):035116. doi: 10.1063/1.5121411.
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 μN 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.
本文介绍了一种推力台的研制，该推力台能够在点火过程中直接测量立方星推进系统的推力和比冲。该推力台是一个倒立摆，并集成了一个质量天平用于直接原位质量测量。所提出的校准程序允许进行精确的性能表征，并通过考虑推进剂消耗导致的推力台零点漂移，实现了80 μN推力和0.01 g质量损失的分辨率。作为推力台概念验证，直接表征了用于立方星的水微电阻喷射推进系统的性能。在单次点火测试的各种条件下，获取了推力、比冲和质量消耗的连续曲线。对于喉部雷诺数在100 - 400范围内，测量到的推力为1 mN至10 mN，比冲为45 s至100 s，最大测量不确定度为±15.3%。
