Demonstration of tethered hovering flight of HTTP-3AT hybrid rocket

Shih Sin Wei, Meng Che Lee, Jhen Wei Huang, Yueh Lu, Che Hao Kang, Sho Tsung Kao, Shao Jung Lu, Chang Hsiang Huang, Jun Jian Zhan, Zuo Ren Chen, Andrew Wang, Tzu Hao Chou, Alfred Lai, Yang Lee, Ming Tzu Ho, Hsin Piao Lin, Jong Shinn Wu

研究成果: Article同行評審

1 引文 斯高帕斯(Scopus)

摘要

This study demonstrated the performance of flight control systems of a hybrid rocket in a hovering flight test by developing a rocket designated HTTP-3AT powered by High Test Peroxide (HTP, a term used for concentrated hydrogen peroxide, H2O2). Hybrid rocket excels in system simplicity, operational safety, oxidizer storability, cost, and throttling capability compared to current solid and liquid rocket engine systems. Although issues such as the severe oxidizer-to-fuel (O/F) ratio shift during combustion and difficulty in gimbaled thrust vector control (TVC) caused by the lengthy chambers need to be solved, hybrid rocket propulsion is nevertheless a promising propulsion technology for future space exploration. To achieve accurate orbit insertion, thrust magnitude control and TVC of the rocket engines are necessary. However, no organizations have successfully implemented this technology on a practical hybrid rocket, not even using this technology for hovering flight tests. On September 8th, 2020, a hovering flight test of HTTP-3AT was conducted, achieving a steady hover 3 m above ground for 25 s utilizing both attitude and position controls. This test showed that a hybrid rocket could achieve a stable hovering flight with the capability of vertical takeoff and vertical landing (VTVL), demonstrating excellent throttling control and TVC capabilities of hybrid rocket propulsion.

原文English
頁(從 - 到)279-292
頁數14
期刊Acta Astronautica
191
DOIs
出版狀態Published - 2022 2月

All Science Journal Classification (ASJC) codes

  • 航空工程

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