著者

Yasuaki SAKAMOTO Kazuhide KURODA Shunsuke ONIBUCHI Susumu HARA

出版者

International Symposium on Space Technology and Science

雑誌

Journal of Evolving Space Activities (ISSN:27581802)

巻号頁・発行日

vol.1, pp.62, 2023 (Released:2023-08-30)

参考文献数

9

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Small rockets using hybrid rocket engines have been developed as a part of space development projects by student groups at various universities. The actively developed technologies include supersonic rockets and self-built engines. However, development based on aerodynamic technology has few precedents. In this paper, a case is described in which the Nagoya University Aerospace Flight Technology NAFT demonstrated attitude control technology, which is indispensable for rockets, by using aerodynamic technology. The main mission of the Masterpiece-05 Leidenschaft launch vehicle used for this launch demonstration was to achieve autonomous attitude control by rolling with movable fins. The goal was to roll the rocket by 45 deg after the engine burnout was stopped. The control law for the roll attitude control was proportionalderivative control, and the value of the gain was determined by estimating the torque in the roll direction generated by the movable fins using computational fluid dynamics. The launch took place during the Izu-Oshima Joint Launch Experiment (Izu-Oshima Space Event) held on November 9–11, 2018. The altitude and attitude of the airframe were logged. After stopping the roll of the airframe, attitude control was performed from 3.90 to 8.45 s after ignition. As a result, the phase difference between the roll attitude angle at the start of attitude control and the converged roll attitude angle at the end of attitude control was approximately 51.8 deg. The mission was confirmed to have been accomplished based on the numerical values of the roll attitude angle obtained from the data logger. These efforts are significant from the viewpoint of educational value in space engineering because there are few examples of extracurricular activities wherein students take such initiatives.

著者

Kikuko Miyata Arata Takaki Susumu Hara

出版者

The Institute of Electrical Engineers of Japan

雑誌

IEEJ Journal of Industry Applications (ISSN:21871094)

巻号頁・発行日

vol.11, no.3, pp.447-457, 2022-05-01 (Released:2022-05-01)

参考文献数

27

被引用文献数

1

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There is an increase in the popularity of small spacecraft because they are expected to introduce large opportunities in the space industry. However, there are two issues with increased use of small spacecraft: enhancement of cost-effectiveness and improvement in the mission failure rate. This study defines the battery state as the most important parameter in spacecraft operations because it directly relates to the health status of the spacecraft. We propose solving problems by introducing high-accuracy in situ state estimations for real-time operation mode selection and on-ground future state estimations of the battery in spacecraft operations planning by utilizing a suitable numerical model. The high-accuracy in situ state estimations allow us to minimize operational margins for battery protection, improve the efficiency of each spacecraft, and achieve safe spacecraft operations. The combination of a model-based system development approach and numerical optimization methods helps establish an efficient autonomous mission operations planner system to maximize mission duration. This enables us to reduce the human resource costs for spacecraft operations. This study addresses two topics: battery and spacecraft modeling, and establishing a mission operations planner system. The details of the system and battery modeling considering temperature dependence are explained using parameter identification results from the experiments. The design policy of the mission operations planner, which utilizes the battery status as the threshold of the operations and constraints, is explained via numerical optimization details. Numerical and experimental case studies are performed to evaluate the proposed method and show its effectiveness.