羽生 宏人

<p>In recent years, demand for launch of the rockets has increased from space development. Although the solid propellant rockets relatively reasonable, it is difficult to safely manufacture a large of solid propellant, and the manufacturing process is non-constant. Therefore, we consider it is more reasonable if it is possible to manufacture the solid propellant safely and continuously. We focused on the movements to mix of the intestinal tract. We have developed a peristaltic pump that based on bowel peristaltic using straight-fiber-type artificial muscle. In this paper, We developed an inter-units heating device as a heating function for realizing a continuous mixing and Transport process using a peristaltic pump, and measured heating performance of inter-units heating device and show its usefulness.</p>

<p>In recent years, the demand for rocket launching has increased due to the development of space technology. However, using inexpensive rockets is not always possible. Although the cost of solid-propellant rockets is relatively reasonable, safely manufacturing a large amount of solid propellant is difficult, and the manufacturing process is disjointed. Therefore, safe and continues manufacturing of solid propellant is necessary. On the basis of the movements of the intestinal tract, we proposed that the movements required for transport and mixing of solid propellants are possible to achieve without the application of a large shear force. The peristaltic motion enables not only the mixing but also conveying even high viscosity slurry. By mimicking these intestinal movements, we have considered and developed the peristaltic pumping by driven artificial muscle as one of the candidates for the continuous and safety mixer. In this research, the mixing completeness of the composite solid propellant slurry by the peristaltic pumping mixer was estimated. The result showed that the mixer we proposed could mix the propellant slurry. In the propellant samples, these variances were sufficiently small.</p>

Copyright © 2017 by the International Astronautical Federation (IAF). All rights reserved. On January 2017, JAXA/ISAS launched the Nano launcher based on the sounding rocket. Unfortunately, the rocket was not able to put a satellite into orbit. This paper discusses the trajectory design regarding how to manage the sounding rocket as a satellite-launching vehicle. At JAXA/ISAS, there are three types of sounding rockets. Two are single-stage rockets called S-310 and S-520, and one is a two-stage rocket called SS-520. These sounding rockets have tail fins for spin stabilization, but usually lack an attitude control system during flight. When attitude control is required to achieve the mission requirements, a gas jet system is available as an optional device. The gas jet system can control the vehicle's spin axis direction and spin rate during coasting fight. To enable the sounding rocket to put a satellite into orbit, a third-stage motor is added to the SS-520 two-stage sounding rocket. The gas jet system is a unique and active attitude control system installed between the first and second stages of the vehicle. Given this constraint, the apogee altitude after burnout of the first-stage motor almost corresponds with the perigee altitude of the elliptical orbit. In this mission, the sounding rocket based Nano launcher is planned to put a 3U-size CubeSat into elliptical orbit. Its targeted apogee altitude is about 1,800 km and its perigee altitude is about 180 km. As the perigee altitude is a relatively low altitude, the orbit life is very short. Thus, any vehicle or environment errors significantly affect the achieved trajectory. Such errors must be small enough to put a CubeSat into orbit. This paper also discusses the effect of orbital distribution depending on various errors.

Copyright © 2016 by the International Astronautical Federation (IAF). All rights reserved. The target of this study is to realize the continuous solid propellant producing technique for a cost reduction of solid rocket motor systems. In the process of the solid propellant manufacture, the mixing process controls the quality of the loaded solid propellant; the batch process is impossible to be replaced at present. We have considered the peristaltic pumping action mixer as one of the candidates for the continuous mixer. This mixer system is based on the artificial muscle actuator (soft actuator), and it is elongated and contracted by the pressurized gas. The system has some segments that has double rubber pipes (inner/outer), and the units can work independently. The outer rubber tube controls the shape change direction; the inner one works as a mixing chamber. The outer tube is swollen by the pressurized gas and the segments constrict axially; the inner tube inflates and the free volume can be changed. We expected that this mixer system has possible to replace the batch process by the continuous one. The peristaltic motion enables not only the mixing but also conveying even high viscosity slurry. The mixing mechanism by the soft actuator compress has no impact for the safety of the solid propellant handling. In this research, the mixing completeness of the composite solid propellant slurry by the peristaltic pumping mixer was estimated. The dispersion of the particle materials in the binder and the existing voids was observed by the X ray CT microscope. The solid propellant samples were made by our mixing system. The test materials were as follows: Hydroxyl terminated polybutadiene (HTPB) polymer as for the binder, aluminum powder as for the metallic fuel, dioctyladipate as for the plasticizer, ammonium perchlorate particles as for the oxidizer. The propellant composition was HTPB/AP/Al = 14/68/18 in massThe result showed that the mixer we proposed could mix the propellant slurry. The X ray CT scanning images showed that the solid materials well dispersed through the analysis of the luminance histograms.

平成27年度宇宙輸送シンポジウム（2016年1月14日-15日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000050034レポート番号: STCP-2015-035 Space Transportation Symposium FY2015 (January 14-15, 2016. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan

© 2015 IEEE. In recent years, the demand for rocket launching has increased due to the development of space technology. However, using inexpensive rockets is not always possible. Although the cost of solid-propellant rockets is relatively reasonable, safely manufacturing a large amount of solid propellant is difficult, and the manufacturing process is disjointed. Therefore, safe and continues manufacturing of solid propellant is necessary. On the basis of the movements of the intestinal tract, we realized that the movements required for transport and mixing of solid propellants are possible to achieve without the application of a large force. By mimicking these intestinal movements, we can safely and continuously manufacture a large amount of solid propellant. We developed a peristaltic pump, based on bowel peristalsis, using straight-fiber-type artificial muscle, and in this study, we demonstrate the usefulness of this pump for transporting the highly viscous fluids and solid-liquid mixed fluid. We consider that the peristaltic pump can also be effectively used as a mixing device. In this paper, we show that mixing one highly viscous fluid with another is possible by measuring the luminance values. In the manufacturing process, we use glass beads with the same diameter as microparticles and a sodium polyacrylate aqueous solution resembling a high viscosity fluid or hydroxyl-terminated polybutadiene as the raw material in the solid propellant. We then measure the glass beads in the resulting solid-liquid mixed fluid.