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1. 发明专利

JP2003020000A Satellite launching method 有权
标题翻译：卫星启动方法
公开(公告)号：JP2003020000A
公开(公告)日：2003-01-21
申请号：JP2001207676
申请日：2001-07-09
申请人： Ihi Aerospace Co Ltd , Inst Of Space & Astronautical Science , 宇宙科学研究所長 , 株式会社アイ・エイチ・アイ・エアロスペース
发明人： KAWAGUCHI JUNICHIRO , HONDA MASAHISA , MAKINO TAKASHI
IPC分类号： B64G1/00
摘要： PROBLEM TO BE SOLVED: To sharply reduce a satellite launching cost by recovering and reusing most of mounting apparatuses such as rocket control avionics.
SOLUTION: When launching a satellite 5 by a multistage type rocket R, most of rocket control is intensively performed during a stage of a rise by burning of a rocket motor 1 of the first stage and an inertial rise succeeding to this rise, and rocket motors 2 and 3 on an after the second stage and the satellite 5 are made to reach a launching altitude, and after separating a capsule 7 mounted with the rocket control avionics from the rear end 2c of the satellite 5 side or the second stage of a machine body on and after the second stage, the rocket motors 2 and 3 on and after the second stage are successively burnt, and the satellite 5 is inputted to a prescribed orbit.
COPYRIGHT: (C)2003,JPO
摘要翻译：要解决的问题：通过恢复和重复使用大多数安装设备（如火箭控制航空电子设备），大大降低卫星发射成本。解决方案：当通过多级火箭R发射卫星5时，通过第一级火箭发动机1的燃烧和上升的惯性升高，火箭发动机的大部分火箭控制在升高阶段进行，而火箭发动机在第二阶段之后的第二和第三阶段和卫星5被制成达到发射高度，并且在将安装有火箭控制航空电子设备的胶囊7与机器的卫星5侧或第二级的后端2c分离在第二阶段和第二阶段之后，第二阶段和之后的火箭发动机2和3被连续地燃烧，卫星5被输入到规定的轨道。

2. 发明专利

JP2003026100A Large membrane space structure and it developing method 有权
标题翻译：大型空间结构及其开发方法
公开(公告)号：JP2003026100A
公开(公告)日：2003-01-29
申请号：JP2001215823
申请日：2001-07-16
申请人： Inst Of Space & Astronautical Science , 宇宙科学研究所長
发明人： KAWAGUCHI JUNICHIRO
IPC分类号： B64G1/22 , B64G1/24 , B64G1/40 , B64G1/44 , H01Q1/28 , H01Q15/16
CPC分类号： H01Q1/288 , H01Q15/161
摘要： PROBLEM TO BE SOLVED: To provide a large membrane space structure and its developing method.
SOLUTION: A sail part 4 of this large membrane space structure has a plurality of petals 6 having the same shape, and respectively symmetrically arranged on the virtual center line OA. These petals 6 are installed on a support 8 of a hub 2 arranged in a spacecraft, and can rotate on the virtual center line OA. Respective membrane materials are stretched along an area surrounded by dividing lines drawn at an optional interval from a second fulcrum A and an outer peripheral part of the petals 6. The mutual film materials are connected by belt materials 10 arranged in a prescribed position. These petals 6 operate centrifugal force by rotation, and operate tensile force in the circumferential direction on the membrane materials to develop the respective petals 6. When developing these petals 6, the support 8 is rotated to a prescribed angle, and a torque quantity applied to the large membrane space structure and a rotating speed of the spacecraft are controlled.
COPYRIGHT: (C)2003,JPO
摘要翻译：要解决的问题：提供大的膜空间结构及其开发方法。解决方案：这个大膜空间结构的帆部4具有多个具有相同形状的花瓣6，并且分别对称地布置在虚拟中心线OA上。这些花瓣6安装在布置在航天器中的轮毂2的支撑件8上，并且可以在虚拟中心线OA上旋转。各个膜材料沿着由第二支点A和花瓣6的外围部分以任意间隔绘制的分割线包围的区域被拉伸。相互膜材料通过布置在规定位置的带材10连接。这些花瓣6通过旋转来操作离心力，并且在膜材料上沿圆周方向操作张力以形成相应的花瓣6.当显影这些花瓣6时，支撑件8旋转到规定的角度，并且施加到控制了太空船的大的膜空间结构和旋转速度。

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