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1. 发明专利

JP2004191423A Retroreflective body 审中-公开
公开(公告)号：JP2004191423A
公开(公告)日：2004-07-08
申请号：JP2002355859
申请日：2002-12-06
申请人： Kawasaki Heavy Ind Ltd , Natl Space Development Agency Of Japan , 宇宙開発事業団 , 川崎重工業株式会社
发明人： KONO ISAO , MOKUNO MASAAKI , SAKATA TAKASHI , KUBOTA NOBUYUKI , ATSUTA TOSHIO , SAKURAI TAKASHI
IPC分类号： G02B5/122
摘要： PROBLEM TO BE SOLVED: To reflect incident light in a comparatively wide region by mitigating retroreflection characteristics.
SOLUTION: A retroreflective body 35 is composed to combine a plurality of μ-CCRs 34. μ-CCR 34 is a triangular pyramid, and the inside of three sides of the triangular pyramid is reflective faces 12-14. Angles α, β and γ making mutually adjacent reflective faces are chosen from the angle separated from 90°. An opening part 16 is formed oppositely to an intersection point 15 of the three reflective faces 12-14, the plurality of μ-CCRs 34 have the opening part arranged on a similar plane, and an arrangement pitch P is chosen so that optical defractive characteristic is optimum. Incident light 18 emitted from the opening part 16 reflects on the three reflective faces 12-14, and emits to six directions inclined at only an angle of ϕ to the incident light 18 from the opening part 16, and since reflective light 19 has broadening due to defractive characteristics, a broadening angle θ to the incident direction of the reflective light 19 is a comparatively wide angle θ4.
COPYRIGHT: (C)2004,JPO&NCIPI

2. 发明专利

JP2003306200A Image navigation for rendezvous docking and navigation device 有权
标题翻译：用于RENDEZVOUS DOCKING和NAVIGATION DEVICE的图像导航
公开(公告)号：JP2003306200A
公开(公告)日：2003-10-28
申请号：JP2002111841
申请日：2002-04-15
申请人： Kawasaki Heavy Ind Ltd , Natl Space Development Agency Of Japan , 宇宙開発事業団 , 川崎重工業株式会社
发明人： KONO ISAO , ISHIJIMA YOSHIYUKI , YOKOO ATSUSHI , ENOMOTO MASAYUKI , KANAMARU TAKAO , KUBOTA NOBUYUKI
IPC分类号： B64G1/64 , B64G1/24 , B64G1/66 , G06T7/60
摘要： PROBLEM TO BE SOLVED: To provide an image navigation for a rendezvous docking and navigation device allowing a non-cooperative target satellite having no special marker launched in the past to effectively navigate at rendezvous docking (RVD) by moving a service satellite so as to approach a place, as a target, having an annular satellite-common structure such as a satellite frame part of a target satellite and corresponding to an object portion to be docked. SOLUTION: Image of the target satellite 2 is picked up including the satellite frame part 21 by the service satellite 1, relative distance between the service satellite 1 and the target satellite 2 is measured, relative position of the satellite frame part 21 for the service satellite 1 is calculated, and the satellite frame part 21 in the picked up image is recognized as at least either an ellipse or a circular arc. Thereby, relative attitude of the satellite frame part 21 for the service satellite 1 is calculated, and the service satellite 1 is moved so as for the satellite frame part 21 in the picked up image to be close to a circle on the basis of the calculated relative position and relative attitude. COPYRIGHT: (C)2004,JPO
摘要翻译：要解决的问题：提供用于会合对接和导航装置的图像导航，允许不具有过去发射的特殊标记的非合作目标卫星通过移动服务卫星而在会合对接（RVD）中有效地导航作为目标接近具有诸如目标卫星的卫星帧部分的环形卫星共同结构并对应于待对接的对象部分的地方。解决方案：由服务卫星1拾取包括卫星帧部分21的目标卫星2的图像，测量服务卫星1和目标卫星2之间的相对距离，卫星帧部分21的相对位置用于计算服务卫星1，将拍摄图像中的卫星帧部21识别为椭圆或圆弧中的至少一个。由此，计算出服务卫星1的卫星帧部21的相对姿态，并且，服务卫星1被移动，使得所拾取图像中的卫星帧部21基于计算出的卫星帧部21接近圆相对位置和相对态度。版权所有（C）2004，JPO

3. 发明专利

JP2004330943A Artificial satellite joint mechanism, spacecraft with the same, and control method 有权
公开(公告)号：JP2004330943A
公开(公告)日：2004-11-25
申请号：JP2003131191
申请日：2003-05-09
申请人： Kawasaki Heavy Ind Ltd , Natl Space Development Agency Of Japan , 宇宙開発事業団 , 川崎重工業株式会社
发明人： ODA MITSUSHIGE , KONO ISAO , UENO HIROSHI , HORIE YOICHI , KUBOTA NOBUYUKI , KAGAYA HIROAKI , MORIYAMA TAKASHI
IPC分类号： B64G1/64
摘要： PROBLEM TO BE SOLVED: To provide an artificial satellite joint mechanism capable of effectively establishing a rendezvous docking with a non-cooperative target satellite launched in the past, and to provide an spacecraft with the same and control method. SOLUTION: A cylindrical frame structure such as PAF I/F (Payload Attach Fitting Interface) 70 that many artificial satellites served as a target satellite have as a common structure is held by oscillating opening/closing operation of two arm members 105, 105 provided with compliance mechanisms 107, 107, thereby capturing a target satellite softly. The PAF I/F 70 which is held is drawn to the service satellite side along with the arm members 25, 25 by a ball screw mechanism 103, and the end face of the PAF I/F 70 is brought into contact with the connection surface (damper plate 111) of the service satellite, thereby rigidly connecting the target satellite. COPYRIGHT: (C)2005,JPO&NCIPI

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