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1.发明公开
公开(公告)号：EP0195554A1
公开(公告)日：1986-09-24
申请号：EP86301556.6
申请日：1986-03-05
IPC分类号： B64G1/44
摘要： A spacecraft is disclosed which comprises a spacecraft body, at least one solar array (44,) extendible outwardly from the spacecraft body, and articulation means (80, 82. 84) for adjusting the position of the solar array (44,) relative to the spacecraft body independently about three axes, each of which is orthogonal to the axis adjacent to it Each articulation means comprises a first rotatable coupling (80) for permitting rotation of the solar array (44,) about a first axis substantially parallel to the surface of the spacecraft body, a second rotatable coupling (82) for permitting rotation of the solar array about a second axis normal to the first axis, and a third rotatable coupling (84) for permitting rotation of the solar array about a third axis normal to the second axis and parallel to the longitudinal axis of the array.
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2.发明公开Apparatus and method for docking spacecraft 失效Gerätund Verfahren zum Andocken eines Raumfahrzeuges。
公开(公告)号：EP0319212A2
公开(公告)日：1989-06-07
申请号：EP88311207.0
申请日：1988-11-25
IPC分类号： B64G1/14
CPC分类号： B64G1/646
摘要： A docking apparatus (20) for coupling two spacecraft comprises a rigid pressure vessel (22) having an internal passage, and first and second ports (24,28) connecting with the interior. The planes of the docking ports form an oblique angle with one another, causing the docked spacecraft to assume a canted or inclined position relative to other. The cant angle eliminates mechanical interference between the adjoining structures of the docked spacecraft. Methods for carrying out docking are also disclosed.
摘要翻译： 用于联接两个航天器的对接装置（20）包括具有内部通道的刚性压力容器（22）和与内部连接的第一和第二端口（24,28）。 对接端口的平面彼此形成一个倾斜的角度，使对接的航天器相对于另一个倾斜的倾斜位置呈倾斜或倾斜。 倾斜角度消除了对接的航天器的相邻结构之间的机械干扰。 还公开了进行对接的方法。
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3.发明授权
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公开(公告)号：EP0196793A1
公开(公告)日：1986-10-08
申请号：EP86301555.8
申请日：1986-03-05
IPC分类号： B64G1/10
CPC分类号： B64G1/641 , B64G1/002 , B64G1/12 , B64G1/14 , B64G1/222 , B64G1/44 , B64G2001/1092 , Y10S136/292
摘要： A modular spacecraft system adapted for orbital flight is capable of expansion by the connection of at least two substantially identical spacecraft modules (20), each of which is capable of independent operation. Each spacecraft module comprises a spacecraft body (21), at least one solar array (44, 46;) extendible outwardly from the spacecraft body, and at least one structural interface means (36) for connecting one spacecraft module to another spacecraft module. Methods for deployment of a spacecraft system utilizing a reusable space vehicle are also disclosed.
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公开(公告)号：EP0196793B1
公开(公告)日：1990-10-10
申请号：EP86301555.8
申请日：1986-03-05
IPC分类号： B64G1/10
CPC分类号： B64G1/641 , B64G1/002 , B64G1/12 , B64G1/14 , B64G1/222 , B64G1/44 , B64G2001/1092 , Y10S136/292
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公开(公告)号：EP0195553B1
公开(公告)日：1990-06-13
申请号：EP86301554.1
申请日：1986-03-05
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公开(公告)号：EP0319212A3
公开(公告)日：1990-05-16
申请号：EP88311207.0
申请日：1988-11-25
IPC分类号： B64G1/14
CPC分类号： B64G1/646
摘要： A docking apparatus (20) for coupling two spacecraft comprises a rigid pressure vessel (22) having an internal passage, and first and second ports (24,28) connecting with the interior. The planes of the docking ports form an oblique angle with one another, causing the docked spacecraft to assume a canted or inclined position relative to other. The cant angle eliminates mechanical interference between the adjoining structures of the docked spacecraft. Methods for carrying out docking are also disclosed.
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9.发明授权Spacecraft with articulated solar array and method for array deployment 失效具有ARICLE SOLAR ARRAY的阵列和阵列部署的方法
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公开(公告)号：EP0195553A3
公开(公告)日：1987-09-16
申请号：EP86301554
申请日：1986-03-05
摘要： A spacecraft (20) is adapted for orbital flight in two alternative modes, referred to as the earth-oriented and quasi sun-oriented modes. The spacecraft comprises a spacecraft body (21), at least one solar array (44, 46) extendible outwardly from the spacecraft body, passive attitude control means (58) utilizing gravity gradient stabilization means which is extendible and retractable relative to the spacecraft body (21), and active attitude control means (69, 71). The gravity gradient stabilization means (58) is effective when extended to stabilize the spacecraft in the earth-oriented mode, and the active attitude (69, 71) control means is effective to stabilize the spacecraft in the quasi sun-oriented mode.
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