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公开(公告)号：US10536674B2
公开(公告)日：2020-01-14
申请号：US15900653
申请日：2018-02-20
发明人： Andrew E. Turner
摘要： A low earth orbiting spacecraft (LEO spacecraft) operable in a first earth orbit includes a main body, a data collection payload, and a first directional antenna, each of the data collection payload and the first directional antenna being coupled with the main body. During a first period of time, the main body is oriented such that the data collection payload views a region of interest on the earth. During a second period of time, the main body and the first directional antenna are oriented such that the first directional antenna is directed toward a first ground station. During a third period of time, the main body and the first directional antenna are oriented such that the first directional antenna is directed toward a second spacecraft operating in a second orbit.
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公开(公告)号：US20180134415A1
公开(公告)日：2018-05-17
申请号：US15849289
申请日：2017-12-20
发明人： Andrew E. Turner
CPC分类号： B64G1/24 , B64G1/1007 , B64G1/1021 , B64G1/1085 , B64G1/222 , B64G1/242 , B64G1/44 , B64G1/503 , B64G2001/643
摘要： A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.
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3.发明申请公开(公告)号：US20170247125A1
公开(公告)日：2017-08-31
申请号：US15441040
申请日：2017-02-23
CPC分类号： B64G1/242 , B64G1/007 , B64G1/1007 , B64G1/1085 , B64G1/40 , B64G1/405
摘要： A constellation of Earth-orbiting spacecraft includes a first spacecraft disposed in a first orbit, a second spacecraft disposed in a second orbit, and a third spacecraft disposed in a third orbit. Each of the first orbit, the second orbit and the third orbit is substantially circular with a radius of approximately 42,164 km, and has a specified inclination with respect to the equator within a range of 5° to 20°. The first orbit has a first right ascension of ascending node RAAN1, the second orbit has a second RAAN (RAAN2) approximately equal to RAAN1+120°, and the third orbit has a third RAAN (RAAN3) approximately equal to RAAN1+240°. A fourth spacecraft is disposed in a fourth orbit that has a period of approximately one sidereal day, an inclination of less than 2°, a perigee altitude of at least 8000 km, and an eccentricity between approximately 0.4 and 0.66.
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公开(公告)号：US20160244189A1
公开(公告)日：2016-08-25
申请号：US14627936
申请日：2015-02-20
发明人： Andrew E. Turner
IPC分类号： B64G1/24
CPC分类号： B64G1/24 , B64G1/1007 , B64G1/1021 , B64G1/1085 , B64G1/222 , B64G1/242 , B64G1/44 , B64G1/503 , B64G2001/643
摘要： A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.
摘要翻译： 在低地球轨道上运行的高度在160至800公里的航天器具有包括散热电气设备和地面有效载荷的主体。 航天器上的控制表面被铰接，以便：使用空气动力学阻力效应为飞船主体提供三轴姿态控制，使得地面有效载荷相对于地球保持在选定的方位; 并且通过铰接控制表面来控制轨道高度和周期中的一个或两个，以便调节空气动力学阻力的量。 所述控制表面包括在悬臂上设置成轨道结构的第一控制表面，所述悬臂与所述主体机械联接，以及与所述电气设备电耦合的太阳能阵列中的一个或两个，以及热辐射 阵列与电气设备热耦合。
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公开(公告)号：US10562647B2
公开(公告)日：2020-02-18
申请号：US15849289
申请日：2017-12-20
发明人： Andrew E. Turner
摘要： A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.
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公开(公告)号：US10364051B1
公开(公告)日：2019-07-30
申请号：US15352471
申请日：2016-11-15
发明人： Andrew E. Turner
摘要： A stationkeeping strategy for a satellite disposed in a TAP orbit includes controlling parameters of the orbit such that, for a constellation of two satellites disposed in the orbit, the constellation provides substantially continuous coverage of a polar region. The stationkeeping strategy includes one or more of: establishing an initial Right Ascension of Ascending Node (RAAN) of the operational orbit such that naturally caused orbital drift results in a mid-life RAAN of approximately 0 degrees (360 degrees); and controlling Argument of Perigee (ARGP), only indirectly, by performing orbit maintenance maneuvers only to directly control one or more of the operational orbit apogee altitude, the operational orbit perigee altitude, and inclination within a respective required range.
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公开(公告)号：US10329034B2
公开(公告)日：2019-06-25
申请号：US15441040
申请日：2017-02-23
摘要： A constellation of Earth-orbiting spacecraft includes a first spacecraft disposed in a first orbit, a second spacecraft disposed in a second orbit, and a third spacecraft disposed in a third orbit. Each of the first orbit, the second orbit and the third orbit is substantially circular with a radius of approximately 42,164 km, and has a specified inclination with respect to the equator within a range of 5° to 20°. The first orbit has a first right ascension of ascending node RAAN1, the second orbit has a second RAAN (RAAN2) approximately equal to RAAN1+120°, and the third orbit has a third RAAN (RAAN3) approximately equal to RAAN1+240°. A fourth spacecraft is disposed in a fourth orbit that has a period of approximately one sidereal day, an inclination of less than 2°, a perigee altitude of at least 8000 km, and an eccentricity between approximately 0.4 and 0.66.
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公开(公告)号：US10214303B1
公开(公告)日：2019-02-26
申请号：US15277505
申请日：2016-09-27
摘要： A launch vehicle includes an upper stage and an integral fairing. In a launch configuration, the integral fairing is configured to enclose, between an aft portion and a forward portion, one or more payloads. The integral fairing includes a mechanical attachment with the upper stage proximal to the aft portion, and a nose cap proximal to the forward portion and a passive venting arrangement that equalizes pressures internal and external to the integral fairing. The integral fairing is configured to permit deployment of at least one payload, while avoiding: (i) separation of the integral fairing into two or more parts, (ii) separation of the integral fairing from the upper stage, and (iii) articulation of the mechanical attachment. The upper stage may provide single stage to orbit capability.
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公开(公告)号：US20180093786A1
公开(公告)日：2018-04-05
申请号：US15689993
申请日：2017-08-29
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
CPC分类号： B64G1/10 , B64G1/002 , B64G1/1078 , B64G1/222 , B64G1/64 , B64G1/646 , B64G4/00 , B64G2001/1092 , B64G2004/005
摘要： A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.
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公开(公告)号：US20170247124A1
公开(公告)日：2017-08-31
申请号：US15441037
申请日：2017-02-23
CPC分类号： B64G1/242 , B64G1/007 , B64G1/1007 , B64G1/1085 , B64G1/40 , B64G1/405
摘要： A constellation of Earth-orbiting spacecraft, the constellation having an orbital maneuver lifetime life (OML), includes a first spacecraft disposed in a first orbit and a second spacecraft disposed in a second orbit, each of orbit being substantially circular with a radius of approximately 42,164 km and having a respective inclination with respect to the equator specified within a range of 10° to 20°. The first orbit has, at beginning of life (BOL), a first right ascension of ascending node (BOL-RAAN1) and the second orbit has, at BOL, a second RAAN (BOL-RAAN2) the BOL-RAAN1 and the BOL-RAAN2 being separated by a first angular separation Δ-RAAN1. A first stationkeeping delta-V (ΔV1) applied over the OML to the first spacecraft, in combination with a second delta-V (ΔV2) applied over the OML to the second spacecraft, maintains the Δ-RAAN1 approximately constant and an actual inclination within specification, and ΔV1 approximately equals ΔV2.
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