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    STACKABLE SATELLITES AND METHOD OF STACKING SAME
    1.
    发明申请
    STACKABLE SATELLITES AND METHOD OF STACKING SAME 审中-公开
    可堆叠卫星及其堆叠方法

    公开(公告)号：WO2016176298A1

    公开(公告)日：2016-11-03

    申请号：PCT/US2016/029509

    申请日：2016-04-27

    Applicant: FIELD, Daniel, W. ,  ASKIJIAN, Armen ,  GROSSMAN, James ,  SMITH, Alexander, D.

    Inventor： FIELD, Daniel, W. ,  ASKIJIAN, Armen ,  GROSSMAN, James ,  SMITH, Alexander, D.

    IPC: B64G1/10 ,  B64G1/64 ,  B64G1/66

    CPC classification number: B64G1/641 ,  B64G1/10 ,  B64G2001/643

    Abstract: A stackable satellite includes a satellite frame and at least one vertical pillar attached to the frame. The vertical pillar has an upper end and a lower end. The upper end is coupled to the lower end of the vertical pillar of the satellite above and the lower end is coupled to the upper end of the vertical pillar of the satellite below. The vertical pillar receives substantially all of the vertical load of the stackable satellite and any other satellites stacked above. Use of such vertical pillars removes the need for a dispenser or substantially lightens the dispenser mass to allow substantially more satellites to be carried in a payload.

    Abstract translation: 可堆叠的卫星包括卫星框架和附接到框架的至少一个垂直支柱。 立柱具有上端和下端。 上端与上述卫星的垂直支柱的下端连接，下端与下方的卫星的垂直支柱的上端连接。 垂直支柱基本上承受可堆叠卫星和任何其他上面堆叠的卫星的所有垂直载荷。 使用这样的垂直支柱不需要分配器或基本上减轻分配器质量以允许在有效载荷中承载更多的卫星。

    METHOD FOR THERMAL STABILIZATION OF A COMMUNICATIONS SATELLITE
    2.
    发明申请
    METHOD FOR THERMAL STABILIZATION OF A COMMUNICATIONS SATELLITE 审中-公开
    通信卫星的热稳定方法

    公开(公告)号：WO2016161275A1

    公开(公告)日：2016-10-06

    申请号：PCT/US2016/025537

    申请日：2016-04-01

    Applicant: SMITH, Alexander, D. ,  ASKIJIAN, Armen ,  FIELD, Daniel, W. ,  GROSSMAN, James

    Inventor： SMITH, Alexander, D. ,  ASKIJIAN, Armen ,  FIELD, Daniel, W. ,  GROSSMAN, James

    IPC: B64G1/10 ,  B64G1/24 ,  B64G1/50 ,  B64G1/58

    CPC classification number: B64G1/58 ,  B64G1/1007 ,  B64G1/242 ,  B64G1/425 ,  B64G1/50 ,  B64G1/503 ,  B64G1/66

    Abstract: A method for thermally stabilizing a communication satellite in orbit around the Earth relies on the discrete rotational symmetry of the pattern of antenna beams of the satellite. Exploiting the symmetry, the orientation of the satellite is changed from time to time by rotating the satellite through a symmetry angle of the rotational symmetry. Because of the symmetry, the beam pattern is unchanged after the rotation; but, because the rotation angle is less than 360°, a different side of the satellite is exposed to sunlight. The use of different thermal radiators and thermal shields on different sides of the satellite means that the thermal budget of the satellite is different after the rotation. By judiciously applying rotations as needed, as the orbit's orientation relative to the Sun evolves in time, it is possible to achieve effective control on the thermal budget of the satellite.

    Abstract translation: 用于热稳定地球周围轨道的通信卫星的方法依赖于卫星的天线波束图案的离散旋转对称性。 利用对称性，通过旋转卫星通过旋转对称的对称角度来不时地改变卫星的方向。 由于对称性，光束图案在旋转后不变; 但由于旋转角度小于360°，所以卫星的不同侧面暴露在阳光下。 在卫星的不同侧面使用不同的热辐射器和热屏蔽意味着卫星的热预算在旋转后是不同的。 根据需要明智地应用轮转，随着轨道相对于太阳的方向发展，可以有效地控制卫星的热预算。

    PASSIVE THERMAL SYSTEM PROVIDING AN EMBEDDED INTERFACE FOR HEAT PIPES
    3.
    发明申请
    PASSIVE THERMAL SYSTEM PROVIDING AN EMBEDDED INTERFACE FOR HEAT PIPES 审中-公开
    为热管提供嵌入式接口的被动热系统

    公开(公告)号：WO2017024187A1

    公开(公告)日：2017-02-09

    申请号：PCT/US2016/045675

    申请日：2016-08-05

    Applicant: SMITH, Alexander D. ,  ASKIJIAN, Armen ,  FIELD, Daniel W. ,  GROSSMAN, James

    Inventor： SMITH, Alexander D. ,  ASKIJIAN, Armen ,  FIELD, Daniel W. ,  GROSSMAN, James

    IPC: B23P15/26

    CPC classification number: B64G1/1007 ,  B64G1/503 ,  B64G1/506 ,  B64G1/66 ,  B64G2001/1092 ,  F28D15/0275

    Abstract: A passive thermal system for use in aerospace vehicles includes a first passive thermal panel having at least one internal resident heat pipe, wherein the first passive thermal panel is further configured to provide an embedded interface between a portion of the resident heat pipe and at least one heat pipe extending from a neighboring passive thermal panel. The embedded interface is facilitated via an internal channel that is adjacent to the internal resident heat pipe. The channel is dimensioned and arranged to receive a portion of a heat pipe extending from a passive thermal panel that will be situated adjacent to the first passive thermal panel. The embedded interface is also facilitated by an arrangement that imparts a compressive force to the non-resident heat pipe that urges it against the resident heat pipe.

    Abstract translation: 用于航空航天车辆的被动热系统包括具有至少一个内部驻留热管的第一被动热板，其中所述第一被动热板还被构造成提供所述驻留热管的一部分与至少一个 从相邻的被动热面板延伸的热管。 通过与内部驻留热管相邻的内部通道便于嵌入式接口。 该通道的尺寸和尺寸被设计成接收从与第一被动热板相邻的被动热板延伸的一部分热管。 嵌入式接口还通过一种向非驻留热管施加压缩力的装置来促使嵌入式接口将其压向驻留的热管。

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