公开(公告)号：US20230406547A1

公开(公告)日：2023-12-21

申请号：US17467361

申请日：2021-09-06

Applicant: Pritok Capital LLC

Inventor： Michael Stesel

IPC: B64G5/00 ,  B64G1/00 ,  B64G1/10

CPC classification number: B64G5/00 ,  B64G1/002 ,  B64G1/10 ,  B64G2005/005 ,  B64G2001/1092

Abstract: Method and apparatus to efficiently launch spacecraft from underwater. Unfortunately, the prior art processes of launching spacecraft from sea either make no use of water buoyancy or waste use rocket fuel to overcome water resistance. As a result, payloads are smaller than are ideal. The instant invention however adds water buoyancy to increase the overall thrust of the spacecraft and therefore makes the spacecraft more efficient than if launched outside of water.

公开(公告)号：US20180093786A1

公开(公告)日：2018-04-05

申请号：US15689993

申请日：2017-08-29

Applicant: Space Systems/Loral, LLC

Inventor： Robert Erik Schwarz ,  Robert Edward Helmer ,  Paul Anthony Briggs ,  John Douglas Lymer ,  Alfred Heikal Tadros ,  Andrew E. Turner

IPC: B64G1/10 ,  B64G1/64 ,  B64G4/00

CPC classification number: B64G1/10 ,  B64G1/002 ,  B64G1/1078 ,  B64G1/222 ,  B64G1/64 ,  B64G1/646 ,  B64G4/00 ,  B64G2001/1092 ,  B64G2004/005

Abstract: 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.

公开(公告)号：US09878805B2

公开(公告)日：2018-01-30

申请号：US14746046

申请日：2015-06-22

Applicant: Los Alamos National Security, LLC

Inventor： Stephen Judd ,  Nicholas Dallmann ,  Kevin McCabe ,  Daniel Seitz

IPC: B64G1/10 ,  B64G1/22 ,  B64G1/42 ,  B64G1/44 ,  B64G1/64

CPC classification number: B64G1/10 ,  B64G1/222 ,  B64G1/428 ,  B64G1/44 ,  B64G1/641 ,  B64G2001/1092

Abstract: A “black box” space vehicle solution may allow a payload developer to define the mission space and provide mission hardware within a predetermined volume and with predetermined connectivity. Components such as the power module, radios and boards, attitude determination and control system (ADCS), command and data handling (C&DH), etc. may all be provided as part of a “stock” (i.e., core) space vehicle. The payload provided by the payload developer may be plugged into the space vehicle payload section, tested, and launched without custom development of core space vehicle components by the payload developer. A docking station may facilitate convenient development and testing of the space vehicle while reducing handling thereof.

公开(公告)号：US20170361948A1

公开(公告)日：2017-12-21

申请号：US15536024

申请日：2015-12-11

Applicant: Thales Alenia Space Italia S.p.A. Con Unico Socio

Inventor： Francesco Lumaca ,  Giuseppe Oronzo

IPC: B64G1/10

CPC classification number: B64G1/10 ,  B64G2001/1092

Abstract: The present invention concerns a method for making a microsatellite, comprising providing: modules of a first type configured to house electronic boards of a microsatellite; modules of a second type configured to house devices and systems of a microsatellite; and modules of a third type comprising first and second interface means configured to be coupled to a launch vehicle and to external appendages of a microsatellite, respectively; said modules of a third type being designed to cause a body of a microsatellite to have a predefined height; wherein all the modules of the first, second and third types are configured to be stacked regardless of the type. The method further comprises making a body of a microsatellite by stacking modules of different types, wherein the stacked modules include at least one module of the second type and at least one module of the third type.

公开(公告)号：US09650160B2

公开(公告)日：2017-05-16

申请号：US14046613

申请日：2013-10-04

Applicant: THALES

Inventor： Bruno Celerier

IPC: B64G1/52 ,  H04B7/185 ,  B64G1/10 ,  B64G1/54 ,  G01S19/02 ,  B64G1/22 ,  B64G1/44 ,  B64G1/50

CPC classification number: B64G1/1007 ,  B64G1/222 ,  B64G1/44 ,  B64G1/503 ,  B64G1/54 ,  B64G2001/1092 ,  G01S19/02

Abstract: A telecommunication satellite with geostationary orbit comprises an upper module, a lower module, and a lateral module, disposed in a storage configuration between the upper module and the lower module, and deployed to an operational configuration of the satellite in the orbit by a rotation in relation to an axis Z oriented towards the earth in the operational configuration. The lateral module comprises two substantially plane and mutually parallel main surfaces, termed dissipative surfaces, able to dissipate by radiation a quantity of heat generated by facilities of the satellite; the dissipative surfaces being, in the operational configuration, held in a manner substantially parallel to the plane of the orbit, making it possible to limit the solar flux received by the dissipative surfaces and to optimize the quantity of heat dissipated by the lateral module.

公开(公告)号：US09571194B2

公开(公告)日：2017-02-14

申请号：US14097667

申请日：2013-12-05

Applicant: The Boeing Company

Inventor： Ronald W. Burch

IPC: H04B10/118 ,  B64G1/64 ,  B64G1/10 ,  H04B5/00 ,  B64G1/42

CPC classification number: H04B10/118 ,  B64G1/428 ,  B64G1/641 ,  B64G1/646 ,  B64G2001/1092 ,  H04B5/0031

Abstract: A system and method for wirelessly communicating between a host bus of a spacecraft and a secondary payload. In one configuration, the host bus and secondary payload each include a wireless interface for establishing a radio or optical communications link thereby allowing for the elimination of a complex wiring harness connected between the host bus and the secondary payload.

Abstract translation: 一种用于在航天器的主机总线和辅助有效载荷之间进行无线通信的系统和方法。 在一种配置中，主机总线和辅助负载每个都包括用于建立无线电或光通信链路的无线接口，从而允许消除连接在主机总线和辅助有效载荷之间的复杂线束。

公开(公告)号：US20170029138A1

公开(公告)日：2017-02-02

申请号：US15303898

申请日：2015-04-03

Applicant: CENTRE NATIONAL D'ETUDES SPATIALES

Inventor： Pascal Bultel

IPC: B64G1/00 ,  B64G1/64 ,  B64G1/40

CPC classification number: B64G1/007 ,  B64G1/402 ,  B64G1/646 ,  B64G2001/1092

Abstract: The invention relates to a method for transferring a space payload from a first orbit to a second orbit. Said method is characterized in that the space payload, moving about the first orbit, is attached to a removable orbital towing assistance device including at least one fuel pouch. Said method includes the steps of: —attaching (E1) an orbital transfer vehicle to the removable orbital towing assistance device; and —transferring (E2) the space payload and the removable orbital towing assistance device to the second orbit by means of the orbital transfer vehicle. The invention also relates to a removable orbital towing assistance device intended for a space payload and an orbital transfer vehicle and enabling direct supply of fuel to the vehicle and/or the space payload.

Abstract translation: 本发明涉及一种将空间有效载荷从第一轨道传送到第二轨道的方法。 所述方法的特征在于，围绕第一轨道移动的空间有效载荷附接到包括至少一个燃料袋的可拆卸轨道牵引辅助装置。 所述方法包括以下步骤：将轨道转移车辆（E1）附接到可拆卸轨道牵引辅助装置; 并通过轨道转运车辆（E2）将空间有效载荷和可移动轨道牵引辅助装置（E2）传送到第二轨道。 本发明还涉及一种用于空间有效载荷和轨道转运车辆并且能够直接向车辆和/或空间有效载荷提供燃料的可拆卸的轨道牵引辅助装置。

公开(公告)号：US09376222B2

公开(公告)日：2016-06-28

申请号：US14538090

申请日：2014-11-11

Applicant: NOVAWURKS, INC.

Inventor： Talbot Jaeger

IPC: B64G1/66 ,  B64G1/40

CPC classification number: B64G1/66 ,  B64G1/10 ,  B64G1/1007 ,  B64G1/1021 ,  B64G1/40 ,  B64G1/402 ,  B64G1/428 ,  B64G1/50 ,  B64G2001/1092

Abstract: A method of cooling spacecraft electronics by transferring fuel between two or more satlets is provided. Each satlet's electronics is thermally coupled to the satlet's fuel tank. A controller connected to a temperature sensor determines that a temperature of a first satlet's electronics is reaching, has reached, or exceeds a predetermined threshold. The controller connected to a second temperature sensor determines that a temperature of a second satlet's propellant is lower than the temperature of the first satlet's electronics. The controller then directs the flow of propellant from the second satlet's fuel tank to the first satlet's fuel tank to cool the first satlet's electronics.

Abstract translation: 提供了一种通过在两个或更多个三脚架之间传送燃料来冷却航天器电子设备的方法。 每个座椅的电子设备都热耦合到座椅的燃油箱。 连接到温度传感器的控制器确定第一个电池的电子装置的温度达到或超过预定的阈值。 连接到第二温度传感器的控制器确定第二个沙粒的推进剂的温度低于第一个沙发电子设备的温度。 然后，控制器将推进剂从第二个座椅的燃料箱引导到第一个座椅的燃料箱，以冷却第一个座椅的电子设备。

公开(公告)号：US20150039879A1

公开(公告)日：2015-02-05

申请号：US14517592

申请日：2014-10-17

Applicant: Cal Poly Corporation

Inventor： Jordi Puig-Suari ,  Austin Williams

IPC: B64G1/66 ,  G06F9/44

CPC classification number: B64G1/66 ,  B64G1/10 ,  B64G1/288 ,  B64G1/32 ,  B64G1/363 ,  B64G1/366 ,  B64G1/428 ,  B64G1/546 ,  B64G2001/1092 ,  G06F9/4406

Abstract: A satellite system includes a chassis, an avionics package included within an upper portion of the chassis. The avionics package includes a main system board, a payload interface board, at least one daughter board and a battery board. The main system board, the payload interface board, the at least one daughter board, and the battery board reside in substantially parallel planes. The payload interface board, the at least one daughter board, and the battery board are coupled to the main system board through one or more stackable connectors. A method of operating a satellite is also described.

Abstract translation: 卫星系统包括机箱，包括在机箱的上部内的航空电子设备组件。 航空电子组件包括主系统板，有效载荷接口板，至少一个子板和电池板。 主系统板，有效载荷接口板，至少一个子板和电池板位于基本平行的平面中。 有效负载接口板，至少一个子板和电池板通过一个或多个可堆叠连接器耦合到主系统板。 还描述了操作卫星的方法。

公开(公告)号：US08702040B2

公开(公告)日：2014-04-22

申请号：US13096078

申请日：2011-04-28

Applicant: Tadayuki Takahashi ,  Takeshi Takashima ,  Hiroyuki Ogawa ,  Shin-ichiro Sakai ,  Naoko Iwata ,  Yoshikatsu Kuroda ,  Kazunori Masukawa

Inventor： Tadayuki Takahashi ,  Takeshi Takashima ,  Hiroyuki Ogawa ,  Shin-ichiro Sakai ,  Naoko Iwata ,  Yoshikatsu Kuroda ,  Kazunori Masukawa

IPC: B64G1/00

CPC classification number: B64G1/1021 ,  B64G1/10 ,  B64G1/428 ,  B64G1/44 ,  B64G1/50 ,  B64G2001/1092

Abstract: An artificial satellite system includes at least two panel type artificial satellites closely connected with a plurality kind of multi networks and the minimum necessary essential tools for one artificial satellite installed on a substrate of each panel type artificial satellite, wherein the multi networks are formed by a communicating network for communicating data among data processing tools installed on each of the panel type artificial satellites, a heat pipe for providing thermal energy among tools installed on each of the panel type artificial satellites and a battery supplying line for connecting battery controlling devices installed in the each panel type artificial satellite so that the artificial satellite system can maintain higher and various controlling performance with a back-up effect of the multi network in the case that any function tool is damaged in one of the panel type artificial satellite.

Abstract translation: 人造卫星系统包括至少两个与多种多重网络紧密连接的面板式人造卫星，以及安装在每个面板型人造卫星的基板上的一个人造卫星的最小必要必要工具，其中多个网络由 用于在安装在每个面板式人造卫星上的数据处理工具之间传送数据的通信网络，用于在安装在每个面板型人造卫星上的工具之间提供热能的热管，以及用于连接安装在所述面板式人造卫星中的电池控制装置的电池供应线 每个面板型人造卫星，使人造卫星系统能够在面板式人造卫星之一任何功能工具损坏的情况下，通过多网络的后备效果来保持更高和各种控制性能。