公开(公告)号：US20230415924A1

公开(公告)日：2023-12-28

申请号：US18340939

申请日：2023-06-26

Applicant: TOYOTA JIDOSHA KABUSHIKI KAISHA

Inventor： Noriyuki NISHI ,  Hiroaki HANZAWA

IPC: B64G1/16 ,  B64G1/54

CPC classification number: B64G1/16 ,  B64G1/546

Abstract: A control device includes a computation section that computes information related to an effect of radiation received by a rover based on error information of a processing device provided to the rover, and a control section that performs control so as to reduce the effect of radiation received by the rover based on the information related to an effect of radiation computed by the computation section.

公开(公告)号：US20230271730A1

公开(公告)日：2023-08-31

申请号：US17748290

申请日：2022-05-19

Applicant: NEC Corporation

Inventor： Norihiko Mochida

IPC: B64G1/54 ,  B64G1/58

CPC classification number: B64G1/546 ,  B64G1/58

Abstract: A ruggedizing apparatus for electronic equipment in a spacecraft is provided that can achieve both a radiation shielding effect and a heat-dissipation effect. The ruggedizing apparatus includes: a pressure vessel that is filled with a coolant and places at least a heat-generating electronic circuit of the electronic equipment within the pressure vessel, wherein the heat-generating electronic circuit is immersed in the coolant; and a forced liquid-flow generator placed within the pressure vessel, wherein the forced liquid-flow generator causes the coolant on the heat-generating electronic circuit to move away from the heat-generating electronic circuit.

公开(公告)号：US20230234725A1

公开(公告)日：2023-07-27

申请号：US18159974

申请日：2023-01-26

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Takaomi Chubachi ,  Naoto Azusawa

IPC: B64G1/56 ,  B64G1/54

CPC classification number: B64G1/56 ,  B64G1/54

Abstract: A bumper is provided on an outer side of a structural body of a spacecraft with a predetermined gap between the bumper and the structural body. The bumper includes: a first layer that is provided on the outer side and that is formed from an impact resistant material; a second layer that is provided on an inner side being on a side of the structural body with respect to the first layer, the second layer having holes; and a third layer that is provided on the inner side with respect to the second layer, the third layer including a resin.

公开(公告)号：US20220204189A1

公开(公告)日：2022-06-30

申请号：US17263512

申请日：2019-07-05

Applicant: Space Talos Ltd.

Inventor： Majed Abdel JAWAD

IPC: B64G1/54 ,  H01F7/02

Abstract: A spacecraft radiation shield system (2) is disclosed for improving the protection from ionising radiation from the external environment and providing an improved freedom of orientation to the spacecraft. The spacecraft radiation shield system includes: at least two magnets arranged in a magnetic multipole (6), a magnetometer (14), and an adjustable magnet (10). The magnetometer (14) is configured to measure the magnetic field experienced at the spacecraft, and the magnetic field orientation of the adjustable magnet (10) is controlled in response to the measured magnetic field thereby controlling the direction and magnitude of the overall dipole moment of the system

公开(公告)号：US11299297B1

公开(公告)日：2022-04-12

申请号：US17179122

申请日：2021-02-18

Applicant: Eamonn Patrick Trainor

Inventor： Eamonn Patrick Trainor

IPC: B64G1/54 ,  B64G1/42

Abstract: A system to create a magnetic field or fields around the outside of a spacecraft to provide protection from cosmic and solar radiation. Electromagnets are placed within one or more layers of the outer shell or surface of a spacecraft and are used to generate magnetic fields. Side electromagnets are placed within one or more of the side layers of the outer shell or surface of the spacecraft and separate configurations of electromagnets are positioned within one or more layers of the outer shell or surface of the spacecraft, in a cross shaped configuration, either Quadrupole electromagnet configuration or two right-angled electromagnet configuration, at the front and rear of the spacecraft in geometric alignment with the opposite poled side positioned electromagnets. Magnetic field lines are channeled around the outside of the spacecraft by use of the right-angled electromagnet configuration or centered on the center of the quadrupole electromagnet configuration.

公开(公告)号：US11199585B2

公开(公告)日：2021-12-14

申请号：US16365221

申请日：2019-03-26

Applicant: Hamilton Sundstrand Corporation

Inventor： Robert P. Wichowski ,  Timothy A. Roberts ,  Darren Woodman ,  Nicholas Van Derzee

IPC: G01R31/3185 ,  G05B23/02 ,  G06F8/34 ,  G06F11/14 ,  B64G1/46 ,  B60W50/02 ,  G07C5/08 ,  B64G1/52 ,  B64G1/54

Abstract: Diagnosing whether controllers of internal vehicle systems are the source of failures detected by a system control managing a vehicle such as a spacecraft. Highspeed data is received via at a field programmable gate array (FPGA) embedded in an assembly of the vehicle. The FPGA includes a controller and a digital diagnostic interface. In one embodiment, the diagnostic interface utilizes Very Highspeed Integrated Circuit (VHSIC) Hardware Description Language (VHDL) for performance modeling of a controller configured to control at least one internal system within the vehicle. The VHDL performance models the controller. Upon receiving an indication of a failure, the performance modeling of the controller is used to ascertain whether or not the controller is the source of the failure. Disassembly of the assembly housing the internal system is not required in order to ascertain whether or not the controller is the source of the failure.

公开(公告)号：US11077627B2

公开(公告)日：2021-08-03

申请号：US16103428

申请日：2018-08-14

Applicant: Northrop Grumman Systems Corporation

Inventor： Steven F. Stone ,  Matt Armentrout ,  Christopher Deemer ,  Carl Madsen ,  Brian Barber

IPC: B29C65/00 ,  B64G1/22 ,  B64G1/54 ,  B64G1/56 ,  B64G1/58 ,  F41H5/04 ,  B64D7/00 ,  B29L31/30 ,  B32B15/02 ,  B32B37/10 ,  B32B37/00 ,  G21F1/10

Abstract: A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

公开(公告)号：US20210188464A1

公开(公告)日：2021-06-24

申请号：US17176710

申请日：2021-02-16

Applicant: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA

Inventor： Donald L. Thomsen, III ,  Sankara N. Sankaran ,  Joel A. Alexa

IPC: B64G1/58 ,  B32B15/01 ,  C23C4/134 ,  C23C4/137 ,  C22C14/00 ,  B64G1/54 ,  C23C4/08 ,  C23C28/02 ,  G21F1/12

Abstract: In some aspects, this disclosure relates to improved Z-grade materials, such as those used for shielding, systems incorporating such materials, and processes for making such Z-grade materials. In some examples, the Z-grade material includes a diffusion zone including mixed metallic alloy material with both a high atomic number material and a lower atomic number material. In certain examples, a process for making Z-grade material includes combining a high atomic number material and a low atomic number material, and bonding the high atomic number material and the low atomic number together using diffusion bonding. The processes may include vacuum pressing material at an elevated temperature, such as a temperature near a softening or melting point of the low atomic number material. In another aspect, systems such as a vault or an electronic enclosure are disclosed, where one or more surfaces of Z-grade material make up part or all of the vault/enclosure.

公开(公告)号：US20210005333A1

公开(公告)日：2021-01-07

申请号：US17026464

申请日：2020-09-21

Applicant: Lockheed Martin Corporation

Inventor： Thomas J. McGuire

IPC: G21B1/11 ,  G21B1/05 ,  H01L39/02 ,  G21B1/17 ,  B64G1/54 ,  G21F3/00 ,  H05K9/00

Abstract: A fusion reactor includes a fusion plasma reactor chamber. A magnetic coil structure is disposed inside of the fusion plasma reactor chamber, and a structural component is also disposed inside of the fusion plasma reactor chamber. The structural component couples the magnetic coil structure to the fusion plasma reactor chamber. A superconducting material is disposed at least partially within the structural component. A plurality of cooling channels are disposed at least partially within the structural component. An insulating material is disposed at least partially within the structural component.

公开(公告)号：US20200270000A1

公开(公告)日：2020-08-27

申请号：US15931419

申请日：2020-05-13

Applicant: Richard Williams

Inventor： Richard Williams

IPC: B64G1/54 ,  B64G1/42

Abstract: Example aspects of an assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The assembly can comprise a deployable deployed electromagnetic radiation deflector shield comprising: a power supply; and an electromagnet configured to generate a magnetic field to deflect radiation; and a spacecraft, wherein the deployed electromagnetic radiation deflector shield is unattached to the spacecraft when deployed from the spacecraft, wherein the deployed electromagnetic radiation deflector shield is deployed at a distance away from the spacecraft, and wherein the distance is configured to prevent the magnetic field generated by the electromagnet from interfering with the spacecraft.