公开(公告)号：US20250002180A1

公开(公告)日：2025-01-02

申请号：US18690210

申请日：2022-08-24

Applicant: UNSEENLABS

Inventor： Jonathan GALIC ,  Marc GRIEU

IPC: B64G1/58 ,  B64G1/54 ,  H05K7/20

Abstract: A system includes a sealed enclosure comprising: an outer layer comprising a metallic foam; a radiation shielding layer; one or more heat transfer elements comprising one or more active heat transfer element disposed on one or more inner faces of the sealed enclosure, and configured or configurable to extract heat from the interior of the sealed enclosure; one or more electronic related components inside the sealed enclosure.

公开(公告)号：US12129054B2

公开(公告)日：2024-10-29

申请号：US18207649

申请日：2023-06-08

Applicant: Zhishang Zhou

Inventor： Zhishang Zhou

IPC: B64G1/62 ,  B64D3/00 ,  B64D17/80 ,  B64G1/58 ,  B64U10/20 ,  B64U101/00 ,  B64U10/60 ,  B64U20/70 ,  B64U101/45

CPC classification number: B64G1/623 ,  B64D3/00 ,  B64D17/80 ,  B64G1/58 ,  B64G1/625 ,  B64U10/20 ,  B64U10/60 ,  B64U20/70 ,  B64U2101/00 ,  B64U2101/45

Abstract: Systems and methods using VTOL (vertical take-off and landing) aircrafts including drones and helicopters for soft capture, preserving, and landing of a returning spacecraft from space are disclosed. The spacecraft is decelerated by parachutes. One or multiple VTOL drones transport a water impermeable pocket meeting and capturing the descending spacecraft in the air. The spacecraft is thus preserved inside the pocket and keeps descending and then softly lands in a body of water. In another embodiment, a recovery helicopter, one type of VTOL aircraft with heavy payload lifting capacity, is used to directly catch the returning spacecraft. One or multiple VTOL drones are coupled to the bottom end of a recovery cable hung from the helicopter. These drones bring a clutch quickly and precisely catching the descending spacecraft directly without interrupting the parachutes. The spacecraft is thus caught and preserved by the helicopter with lifting function of the parachutes maintained.

公开(公告)号：US20240300676A1

公开(公告)日：2024-09-12

申请号：US18669991

申请日：2024-05-21

Applicant: Blue Origin, LLC

Inventor： David Harper ,  Jeramy Kimball ,  Logan Sailer ,  Curtis Wen

IPC: B64G1/58 ,  B64G1/40 ,  F28F3/02

CPC classification number: B64G1/58 ,  B64G1/4021 ,  F28F3/02

Abstract: Rocket components having internal heat fins are described herein. The disclosed components have internal heat fins that mitigate buckling and uneven force application by adding thermal capacity to the component without adding component stiffness. This reduces a thermal force fight (i.e., tension versus compression between cold and hot areas, respectively), which inhibits the buckling loads on the propellant tank. The internal heats fins also provide for a reduced mass of the propellant tank wall relative to a propellant tank wall without internal heat fins. By reducing the thermal force fight, as discussed above, less material can be used which further allows for thinner welds to be used (i.e., less welding material).

公开(公告)号：US20240286768A1

公开(公告)日：2024-08-29

申请号：US18176219

申请日：2023-02-28

Applicant: Lockheed Martin Corporation

Inventor： Mark Ramirez ,  Donna Hooker ,  Olivia Christine Chen ,  Megan Taylor Isabelle ,  David Wayne Knapp ,  Meredith Swegan Nevius

IPC: B64G1/58 ,  B64G1/54

CPC classification number: B64G1/58 ,  B64G1/546

Abstract: According to some embodiments, a spacecraft includes an electronics housing having a sun-facing side. The spacecraft further includes a peel-and-stick thermal control material coupled to the sun-facing side of the electronics housing. The peel-and-stick thermal control material includes a non-metallic optical interface coating, a carrier film, and an adhesive.

公开(公告)号：US20240228067A1

公开(公告)日：2024-07-11

申请号：US18557222

申请日：2022-04-14

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Delphine CARPONCIN ,  Sébastien LEFOLL ,  Christophe FIGUS

IPC: B64G1/50 ,  B33Y80/00 ,  B64G1/10 ,  B64G1/58

CPC classification number: B64G1/503 ,  B64G1/1028 ,  B64G1/58 ,  B33Y80/00

Abstract: A thermoregulated thermomechanical structure for a focal plane suitable for operating in a space environment is disclosed having an interface for supporting dissipative electronic equipment, the structure being monolithic, metallic and including a radiator and a first two-phase heat-transfer fluid transport cavity, extending within the radiator and providing direct thermal transport between the interface and the radiator. The structure also includes a second cavity encapsulating a phase change material.

公开(公告)号：US11794927B2

公开(公告)日：2023-10-24

申请号：US16554150

申请日：2019-08-28

Applicant: The Boeing Company

Inventor： Richard W. Aston ,  Nicole Diane Schoenborn ,  Nicole Marie Hastings ,  Christopher David Joe

IPC: B64G1/22 ,  B33Y10/00 ,  B33Y80/00 ,  B64G1/58 ,  B22F10/28 ,  B22F10/66 ,  B64G1/56

CPC classification number: B64G1/22 ,  B33Y10/00 ,  B33Y80/00 ,  B22F10/28 ,  B22F10/66 ,  B64G1/56 ,  B64G1/58

Abstract: A method of additively manufacturing a spacecraft panel includes printing a first skin and a second skin, spaced apart from the first skin. The method further includes printing a first truss structure connecting the first skin to the second skin.

公开(公告)号：US11746214B2

公开(公告)日：2023-09-05

申请号：US17231980

申请日：2021-04-15

Applicant: THE BOEING COMPANY

Inventor： Kelly Jonathan Courter ,  Patrick Jacob Mobers ,  Bryan Brewer

IPC: B64G1/58 ,  C08K7/26 ,  C09D183/04 ,  C08K7/28 ,  B29C48/00 ,  B64G1/62 ,  B29B7/90 ,  C08J3/20 ,  C08K3/32 ,  C08K3/38 ,  B29K83/00 ,  B29K105/16 ,  B29L31/30

CPC classification number: C08K7/26 ,  B29B7/90 ,  B29C48/022 ,  B64G1/58 ,  B64G1/62 ,  C08J3/203 ,  C08K3/32 ,  C08K3/38 ,  C08K7/28 ,  C09D183/04 ,  B29K2083/00 ,  B29K2105/16 ,  B29L2031/3076 ,  C08J2383/04 ,  C08K2003/322 ,  C09D183/04 ,  C08K7/28 ,  C08K2003/322 ,  C08K2003/387 ,  C09D183/04 ,  C08K7/26 ,  C08K3/32 ,  C08K3/38

Abstract: A lightweight ablator formulation has been developed which offers superior thermal performance compared to current state of the art ablator formulations. The lightweight ablator formulations described herein typically include at least one endothermically decomposing (energy absorbing) material with a fluxing agent resulting in significantly reduced backface temperature response and a more stable surface. According to one implementation the ablator composition comprises about 30 to about 70 percent by weight of a base silicone resin, about 25 to about 67 percent by weight of a low-density filler, about 3 to about 7 percent by weight of a curing agent and greater than 0 and up to about 10 percent by weight of a boron-containing compound.

公开(公告)号：US11724836B2

公开(公告)日：2023-08-15

申请号：US14469941

申请日：2014-08-27

Applicant: Arthur M Dula

Inventor： Arthur M Dula

IPC: B64G1/64 ,  B64G1/26 ,  B64G1/62 ,  B64G1/24 ,  B64G1/12 ,  B64G1/58 ,  B64G1/14 ,  B64G1/52 ,  B64G1/22

CPC classification number: B64G1/648 ,  B64G1/244 ,  B64G1/26 ,  B64G1/62 ,  B64G1/12 ,  B64G1/14 ,  B64G1/52 ,  B64G1/58 ,  B64G2001/224 ,  B64G2001/525

Abstract: A spacecraft reaction control system comprising: a spacecraft having a center of mass; a length of tether extending from said spacecraft and offset from said spacecraft's center of mass and means for controllably changing said extension of said offset such that a variable force is exerted upon said spacecraft by said tether, said force being offset from said center of mass.

公开(公告)号：US11718424B2

公开(公告)日：2023-08-08

申请号：US16387204

申请日：2019-04-17

Applicant: The Boeing Company

Inventor： Eric S. Mindock ,  Richard W. Aston ,  Anna Maria Tomzynska-Engers ,  Raynaldo Santiago, Jr.

IPC: B64G1/58 ,  H05B3/00 ,  H05B3/14 ,  H05B3/34

CPC classification number: B64G1/58 ,  H05B3/0014 ,  H05B3/145 ,  H05B3/34 ,  H05B2203/011 ,  H05B2214/04

Abstract: Protective blankets comprise a flexible blanket body and a voltage supply. The flexible blanket body comprises a plurality of sheets of material operatively coupled together to define the flexible blanket body. The plurality of sheets comprises one or more sheets composed at least in part of a carbon nanotube material and at least one sheet composed of a different material. The voltage supply is electrically coupled at least to a first sheet of the one or more sheets composed at least in part of the carbon nanotube material, such that the first sheet defines a resistive heater.

公开(公告)号：US20230232588A1

公开(公告)日：2023-07-20

申请号：US18008685

申请日：2020-08-04

Applicant: Mitsubishi Electric Corporation

Inventor： Takashi MORIYAMA ,  Hiroaki ISHIKAWA ,  Tomohiko SAITO ,  Tatsuya KUSASHIMA

IPC: H05K7/20 ,  B64G1/58

CPC classification number: H05K7/2039 ,  B64G1/58 ,  H05K7/20327

Abstract: A cooling apparatus (100) cools a heat-generating instrument, such as an electronic instrument (2), installed in an installation apparatus. The cooling apparatus (100) includes a refrigerant flow path configured circularly by sequentially connecting a pump (1) that circulates a refrigerant in a liquid state, a cooler (3) that cools the heat-generating instrument with the refrigerant, and a radiator (5) that cools the refrigerant. The cooling apparatus (100) includes a discharge-side heat exchanger (7) provided in a flow path from the pump (1) to the cooler (3) in the refrigerant flow path, a suction-side heat exchanger (8) provided in a flow path from the radiator (5) to the pump (1) in the refrigerant flow path, and a Peltier device (9) that is provided between the discharge-side heat exchanger (7) and the suction-side heat exchanger (8), and transfers heat from the refrigerant flowing through the suction-side heat exchanger (8) to the refrigerant flowing through the discharge-side heat exchanger (7).