公开(公告)号：US20230373662A1

公开(公告)日：2023-11-23

申请号：US18198569

申请日：2023-05-17

申请人： Sunlight Aerospace Inc.

发明人： Michael CYRUS ,  John P. MOUSSOURIS

IPC分类号： B64U50/34 ,  B64G1/10 ,  B64U50/31 ,  B64U50/32 ,  B64U50/33

CPC分类号： B64U50/34 ,  B64G1/1007 ,  B64U50/31 ,  B64U50/32 ,  B64U50/33 ,  B64U2101/20

摘要： Methods, apparatuses and systems for providing renewable energy powered, continuous geostationary orbital communications include arranging a plurality of renewable energy powered unmanned aerial vehicles (UAVs) having ground and air communication capabilities in a belt configuration around the earth, spacing apart the plurality of UAVs to provide intercommunication between at least neighboring ones of the plurality of UAVs, and positioning the plurality of UAVs in a relatively stationary location above the earth at a height of between 12 to 15 miles.

公开(公告)号：US11816867B2

公开(公告)日：2023-11-14

申请号：US17176988

申请日：2021-02-16

申请人： The Government of the United States of America, as represented by the Secretary of the Navy

发明人： Jason K. Jolliff

IPC分类号： B64G1/10 ,  G06T7/90 ,  H04N9/67

CPC分类号： G06T7/90 ,  B64G1/1021 ,  H04N9/67 ,  B64G2001/1028 ,  G06T2207/10024 ,  G06T2207/10032

摘要： Systems and methods are provided for color-enhancing satellite data in a manner that is specific to the true color ocean signal, i.e., the light that is emanating from the ocean surface. These color enhanced images, in turn, can be used as a scientific research and monitoring tool for studying the coastal ocean.

公开(公告)号：US11814195B1

公开(公告)日：2023-11-14

申请号：US16550977

申请日：2019-08-26

申请人： United States of America as represented by the Administrator of NASA

发明人： Michael Choi

IPC分类号： B64G1/22 ,  B64G1/40 ,  B64G1/10 ,  B64G1/42 ,  B64G1/44 ,  C04B35/14 ,  C04B35/622 ,  C01B33/12 ,  H01B1/14

CPC分类号： B64G1/226 ,  B64G1/10 ,  B64G1/409 ,  B64G1/425 ,  B64G1/443 ,  C01B33/12 ,  C04B35/14 ,  C04B35/62222 ,  C04B2235/3293 ,  C04B2235/3418 ,  H01B1/14

摘要： The present invention relates to an innovative thermal design concept of tailoring the absorptance and emittance of a coating—namely silicon oxide (SiOx) coated aluminized Kapton—as a radiator coating for small, nano-satellite (i.e., CubeSat) thermal management. The present invention improves on the thermal design of existing satellites, by: a) thermally coupling all components to the baseplate to eliminate the need for heater power for the battery; b) using all six sides of the CubeSat as radiators by changing the wall material from fiberglass to aluminum; c) using a different ratio of absorptance to emittance for each side by tailoring the SiOx thickness; d) having a high emittance for the wall interior and components; and e) eliminating the need for MLIs. The elimination of the MLIs reduces the volume and increases the clearance to minimize the risk for solar array deployment and cost of the thermal control subsystem.

公开(公告)号：US20230303268A1

公开(公告)日：2023-09-28

申请号：US18179880

申请日：2023-03-07

申请人： AST & Science, LLC

发明人： Adam H. Halperin ,  Raymond J. Sedwick

IPC分类号： B64G1/10 ,  B64G1/28 ,  B64G1/44

CPC分类号： B64G1/1007 ,  B64G1/286 ,  B64G1/443 ,  H02S20/32

摘要： An antenna system is configured for use in Low Earth Orbit (LEO) around Earth. The system has a plurality of antenna satellites coupled together to form a phased array. Each of the plurality of antenna satellites have an antenna body with an antenna and a solar cell. A processing device determines an orientation of the plurality of antenna satellites and position the phased array in the orientation based on an analysis of the solar cell of the antenna bodies facing the sun, the antenna of the antenna bodies facing the Earth, and maintaining a torque equilibrium of the phased array.

公开(公告)号：US20230271726A1

公开(公告)日：2023-08-31

申请号：US18143744

申请日：2023-05-05

申请人： Katalyst Space Technologies, LLC

发明人： Erik Olaf Harang ,  Ghonhee Lee ,  Nicholas Peter Liapis

IPC分类号： B64G1/24 ,  H04W64/00 ,  B64G1/10

CPC分类号： B64G1/242 ,  H04W64/003 ,  B64G1/10 ,  H04W84/18

摘要： Retrofittable satellite systems for an in-orbit host satellite comprising an enhancement module for adding a capability to the in-orbit host satellite, modifying the function of the in-orbit host satellite, and/or extending the function of the in-orbit host satellite. The in-orbit, retrofittable satellite system comprises a transfer vehicle for transferring the enhancement module from a first to a second location and a service vehicle for receiving the enhancement module from the transfer vehicle and installing the enhancement module on the in-orbit host satellite. In-orbit space situational awareness systems, comprising one or more in-orbit host satellites having one or more enhancement modules attached thereto, the enhancement modules comprising sensors such as satellite spatial location/position sensors, range sensors, navigation sensors, and/or proximity sensors for detecting other objects in-orbit, their location, speed, acceleration, orbital trajectory or the like, wherein the enhancement modules communicate to create a mesh network between the satellites.

公开(公告)号：US11725513B2

公开(公告)日：2023-08-15

申请号：US17450444

申请日：2021-10-08

申请人： Trans Astronautica Corporation

发明人： Joel C. Sercel ,  Anthony Price Longman ,  James G. Small

IPC分类号： E21C51/00 ,  E21C37/16 ,  B64G4/00 ,  B64G99/00 ,  B64G1/10

CPC分类号： E21C51/00 ,  B64G4/00 ,  B64G99/00 ,  E21C37/16 ,  B64G2001/1071

摘要： Systems and methods are disclosed for mining lunar and Martian polar permafrost to extract gas propellants. The method can comprise identifying a plurality of near-polar landing sites in craters in which the surface comprises permafrost in perpetual darkness, wherein such landing sites have perpetual sunlight available at altitudes of about 100 to 200 m. A mining outpost can be established in at least one of the sites and a high altitude solar array deployed at the landing site using a lightweight mast tall enough to generate near continuous power for the outpost. Systems and apparatus are disclosed for mining the permafrost at the landing sites using radiant gas dynamic mining procedures. The systems can comprise a rover vehicle with an integrated large area dome for cryotrapping gases released from the surface and multi-wavelength radiant heating systems to provide adjustable heating as a function of depth.

公开(公告)号：US11724827B2

公开(公告)日：2023-08-15

申请号：US17548464

申请日：2021-12-10

申请人： Valor Robotics, LLC

发明人： Deepak Sathyanarayan

IPC分类号： B64G1/10 ,  B64G1/40 ,  B64G1/64

CPC分类号： B64G1/1078 ,  B64G1/402 ,  B64G1/646

摘要： A spacecraft refueling and storage system comprising a first tank and a second tank for storing propellant, a rotatable shaft to which the first and second tanks are mounted for rotating the first and second tanks about an axis of the shaft, and a drive motor for rotating the shaft so that upon rotation of the first and second tanks, liquid propellant is separated from gas in the propellant and settled to an outer portion of the first and second tanks.

公开(公告)号：US11724825B1

公开(公告)日：2023-08-15

申请号：US17071901

申请日：2020-10-15

申请人： Blue Digs LLC

发明人： Robert Hawkins ,  Peterson Browning

IPC分类号： B64G1/00 ,  B64G1/10 ,  B64G1/24

CPC分类号： B64G1/007 ,  B64G1/1007 ,  B64G1/1085 ,  B64G1/242

摘要： A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.

公开(公告)号：US11719926B2

公开(公告)日：2023-08-08

申请号：US17365343

申请日：2021-07-01

申请人： Andrew Simon Filo

发明人： Andrew Simon Filo

IPC分类号： G02B26/02 ,  G01S17/74 ,  H10N30/20 ,  H10N30/857 ,  H10N30/87 ,  H10N39/00 ,  H01L31/053 ,  G09F3/02 ,  G09F3/10 ,  B64G1/10 ,  B64G1/66

CPC分类号： G02B26/02 ,  G01S17/74 ,  G09F3/02 ,  G09F3/10 ,  H01L31/053 ,  H10N30/204 ,  H10N30/857 ,  H10N30/878 ,  H10N39/00 ,  B64G1/1085 ,  B64G1/66 ,  G09F2003/0257

摘要： Provided herein is a modulating retroreflective multilayer film comprising retroreflective elements, a piezoelectric layer, a photovoltaic layer, and an energy storage device. The stacked and transparent layered configuration of the film allows the retroreflective elements and the photovoltaic layer to be simultaneously illuminated by a narrow beam. The low power piezoelectric layer and the energy harvesting of the photovoltaic layer allow the retroreflector to be energetically self-sufficient and suitable for remote deployment. The flexible properties of the component layers allow the retroreflector to be adhered to nonplanar or irregular surfaces for the purpose of labeling and tagging.

公开(公告)号：US11718420B2

公开(公告)日：2023-08-08

申请号：US17229812

申请日：2021-04-13

申请人： Northrop Grumman Systems Corporation

发明人： James Garret Nicholson ,  Daniel Carl Treachler ,  Oliver Benjamin Ortiz ,  Robert Bryan Sullivan ,  Carlos Guillermo Niederstrasser ,  Michael Joseph Glogowski ,  William A. Llorens ,  Kenneth Siu-Kin Chow ,  Peter Michael Cipollo

IPC分类号： B64G1/10 ,  B64G1/00 ,  B64G1/40 ,  B64G1/64

CPC分类号： B64G1/1078 ,  B64G1/007 ,  B64G1/40 ,  B64G1/402 ,  B64G1/646

摘要： Spacecraft servicing systems include a spacecraft servicing device and at least one mission extension pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.