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Matches 1 - 50 out of 13,639

Document Document Title
WO/2018/226287A1
A method, operable in the presence of ambient cosmic rays, is provided for braking a craft upon approach to a planet, moon or other space body, e.g. in preparation for landing. Deuterium-containing particle fuel material is projected in ...  
WO/2018/225688A1
Provided is a multilayer heat-insulating material which reduces a deterioration in heat-insulating performance at the periphery of a mounting means for mounting on a mounting subject and which facilitates deformation into a desired shape...  
WO/2018/224998A1
An attitude control and thrust boosting system (100) for a space launcher is disclosed, wherein the space launcher is equipped with a rocket engine (303) provided with an exhaust nozzle. The exhaust nozzle comprises a divergent portion (...  
WO/2018/224803A1
A phased array antenna and apparatus incorporating the same An electromagnetic phased array (100) is disclosed comprising a plurality of antenna elements (102), each antenna element (102) comprising at least three constituent antennae (1...  
WO/2018/220990A1
[Problem] To provide a sheet-like optical device that is capable of selectively emitting light of which the direction of the optical path is changed. [Solution] An optical device (1) is provided with a first sheet (50) and a second sheet...  
WO/2018/220699A1
A lunar orbiter system is obtained in which functions (positioning, communication, flashing) are assigned to artificial satellites in accordance with the relative positions of the artificial satellites in relation to the moon when the mo...  
WO/2018/222796A1
A satellite that includes a housing, a circuit board containing circuitry and disposed in the housing, a battery disposed in the housing and electrically connected to the circuit board, one or more weights disposed in the housing, wherei...  
WO/2018/216761A1
A robot comprises a telescoping device that can freely extend and contract in at least one direction, at least two end effectors that are respectively connected to at least two ends of the telescoping device, and a control unit that can ...  
WO/2018/210929A1
Device (52) for regulating the rate of flow of propellant fluid for an electric thruster, of the thermo-capillary device type comprising at least one capillary duct that is electrically conductive and capable of regulating the rate of fl...  
WO/2018/208201A1
A payload dispenser (1)for a launch vehicle comprising a plurality of panels (2), wherein at least one panel (2) comprises at least one payload (3) mounted onto the panel (2). The panels (2)are attachable to each other by means of attach...  
WO/2018/208193A1
A payload dispenser (1)for a launch vehiclecomprising a plurality of panels (2), wherein at least one panel (2) comprisesat least one payload (3) mounted onto the panel (2). The panels (2)are attachable to each other forming a self-suppo...  
WO/2018/209185A1
Integrated power module device, systems, and methods are provided in accordance with various embodiments. For example, some embodiments include a system that may include one or more integrated power modules. Each integrated power module ...  
WO/2018/200183A1
A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have a...  
WO/2018/196888A1
The invention relates to an electromagnetic toroidal impeller in the field of physics applied to electromagnetism. The invention comprises a cylindrical arrangement of superconducting antennas (9) which are separated by a dielectric (8) ...  
WO/2018/191992A1
Disclosed is a dual-axis rotation cycloid ring acceleration power device, comprising a main ring (1) connected to a motion carrier, and a secondary ring (2) movably arranged on the inner side of the main ring. The main ring and the secon...  
WO/2018/195512A1
A system for compact stowage and deployment of a flexible solar array includes a deployer unit and a blanket container for containing the flexible solar array. The deployer unit includes a frame, a closed-section collapsible mast for dep...  
WO/2018/192898A1
The subject matter of the invention is a deployable tubular structure, for protecting a piece of equipment (40) of a satellite (100), comprising a membrane (20) and a support frame of the membrane, the frame comprising a base (10a), a pl...  
WO/2018/191256A1
Methods, systems, and devices for foldable tube with unitary hinge are provided in accordance with various embodiments. Some embodiments include a device that may include one or more foldable tube sections configured to facilitate the de...  
WO/2018/189633A1
An automatic apparatus (1) for the controlled launch and recovery of a "tethered" mass (M) in orbit (or in free fall) comprising: a support structure (2) abutting on a reference surface, a winding assembly (3) coupled to the support stru...  
WO/2018/188555A1
Disclosed in the present invention is a method for reducing air resistance to a high speed moving object, comprising: first, using a multi-microporous air permeable material to prepare the housing of a moving object, such that one side o...  
WO/2018/190943A1
Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft (10) and a second spacecraft (11) as the first spacecraft approaches the second spacecraf...  
WO/2018/189259A1
The present invention relates to an extending device (1000) for extending at least one upper panel (1310) and at least one lower panel (1110), comprising at least: - a frame (1003) extending along a main extension axis (1410) and support...  
WO/2018/190944A1
Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an asse...  
WO/2018/191427A1
This description relates to an extensible space-based infrastructure platform having modules that can be launched in a stowed configuration, placed in orbit, and then deployed to extend the modules away from each other for an integrated ...  
WO/2018/187204A1
A modular micro-cathode arc thruster for use in satellites. An exemplary satellite has a plurality of stacked modular arc thrusters, each having an external anode, an internal cathode, and an insulator therebetween. The arc thrusters are...  
WO/2018/185478A1
A system (100) for detecting objects in space comprises an array of satellite nodes (1011 to 101N). The array of satellite nodes comprise at least one transmitter module (107) for transmitting an electromagnetic signal, and a plurality o...  
WO/2018/176877A1
Disclosed is an on-orbit fault countermeasure method using an optimized control mode for dynamics of a satellite with multiple flexible appendages. According to the method, a three-axis attitude controller of a satellite with multiple fl...  
WO/2018/179547A1
Spacecraft including a spacecraft bus (100). An additive manufacturing system of the spacecraft bus including at least one extruder (110A, 110B) for delivering feedstock to print an object outside of the spacecraft bus (100). A sensor fo...  
WO/2018/180086A1
The present invention is provided with a resistance generation mechanism which is provided with: a base ring 2 disposed on one space vehicle A; a one-side capturing ring 3 that comes into contact with the other-side space vehicle B; six ...  
WO/2018/175037A1
Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical i...  
WO/2018/173348A1
This low-temperature tank is provided with a container main body (10). The container main body (10) includes: a metal liner (13) that forms a storage space; and a wall member (14) wound on an outer peripheral surface (13a) of the metal l...  
WO/2018/172659A1
The invention relates to a heat transfer device (2) capable of transferring heat, comprising a housing (5) having a first main wall (12) and a second main wall (14), said housing (5) comprising an internal cavity (6) closed in a sealed m...  
WO/2018/167473A1
The present subject matter relates to a system and a method for galactic transportation (100). The galactic transportation system (100) may comprise multiple rails (102) arranged in a first direction (103), a platform (108) for supportin...  
WO/2018/167840A1
The present invention is configured such that, for each RSO(n), in each combination of observation-possible time periods OT(h) for a number R(n) of requested observations, an evaluation value E(m,n,h) is integrated that was calculated by...  
WO/2018/167161A1
The invention relates to a method for determining, by reanalysis, a vibratory environment of a coupled vehicle/passenger system, the vehicle being subjected to external forces Fext and being coupled to a new passenger comprising x=l, ......  
WO/2018/162831A1
An electrodynamic assembly (3) for propelling a spacecraft (1) in orbit around a star having a magnetic field, comprising at least one coaxial cable (7) comprising an electrically conductive core (8) surrounded by a first electrically in...  
WO/2018/164426A1
The present invention relates to a method for detecting a porphyry copper ore body by using hyperspectral imaging of malachite, the method comprising the steps of: obtaining hyperspectral image data of an alteration zone indicated by alt...  
WO/2018/160215A1
This invention relates to magnetic propulsion systems. Previously, motors required electronic control systems for efficiency. Embodiments of the present invention use a first axel (120) joined to a first permanent magnet (113) of a first...  
WO/2018/158531A1
The invention relates to a device and a method for the connection and linear separation of two elements (1, 2), such as the two stages of a spacecraft, consisting in using a tube (4) containing a pyrogenic-type material (5) and a glue (3...  
WO/2018/160740A1
A three-axis spacecraft including a spacecraft body including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck and a zenith deck. The zenith deck faces the Earth when the space...  
WO/2018/158746A1
The present disclosure relates launch systems, launch vehicles for use with the launch system, and methods of launching articles utilizing the launch vehicle and/or the launch system. In particular, various improvements for electroantima...  
WO/2018/157176A1
Transfer of objects between spacecraft can be achieved in a low gravity environment. A capture device can be part of a module that facilitates visualization of a vessel that approaches the capture device. The module can facilitate positi...  
WO/2018/157061A1
A tape drive comprises a roll of a tape (202) that can be extended from a rolled state to an extended state. The tape includes a rigid material that supports the tape and a pliable material disposed at least partially on one side of the ...  
WO/2018/154603A1
The present subject matter relates to an apparatus (100) that use of a tuft of numerous wires as a drag enhancing system for spacecrafts (102). When these ultra-thin wires are used in high numbers and deployed on-board a spacecraft, they...  
WO/2018/150883A1
Provided is a capturing system for capturing an object to be captured in outer space, wherein the success rate of missions is increased at low costs. This capturing system 1 for capturing an object T to be captured in outer space compris...  
WO/2018/147760A1
The invention relates to spacecraft of the platform type, developed in accordance with the CubeSat standard. The present spacecraft comprises a body in the shape of a parallelepiped and consisting of an upper panel and side panels, faste...  
WO/2018/147925A1
A satellite system operates at altitudes between 100 and 350 km relying on vehicles including a self-sustaining ion engine to counteract atmospheric drag to maintain near-constant orbit dynamics. The system operates at altitudes that are...  
WO/2018/146220A1
The invention relates to a small satellite (10) which is capable of formation flying, in particular a nanosatellite or picosatellite with a mass weight of 10 kg or less, for LEO applications, comprising a housing (12) and at least one in...  
WO/2018/138112A1
The invention relates to a flying craft (8, 98, 298, 308, 318) comprising lighter than air gas in a receptacle for creating a lifting force by means of buoyancy and a thrust force by combustion in combustion engine as a fuel together wit...  
WO/2018/139357A1
[Problem] To provide a spatial optical communication device that can transmit uplink light waves with high accuracy without the use of a laser guide star by measuring and compensating for variations in the atmosphere. [Solution] The pres...  

Matches 1 - 50 out of 13,639