| Document |
Document Title |
|
WO/2023/286435A1 |
[Problem] To lessen the burden on users by enabling flexible control of communication lines according to service requirements when realizing satellite formation flight. [Solution] In order to control a movement body group involved in for...
|
|
WO/2023/288335A2 |
A ground station communicates with a satellite having a field of view (FOV), the satellite directly communicating with user equipment (UE) over uplink signals and downlink signals. The ground station has a Dynamic Time Division Duplex (D...
|
|
WO/2023/286861A1 |
An ionized body collecting device (1) according to the present invention is characterized by being provided with: one or a plurality of container main bodies (2) having a peripheral wall (2A) and a bottom wall (2B), and having an opening...
|
|
WO/2023/285432A1 |
A satellite (140) for operation in orbit around the earth comprises an ADCS (131, figure 1) configured for mechanically steering the satellite in the azimuth direction to prolong a dwell time (1105), during which a selected target is vis...
|
|
WO/2023/281282A1 |
A docking structure (1, see figure 1) for a satellite includes a magnetic plate (2) and a housing (10, 12) for mounting and constraining the magnetic plate (2). The magnetic plate includes an outer face and an inner face. The magnetic pl...
|
|
WO/2023/281632A1 |
A capturing device (14) includes a driving mechanism control unit that drives one or more driving mechanisms (21a, 21b) to feed a tape-like enclosing member (31) toward the outside of a housing (32) by a target feed amount. When a space ...
|
|
WO/2023/282949A2 |
Methods, devices, and systems are described for a core of a space habitat. The core includes a plurality of internal beams extending a length of the core. The core also includes a plurality of end rings at a first end of the core and a s...
|
|
WO/2023/282948A2 |
Methods, devices, and systems are described for a bracket fixture for securing a load to a soft goods layer in a space habitat. The bracket fixture includes a base having a plurality of sides, the plurality of sides having a pin parallel...
|
|
WO/2023/276031A1 |
[Problem] To provide a new technology for utilizing formation flight of a plurality of artificial satellites having light sources in the entertainment field. [Solution] The present invention is an artificial satellite control device whic...
|
|
WO/2023/276030A1 |
[Problem] To provide a novel technology that uses flight by a plurality of satellites that each have a light source for entertainment. [Solution] The present invention is an artificial satellite control device that controls the plurality...
|
|
WO/2023/278005A1 |
Methods, devices, and systems are described for a mounting flange and bracket for a space habitat. The bracket system couples a bladder of a space habitat to a cylindrical core. The bracket system includes a soft goods layer configured t...
|
|
WO/2023/276029A1 |
[Problem] To provide a new technology for utilizing formation flight of a plurality of artificial satellites having light sources in the entertainment field. [Solution] The present invention provides a content provision device which prov...
|
|
WO/2023/275970A1 |
[Problem] To provide a novel and improved information processing device, an information processing method, and a program, which are capable of improving robustness of a camera with regard to rotation, when identifying stars corresponding...
|
|
WO/2023/278001A1 |
A navigation processing system includes at least one processor configured to execute operational instructions that cause the at least one processor to perform operations that include generating navigation data. A data stream is generated...
|
|
WO/2023/276033A1 |
[Problem] To provide a novel technology which utilizes, in the entertainment field, flight control by a plurality of artificial satellites having a light source. [Solution] The present invention is an artificial satellite control system ...
|
|
WO/2023/276032A1 |
[Problem] To provide a novel technology that utilizes formation flights by a plurality of satellites with light sources in the entertainment field. [Solution] The present invention is a satellite control device that controls a plurality ...
|
|
WO/2023/276028A1 |
[Problem] To provide a novel entertainment application for flight control of a plurality of artificial satellites that have a light source. [Solution] The present invention is an artificial satellite control device that controls a plural...
|
|
WO/2022/271789A1 |
In an embodiment, there is provided a method for determining a spacecraft instantaneous velocity using starlight. The method includes determining, by a star pairing module, a plurality of star pairs in a selected star field image. The se...
|
|
WO/2022/270337A1 |
A backup satellite group (22) including a plurality of satellites (30) stands by at an orbital altitude lower than the orbital altitude of a stationary operation satellite group (21) in a satellite constellation (20). When a satellite (3...
|
|
WO/2022/269597A1 |
A connection system is provided for releasably connecting a first component and a second component in a first direction parallel to a reference longitudinal axis, including one or more locking devices and an actuator. Each locking device...
|
|
WO/2022/264177A1 |
Electromagnetic propulsion system for spacecraft movement without the emission of reaction mass, characterised in that it comprises two arms (10) which share one of their vertices at a point called feedpoint (14); said feedpoint (14) bei...
|
|
WO/2022/261423A1 |
A pair of interconnected vertical solar arrays at two preselected lunar sites are provided. A cable transmits power between one of the vertical solar arrays and the other vertical solar array, so that one of the vertical solar arrays can...
|
|
WO/2022/258123A1 |
This is a propulsion motor with a closed system and without reaction The way it works is to produce impulse in a plurality of coordinated physical steps. Step 1: The conversion of low voltage electrical energy LVCD into high current HVDC...
|
|
WO/2022/259966A1 |
Provided is a satellite monitoring device having a reception processing unit that receives a plurality of first data groups outputted from a plurality of satellites and expressed in a corresponding format unique to each of the plurality ...
|
|
WO/2022/254398A1 |
Device for disinfecting at least one working volume (5) in an artificial space environment (2), comprising a concentrator (6) of solar radiation associated with the at least one working volume (5), and filtering means (7) for selecting a...
|
|
WO/2022/255405A1 |
A liquid tank (oxidant tank 2) comprises: a cylindrical seamless tank body 21 with both end portions having a decreasing diameter toward ends; and a plurality of annular baffles 221 disposed in the tank body 21, and spaced apart from eac...
|
|
WO/2022/254327A1 |
A data acquisition system for a satellite (10) comprises at least one camera (2), a device for controlling ambient parameters and processing radiofrequency signals (3) and a microprocessor (4). The camera (2) can be activated so as to ac...
|
|
WO/2022/253837A1 |
The invention relates to a profile section (34) for an equipment (26) support panel (27). Said profile section is formed in one piece, comprising a tube (38) suitable for forming a heat pipe by introducing and confining a heat-transfer f...
|
|
WO/2022/249833A1 |
An integrated data library (300) is referenced by: a monitoring satellite group (110G) for tracking a flying object (10); a ground-based monitoring facility (120) for controlling the monitoring satellite group (110G); a communication sat...
|
|
WO/2022/248418A1 |
A thermal power reactor (100) is provided. The thermal power reactor (100) includes a reactor core (102; 202; 410; 502) arranged to generate thermal energy and a solid state thermal conductor (106; 206; 406) including a graphene based me...
|
|
WO/2022/249832A1 |
A communication satellite (200A) flies in an orbit (21) of orbital inclination angle θideg and is equipped with a communication device (51) having a view change range of ±θideg with respect to a +X axis about a Z axis, with the direct...
|
|
WO/2022/249428A1 |
A satellite deceleration device having a ranging function according to the technology of this disclosure comprising: a pulsed light source (39); a second light output part (27) which outputs, to a space, light output from the pulsed ligh...
|
|
WO/2022/249430A1 |
A device for changing the trajectory of an object in space according to the disclosed technology includes: light sources (2a, 2b, ...) that output light signals on two or more wavelengths; a filter controller (16) that determines a trans...
|
|
WO/2022/249429A1 |
A device for measuring the distance to an object in space according to the disclosed technology includes: light sources (2a, 2b, ...) that output light signals on two or more wavelengths; a filter controller (16) that determines a transm...
|
|
WO/2022/243543A1 |
A thermal management system (5) for a magnetoplasmadynamic thruster (10) for a space craft is disclosed. The thermal management system (5) is located between at least one superconducting magnet (120) and a plasma discharge unit (15 and c...
|
|
WO/2022/245772A1 |
An apparatus comprises both a first side and a second side that is opposite the first side. The apparatus includes a plurality of photovoltaic cells disposed on the first side of the substrate and a plurality of microwave antennas dispos...
|
|
WO/2022/237965A1 |
A vehicle for supersonic or hypersonic flight comprises a thermal rocket engine (lb) with a nozzle (2) and an active cooling system (8). The active cooling system cools a heat shield (6, 7). A working fluid absorbs heat inside the active...
|
|
WO/2022/238660A1 |
The invention relates to a spacecraft (1) for the distribution of electrical energy to client craft (2) at points situated in free space, in orbit and/or on a celestial body, the spacecraft (1) comprising a main structure (10) equipped w...
|
|
WO/2022/234669A1 |
A thrust generating device according to the present invention is for generating thrust in an object by irradiating the object with a laser, the thrust generating device comprising: a laser generating device that generates first laser lig...
|
|
WO/2022/229546A1 |
The invention relates to a reflective satellite (1) comprising at least one curved reflection surface (11), the satellite (1) being characterised in that it comprises at least one load-bearing structure (10) connected to at least four po...
|
|
WO/2022/230560A1 |
A monitoring satellite (110), which has detected significantly high brightness, indicates emission time corresponding to the detection time, an emission coordinate value indicating the position where the significantly high brightness has...
|
|
WO/2022/229185A1 |
The invention relates to a motor comprising a rotor rotating about an axis of rotation, at least two rockers articulated about a shaft attached to the rotor and centred about an axis separate from the axis of rotation of the rotor, at le...
|
|
WO/2022/229537A1 |
The invention relates to a thermoregulated thermomechanical structure (10) for a focal plane (100) suitable for operating in a space environment, comprising an interface (17) for supporting dissipative electronic equipment, said structur...
|
|
WO/2022/222807A1 |
Disclosed in the present utility model is a novel object propulsion apparatus, comprising a propulsion apparatus, the propulsion apparatus comprising a thermal insulation cover, and the thermal insulation cover being used for keeping an ...
|
|
WO/2022/209149A1 |
One problem associated with conventional satellite systems is the difficulty in reducing size and weight of a satellite. A position measurement method according to the present invention includes: observing, in a first satellite (11), pha...
|
|
WO/2022/125264A9 |
A method includes producing an electric propulsion (EP) rocket engine. The method selects a core discharge chamber. A discharge cathode assembly (DCA) is selected along with a DCA common interface (CI). The DCA CI is connected to the cor...
|
|
WO/2022/208794A1 |
Provided is a heat insulation structure (100) provided with a heat insulation film (200) and a plurality of support members (300) for supporting the heat insulation film (200), the heat insulation structure being characterized in that: t...
|
|
WO/2022/207558A1 |
The invention relates to a spacecraft membrane (2) which is self-supporting and flexible. The spacecraft membrane (2) has a substrate (5) made of a fluoropolymer. Furthermore, the spacecraft membrane (2) has a silicon oxide layer (6; 7)....
|
|
WO/2022/199886A1 |
The invention relates to an atmosphere reentry and landing device (1) for a rocket stage (2) for the safe reentry of a rocket stage (2) into the atmosphere and/or the safe landing of a rocket stage (2) in water. The invention also relate...
|
|
WO/2022/200714A1 |
The invention relates to a transport system (1) intended to be installed on a space launcher (100, figure 1) and comprising: • - an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of f...
|
