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WO/2017/140972A1 |
The invention relates to a method for controlling the guidance of attitude of a satellite (1), the satellite comprising an optical instrument (2), and a solar generator (4) defining a functional surface. The method comprises a first step...
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WO/2017/142476A1 |
An electric circuit (200) configured to provide motive force comprises a first circuit portion (204) and a corresponding second circuit portion (206). The first circuit portion is configured, when the electric circuit is disposed in a ma...
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WO/2017/138165A1 |
The present invention provides a compact control moment gyroscope capable of lengthening the lifespan of a gimbal bearing and suppressing the increase of disturbance to a spacecraft caused by the axial vibration of a rotor. This control ...
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WO/2017/137082A1 |
The present invention provides a system and method for guiding and reflecting sunlight to regions on earth where normally no high incident solar radiation is available. Mirror based systems are therefore provided that are located above e...
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WO/2017/136650A1 |
A new system and apparatus for detachably joining a first component to a second component is disclosed, along with a method for detachably joining two components. Embodiments of the present invention include a tensioning apparatus and sy...
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WO/2017/129661A1 |
The invention relates to a curable resin that represents an excellent substitute for phenolic resins and is therefore able to replace phenolic resins in all applications in which they are used. Said resin is characterised in that it comp...
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WO/2017/121629A1 |
The present invention relates to a release system (1, 2, 3, 4, 5), that includes a segmented structural element (10) comprising : a first segment (10a) designed to be coupled to a first structure, a second segment (10b) designed to be co...
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WO/2017/120432A1 |
Systems, devices, and methods are provided for extendible membranes, such as solar arrays. Some embodiments include an extendible membrane system that may include: an extendible central column; one or more membranes; and/or one or more f...
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WO/2017/115794A1 |
A spacecraft fuel tank for storing propulsion fuel of a spacecraft, and equipped with a carbon fiber-reinforced plastic layer (101) and a metal plating layer (102), wherein the carbon fiber-reinforced plastic layer (101) has, on the inne...
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WO/2017/116534A1 |
The disclosed technology relates to systems and methods for managing one or more ground stations that track satellites. A non-transitory computer-readable storage medium stores information of a ground station at a first position at a fir...
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WO/2017/110105A1 |
The present invention comprises a satellite deployment step S2, a spacecraft acceleration step S4, a spacecraft orbiting step S5, and a spacecraft deceleration step, and the foregoing are repeated in the order given. In the satellite dep...
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WO/2017/103173A1 |
There is provided a satellite for observing a target from space, comprising an image capturing module for capturing an image of a target moving relative to the satellite, an image processing module for processing one or more images captu...
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WO/2017/103481A1 |
The present invention relates to a method (50) for acquiring images by means of a constellation of satellites (20) in non-geosynchronous terrestrial orbit in which, said satellites (20) comprising respective means of inter-satellite comm...
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WO/2017/103126A1 |
The invention relates to a technique for subsurface prospection by means of a drilling head system (10) having an integrated acoustic source (101, 102, 103) and an arm (20) which is equipped with electrodynamic detectors (201). The drill...
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WO/2017/103297A1 |
The invention relates to a dispenser (1) for lightweight spacecraft, consisting of a ring structure with multiple payload ports (2), the surface (3) of the ring structure being at least partially spherical.
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WO/2017/090995A1 |
The present invention relates to a manual microwave probe for a satellite, having a fixed reflection plate and comprising: a motor (100) including a first rotary shaft (110) formed to extend in the progressing direction of the satellite;...
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WO/2017/088062A1 |
The present invention relates to satellite systems and more particularly, to the provision of a novel, non-geostationary satellite system and method for weather and climate monitoring, communications applications, scientific research and...
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WO/2017/091374A1 |
Disclosed is a thrust-producing device that can generate force in any medium (in air, in space, underwater). The device, in and of itself, does not have an external intake, or exhaust. Thrust is produced when electro-mechanical and/or th...
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WO/2017/085455A1 |
A hinge (1) attaches between two elements (4) in a deployable structure. The hinge (1) includes support members (2) for attaching to or forming part of the elements (4). The hinge (1) also includes two gears (8) in mesh with each other, ...
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WO/2017/085399A1 |
The invention relates to a heat exchange device intended to ensure an exchange of heat between a heat transfer fluid of a first network (26) of capillary heat pipes and a heat transfer fluid of a second network (36) of capillary heat pip...
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WO/2017/085746A1 |
The present invention relates to a Microwave Electrothermal Thruster(MET) adapted for in-space electrothermal propulsion comprising a tunable frequency Microwave Electrothermal Thruster propulsion module enabling primary propulsion and a...
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WO/2017/081351A1 |
The invention relates to a system for in-orbit propulsion via floating conductor cables loaded in a spacecraft (1), comprising two sets of electro-dynamic conductor cables (2, 3) respectively connected to each of the two poles (4, 5) of ...
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WO/2017/081450A1 |
An airframe (10) for an air vehicle comprising an outer skin layer (12) and a support layer (13) defining a fuselage of said air vehicle, wherein said outer skin layer (12) is magnetically coupled to said support layer (13).
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WO/2017/081350A1 |
The invention relates to a system for generating electrical power in orbit by means of floating conductor cables, which system is mounted in a space vehicle (1) and comprises: two sets of bare (without electrical insulation) electro-dyna...
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WO/2017/081521A1 |
The invention relates to the field of aerospace and describes a carrier aircraft device intended for carrying aircraft and spacecraft into the atmosphere for the subsequent launch thereof (so-called air launch) from a vertical position â...
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WO/2017/077469A1 |
The flexible pivot comprises a first stage comprising a first cylinder (21) and a first interface structure (38) and a second stage comprising a second cylinder (23) and a second interface structure (39) in axial alignment with those of ...
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WO/2017/078687A1 |
A system and method are provided to support accommodating safe integration of small Unmanned Ariel systems (sUASs) or drones for the recognition of the ownership of the device. This high altitude cellular communications system platform u...
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WO/2017/071140A1 |
A menu-type design method for a GEO satellite control system based on optimized information integration, comprising the following steps: configuring four long-life inertial attitude sensor gyroscopes arranged in pyramid fashion for a lon...
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WO/2017/072457A1 |
A system for the in-flight attitude and direct thrust flight control of a vehicle comprises a propulsion body (120) and a plurality of valves distributed into a first and a second set of valves (170, 180). The system further comprises - ...
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WO/2017/069816A1 |
A spacecraft (10), such as a satellite, uses a shape memory polymer actuator (18) to deploy one or more deployable parts (14). The shape memory polymer actuator may be formed integrally with a deployable part and/or with a fuselage (12) ...
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WO/2017/069728A1 |
A propulsion system includes at least one group of electric thrusters that are spatially distributed in a multi-axis system. A controller is in communication with each of the electric thrusters. The controller is configured to differenti...
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WO/2017/068154A1 |
The invention relates to an actuator (10) including a magnetohydrodynamic wheel (20) comprising a fluidic ring and at least one magnetohydrodynamic pump for moving a conductive liquid. Each magnetohydrodynamic pump comprises a means for ...
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WO/2017/059545A1 |
A geostationary platform is held afloat by a superpressure balloon. A suitable altitude is 25 km. The craft carries electrohydrodynamic thrusters, to overcome winds, held within a scaffold. Sensors determine position, velocity, accelerat...
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WO/2017/060392A1 |
The invention seeks to use a satellite panel material without the disadvantages inherent to the composite materials habitually used, particularly the complexity of creating perforations and of installing inserts in these perforations. To...
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WO/2017/062140A1 |
A method for solar array (28a, 28b) deployment includes deploying a first portion of solar cells of a solar array responsive to a first drag condition, charging a battery (26) with the first portion of solar cells, activating an electric...
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WO/2017/055706A1 |
The invention relates to a device (6) for controlled separation of a first so-called stationary part (7) and a second so-called mobile part (8), the stationary part (7) having a stationary connecting surface (9) opposite a mobile connect...
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WO/2017/055653A1 |
The invention relates to a method for obtaining a state of microgravity in a controlled space, which comprises using a unmanned aerial vehicle that has propulsion systems, is capable of vertical takeoff and landing and contains the contr...
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WO/2017/055750A1 |
The invention relates to a satellite (1) which comprises: at least one optical photography instrument (3) comprising a main lens having an optical axis (V) and the optical instrument (3) having a field of view; at least one launcher inte...
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WO/2017/055770A1 |
The invention relates to a satellite (1) comprising a cylindrical main body (2), the main body (2) having an inner wall (3) defining an inner space (9) and an outer wall (4), and extending along a main axis (A) between a lower end surfac...
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WO/2017/050372A1 |
The satellite launcher comprises a plurality of stages detachable from each other, at least one stage including at least one engine, and at least one of said stages carrying a payload, and said stages are placed one beside or around the ...
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WO/2017/053694A1 |
A hybrid communications assembly for a spacecraft is provided. The hybrid communications assembly may include an assembly base, one or more laser communications terminals mounted on the assembly base, and a radio frequency antenna system...
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WO/2017/045475A1 |
A magnetic-fluid momentum sphere is used for satellite attitude adjustment. The magnetic-fluid momentum sphere comprises stators and a spherical shell. The stators are classified into three groups, axes of the three groups of stators are...
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WO/2017/049297A1 |
Systems and methods are described herein for mounting a thruster onto a vehicle. A thruster mounting structure may comprise a first, second, and third rotational joint, a boom, and thruster pallet, and a thruster attached to the thruster...
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WO/2017/046279A1 |
The present invention relates to a method (50) for estimating the attitude of a satellite (20), said satellite being configured to generate and transmit a first reference signal on a downlink by means of a first transmitting antenna (21)...
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WO/2017/045020A1 |
Disclosed herein is a propulsion system comprising: a solid conductive or semiconductive cathode (130); an anode (110) having a potential difference relative to said cathode (130), said potential difference creating an electric field bet...
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WO/2017/046497A1 |
The invention relates to a space vehicle (1, 100), such as a satellite, the vehicle (1, 100) comprising: at least one equipment-carrying module (2) for carrying equipment of the vehicle (1); at least three posts (12) extending at least p...
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WO/2017/044148A1 |
A system for generating force is provided. The system includes a rotating disk with a plurality of recesses, and bearings disposed within each recess. The system further includes at least one guide, disposed adjacent to the disk, which c...
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WO/2017/044184A2 |
A carbon nanotube-based thermal gasket for space vehicle applications, and process for making the same, is disclosed. A thermal gasket is created that includes one or more free-standing carbon nanotube (CNT) sheets formed of a CNT compos...
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WO/2017/044683A1 |
A composite has a) a PMC layer, and b) a tile layer comprising a plurality of Ox/Ox CMC tiles each has: i) a central portion, ii) an outer portion disposed surrounding the central portion, the bottom surface of the outer portion is dispo...
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WO/2017/040462A1 |
A rigidizing latch assembly 1 which, in embodiments, is a robotically compatible aerospace attachment mechanism, may be used to rigidly attach units to a structure and typically comprises male latch 10 and receptacle 20 configured to coo...
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