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Matches 1 - 50 out of 13,786

Document Document Title
WO/2019/073167A1
The invention relates to thermal protection (18) comprising, superposed on one another in order, a metal plate, a first layer of insulating material, a layer of refractory fibres, and a second layer of insulating material, the metal plat...  
WO/2019/074317A2  
WO/2019/068649A1
- The subject matter of the invention is a deployable satellite mast consisting of an inflatable tube (1), which is stored in fan-fold form (1a) before deployment (1b) and can be deployed by filling the tube with a gas, and which compris...  
WO/2019/057630A1
The invention relates to a double-walled component of a space vehicle, comprising supporting structures (3) and a latent heat storage medium (4) between the two walls (1, 2), said component being produced by means of 3D pressure. Passive...  
WO/2019/055122A1
Operating a remote sensing vehicle 250 comprising a host bus platform 252 and a variable pitch instrument platform 254 movably coupled to the host bus platform in at least one degree of freedom. The method comprises establishing a pointi...  
WO/2019/051423A1
Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in w...  
WO/2019/049924A1
The purpose of the invention is to provide a space environment test apparatus for performing initial cooling while reducing consumption of liquid nitrogen and an initial cooling method for the space environment test apparatus. Provided i...  
WO/2018/231310A3
A spacecraft propulsion method uses cosmic ray triggered nuclear micro-fusion events to provide repeated or continuous thrust for artificial gravity during a space flight. In one embodiment, successive packages of deuterium-containing mi...  
WO/2019/048262A1
The invention relates to a reconnaissance rover (100) designed for multiple agile and autonomous landings over a small body (A) or moon. The reconnaissance rover (100) comprises a detection unit (140), a processing unit (150), a control ...  
WO/2019/045611A1
The invention relates to a separation device (1) for a spacecraft or launcher. The separation device (1) comprises an inner housing (2) divided into at least two portions locked to each other by a locking device (3) in a locking position...  
WO/2019/044735A1
An angular momentum calculator (12) calculates the angular momentum of a spacecraft. A command value calculator (13) calculates a thruster command value and an angle command value by establishing the solution to a nonlinear programming p...  
WO/2019/045613A1
The invention relates to a separation device (1) for a spacecraft or launcher. The separation device (1) comprises an inner housing (2) divided into at least two portions locked to each other by a locking device (3) in a locking position...  
WO/2019/038708A1
The invention concerns a satellite deployment system (30) for launch vehicles. Said satellite deployment system (30) comprises an outer dispenser (31) that is fitted, externally, with first releasable attachment means for releasably atta...  
WO/2019/035732A1
The invention relates to space vehicles (modules) which are equipped with an artificial gravity system and have an audio-video studio integrated therein, capable of recording a sound from microphones inside spacesuits (99) and musical in...  
WO/2019/036462A1
A protective assembly (100) comprises a first region (102) formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region (104) formula...  
WO/2019/035378A1
A spacecraft (100) includes a principal airframe (6), a parachute (1), which is an air brake structure, and a jetting nozzle (5). The air brake structure is provided farther on one side in a traveling direction with respect to the princi...  
WO/2019/030950A1
A control system for controlling an operation of a spacecraft. A model predictive controller (MPC) produces a solution for controlling thrusters of the spacecraft. The MPC optimizes a cost function over a finite receding horizon using a ...  
WO/2019/030787A1
Structured set (10) suitable to make modular satellite structures (20), flat or three- dimensional, which is able to shield electromagnetic fields and/or variations in temperature in orbit, comprising a plurality of structural elements (...  
WO/2019/030455A1
The invention proposes a method for building a rigid structure (1) comprising a framework (10) in space, characterized in that it comprises: the production of at least two reinforcing elements (12) from a reel of wire or metal strip, and...  
WO/2019/030949A1
A spacecraft including a set of thrusters for changing a pose of the spacecraft. At least two thrusters mounted on a gimbaled boom assembly and are coupled together sharing the same gimbal angle. A model predictive controller (MPC) to pr...  
WO/2019/032372A1
The present technology provides power generation using thermoradiative cell (TRC) structures, which generate electricity by radiating heat from a hotter area/body to a cooler area/body. The TRC structures may be used in conjunction with ...  
WO/2019/028404A1
A satellite dispenser door release mechanism is disclosed. In various embodiments, a satellite door dispenser as disclosed herein includes a wire or cable having a first end configured to be secured in a structure comprising or coupled t...  
WO/2019/028408A1
A satellite dispenser is disclosed. In various embodiments, a satellite dispenser as disclosed herein includes a dispenser body defining an interior cavity configured to receive a payload; and a composite guide rail comprising a groove c...  
WO/2019/026179A1
A wireless communication device installed in a drone transmits information pertaining to the drone, a relay that flies at a first altitude between the altitude at which the drone can fly and the altitude of a communication satellite rece...  
WO/2019/028407A1
A satellite dispenser door assembly is disclosed. In various embodiments, a satellite dispenser door assembly as disclosed herein includes a dispenser door having a hinge pin; and a one way clutch bearing within which the hinge pin is fr...  
WO/2019/028410A1
A satellite dispenser and method of using same are disclosed. In various embodiments, a satellite dispenser as disclosed herein includes a dispenser body defining an interior cavity to accommodate a payload; and a plurality of externally...  
WO/2019/020330A1
An electric thruster comprises a propellant delivery system, wherein the propellant delivery system comprises: a pipe for carrying propellant; a valve which is adapted to adjust a volume or mass flow of the propellant in the pipe; and an...  
WO/2019/022655A1
A multiple payload set (3) for a launch vehicle, wherein the multiple payload set (3) comprising a plurality of payloads (2). The plurality of payloads is interconnected via a non-self-supported connection structure (16) before assembly ...  
WO/2019/021220A1
The present invention relates to a re-entry module comprising an alpha-dome comprising a petal structures [1-5, 49] positioned on the upper surface [7] of the base for enclosing the payload; Omega hexon positioned parallel to surface [9]...  
WO/2019/021036A1
A device which assists vertical landing of a returnable rocket stage not equipped with stabilization means during landing. The device is a structure made of mechanisms and supports which hold the stage in a vertical position during landi...  
WO/2019/020499A1
The invention relates to a method (100) for simulating the estimation of a lag in producing satellite images associated with at least one predetermined zone of the Earth (20), by at least one Earth observation satellite comprising an opt...  
WO/2019/018139A1
Artificially directing a plurality of space-borne natural bodies to a target accretion region, such that gravitational forces amongst the plurality of space-borne natural bodies within the target accretion region produces an agglomerated...  
WO/2019/018826A1
Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform...  
WO/2019/018001A1
A three-dimensional multi-shell insulation configured to conform to the shape of a spacecraft component to be insulated. The insulation may have a plurality of nested shell layers that are displaceable relative to each other for providin...  
WO/2019/018821A1
Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.  
WO/2019/018085A1
Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual "cells", which are individual space vehicles...  
WO/2019/016888A1
Provided is a terminal for displaying the surroundings of a probe vehicle, the terminal having: an operating unit that receives, from a user, the position of a target present around the probe vehicle and designation of the type of said t...  
WO/2019/017979A1
Systems, methods, and software described herein provide enhancements for orbital satellite platform. In one example, an orbital satellite platform includes a plurality of satellite devices configured to establish a pseudo-geosynchronous ...  
WO/2019/018086A1
Cell-based space systems with nested-ring structures that interlock and can change configuration to support a mission are provided. The cells may self-assemble into a larger structure to carry out a mission. Multiple rotatable rings may ...  
WO/2019/018819A1
Spacecraft servicing systems include a spacecraft servicing device and at least one pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least one pod to a target sp...  
WO/2019/012755A1
[Problem] To provide a sheet-like structure which allows the sheet-like shape thereof to be estimated with a high degree of precision. [Solution] This sheet-like structure is equipped with a sheet-like member and a plurality of detection...  
WO/2019/014386A1
A system for enhancing the thrust produced by an aircraft propulsion element having a propulsion fluid outlet includes a shroud element having an inlet, an outlet and a diffusing section positioned between the shroud element inlet and sh...  
WO/2019/011919A1
The invention relates to a navigation satellite (10, 10', 10"), in particular for a medium earth orbit (MEO), having a housing (12) and a navigation antenna (16) connected to the housing (12) for emission of navigation signals in a prefe...  
WO/2019/014085A1
An apparatus is disclosed. The apparatus has a cooling fluid passage (310, 510, 810, 910), a gaseous fluid blower (315, 515, 705) disposed at an upstream portion or a downstream portion of the cooling fluid passage (310, 510, 810, 910), ...  
WO/2019/009154A1
This mobile image pickup device is provided with: an image pickup unit (20) and an acceleration/angular velocity detection unit; a processing unit that processes acceleration/angular velocity information detected by the acceleration/angu...  
WO/2019/005840A1
A wide field-of-view celestial sighting system (400) and method (500) are provided. The method (500) includes orienting an imaging optic (14, 42, 44) to collect light from at least one light source, such as at least one celestial body (1...  
WO/2019/003468A1
Provided is an aerial vehicle that prevents others from precisely measuring the position of a subject vehicle and allows friends to precisely measure the position of the subject vehicle. An aerial vehicle (10) is provided with a reflecti...  
WO/2018/234705A1
Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) c...  
WO/2018/231800A1
Propulsion systems that generate thrust from pressure generated by thermally decomposing a chemical blowing agent (CBA). In some embodiments, the CBA decomposes exothermically such that once thermal decomposition has been initiated, the ...  
WO/2018/231310A2
A spacecraft propulsion method uses cosmic ray triggered nuclear micro-fusion events to provide repeated or continuous thrust for artificial gravity during a space flight. In one embodiment, successive packages of deuterium-containing mi...  

Matches 1 - 50 out of 13,786