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Patent Searching and Data


Matches 1 - 50 out of 13,449

Document Document Title
WO/2018/104521A1
The invention concerns a method for gauging the liquid propellant tank (10) of a spacecraft during a phase of high-thrust along an axis (12), said tank being thermally conductive and having a known geometry. The method comprises steps of...  
WO/2018/103762A1
A distributed propulsion system, wherein an input end of a gas collection device of a high energy working medium collection device is connected to an output end of a core machine gas compressor of a turbine engine core machine, an output...  
WO/2018/100274A1
A system for correcting POGO effect for a system for supplying liquid propellant to a rocket engine, comprising a liquid propellant supply line portion (70), a hydraulic accumulator (11), comprising a tank (12) connected to the supply li...  
WO/2018/096236A1
Device and method for regulating a flow rate of gas intended to supply a propulsion apparatus for a spacecraft comprising xenon tank (2), a circuit comprising a withdrawing pipe (3) having an upstream end connected to the tank (2) and a ...  
WO/2018/096244A1
The invention relates to a system for correcting pogo oscillation for a system for supplying liquid propellent to a rocket engine, comprising a supply duct portion (70) for supplying liquid propellent, a hydraulic accumulator (11), compr...  
WO/2018/094504A1
A system and a method for laser-driven propulsion, comprising transferring momentum to a projectile through a low-density material at laser fluences below plasma ablation threshold, the method comprising providing a metal layer having a ...  
WO/2018/093761A1
In an example embodiment, an attitude, orbit, and de-orbit control system (AODCS) for a satellite is provided. In an example embodiment, the AODCS system comprises one or more selectively retractable booms. The one or more selectively re...  
WO/2018/087541A1
A deployable wrapped rib assembly is disclosed, comprising a hub, a plurality of ribs each being connected to the hub at a fixed angle such that each rib is inclined with respect to a perimeter of the hub, each one of the plurality of ri...  
WO/2018/087273A1
The invention relates to a spacecraft (100) comprising a main body (110) and an attitude control system, said attitude control system including active attitude control means (150). In addition, the attitude control system also comprises ...  
WO/2018/078258A1
The attachment system (4) for a spacecraft (1) comprises a first support structure (5), a second support structure (6), and an attachment (7) in order to mechanically link the first structure (5) to the second structure (6). The second s...  
WO/2018/076780A1
A plate folding and unfolding device and a solar panel structure. The plate folding and unfolding device comprises: cams (120, 220, 320) fixed with first plates (111, 211) and provided therein with rotating shafts (130, 230, 330) in the ...  
WO/2018/075083A1
Systems, methods, and software described herein provide enhancements for deploying applications in satellites. In one example, a satellite may receive software applications capable of execution as virtual nodes on the satellite, and rece...  
WO/2018/071645A1
A microsatellite may include a module having a power source and a housing for containing an experiment, a drag device structurally configured to facilitate an orbit of the microsatellite when the microsatellite is deployed in space, wher...  
WO/2018/069994A1
The present invention suppresses, without greatly increasing the mass of a satellite, the time average peak value of a low-frequency magnetic noise or a low-frequency conduction noise generated from a power supply device which drives a h...  
WO/2018/071070A1
An impulse momentum propulsion apparatus includes a power source and a track arranged radially relative to a vertical axis with a proximal end of the track nearest the vertical axis and a distal end of the track farthest from the vertica...  
WO/2018/065704A1
The invention relates to a device for mechanical locking/separation by rotation, comprising a main body (1) secured to a first system, provided with an actuator (2) for rotatably actuating a rotatable rod (3) inserted into the main body;...  
WO/2018/065703A1
The invention is directed to an attachment device (1) for attaching a booster (200) along a main body (100) of a space launch vehicle, comprising a combination of two pivots (2, 3) and of an annular linear connection (4), and to a space ...  
WO/2018/061138A1
If a first number of operating thrusters, which is the number of thrusters brought into operation in a first thruster group (115), differs from a second number of operating thrusters, which is the number of thrusters brought into operati...  
WO/2018/061230A1
A cable (130) comprises a flat wire (134). A parallel wire (133) is configured from a first wire (131) and a second wire (132) forming a pair and arranged side-by-side without being twisted together. The flat wire is configured such that...  
WO/2018/062983A1
In summary, the operation of the ultra-high-frequency (UHF) magnetic motor of this invention is based on generating extremely short and powerful electric, magnetic or electromagnetic field pulses and separating or disassociating said fie...  
WO/2018/061226A1
An artificial satellite (100) is provided with two pointing mechanisms (110, 120). Each pointing mechanism is provided with a main body-side gimbal (111, 121), an expansion boom (112, 122), a thruster-side gimbal (113, 114), and a thrust...  
WO/2018/057068A2
Severe weather agility thrusters, and associated systems and methods are disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end, and is elongated along a vehicle ...  
WO/2018/057068A9
Severe weather agility thrusters, and associated systems and methods are disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end, and is elongated along a vehicle ...  
WO/2018/055612A1
A propulsion system attached to a space vehicle for propelling the space vehicle in an essentially gravity free environment, comprises: a) a first section of tubing; b) a second section of tubing having a cross-sectional area significant...  
WO/2018/052527A3
A configuration for a satellite constellation has a plurality of planes, each plane including a plurality of satellites therein, at least some of the planes situated at a different altitude than other of the planes, in some embodiments, ...  
WO/2018/051025A1
In order to provide a temporary connection between two structure elements (12, 14), such as two parts of a space launcher or of another type of spacecraft or aircraft, a connection device (16) with controlled separation comprises a therm...  
WO/2018/047549A1
A spacecraft (10) is provided configured so that after entering the atmosphere by a nose entry, the spacecraft (10) changes posture so as to achieve a target posture angle in which a vertical landing can be performed, and then lands afte...  
WO/2018/047817A1
When finding a gimbal angle trajectory that satisfies the boundary conditions set by a posture boundary condition setting unit 2131 of a ground station 21, a gimbal angle trajectory calculation unit 2132 calculates a gimbal angle traject...  
WO/2018/048501A9
An arcjet thruster system for a spacecraft is provided. The arcjet thruster system may include a power supply that includes a radio-frequency start power supply and a continuous direct-current power supply, each selectively coupled to el...  
WO/2018/048501A1
An arcjet thruster system for a spacecraft is provided. The arcjet thruster system may include a power supply that includes a radio-frequency start power supply and a continuous direct-current power supply, each selectively coupled to el...  
WO/2018/042106A1
A rocket engine having improved stability during its starting phase, the rocket engine (1) comprising a divergent (13) and a securing system (40) configured to retain the divergent (13) when the rocket engine (1) is started, the securing...  
WO/2018/043665A1
[Problem] To provide a technology for reliably landing a flying body on a ground surface that is covered with a granular medium. [Solution] The present invention is a leg part structural body which can support a body part of a flying bod...  
WO/2018/043737A1
This flying mobile unit comprises a hull, a wheel, a propulsion device, and a control unit. The wheel has an axis of rotation oriented in the same direction as the direction of a thrust force to be produced by the propulsion unit. The co...  
WO/2018/037424A1
The embodiments herein provide a system and method for integrated optimization of design and performance of satellite constellations. The present disclosure provides a method for optimization of design and performance of satellite conste...  
WO/2018/030368A1
Disclosed is a probe capable of travelling, said probe having: wheels; a first camera disposed facing the direction in which the probe can travel; and a second camera disposed facing the directions except the direction in which the probe...  
WO/2018/029840A1
This probe, which is capable of travel, includes: wheels; a first camera disposed so as to face a direction in which the probe can travel; and a second camera disposed so as to face a direction other than the direction in which the probe...  
WO/2018/029841A1
The present invention includes: a first probe that includes a solar battery and that supplies electric power generated by the solar battery; and a second probe that probes natural resources by using the electric power supplied from the f...  
WO/2018/030367A1
The present invention has a first step for propelling, by electrical propulsion, a transport ship from a low earth orbit or a geostationary transfer orbit to a target orbit or destination.  
WO/2018/029833A1
The present invention has a step for exploring for a natural resource in a satellite, an asteroid, or a planet, a step for acquiring the natural resource detected by the exploration, and a step for storing the acquired natural resource.  
WO/2018/029839A1
The present invention relates to a transport method, a transport ship and a method for manufacturing a transport ship. The present invention has a first step for electrically propelling a transport ship to a lunar transfer orbit from a l...  
WO/2018/026786A1
Various examples related to a deployable gridded ion thruster are described. A deployable gridded ion thruster can include: a thruster body including an ion generating unit; and an expandable discharge chamber configured to expand from a...  
WO/2018/021493A1
In order to make it possible to use a low toxicity HAN-based propellant in a thruster, the purpose of the present invention is to provide: a HAN-based propellant decomposition catalyst that is sufficiently heat resistant and stable with ...  
WO/2018/020171A3
The present invention relates to a method (50) for estimating the direction of a satellite (20) in the transfer phase, said satellite direction being estimated relative to a measurement antenna (30) by executing a plurality of steps (52)...  
WO/2018/021236A1
A reaction wheel device having reaction wheels disposed inside a polyhedron-shaped case, wherein each of the constituent surfaces of the polyhedron is configured with a frame part corresponding to each constituent surface of the polyhedr...  
WO/2018/020160A1
The invention relates to a solid-state thermochromic device comprising a stack, said stack sucessively comprising, from a rear face to a front face exposed to solar radiation: a) a solid substrate consisting of an inorganic material resi...  
WO/2018/016471A1
This autonomous operation planning system comprises a satellite side having a satellite-side operation parameter storage unit 22 and an operation planning unit 23 and a terrestrial side having a terrestrial-side operation parameter setti...  
WO/2018/015256A1
The invention relates to a locking coupling (1) comprising a first coupling unit (11) and a second coupling unit (12), which in each case extend along a longitudinal axis (A) and are designed to be identical. Each coupling unit (11) comp...  
WO/2018/015598A1
The invention relates to a cylindrical concentrator with a frustoconical cross section, which uses flat movable mirrors (1) rotating on a shaft parallel to the axis of the cylinder and which has low concentration levels (typically ≤ 2)...  
WO/2018/017788A1
A liquid propellant rocket engine includes a main turbo-pump and a boost turbo-pump. The main turbo-pump has a main pump with an outlet that is fluidly coupled with a supply line. The boost turbo-pump includes a housing, a rotor, a boost...  
WO/2018/014676A1
A spacecraft docking system and method, the system comprising an active docking device (100) and a passive docking device (200), the active docking device (100) comprising an active docking ring (101) and a docking frame (104), and the a...  

Matches 1 - 50 out of 13,449