Class / Patent application number | Description | Number of patent applications / Date published |
244172200 | With fuel system details | 19 |
20080237400 | Satellite refuelling system and method - The present invention provides a method, system and apparatus for robotic refueling of satellites. The system may include a dedicated refueling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refueling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station. Cameras are included focussed on the robotic arm and end effector and images are transmitted to the operator to allow the operator to direct and control the refueling procedure. The system may also be configured to be operated autonomously under computer control. | 10-02-2008 |
20100252686 | METHOD AND DEVICE ENABLING A ROCKET ENGINE PUMP TO BE DRIVEN BY AN INTERNAL COMBUSTION ENGINE - The subject of the invention is a device for driving a pump of a rocket engine of a space vehicle that comprises an air-breathing internal combustion engine running on an oxidizer/fuel mixture of the air/hydrocarbon type, wherein the supply of oxidant and fuel is provided by tanks and a circuit that are separate from the propellant tanks of the rocket engine. The invention applies to a device for fueling a rocket engine that includes at least two pumps, each driven by the device of the invention, and means for controlling the internal combustion engines for driving the pumps, adapted for independently varying the operating parameters of these engines so as to independently adjust the rotation speeds of the pumps. | 10-07-2010 |
20100264275 | Bubble trap for a fuel tank in a spacecraft - A bubble trap is especially suitable for separating gas bubbles from liquid fuel supplied from a fuel tank in a spacecraft. The bubble trap includes a rotationally symmetrical collecting container forming a container wall, plural liquid guide vanes extending radially and longitudinally along the inside of the container wall, a perforated conical gas separator that tapers conically toward an outlet of the collecting container, and screens arranged between the gas separator and the outlet. | 10-21-2010 |
20110017873 | DEVICE FOR POWERING THE PUMP OF A ROCKET ENGINE USING AN INERTIA WHEEL - An apparatus for driving a pump for fueling a rocket engine of a space vehicle. The apparatus comprises an inertia wheel and a transmitting device to transmit a rotation of the inertia wheel to the pump. The apparatus further comprises a measuring device to measure the rotation speed of the inertia wheel a clutching device to decouple the wheel and the pump for a speed lower than a pre-determined speed lower, which is lower than the nominal rotation speed of the wheel. The invention is particularly applicable to a space vehicle comprising a rocket engine wherein the fuel supply system comprises at least one pump driven by the apparatus of the invention and a starting device to start the apparatus while the space vehicle is in flight. | 01-27-2011 |
20110017874 | Means of fuel and oxidizer storage - The instant invention relates to improved means for the storage of H | 01-27-2011 |
20110303794 | METHOD AND SYSTEM FOR FEEDING JET ENGINES - The inventions relate to engine systems of space transportation means. The method is carried out with the aid of a system which comprises a spacecraft (KLA/SC) with a propulsive jet engine ( | 12-15-2011 |
20120112009 | SATELLITE REFUELLING SYSTEM AND METHOD - The present invention provides a method, system and apparatus for robotic refuelling of satellites. The system may include a dedicated refuelling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refuelling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station. Cameras are included focussed on the robotic arm and end effector and images are transmitted to the operator to allow the operator to direct and control the refuelling procedure. The system may also be configured to be operated autonomously under computer control. | 05-10-2012 |
20120205493 | Common Bulkhead for Composite Propellant Tanks - An apparatus comprising a first structure, a second structure, a first layer, and a second layer. The first structure has a first plurality of channels extending towards a number of edges of the first structure. The second structure has a second plurality of channels extending towards a number of edges of the second structure. A first side of the first structure is connected to a first side of the second structure. The first plurality of channels and the second plurality of channels have an orientation with respect to each other. The first layer is connected to a second side of the first structure. The second layer is connected to a second side of the second structure. | 08-16-2012 |
20130313370 | Propellant Tank with Radiometric Measurement of Content Quantity - A propellant tank for containing a propellant with a liquid phase, preferably for a satellite, includes a tank shell wrapped or wound with scintillating glass fibers, a gamma radiation emitter arranged preferably in the center of the tank, and photodiodes allocated to the glass fibers. Preferably, plural glass fibers are wound in cylindrically symmetrical sections around the tank, and the winding axis of the glass fibers extends through the tank outlet. The glass fibers scintillate and emit pulses of light in response to being impinged upon by gamma radiation. The quantity and location of liquid propellant in the tank is determined by evaluating the light signals emitted by the glass fibers. The tank shell is preferably fabricated of a lightweight metal such as aluminum or titanium, to minimize gamma radiation absorption in the tank shell wall, and thereby minimize the required emitting magnitude of the gamma radiation source. | 11-28-2013 |
20140326832 | METHOD AND SYSTEM FOR FEEDING JET ENGINES - A method for feeding a ramjet of a spacecraft beyond the dense layers of the atmosphere includes providing a fueling apparatus having an amount of a propellant for feeding a ramjet of the spacecraft. The propellant is ejected from the fueling apparatus in form of a solid and flexible propellant cord, wherein said propellant cord being placed on a flight path of the spacecraft. The solid and flexible propellant cord enters into the ramjet of the spacecraft. At least a part of a propellant of the solid and flexible propellant cord is used for feeding the ramjet. The cord includes an amount of a propellant stabilized in density relating to an environmental air by introducing one or more linear elements selected from ribbons, threads, or fibers, reticulate or membrane structures. | 11-06-2014 |
20150069188 | PROPELLANT TRANSFER SYSTEM AND METHOD FOR RESUPPLY OF FLUID PROPELLANT TO ON-ORBIT SPACECRAFT - Herein is disclosed a propellant transfer system and method for refueling on-orbit spacecraft. The system and method are configured to allow for resupply of spacecraft configured to be fueled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The system and method are particularly suited for resupply of satellites not originally prepared for refueling as well but the system may also be used for as satellites specifically designed for refueling. | 03-12-2015 |
244172300 | Fuel tank arrangement | 8 |
20090200429 | Fuel pickup with wicking material - A fuel pickup includes a fuel pickup tube having a plurality of holes for receiving fuel from inside a fuel container; and a wicking material enveloping at least one of the plurality of holes. Aircraft fuel systems including a fuel pickup comprising a wicking material are also disclosed. | 08-13-2009 |
20100012788 | Exchangeable Propellant Cartridge System - A propellant depot ( | 01-21-2010 |
20100170997 | AIRCRAFT WITH OPTIMISED UTILITY VOLUME AND METHOD FOR OPTIMISING THE UTILITY VOLUME OF AN AIRCRAFT - An aircraft including a fuselage including a cabin to accommodate persons and/or a load, and a propulsion system. The propulsion system includes at least one tank and/or one combustion chamber, wherein part of the propulsion system can be used as an extension of the cabin to accommodate persons and/or a load, the part of the propulsion system lying adjacent the cabin and separated from the cabin by a partition. | 07-08-2010 |
20120018587 | Fabric Preform Insert for a Composite Tank Y-Joint - A method and apparatus for forming a joint. A composite insert may be placed into a joint region for a first structure. The composite insert may comprise a structure having a first portion, a second portion, and a third portion all extending from a junction; and a resin impregnated into the structure to form the composite insert. The second structure may be laid up. The composite insert may be bonded to the first structure and the second structure. | 01-26-2012 |
20120286099 | DEVICE FOR DRAINING A TANK OF A SPACEBORNE SYSTEM | 11-15-2012 |
20140077037 | STRONG BONDED JOINTS FOR CRYOGENIC APPLICATIONS - A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form. | 03-20-2014 |
20140103164 | SPACECRAFT PROPELLANT TANK MOUNT - A spacecraft having a primary structural frame and a propellant tank, in which the spacecraft may include a tank mount adopted to engage a portion of the propellant tank, the tank mount being configured to transfer launch loads directly from the propellant tank to a lunch vehicle interface ring. | 04-17-2014 |
20140239125 | MODULAR CORE STRUCTURE FOR DUAL-MANIFEST SPACECRAFT LAUNCH - A spacecraft may include an upper core structure or a lower core structure. The upper core structure may include an upper cylinder for supporting an upper spacecraft of a dual-manifest launch configuration. The lower core structure may include a lower cylinder for supporting a lower spacecraft with the upper cylinder mounted on top of the lower cylinder. The upper cylinder may have an upper cylinder inner diameter that may be substantially similar to the lower cylinder inner diameter. | 08-28-2014 |