| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244171100 | With propulsion | 65 |
| 20080197238 | PHOTONIC LASER-BASED PROPULSION HAVING AN ACTIVE INTRACAVITY THRUST AMPLIFICATION SYSTEM - The invention is a system and method for propelling and slowing down spacecraft and other space systems and objects using the thrust generated from the direct laser photon momentum transfer between two platforms to and from unprecedented high speeds approaching the speed of light. The thrust from the direct laser photon momentum is amplified in an intracavity arrangement, in which laser photons bounce between two high reflectance mirrors separately located in two platforms. The laser gain medium is typically located between two mirrors, and amplifies the intracavity photon power, thus creating amplified thrust. This intracavity medium location arrangement offers two critical advantages: 1) the ability to maintain the intracavity photon power constant when the distance between the mirrors rapidly changes; and 2) the ability to overcome the power loss mechanisms, such as scattering and absorption. | 08-21-2008 |
| 20080217482 | Thruster-Solar-Sails or ThrusterRing-Spacecraft improved through additional fuel less steering/-attitude control ( - Attitude Control System - ACS ). Solar-Sail-Launch-System, consisting of a self expanding solar sail with docking station and primary fuel-less attitude control/-steering-system - Fuel less ACS for solar sails, using furl- and unfurl able ballast-sail-foil-segments for simultaneously displacement of center of mass and center of solar radiation pressure into opposite directions to each other. | 09-11-2008 |
| 20080265099 | Multi-Functional Annular Fairing for Coupling Launch Abort Motor to Space Vehicle - An annular fairing having aerodynamic, thermal, structural and acoustic attributes couples a launch abort motor to a space vehicle having a payload of concern mounted on top of a rocket propulsion system. A first end of the annular fairing is fixedly attached to the launch abort motor while a second end of the annular fairing is attached in a releasable fashion to an aft region of the payload. The annular fairing increases in diameter between its first and second ends. | 10-30-2008 |
| 20080296436 | IN ORBIT SPACE TRANSPORTATION & RECOVERY SYSTEM - An In Orbit Transportation & Recovery System (IOSTAR™) ( | 12-04-2008 |
| 20090206205 | AEROSPACE VEHICLE SYSTEM - In an aerospace vehicle in which a satellite is detachably adapted to the first step rocket and the second step rocket, an electronic device | 08-20-2009 |
| 20090212163 | Propulsion Enhancement Arrangement for Rocket - A rocket includes a front warhead, a rear propellant actuator, and a propulsion enhancement arrangement which comprises at least two propulsion impulse generators longitudinally cascadedly mounted between the warhead and the rear propellant actuator, wherein each propulsion impulse generator comprises a storage barrel for storing a predetermined amount of explosive materials to provide propelling impulse upon controlled explosion thereof, and a time-internal control arrangement comprising a time-interval control device mounted on a bottom of the front warhead, a time-interval trigger wire operatively connected with the time-interval control device, and at least two time-interval triggers mounted along the time-interval trigger wire and inside of each of the storage chambers respectively, wherein the time-interval triggers trigger the explosion of the explosive material stored in the storage chamber from the bottom propelling impulse generator to the top propelling impulse generator one by one at a predetermined time intervals, so as to further propels the front warhead to the predetermined position at a predetermined velocity and after each explosion. | 08-27-2009 |
| 20100213319 | Craft and Method of Coupling a Propulsion System to a Regenerative Fuel Cell System - The invention relates to a craft comprising an energy storage system of the RFCS (regenerative fuel cell system) type and a system for pressurizing the propellants used for propulsion. The craft also comprises a plurality of means ( | 08-26-2010 |
| 20100224731 | PROPULSION SYSTEM AND METHOD USING A COMBUSTION CHAMBER DISCHARGING A CONCENTRATED MASS - A propulsion system and method are described configured to exert a force upon a vehicle. The system includes a concentrated mass which may be discharged from the vehicle by a propellant typically via an ejection tube. The system is optimized so that the discharged concentrated-mass imparts a large impulse upon the vehicle. The system and method may be used to alter the momentum of vehicles for propulsion, attitude correction, vehicle separation and the like. | 09-09-2010 |
| 20100276546 | High speed airship structure - The structure provided multi-Levels of the center fuselage, two front wings, Extended mid-two wings and two rear wings with two vertical winglets. | 11-04-2010 |
| 20110024572 | DEVICE FOR REDUCING AERODYNAMIC DRAG - A device for reducing the aerodynamic drag of a vehicle includes at least one masking element for at least one part of a nozzle of the vehicle's engine, the masking element having a resorbable material designed to be eliminated in the nozzle's flow once the engine is ignited. A space craft includes the nozzle attached to the fuselage of the space craft. | 02-03-2011 |
| 20110073713 | DRIVE ARRANGEMENT IN A SPACECRAFT - The invention relates to a drive arrangement in a spacecraft, comprising several drive units (TW | 03-31-2011 |
| 20110073714 | Solar powered spacecraft power system for a hall effect thruster - a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array in parallel with the spacecraft power system; the electric propulsion system including a Hall effect thruster, a thruster power supply for driving the thruster; a sensor for sensing the power output of the solar array and a controller responsive to the power output of the solar array and configured to periodically adjust an operating parameter of the thruster to operate the thruster at the maximum available output power of the solar array including comparing a previous solar array output power level with a later solar array output power level, and incrementing the operating parameter with a positive value if the later is greater and with a negative value if the later is lesser; a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array, and a power management and distribution system connected to the solar photovoltaic array for distributing power to one or more bus loads and payloads. | 03-31-2011 |
| 20110240801 | MICROSATELLITE COMPRISING A PROPULSION MODULE AND AN IMAGING DEVICE - A microsatellite comprising a propulsion module for moving and/or pointing said microsatellite and an imaging device ( | 10-06-2011 |
| 20110297795 | SPACECRAFT PANEL ARCHITECTURE - One embodiment of the invention includes a spacecraft system. The system includes a spacecraft payload system coupled to a spacecraft frame. The system also includes a plurality of spacecraft panels disposed about the spacecraft frame. Each of the plurality of spacecraft panels can be communicatively coupled together via a network and configured substantially identically with respect to each other, and can include a processor and associated spacecraft control components. The processors of each of the spacecraft panels controlling the respective spacecraft control components independently to cooperatively and autonomously implement spacecraft control functions to implement a common mission objective. | 12-08-2011 |
| 20120312927 | LAUNCH ABORT AND ORBITAL MANEUVER SYSTEM - A spacecraft includes a first engine configured to provide primary launch abort thrust and a second engine disposed radially from a center of gravity, the second engine configured to provide a secondary launch abort thrust, a primary orbital maneuvering thrust, and a primary control thrust. | 12-13-2012 |
| 20120318927 | Carrier for space craft - A spacecraft carrier is disclosed. The carrier has a large internal volume for housing at least one spacecraft. The carrier can be used as a repair and maintenance facility in space for spacecraft. Manned and unmanned devices can be stored, repaired and resupplied. The carrier can also transport a number of spacecraft to other locations allowing for an efficient coordinated movement of many spacecraft. | 12-20-2012 |
| 20120325971 | Space vacuum propulsion system - This propulsion system is based on the theory of vacuum propulsion wherein a propulsion System utilizes space vacuum to propel the space ship through space. Vacuum Pumps are used to vacuum in space through the rear of the ship where it is gathered or collected in a pressure chamber. There the collected space is contained while yet more space vacuum is collected. The chamber has a containment valve at the end of the chamber and can be breached after vacuum collected reaches critical mass overcoming the containment valve where it is then released into the hull. This release of the vacuum chamber containment valve and the collected vacuum oozes from the vacuum chamber filling the hull mixing with carbon dioxide and heat changing the nature of space vacuum and creating a propellant fuel for propulsion. The chamber is situated at the rear of the starship. | 12-27-2012 |
| 20130043352 | THROTTLEABLE PROPULSION LAUNCH ESCAPE SYSTEMS AND DEVICES - The present invention relates to throttleable propulsion launch escape systems and devices. In one embodiment, the system includes a tower and at least one throttleable motor secured to the tower. The throttleable motor is able to throttle to a reduced power setting during flight. In another embodiment, the system includes at least one throttleable motor and a space vehicle unit that includes a containing structure. In a further embodiment, the throttleable motor may be secured about a boost escape system of a space vehicle unit. In an additional embodiment, the present invention is a three-dimensional nozzle. | 02-21-2013 |
| 20130140402 | METHODS AND SYSTEMS FOR PROPELLING AN EXTERNALLY POWERED VEHICLE - A vehicle is disclosed that includes a propellant tank, an optical absorber operable to transform optical energy into thermal energy, a quantity of solid lithium within the propellant tank, a heat exchanger, and an engine. The heat exchanger is operable to transfer thermal energy from the optical absorber to the quantity of solid lithium to liquefy at least a portion of the solid lithium, and further operable to boil the liquefied portion of the solid lithium. The engine is operable to utilize lithium vapor from the boiled lithium to propel the vehicle. | 06-06-2013 |
| 20130175401 | Salvaging and Braking Device for Objects Flying Freely in Space - In a recovery and braking device for objects flying freely in space, particularly for capturing satellites and other orbital objects, (at least one,) preferably a larger number of capturing units ( | 07-11-2013 |
| 20130200219 | ELECTRIC THRUSTER, A METHOD OF STOPPING AN ELECTRIC ENGINE INCLUDED IN SUCH A THRUSTER, AND A SATELLITE INCLUDING SUCH A THRUSTER - An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection. The thruster can be for use in a satellite, | 08-08-2013 |
| 20130256459 | Airship - An improved airship having a plurality of resilient gas bags & gas containers, a straight fuselage tubular hull, with an inner air passageway & propulsion means located therein, connecting air inlet, & outlet funnels fore, & aft, with air deflector cones axially positioned therein; further, propulsion, reverse, & directional rocket-thrusters, additionally to typical airship components; furthermore, said airship having improved speed, maneuverability, efficiency, & adverse weather capability, reduced forward air resistance, & rearward drag in the air; and propulsive, attitudinal, & directional control in space. | 10-03-2013 |
| 20130299641 | Multiple Space Vehicle Launch System - A multiple space vehicle launch system that may be adapted to be disposed within a payload region of a launch vehicle fairing. The launch system may include a first space vehicle, a second space vehicle releasably attached to the first space vehicle and oriented relative to the first space vehicle such that, when placed within the fairing, a launch load of the first space vehicle is transmitted to and borne by the second space vehicle. In certain embodiments, the first and second space vehicles each may include one of an electrical propulsion unit and a hybrid chemical and electrical propulsion unit. Use of electrical or hybrid chemical and electrical propulsion units enables the second space vehicle to bear all or a significant portion of the launch load of the first space vehicle, thereby eliminating the need for additional support structure. | 11-14-2013 |
| 20140203148 | CRYOGENIC THRUSTER ASSEMBLY - A cryogenic thruster assembly including: a reignitable main thruster; a first cryogenic tank connected to the main thruster to feed the main thruster with a first propellant; a first gas tank; at least one settling thruster; and a first feed circuit for feeding the first gas tank. The feed circuit of the first gas tank is connected to the first cryogenic tank and includes a heat exchanger for using heat given off by the at least one settling thruster to vaporize a liquid flow of the first propellant as extracted from the first cryogenic tank to feed the first gas tank with the first propellant in the gaseous state. A method feeds the first gas tank with the first propellant in the gaseous state. | 07-24-2014 |
| 20140263846 | CENTRIFUGAL FORCE AMPLIFICATION METHOD AND SYSTEM FOR GENERATING VEHICLE LIFT - A method and system generate lift for a vehicle relative to a planetary body rotating at a rotational speed. The vehicle incorporates two concentric lift rings in a common plane. The lift rings are positioned such that their common plane is approximately perpendicular to a force of gravity on the planetary body. The lift rings are rotated in opposing directions at speeds that are at least 20 times greater than the rotational speed of the planetary body. | 09-18-2014 |
| 20140306064 | LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF - The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor. | 10-16-2014 |
| 20140306065 | LAUNCH VEHICLE AND SYSTEM AND METHOD FOR ECONOMICALLY EFFICIENT LAUNCH THEREOF - The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided. | 10-16-2014 |
| 20150008288 | Standard Transit Tug - A standard transit tug is disclosed. The tug can dock with spacecraft to provide propulsion for the spacecraft. Further, the tug may dock with other specialty tugs to form a custom transport system. | 01-08-2015 |
| 20150021439 | SPACE VEHICLE WITH ELECTRIC PROPULSION AND SOLID PROPELLANT CHEMICAL PROPULSION - A space vehicle ( | 01-22-2015 |
| 20150097084 | SPACECRAFT SYSTEM FOR DEBRIS DISPOSAL AND OTHER OPERATIONS AND METHODS PERTAINING TO THE SAME - A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing. | 04-09-2015 |
| 20150115107 | SPACE DEBRIS REMOVER - A space debris remover aiming to remove a space debris object in earth orbits. Angular thrust calculation unit calculates angular thrust. Radial thrust calculation unit calculates radial thrust based on the angular thrust, estimated angular momentum and estimated space debris mass. A foam bonding mechanism connects the space debris remover and the space debris object. A space debris removal controller calculates firing time, and sends a space debris removal control signal comprising the radial thrust, the angular thrust and the firing time. A plurality of first stage thrusters generate the radial thrust and the angular thrust after the firing time. After the stage separator separates a first stage and a second stage of the space debris remover, a plurality of second stage thrusters generate the radial thrust and the angular thrust, and propel the space debris object towards the sun. | 04-30-2015 |
| 20150136913 | Systems and Methods for Launching Space Vehicles - Systems and methods for launching space vehicles into orbit involve placing a space vehicle into a protective container. The protective container is placed on a sled in a maglev tunnel and then launched into the atmosphere. Once the protective container reaches a certain height the space vehicle is released from the protective container and the space vehicle then proceeds to the desired orbital position. | 05-21-2015 |
| 20150303005 | SHAFT ASSEMBLY FOR ROTARY SWITCH - Described herein is a shaft assembly for a rotary switch that includes a shaft made from an electrically non-conductive material. The shaft includes at least one circumferential groove that has a generally T-shaped cross-section. The shaft assembly also includes at least one conductive ring segment made from an electrically conductive material positioned within the circumferential groove. The conductive ring segment has a generally T-shaped cross-section. Additionally, the shaft assembly includes a bonding adhesive that is positioned between the circumferential groove and the conductive ring segment. | 10-22-2015 |
| 20160031571 | MULTIPLE STAGE TRACTOR PROPULSION VEHICLE - A multiple stage orbital delivery vehicle that uses tractor propulsion to launch the vehicle into space. Only the upper stage of the vehicle includes an engine and avionics allowing the lower stages to be only liquid propellant tanks that may be dumped when empty. The liquid propellant may be either monopropellant or bi-propellant. The upper stage may include multiple nozzles that burn the propellant. Alternatively, the upper stage may include an aerospike engine instead of nozzles. The multiple stage orbital delivery vehicle may be air launched from an airborne aircraft or may be launched from the ground. | 02-04-2016 |
| 20160061148 | PROPULSION SYSTEM COMPRISING PLURALITY OF INDIVIDUALLY SELECTABLE SOLID FUEL MOTORS - A propulsion system for use with a satellite comprises a substrate, a communication network and a cluster of individually selectable solid fuel motors mounted on the substrate and operatively connected to the communication network. A controller is also operatively connected to the communication network and operative to select any one of more motors of the cluster of individually selectable solid fuel motors and transmit signals to fire the one or more motors of the individually selectable solid fuel motors. The substrate may have various configurations. The cluster of motors may comprise 10-1000 motors, which may be arranged in a rectangular array or other formation. Subsets of motors having different impulse capabilities may be employed. In this manner, lighter, smaller, flexible and more efficient propulsions systems may be provided for use in attitude control, etc. of satellites. | 03-03-2016 |
| 20160075454 | Spherical Aerospace Fuselage - The invention relates to aerospace fuselages or space vehicles comprising a spherical shape used to hold at least one propulsion device. A method of providing a way to correctly move, stop, and change directions in space since multi-directional propulsion is now available at any instant in time without the need to rotate a fuselage. when using a plurality of propulsion devices distributed on or within the bulkhead of the spherical fuselage. | 03-17-2016 |
| 20160122040 | THRUST APPARATUSES, SYSTEMS, AND METHODS - Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters. | 05-05-2016 |
| 20160200457 | SMALL SATELLITE PROPULSION SYSTEM | 07-14-2016 |
| 20160376001 | VEHICLE INCLUDING A TETRAHEDRAL BODY OR CHASSIS - A vehicle constructed in the shape of tetrahedral. The vehicle may be an aircraft, a space-craft, a sub-surface vehicle, or an unmanned drone. A tetrahedral body component is one of: a regular tetrahedron, an extended tetrahedron, a foreshortened tetrahedron, a tapered tetrahedron, and a truncated tetrahedron. A means for propulsion is mounted to at least one of the faces of the tetrahedral body component. The means for propulsion may include a turbine engine, a water jet, a gas jet, or electromagnetic propulsion. In another embodiment, the means for propulsion include an engine and a propeller. The engine block is mounted internal to the tetrahedral body component, and is located at the intersection of a tetrahedral shape with a cube shape. The engine block is mounted to the tetrahedral body component by struts perpendicular to the faces of the engine block. | 12-29-2016 |
| 20170233111 | Integration of Fuel Cell with Cryogenic Source for Cooling and Reactant | 08-17-2017 |
| 244171200 | Steerable mount | 6 |
| 20090314895 | DEVICE FOR DAMPING THE LATERAL FORCES DUE TO JET SEPARATION ACTING ON A ROCKET ENGINE NOZZLE - The invention relates to a device for damping the lateral forces due to jet separation that act on a rocket engine nozzle during a stage of starting or stopping the engine, the engine including at least two identical drive assemblies mounted on the nozzle to take up the lateral forces acting thereon, each drive assembly comprising a first member forming a strut, a second member forming an anchor structure, and an actuator. Each strut comprises means enabling it to act as a rigid strut so long as the lateral forces acting on the corresponding actuator remain below a determined force threshold, and as an element for peak limiting force and for dissipating residual kinetic energy once the forces acting on the actuator exceed the determined force threshold. | 12-24-2009 |
| 20100301168 | System and Process of Vector Propulsion with Independent Control of Three Translation and Three Rotation Axis - The present invention relates to a propulsion system of a vertical takeoff and landing aircraft or vehicle moving in any fluid or vacuum and more particularly to a vector control system of the vehicle propulsion thrust allowing an independent displacement with six degrees of freedom, three degrees of translation in relation to its centre of mass and three degrees of rotation in relation to its centre of mass. The aircraft displacement ability using the propulsion system of the present invention depends on two main thrusters or propellers and which can be tilted around pitch is (I) by means of tilting mechanisms and, used to perform a forward or backward movement, can be tilted around roll axis (X) by means of tilting mechanisms and, used to perform lateral movements to the right or to the left and to perform upward or downward movements (Z), the main thrusters being further used to perform rotations around the vehicle yaw axis (Z) and around the roll is (X). The locomotion function also uses one or two auxiliary thrusters or propellers and mainly used to control the rotation around the pitch axis, these thrusters or propellers and being fixed at or near the longitudinal is of the vehicle, with there thrust perpendicular or nearly perpendicular to the roll and pitch axis of the vehicle. | 12-02-2010 |
| 20130292519 | TURBINE POWERED ELECTROMECHANICAL ACTUATION SYSTEM - An electromechanical actuation system ( | 11-07-2013 |
| 20150008289 | Solar generator tug - A solar generator tug is disclosed. The tug can dock with spacecraft to provide power for the spacecraft. Further, the tug may dock with other specialty tugs to form a custom transport system. | 01-08-2015 |
| 20160167810 | Adjustment Mechanism for Adjusting at Least One Engine of a Spacecraft | 06-16-2016 |
| 20160200456 | ASSEMBLY FOR AIMING AN INSTRUMENT | 07-14-2016 |
| 244171300 | Launch from surface to orbit | 10 |
| 20090108137 | PRESSURE VESSEL HAVING CONTINUOUS SIDEWALL - A spacecraft pressure vessel has a tub member. A sidewall member is coupled to the tub member so that a bottom section of the sidewall member extends from an attachment intersection with the tub member and away from the tub member. The bottom section of the sidewall member receives and transfers a load through the sidewall member. | 04-30-2009 |
| 20100090066 | LATCHING SEPARATION SYSTEM - Latching elements on a first structure are configured to securely engage corresponding bearings on a second structure, via a lateral member that drives all of the latching elements simultaneously. When engaged, or when disengaged, the system is in a stable state, requiring no active force by the controlling system to maintain the system in each state. Preferably, each latching element is coupled to the lateral member via a pinion that provides a mechanical advantage that substantially reduces the force required on the lateral member to effect the coupling or decoupling. Also preferably, the elements are formed from extruded aluminum forms, thereby providing for a relatively inexpensive and lightweight configuration that is particularly well suited for spacecraft applications. | 04-15-2010 |
| 20100176247 | METHOD AND APPARATUS TO REDUCE THRUST OSCILLATIONS IN A LAUNCH VEHICLE - A launch vehicle comprising a casing, a solid propellant, a channel, a geometric feature, and a suppression structure. The solid propellant is located within the casing. The channel is through the solid propellant, and the geometric feature is in the channel. The suppression structure is located around a centerline for the channel and located upstream in a flow path from the geometric feature. | 07-15-2010 |
| 20100176248 | SPACECRAFT PROPULSION SYSTEM WITH GYROSCOPIC MECHANISM - A propulsion method employing gyroscopes ( | 07-15-2010 |
| 20120032029 | SPACE LAUNCH VEHICLE USING MAGNETIC LEVITATION - A space launch vehicle used for launching spacecraft uses a magnetic levitation system in order to reduce friction since the vehicle floats above rails. The system uses magnetic coils to propel and move the vehicle away from the quiescent point thereof. The invention facilitates the launch of a spacecraft, the time at which most fuel is required, so that the spacecraft is subsequently propelled by its own means. This method saves a large amount of fuel, which adds weight to the vehicle, such that saved weight can be used for payload. The system has the additional advantage of being reusable, as well as being modular to adapt to various types of spacecraft. Furthermore, the rocket or craft is launched at an angle of 57 degrees, dispensing with the need to change the angle of the craft from 90 to 57 degrees, as is currently the case, thus also saving fuel. | 02-09-2012 |
| 20140158831 | SPACE FLIGHT DRIVE AND FLIGHT CRAFT - In order to produce a space flight drive for propelling a spacecraft which can use the available fuel with great efficiency and which can transport heavy payloads to great heights, it is proposed that the space flight drive should comprise a fuel tank for holding a fuel, an oxidizer tank for holding an oxidizer, a combustion chamber device for the conversion of the fuel by the oxidizer, a propulsion nozzle device adjoining the combustion chamber device and a shroud device which surrounds the propulsion nozzle device annularly at least in sections for the production of an air sheath flow during a flight of the spacecraft through the atmosphere. | 06-12-2014 |
| 20150375875 | Space Launch Apparatus - A space launch apparatus comprising a solid triangular space frame constructed of a plurality of connected truss members that are attached to each other at nodes and are also attached to at least one rocket motor and to at least one payload whereby the force produced by the operation of the rocket motor is transferred to the payload and aerodynamic and vibration loads are distributed through the truss members and their nodes. | 12-31-2015 |
| 20160075453 | SATELLITE SYSTEM COMPRISING TWO SATELLITES ATTACHED TO EACH OTHER AND METHOD FOR LAUNCHING THEM INTO ORBIT - A satellite system includes a so-called carrier satellite and a so-called piggyback satellite, each one having an Earth face. The piggyback satellite is attached to the carrier satellite by fastening elements that can be released on command. The piggyback satellite includes propulsion elements suitable for maintaining same in orbit, and the carrier satellite includes propulsion elements for performing a change of orbit of the satellite system including the carrier satellite and the piggyback satellite. The piggyback satellite is attached to the Earth face of the carrier satellite in such a way that the Earth face of the piggyback satellite is essentially perpendicular to the Earth face of the carrier satellite. | 03-17-2016 |
| 20190144144 | LAUNCH VEHICLE WITH SOLAR CELLS, MANUFACTURING METHOD AND TRANSPORT METHOD | 05-16-2019 |
| 244171400 | Horizontal launch | 1 |
| 20150344158 | SPACE AIRCRAFT - According to the invention, said space aircraft comprises, at the front of each of the air inlets of the turbo engines, a mobile flap that can move, in both directions, between a first position for which said flap opens said air inlet and a second position for which said flap prevents air from entering said air inlet. | 12-03-2015 |
| 244171500 | Without mass expulsion | 9 |
| 20080296437 | Method and Device to Generate a Transverse Casimir Force for Propulsion, Guidance and Maneuvering of a Space Vehicle - Method and device for directly generating a transverse Casimir force comprising a technique for fabricating a microstructure array of non-parallel conducting plates held in place by an insulating material and affixed either to a conducting or insulating substrate are disclosed. As described by the illustrative embodiment, the lateral or transverse force component generated by the present invention works in an orthogonal direction to the normal Casimir force, thereby allowing its use as a means of vectored thrust for precise positioning, guidance, maneuvering and propulsion in a manned or unmanned space vehicle, or any application requiring precise forces. | 12-04-2008 |
| 20090194639 | SPACECRAFT AND METHOD FOR OPERATING THE SPACECRAFT - The present invention relates to a spacecraft (P) comprising a propulsion system ( | 08-06-2009 |
| 20100108820 | Highly-integrated low-mass plastic film - Low mass-per-unit-area plastic film, preferably polyimide, prepared by a process of controlled treating of a supply of plastic film, possibly with one surface reflectively coated, at a microlithography workstation with included photoablation optics. This treatment achieves significant controlled removal of material in a selected pattern by providing relative motion between untreated plastic film and the workstation's photoablation optics while controlling photoablation of a pattern in the film. The material has a significant quantity of the mass of its plastic removed by photoablation, leaving a tessellated pattern of ridges surrounding individual wells. The resulting low-mass, rip-resistant film retains the general attributes of a large-area plastic film. The treated film also retains its reflective surface, on which amorphous silicon may be deposited. The silicon may be thereafter crystallized, utilizing the same optics, and used for fabrication of microelectronics. | 05-06-2010 |
| 20100237198 | Switchable Article and Device to Generate a Lateral or Transverse Casimir Force for Propulsion, Guidance and Maneuvering of a Space Vehicle - An article and device are provided comprising a switchable microstructure or nanostructure array of non-parallel conducting plates, supported by a plurality of shaped prismatic oxide stages upon layered conductive and substrate-base materials, for directly generating a lateral or transverse Casimir force. Illustrative embodiments include a device for switchable generation of lateral or transverse Casimir force components that work in an orthogonal direction to normal Casimir forces which can be externally switched “on” or “off” electronically, mechanically or thermally by using a semiconductor PN-junction or superconductor to produce a thrust for guidance, maneuvering and propulsion of a manned or unmanned space vehicle, or in other novel applications requiring generation of precisely switched or continuous forces. | 09-23-2010 |
| 20100243816 | Aircraft also called a spacecraft, an aerospace craft, or a submersible craft - The invention relates to a plasma based aircraft maintained in a flight mode by rotating plasma vortices located above and beneath said aircraft. Said aircraft is comprised of chromium steel, or higher ferrochromium steel can be used. Said aircraft receives energy from aircraft produced plasma obtained from the atmosphere. | 09-30-2010 |
| 20110073715 | Method and apparatus for generating propellantless propulsion - Existing spacecraft accelerate by ejecting propellant, and VTOL craft hover by creating violent downdrafts of air. We describe a propellantless propulsion system that can achieve practical spaceflight and hovering flight by exchanging momentum with normally unobservable quantum particles that pervade all of space. | 03-31-2011 |
| 20120097798 | INERTIAL MASS SUSPENSION - A craft, having at least two counter rotating rotors within, or a multi unit craft having two or more units as desired, with counter rotating rings, having the ability to store inertia, within the spinning rings, so as to enable the craft to either accelerate from the front or decelerate from the back of the Earth, relative to the absolute inertial frame of reference. | 04-26-2012 |
| 20140061386 | METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS - Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes a frame, a power source coupled to the frame and a payload coupled to the frame, the payload to receive or transmit data. The apparatus also includes an electric propulsion system coupled to the frame. The electric propulsion system is to enable attitude control, momentum control, and orbit control of the apparatus. | 03-06-2014 |
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