Class / Patent application number | Description | Number of patent applications / Date published |
244158900 | Reusable or returnable | 31 |
20080272239 | Reversible space plane - A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction. | 11-06-2008 |
20090140100 | REUSABLE ORBITAL VEHICLE WITH INTERCHANGEABLE CARGO MODULES - A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module. | 06-04-2009 |
20090302166 | Space station, launch vehicle, and method of assembly - A launch vehicle for a space station includes a crew transport vehicle having an orbiter, a cylindrical cargo module separable from the orbiter when in low earth orbit, and a first liquid fuel rocket engine section coupled to the cargo module operable to assist in placement of the launch vehicle in low earth orbit. The first engine section is separable from the cargo module in low earth orbit. The launch vehicle also includes booster rockets operable to place the launch vehicle in low earth orbit, and a liquid fuel tank, which is convertible to form living and working spaces for the space station. The space station includes rentable space that is used to recover launch and assembly costs associated with the space station. | 12-10-2009 |
20100051751 | REUSABLE ORBITAL VEHICLE WITH INTERCHANGEABLE MODULES - A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV, aerodynamic characteristics, and mounting configurations to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. The module may be a cargo module, a satellite payload module or a passenger module. The passenger module is provided in a variety of configurations to accommodate a different number of passengers and cargo based on mission parameters. | 03-04-2010 |
20100276545 | Aerodynamic and Spatial Composite Flight Aircraft, and related Piloting Method - This aircraft comprises both propulsion units ( | 11-04-2010 |
20100314497 | COMPENSATING FOR WIND PRIOR TO ENGAGING AIRBORNE PROPULSION DEVICES - Technology is described for enabling a reusable launch vehicle to compensate for wind prior to engaging propulsion during approach to landing. The technology can cause the reusable launch vehicle to begin un-powered descent; determine a first rotation angle of the reusable launch vehicle about a specified vertical descent path, the first rotation angle corresponding to a first attitude of the reusable launch vehicle selected to stabilize the reusable launch vehicle on the vertical descent path based on a wind speed and angle; and prior to engaging a propulsion device, command a second rotation angle for the reusable launch vehicle, the second rotation angle corresponding to a second attitude that, when the propulsion device is engaged, will cause the reusable launch vehicle to remain at least approximately at the vertical descent path. | 12-16-2010 |
20100320329 | LAUNCH VEHICLES WITH FIXED AND DEPLOYABLE DECELERATION SURFACES, AND/OR SHAPED FUEL TANKS, AND ASSOCIATED SYSTEMS AND METHODS - Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle. In a further particular embodiment, the exposed surface can include a deployable flare surface that is positioned toward the forward section of the vehicle and is stowed during an ascent phase of the vehicle. During descent, the deployable flare surface can pivot outwardly to slow the vehicle down for a tail-down landing. Systems is accordance with other embodiments include launch vehicles with fuel tanks shaped to control the motion of the center of gravity of fuel in the tanks as the fuel level in the tank changes. | 12-23-2010 |
20110017872 | SEA LANDING OF SPACE LAUNCH VEHICLES AND ASSOCIATED SYSTEMS AND METHODS - Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors. After landing, the sea-going platform can be towed by, e.g., a tug, or it can use its own propulsion system, to transport the booster stage back to the coastal launch site or other site for reconditioning and reuse. In another embodiment, the booster stage can be transferred to another vessel for transport. In still further embodiments, the booster can be refurbished while in transit from a sea-based or other landing site. | 01-27-2011 |
20110297793 | REUSABLE MODULE FOR LAUNCHER - A propulsion module configured to launch a craft into space including a recoverable module and a non-recovered part, which is secured to the recoverable module at launch. The recoverable module includes a propulsive system to launch the craft, systems for command and control of the propulsive system, a subsonic flight propulsion motor, airfoils for the subsonic flight, a landing gear, and a braking parachute. The recoverable module is installed in a lower position of the craft when the craft is in the launch position. The non-recovered part includes at least one tank to feed the propulsive system. The recoverable module and the non-recovered part are configured to be separated when the propulsion module reaches a given altitude, and the recoverable module is capable of landing in a controlled fashion after a coasting flight, for example for a return to the launch site. | 12-08-2011 |
20120119035 | Collapsible space shuttle - The invention relates to an airship which can be unfolded and folded up automatically on the ground and during flight and which can be operated as an aircraft or as a reusable space shuttle, having a combined collapsible gas cell ( | 05-17-2012 |
20120228434 | POD FOR SPACE OR NEAR-SPACE FLIGHTS | 09-13-2012 |
20120280086 | Reversible Space Plane - A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, and an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction. | 11-08-2012 |
20130087659 | SIMPLIFIED REUSABLE MODULE FOR LAUNCHER - A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function. | 04-11-2013 |
20140151509 | CAPSULE SYSTEM, SERVICE MODULE, AND REUSEABLE REENTRY PAYLOAD AND DOCKING MODULE - A modular spacecraft comprising: | 06-05-2014 |
20140263841 | LAUNCH VEHICLES WITH RING-SHAPED EXTERNAL ELEMENTS, AND ASSOCIATED SYSTEMS AND METHODS - Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent. | 09-18-2014 |
20140319281 | SPACE SHUTTLE ORBITER AND RETURN SYSTEM - A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections. | 10-30-2014 |
20160176546 | CONTROL SURFACES FOR USE WITH HIGH SPEED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS | 06-23-2016 |
244159100 | With reentry shield | 3 |
20090050745 | COMMERCIAL EXTERNAL RE-ENTRY TESTING FROM ORBIT - An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Previously expensive arc jet wind tunnels attempted to simulate the re-entry temperatures and ever changing re-entry flow environment for researchers. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system. | 02-26-2009 |
20090127399 | SYSTEM FOR USE OF EXTERNAL SECONDARY PAYLOADS - An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system. | 05-21-2009 |
244159200 | Inflatable | 1 |
20160137320 | ENVELOPING AERODYNAMIC DECELERATOR - An inflatable aerodynamic deceleration method and system is provided for use with an atmospheric entry payload. The inflatable aerodynamic decelerator includes an inflatable envelope and an inflatant, wherein the inflatant is configured to fill the inflatable envelope to an inflated state such that the inflatable envelope surrounds the atmospheric entry payload, causing aerodynamic forces to decelerate the atmospheric entry payload. | 05-19-2016 |
244159300 | Having aerodynamic lifting body (e.g., Space Shuttle) | 11 |
20080217481 | Reversible space plane - A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction. | 09-11-2008 |
20090140101 | Direct Flight Far Space Shuttle - A vehicle and method for enabling propulsive flight from suborbital altitudes and velocities directly to far space, or beyond Low Earth Orbit (LEO), preferably without requiring injection into or refueling in LEO. The vehicle is preferably reusable and can withstand re-entry speeds and temperatures higher than those that are typical for LEO vehicles. The vehicle preferably lands horizontally, for example on a runway. The vehicle forms the upper stage of a booster vehicle system which can be launched either from the ground or from a subsonic air platform. The vehicle may optionally be used for LEO missions. | 06-04-2009 |
20090173830 | Rocket-powered kite plane for gentle climb and acceleration to extreme staging altitudes - A two-stage space vehicle is provided for achieving low earth orbit that includes a carrier and an orbiter. The carrier has a large airfoil area relative to its dry weight, and the thrust of the rocket engine is controlled such that the carrier achieves a launch altitude and speed for the orbiter without exceeding a wingloading pressure beyond 3,500 Pa., which allows the carrier to be inexpensively constructed. Liquid propellant for the rocket engine is advantageously stored within the relatively large airfoil of the carrier, which is preferably a delta wing. The ratio of airfoil area to dry weight is about 33 m | 07-09-2009 |
20100314498 | Personal spacecraft - The spacecraft structure is provide, the spacecraft structure for the spacecraft includes, a center fuselage, right wing side fuselage, left wing side fuselage, front wings, and rear wings of Arch-Wings, vertical winglets, and the first levels, the fuselage has a cross-section of substantially flat floor fuselage shape, being is wide enough to provide lifting force. | 12-16-2010 |
20110042521 | Spacecraft Launch and Exploration System - This invention is a launch-to-space, refuel and return system which comprises: a unique circular and straight maglev track and maglev sled spacecraft launcher; a single stage-to-LEO spacecraft (Mother Spacecraft); an orbiting space platform (OSP); a currently utilized Space Shuttle is altered to improve its safety, range, longevity and versatility which serves as a prototype for the Mother Spacecraft design. The Mother Spacecraft is releasably attached to the maglev sled and propulsion for the maglev sled is supplied by magnetic propulsion and on-board rocket propulsion. The collapsible OSP can fit into the Space Shuttle storage bay and is remotely deployed. The OSP is a refueling depot for the Mother Spacecraft, the Space Shuttle, as well as a rendezvous point for various space missions. A single, liquid, non-cryogenic rocket fuel is standardized throughout the entire system which eliminates: all vertical launches; all expendables; all solid rocket propellants. | 02-24-2011 |
20110180670 | In orbit space transportation & recovery system - An In Orbit Transportation & Recovery System (IOSTAR™) ( | 07-28-2011 |
20140014779 | Direct Flight Far Space Shuttle - A vehicle and method for enabling propulsive flight from suborbital altitudes and velocities directly to far space, or beyond Low Earth Orbit (LEO), preferably without requiring injection into or refueling in LEO. The vehicle is preferably reusable and can withstand re-entry speeds and temperatures higher than those that are typical for LEO vehicles. The vehicle preferably lands horizontally, for example on a runway. The vehicle forms the upper stage of a booster vehicle system which can be launched either from the ground or from a subsonic air platform. The vehicle may optionally be used for LEO missions. | 01-16-2014 |
20140124626 | SPACE SHUTTLE PROGRAM ORBITAL VEHICLE COMPRISING A MULTIPLE PASSENGER BAY MODULE - The application provides a Space Shuttle Program (SSP) Orbital vehicle comprising a payload bay comprising a pressure vessel comprising a passenger bay module adapted to provide and maintain habitable conditions for twenty or more passengers during a mission traveling from earth to space and back to earth. | 05-08-2014 |
20140124627 | COMMERCIALLY FEASIBLE METHOD OF FLYING REPEATED ORBITAL MISSIONS USING A SPACE SHUTTLE PROGRAM ORBITAL VEHICLE - The application provides a commercially feasible method of flying repeated orbital missions using a Space Shuttle Program (SSP) Orbital Vehicle. | 05-08-2014 |
20140263842 | Reusable Global Launcher - A reusable unmanned single-stage boost-glide suborbital Earth launcher, able to propel large or smaller payloads from Earth surface or from air launch, to a nearly Earth-orbital condition, then glide circum-globally to horizontal airstrip landing at its launch site or similar circum-global recovery site. The payload, using its own propulsion, is thus enabled to complete insertion into low-Earth-orbit (LEO) or destinations beyond LEO. This technically feasible capability, beyond conferring economic benefits of reusability and maneuverability, can be adapted to increase payload by adding drop tanks, or solid or liquid “strap on” boosters, and might eventually be modified and evolved to perform manned aerospace missions, as well as single stage to orbit (SSTO) missions. | 09-18-2014 |
20160052650 | DEVICE FOR CONTROLLING THE SPEED OF A SPACEPLANE DURING THE TRANSITION FROM A PHASE OF SPACE FLIGHT TO A PHASE OF AERONAUTICAL FLIGHT AND ASSOCIATED TRANSITION METHOD - A spaceplane suitable for aeronautical flight comprising a body and a wing defining a lower airfoil surface in addition to attitude control means that comprise one or a plurality of shutters disposed under the lower airfoil surface of same and maneuverable between a stowed position and an inclined extended position for aerodynamic braking during the transition from a phase of space flight to a phase of aeronautical flight of the aircraft. | 02-25-2016 |