Having Aerodynamic Lifting Body (e.g., Space Shuttle) Patents (Class 244/159.3)
  • Patent number: 12037142
    Abstract: Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.
    Type: Grant
    Filed: February 10, 2022
    Date of Patent: July 16, 2024
    Assignee: Space Arena, Inc.
    Inventor: Daniel Faber
  • Patent number: 11926439
    Abstract: A recoverable rocket stage (2) for propelling a rocket (100) towards space includes a rocket propellant tank assembly (4) having a generally cylindrical outer shape; at least one engine (6), coupled to the rocket propellant tank assembly (4); and a plurality of drag enhancing elements (8), the plurality of drag enhancing elements (8) forming longitudinal extensions of the generally cylindrical outer shape of the rocket propellant tank assembly (4) in their launch positions and being inclinable with respect to the generally cylindrical outer shape of the rocket propellant tank assembly (4) for return of the recoverable rocket stage (2) to earth.
    Type: Grant
    Filed: November 13, 2019
    Date of Patent: March 12, 2024
    Assignee: ORBITAL EXPRESS LAUNCH LIMITED
    Inventor: Jonas Baekby Bjarnoe
  • Patent number: 11518547
    Abstract: A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.
    Type: Grant
    Filed: June 18, 2021
    Date of Patent: December 6, 2022
    Assignee: AT SPACE PTY LTD
    Inventor: Yen-Sen Chen
  • Patent number: 11472576
    Abstract: An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.
    Type: Grant
    Filed: April 3, 2019
    Date of Patent: October 18, 2022
    Inventor: Geoffrey T. Sheerin
  • Patent number: 11353304
    Abstract: A missile including an upper stage and at least one lower stage is provided. The upper stage includes a primary flight computer configured to control a flight of the upper stage along a missile flight path such that, for example, it reaches a predetermined target. The lower stage is mounted to the upper stage and includes a propellant for initially propelling the upper stage along the missile flight path. The lower stage is configured to be jettisoned from the upper stage when the propellant is spent. The lower stage includes a secondary flight computer configured to receive data from the primary flight computer prior to the propellant of the lower stage being spent, and to control a flight of the lower stage along a jettisoned stage flight path of the jettisoned lower stage such that, for example, the jettisoned lower stage glides to a predetermined safe landing zone.
    Type: Grant
    Filed: August 18, 2020
    Date of Patent: June 7, 2022
    Assignee: Raytheon Company
    Inventor: Ralph H. Klestadt
  • Patent number: 11008121
    Abstract: A space body has at least two space modules which can be interchangeably connected to one another. At least one closable connection opening is in each case provided on the space modules, via which a passage is produced when the space modules are connected. Furthermore, at least one coupling device connects in each case the space modules to one another. A supply interface is provided for coupling a supply line of the space modules.
    Type: Grant
    Filed: May 12, 2017
    Date of Patent: May 18, 2021
    Assignee: iBOSS GmbH
    Inventor: Jörg Kreisel
  • Patent number: 10773791
    Abstract: An aircraft with stealth double wings comprises a main body and stealth double wings. The main body has two main wings respectively having a surface into which a space is formed. The stealth double wings respectively are located in the spaces and include a first and a second rotating shaft, a link rod, a first and a second wing. The link rod has two ends respectively connected with the two rotating shafts. The two rotating shafts respectively have another end connected with the first and second wings. Thereby, when the first wing is moved to cover and enclose the space's opening, the second wing is driven to be located within the space, and when the first wing is moved upwardly away from the space, the second wing is driven to cover and enclose the space's opening, so as to keep the surface intact.
    Type: Grant
    Filed: July 24, 2018
    Date of Patent: September 15, 2020
    Inventor: Shih-Ping Lee
  • Patent number: 10773788
    Abstract: A fairing assembly for an aerial vehicle having a tank that forms a body of the vehicle and a wing coupled to the tank is provided. The fining assembly includes a substructure configured to couple with a tank skin of the tank, a thermal protection system coupled to the substructure, and a seal assembly coupled to the substructure, the seal assembly being configured to overlap at least a portion of an edge of the wing.
    Type: Grant
    Filed: August 15, 2017
    Date of Patent: September 15, 2020
    Assignee: The Boeing Company
    Inventors: Michael J. Best, Jonathan D. Embler, John S. Kruse, Thomas R. Pinney, Drew L. Smallwood
  • Patent number: 10669047
    Abstract: An apparatus includes a body having at least one pitch control system and a mounting system, the mounting system configured to couple to a payload. The apparatus also includes a rocket engine coupled to the body and configured to accelerate the body to a hypersonic speed. The apparatus further includes a control system configured to release the payload while the body moves at the hypersonic speed by commanding the at least one pitch control system to adjust an angle of attack of the body to a negative angle of attack and commanding the mounting system to release the payload while the body is moving at the hypersonic speed and at the negative angle of attack.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: June 2, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Ashwani K. Chaudhary, David Poladian
  • Patent number: 10514024
    Abstract: A detachment system for a delivery aerial drone is disclosed. The detachment system uses a pump to apply a negative pressure to a suction cup for attaching an object to be delivered. The weight of the object is coupled to a mechanical switch, such that setting down the object opens the switch and disconnects the pump. Once the pump is disconnected from its power source, the suction is removed and the object disconnects from the vacuum system. The weight of the object is coupled to a mechanical switch, such that setting down the object opens the switch and disconnects the pump. Thus, the object releases once it is gently placed on a surface such that its weight is removed from the drone.
    Type: Grant
    Filed: May 1, 2019
    Date of Patent: December 24, 2019
    Inventor: Stephen P. Shoemaker, Jr.
  • Patent number: 10089507
    Abstract: An accessory for holding a scanning instrument, comprising: a sleeve to receive the scanning instrument; a fastener coupled to the sleeve to releasably secure the scanning instrument in the sleeve; a coupling mechanism having a first end and a second end, the first end rotatably coupled to the sleeve such that the sleeve rotates about an axis defined by the first end, the second end rotatably coupled to the first end such that the first end and the sleeve rotate about an axis defined by the second end; and an extension pole coupled to the coupling mechanism at the second end. In one embodiment, the coupling mechanism further comprises a motion inducer configured to induce movement of the sleeve with respect to the coupling mechanism and the extension pole.
    Type: Grant
    Filed: April 7, 2017
    Date of Patent: October 2, 2018
    Assignee: SPEEDTHOUGHT CONSULTING, INC.
    Inventor: John-Pierre Kamel
  • Patent number: 10054958
    Abstract: One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body encapsulating an engine and the flight control system. The VTOL UAV further includes a propeller disk coupled to the engine and configured to provide vertical thrust in the hover mode and to provide horizontal thrust for flight during the level-flight mode.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: August 21, 2018
    Assignee: Northrop Grumman Systems Corporation
    Inventor: Son F. Creasman
  • Patent number: 9193457
    Abstract: An apparatus and method for mitigating the shock front of an aerospace plane flying at hypersonic speeds. The invention employs supercooling driven by the cryogenic power of liquid hydrogen, regenerative evaporation of liquid hydrogen or liquid nitrogen and consequential isothermal compression, to usurp the shock front in totality at Mach 1.
    Type: Grant
    Filed: August 16, 2013
    Date of Patent: November 24, 2015
    Inventor: Charl Emelio Janeke
  • Patent number: 9174749
    Abstract: 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.
    Type: Grant
    Filed: December 18, 2009
    Date of Patent: November 3, 2015
    Assignee: ASTRIUM SAS
    Inventors: Marco Prampolini, Olivier Gogdet
  • Patent number: 9139311
    Abstract: 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.
    Type: Grant
    Filed: July 17, 2013
    Date of Patent: September 22, 2015
    Inventor: Robert Salkeld
  • Patent number: 9121680
    Abstract: An air vehicle, such as a missile, for example an interceptor, includes control surfaces and a vectored thrust system, both used for steering the missile. A controller is operatively coupled to both steering mechanisms, and is configured to operate in a low dynamic pressure mode, which uses the vectored thrust system for at least part of the steering, only when the dynamic pressure is low, such as when the missile is at high altitude. At higher dynamic pressure, such as at lower altitude, the controller is configured to operate in a high dynamic pressure mode that uses only the control surfaces for steering. This allows the interceptor to operate at higher altitudes than interceptors that use only control surfaces for steering during flight. During flight for a high altitude interception the missile shifts from the high dynamic pressure mode to the low dynamic pressure mode.
    Type: Grant
    Filed: January 17, 2013
    Date of Patent: September 1, 2015
    Assignee: Raytheon Company
    Inventors: Robert W Morgan, James P Normoyle, Kurt J Wuest, David Drake
  • Patent number: 8925857
    Abstract: Aircraft systems that are optimized for multiple phases of flight are disclosed. In an aspect, an in-line staged aircraft is disclosed comprising a launch vehicle and a flight vehicle which are configured to join together along a common center line and form a single air foil in the joined configuration. The flight vehicle and the launch vehicle are separable in flight. In an aspect, the flight vehicle is an unmanned aerial vehicle configured for high-altitude, long-endurance operations.
    Type: Grant
    Filed: December 10, 2013
    Date of Patent: January 6, 2015
    Inventor: David Luther
  • Publication number: 20140263842
    Abstract: 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.
    Type: Application
    Filed: July 17, 2013
    Publication date: September 18, 2014
    Inventor: Robert Salkeld
  • Patent number: 8800934
    Abstract: A space access system may include a reusable booster limited to sub-orbital operation and having a fuselage. The reusable booster may include a tri-propellant propulsion system which may be configured to shift from a tri-propellant mode of operation to a bi-propellant mode of operation. The tri-propellant propulsion system may include at least one tri-propellant engine and at least one internal propellant tank mounted within the fuselage and being fluidly coupled to the tri-propellant engine. A payload may be mounted with the fuselage. The payload may have an upper stage.
    Type: Grant
    Filed: October 24, 2012
    Date of Patent: August 12, 2014
    Assignee: The Boeing Company
    Inventor: Anthony D. Straw
  • Publication number: 20140124627
    Abstract: The application provides a commercially feasible method of flying repeated orbital missions using a Space Shuttle Program (SSP) Orbital Vehicle.
    Type: Application
    Filed: November 5, 2012
    Publication date: May 8, 2014
    Inventor: Joseph MICHAEL CLAY
  • Publication number: 20140124626
    Abstract: 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.
    Type: Application
    Filed: November 5, 2012
    Publication date: May 8, 2014
    Inventor: JOSEPH MICHAEL CLAY
  • Publication number: 20140014779
    Abstract: 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.
    Type: Application
    Filed: September 13, 2013
    Publication date: January 16, 2014
    Inventor: Robert Salkeld
  • Patent number: 8534598
    Abstract: 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.
    Type: Grant
    Filed: May 5, 2008
    Date of Patent: September 17, 2013
    Inventor: Robert Salkeld
  • Patent number: 8528853
    Abstract: A vehicle includes a first sub-vehicle, and a second sub-vehicle which is repeatably moveable between coupled and uncoupled conditions with the first sub-vehicle. The first and second sub-vehicles each include a landing system and propulsion system. The first and second sub-vehicles are in the coupled condition during take-off. The first and second sub-vehicles are separately flyable in the uncoupled condition. Both vehicles are launched horizontally, by a ramp, or vertically, using atmospheric lift to achieve atmospheric flight, orbital, or sub-orbital launch.
    Type: Grant
    Filed: July 26, 2011
    Date of Patent: September 10, 2013
    Inventor: David I. Luther
  • Patent number: 8500070
    Abstract: The present invention relates to a spacecraft structure that comprises a flat-wide body center fuselage, right and left side arch-wings and rocket propulsion power plant compartments, wherein the arch-wing is anchored to the fuselage via a foldable hinge mechanism. The fuselage structure is constructed as a single solid structure body of the spacecraft. A top portion at the rear of fuselage comprises a jet propulsion power plant to provide thrust during take-off from the airport. Both the left and right side arch-wings are anchored to a front and a rear portion of the center fuselage structure. Both the front and rear wing portions enable spacecraft lift and superior maneuverability during flight. The spacecraft is air tight and water tight and includes floatation devices.
    Type: Grant
    Filed: June 10, 2009
    Date of Patent: August 6, 2013
    Inventor: Sunstar Im
  • Patent number: 8478571
    Abstract: Systems and methods reduce development, integration and testing time of a spacecraft implemented with one or more reconfigurable processor boards. Mission spacecraft design tools design, configure, simulate and analyze the spacecraft based upon constraints of the mission requirements. The mission spacecraft design tools utilize a database of defined module specifications and firmware components. One or more RPBs are programmed based upon the configuration and interfaced to other end item components defined by the configuration to form the spacecraft.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: July 2, 2013
    Assignee: Design—Net Engineering, LLC
    Inventors: Gerald B. Murphy, James L. Wolf, Ramon Krosley
  • Publication number: 20130007935
    Abstract: A rocket launch system (1) includes a tubular rocket launcher carriage (2) with electromotive cableway traction drives (26) conveyed beneath a two axis pivot (63) anchored to the earth, elevated into a co-axial transfer tube (124, 143) leading to three primary tether cables (27) whose weight is offset by balloons (164). The carriage is conveyed to a docking station (166) supported into the stratosphere by a pair of secondary cables (184) suspended under an attachment frame (162) for tensioning balloons. The carriage is engaged by a carriage end gripper (196) guided by two secondary and two tertiary cables (186) and lifted by a lower hoist (198) guided by the secondary cables. This lower hoist is supported by an upper hoist (168) suspended from the tensioning balloons attachment frame.
    Type: Application
    Filed: February 10, 2011
    Publication date: January 10, 2013
    Inventors: Howard M. Chin, Kimberly A. Carraha
  • Patent number: 8275498
    Abstract: A system and method for assessing the risk of conjunction of a rocket body with orbiting and non-orbiting platforms. Two-body orbital dynamics are used to initially determine the kinematic access for a ballistic vehicle. The access may be represented in two ways: as a volume relative to its launcher and also as a geographical footprint relative to a target position that encompasses all possible launcher locations.
    Type: Grant
    Filed: August 2, 2010
    Date of Patent: September 25, 2012
    Assignee: Analytical Graphics Inc.
    Inventor: Salvatore Alfano
  • Patent number: 8168929
    Abstract: A non-powered pre-stage (10) with a commensurably large wing area is used to launch a variety of single-stage and multiple-stage space vehicles (20), such as conventional ballistic rockets and prospective spaceplanes, from conventional runways. This method of launch eliminates need in dedicated ground launch structures and/or dedicated long runways. The vehicle to be launched (20) is mated to this non-powered aero-assisted pre-stage (NAP) (10), with their flight directions aligned, using a lock-and-release mechanism (30). The resulting stack takes off like a conventional airplane using the propulsion of the vehicle and aerodynamic lift of the NAP. After the desired trajectory of the vehicle is achieved, the vehicle is separated from the NAP and continues its ascent. The NAP returns back to the surface for reuse or disposal. Thus, a wide variety of conventional airfields can be used for launch of ballistic and aero-assisted flight vehicles.
    Type: Grant
    Filed: January 15, 2009
    Date of Patent: May 1, 2012
    Inventor: Eugene Alexis Ustinov
  • Publication number: 20110180670
    Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.
    Type: Application
    Filed: February 7, 2007
    Publication date: July 28, 2011
    Inventors: Robert F. D'Ausilio, James R. Stuart, Franklin H. Williams, JR.
  • Publication number: 20110042521
    Abstract: 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.
    Type: Application
    Filed: November 17, 2009
    Publication date: February 24, 2011
    Inventor: Daniel S. Sample
  • Publication number: 20100314498
    Abstract: 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. The front wings of the Arch-Wings are disposed horizontally in rear portions of the fuselage the vertical winglets are disposed the top of the rear fuselage the first level disposed fuel tank storage, plurality of landing gear bays, cockpit with control panel, various avionic instruments, cabin doors. The top of the rear fuselage disposed jet-power plants and further more at compartment of the Arch-Wings disposed rocket power plants.
    Type: Application
    Filed: June 10, 2009
    Publication date: December 16, 2010
    Inventor: Sunstar Im
  • Patent number: 7834859
    Abstract: The process comprises the steps of: 1) launching the vehicle from the launch site using the first stage booster rocket engine system; 2) separating the at least one upper stage from the first stage booster; 3) terminating operation of the first booster stage rocket engine system; 4) turning the first stage booster back toward the launch site using the aerodynamic flight control system; 5) operating the first stage booster rocket engine system to boost the first stage booster to an altitude sufficient to allow non-powered flight back to the launch side; and 6) landing the first stage booster at the launch site.
    Type: Grant
    Filed: November 15, 2006
    Date of Patent: November 16, 2010
    Assignee: Northrop Grumman Corporation
    Inventors: Barnaby S. Wainfan, Warren W. James, Daniel H. Sokol
  • Patent number: 7654489
    Abstract: A lifting body aircraft suitable for atmospheric flight and/or as a reentry vehicle. The craft has a substantially flat upper surface, a lower surface with a doubly convex first section and a flat sloping second section. Chines may be provided between the upper and lower surfaces. The doubly convex first section allows the craft to have its center of gravity forward of its longitudinal center line. The flat sloping second half of the lower surface and the substantially flat upper surface form the aft end of an airfoil. A pair of vertical stabilizers enhance stability and include rudders which, along with a pair of elevons, provide steerage. The craft may glide or it may have an engine or rockets for thrust. The result is an extremely stable lifting body design that is well suited for launch or conventional take off, insertion, orbital operations, reentry, atmospheric flight, and conventional landings.
    Type: Grant
    Filed: June 27, 2005
    Date of Patent: February 2, 2010
    Assignee: Aviation Dynamics, Corp
    Inventor: Jon C. Stephenson
  • Publication number: 20090173830
    Abstract: 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 m2 per ton, which allows the carrier to descend and land after launching the orbiter with low wingloading on the order of 300 Pa.
    Type: Application
    Filed: April 21, 2006
    Publication date: July 9, 2009
    Inventor: Leonard N. Cormier
  • Publication number: 20090140101
    Abstract: 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.
    Type: Application
    Filed: May 5, 2008
    Publication date: June 4, 2009
    Inventor: Robert Salkeld
  • Patent number: 7509774
    Abstract: For an inflatable structure having a flexible outer shell or wall structure having a flexible restraint layer comprising interwoven, load-bearing straps, apparatus for integrating one or more substantially rigid members into the flexible shell. For each rigid member, a corresponding opening is formed through the flexible shell for receiving the rigid member. A plurality of connection devices are mounted on the rigid member for receiving respective ones of the load-bearing straps.
    Type: Grant
    Filed: December 13, 2006
    Date of Patent: March 31, 2009
    Assignee: The United States of America as represented by the National Aeronautics and Space Administration
    Inventors: Christopher J. Johnson, Ross M. Patterson, Gary R. Spexarth
  • Publication number: 20080217481
    Abstract: 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.
    Type: Application
    Filed: May 19, 2008
    Publication date: September 11, 2008
    Inventor: Charl E. Janeke
  • Publication number: 20080111030
    Abstract: The invention is a process for returning the first stage booster of a launch vehicle having at least one upper stage, the first stage booster having a rocket engine system and aerodynamic flight control system, to the launch site, the process comprising the steps of: 1) launching the vehicle from the launch site using the first stage booster rocket engine system; 2) separating the at least one upper stage from the first stage booster; 3) terminating operation of the first booster stage rocket engine system; 4) turning the first stage booster back toward the launch site using the aerodynamic flight control system; 5) operating the first stage booster rocket engine system to boost the first stage booster to an altitude sufficient to allow non-powered flight back to the launch side; and 6) landing the first stage booster at the launch site.
    Type: Application
    Filed: November 15, 2006
    Publication date: May 15, 2008
    Inventors: Barnaby S. Wainfan, Warren W. James, Daniel H. Sokol
  • Patent number: 7313362
    Abstract: The present invention relates to an aircraft and to a method of getting the aircraft onto station. According to the invention, said aircraft (1) includes propulsion means (2) capable only of enabling said aircraft (1) to move and to orient itself at high altitude, and said aircraft (1) is taken to its station in the high atmosphere, in particular in the stratosphere, by means of an independent transporter (3).
    Type: Grant
    Filed: June 19, 2000
    Date of Patent: December 25, 2007
    Assignee: Alcatel
    Inventor: Hervé Sainct
  • Patent number: 7281682
    Abstract: A spacecraft system for achieving LEO and beyond includes a lifting body spacecraft, and an acceleration bed unit for accelerating the spacecraft horizontally on a runway to liftoff. The rocket engines of the spacecraft then power the spacecraft into LEO, and the spacecraft glides back to earth, where it is refurbished for reiterative use. A belly assembly of the spacecraft is removable and replaceable. The hydrogen fuel tanks of the spacecraft are modular units, and each include a bladder that expands to fill the tank when empty to prevent explosion hazards.
    Type: Grant
    Filed: March 16, 2004
    Date of Patent: October 16, 2007
    Assignee: DBI/Century Fuels & Aerospace Services
    Inventor: Hector A. D'Auvergne
  • Patent number: 7240878
    Abstract: The Hypersonic Orbital Fighter and the methods of flying it are disclosed. The Hypersonic Orbital Fighter is characterized by a winged, modified lifting body shape with the forward ventral section comprising an X-30 type compressive air inlet, throttleable supersonic combustion ramjet array under the center of gravity and half-cone exhaust outlet at the back, fore mounted canards, cockpit/payload area top front and mid section and one or more tailplanes at the top back. Flight profile comprising runway takeoff, high subsonic climb up to 65,000 feet, alternatively full power climb from zero to 65,000 feet, with progressive acceleration from there up to Mach 24 @ required orbital altitude. Able to intercept missiles from early through post-boost phase from chosen orbit or suborbital arc, to intercept aircraft and to interdict surface targets. Winged dynamic soaring capability in reentry followed by powered runway landing.
    Type: Grant
    Filed: September 2, 1997
    Date of Patent: July 10, 2007
    Inventor: Andrew James Towne
  • Patent number: 7229048
    Abstract: A hypersonic vehicle having in one or more embodiments a control surface that is movable to a deployed position. The control surface is movable in a pivotal manner that establishes a gap between the leading edge of the control surface and the outer surface of the vehicle to provide a flow path. The gap allows a boundary layer along the outer surface of the vehicle to pass through the flow path with out separation from the outer surface, to further improve the effectiveness of the control surface.
    Type: Grant
    Filed: November 30, 2005
    Date of Patent: June 12, 2007
    Assignee: The Boeing Company
    Inventor: Henry August