Search Patents
  • Publication number: 20170225362
    Abstract: A hybrid mold includes (a) an Invar® eggcrate structure, (b) an Invar® interim working surface and (c) a CF composite material overlay. The eggcrate and interim working surface are welded or otherwise connected together to form a unitary base mold. The CF overlay is bonded to the interim working surface. The CF overlay is easily reconfigurable and can be replaced without destroying the integrity of the base mold.
    Type: Application
    Filed: January 11, 2017
    Publication date: August 10, 2017
    Applicant: Ascent Aerospace, LLC
    Inventors: Jerry Anthony, Michael Fox, Zachary Skelton, Daniel Brennan, Randel Dean Moruzzi, JR.
  • Publication number: 20190358860
    Abstract: A hybrid mold includes (a) an Invar® eggcrate structure, (b) an Invar® interim working surface and (c) a CF composite material overlay. The eggcrate and interim working surface are welded or otherwise connected together to form a unitary base mold. The CF overlay is bonded to the interim working surface. The CF overlay is easily reconfigurable and can be replaced without destroying the integrity of the base mold.
    Type: Application
    Filed: May 23, 2019
    Publication date: November 28, 2019
    Applicant: Ascent Aerospace, LLC
    Inventors: Parme G, Anthony, Michael Fox, Zachary Skelton, Daniel Brennan, Randel Dean Moruzzi, JR.
  • Patent number: 10427330
    Abstract: A hybrid mold includes (a) an Invar® eggcrate structure, (b) an Invar® interim working surface and (c) a CF composite material overlay. The eggcrate and interim working surface are welded or otherwise connected together to form a unitary base mold. The CF overlay is bonded to the interim working surface. The CF overlay is easily reconfigurable and can be replaced without destroying the integrity of the base mold.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: October 1, 2019
    Assignee: Ascent Aerospace, LLC
    Inventors: Parme G. Anthony, Michael Fox, Zachary Skelton, Daniel Brennan, Randel Dean Moruzzi, Jr.
  • Patent number: 10596730
    Abstract: A hybrid mold includes (a) an Invar® eggcrate structure, (b) an Invar® interim working surface and (c) a CF composite material overlay. The eggcrate and interim working surface are welded or otherwise connected together to form a unitary base mold. The CF overlay is bonded to the interim working surface. The CF overlay is easily reconfigurable and can be replaced without destroying the integrity of the base mold.
    Type: Grant
    Filed: May 23, 2019
    Date of Patent: March 24, 2020
    Assignee: Ascent Aerospace, LLC
    Inventors: Parme G. Anthony, Michael Fox, Zachary Skelton, Daniel Brennan, Randel Dean Moruzzi, Jr.
  • Patent number: 10532819
    Abstract: Apparatus and methods for supporting human external cargo from the hoist of a hoist-equipped helicopter are provided. The apparatus has at least one personal harness for supporting a user; and at least one harness segment with a top end point attachable to the helicopter hoist through an attachable fitting and at least one bottom end point directly or indirectly attachable to the personal harness. The harness segment, and the personal harness externally support the user from the helicopter hoist and allows the user to be safely suspended from the helicopter in order for work or rescue operations to be administered by the user.
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: January 14, 2020
    Assignee: Ascent Aerospace Ltd.
    Inventor: Trent Lemke
  • Publication number: 20170291296
    Abstract: The present invention provides a work piece processing system for operating on a work piece or at least one component of a work piece. The processing system includes a base system for transporting the at least one work piece component, at least one processing head for operating on the work piece component, and means for controlling, the means for controlling the processing system. In a first embodiment, the processing system further includes a support structure, the support structure including at least one frame member having a track. Here, the at least one processing head travels along the track. In a second embodiment, the processing system further includes a multi-linkage robotic arm, the robotic arm including a plurality of rotary joints and a plurality of arm segments interconnecting the rotary joints. Here, the at least one processing head is operably mounted to a free end of one of the plurality of arm segments.
    Type: Application
    Filed: April 12, 2017
    Publication date: October 12, 2017
    Applicant: Ascent Aerospace
    Inventor: Mark W. Brown
  • Patent number: 9358668
    Abstract: A jet receiving receptacle is provided which is coupleable to a high-pressure fluid jet system opposite a nozzle thereof to receive a fluid jet discharged from the nozzle after it acts on a workpiece. The jet receiving receptacle may include an elongated inlet alignable with a direction of travel of the nozzle to receive the fluid jet in a deflected state. The jet receiving receptacle may further include a jet deflection device positioned downstream of the elongated inlet to redirect at least a portion of the fluid jet and a jet rebound device located upstream of the jet deflection device to be impinged on by the redirected portion of the fluid jet. The jet deflection device and jet rebound device may form, in combination with a housing, a device to trap the fluid jet. Fluid jet cutting systems incorporating a jet receiving receptacle and related methods are also provided.
    Type: Grant
    Filed: March 1, 2013
    Date of Patent: June 7, 2016
    Assignee: Ascent Aerospace, LLC
    Inventors: Mohamed A. Hashish, Eckhardt R. Ullrich, Michael Knaupp, Steven J. Craigen, Charles M. Brown, Bruce M. Schuman
  • Publication number: 20170129579
    Abstract: A system for elevation control. The system comprises a substantially gastight envelope containing lifting gas wherein the envelope further comprises a plurality of envelope segments in fluid communication with one another. At least one tension cable connects at least two of the envelope segments. A control device including a motor adjusts the length of the tension cable to change the pressure within the envelope to thereby facilitate ascent and descent of the system. The control device causes the system to operate in ascent, descent, or vertically stationary modes.
    Type: Application
    Filed: January 21, 2017
    Publication date: May 11, 2017
    Applicant: THIN RED LINE AEROSPACE LTD
    Inventor: Maxim de Jong
  • Patent number: 10196123
    Abstract: A system for elevation control. The system comprises a substantially gastight envelope containing lifting gas wherein the envelope further comprises a plurality of envelope segments in fluid communication with one another. At least one tension cable connects at least two of the envelope segments. A control device including a motor adjusts the length of the tension cable to change the pressure within the envelope to thereby facilitate ascent and descent of the system. The control device causes the system to operate in ascent, descent, or vertically stationary modes.
    Type: Grant
    Filed: January 21, 2017
    Date of Patent: February 5, 2019
    Assignee: THIN RED LINE AEROSPACE LTD
    Inventor: Maxim de Jong
  • Patent number: 6113032
    Abstract: A system is provided for delivering liquid propellant in a booster stage of a launch vehicle. The system includes an arrangement of tanks and valves to direct a first supply of liquid propellant during ascent of the booster stage and a second supply during descent of the booster stage. In disclosed embodiments, tanks may be arranged in series or parallel.
    Type: Grant
    Filed: February 25, 1998
    Date of Patent: September 5, 2000
    Assignee: Kistler Aerospace Corporation
    Inventors: David B. Cochran, Charles D. Limerick
  • Patent number: 6059234
    Abstract: A payload module couples to a forward end of a re-entry vehicle. The payload module includes a cap and a fairing to contain a payload during ascent of the vehicle and to withstand aerodynamic heating from the atmosphere upon re-entry of the vehicle. In a particular embodiment, the fairing has an extended position to contain the payload and a retracted position for re-entry into the atmosphere after payload deployment.
    Type: Grant
    Filed: February 25, 1998
    Date of Patent: May 9, 2000
    Assignee: Kistler Aerospace Corporation
    Inventors: George E. Mueller, David B. Cochran
  • Patent number: 7557753
    Abstract: A GPS tracker is disposed on launch hardware that separates from a spacecraft launch vehicle during ascent to orbit with the launch hardware having a suborbital trajectory from launch to impact while being tracked so as to track the launch hardware during suborbital flight, such as for tracking separated fuel stages, external tanks, external boosters, and payload fairings that return to earth.
    Type: Grant
    Filed: April 30, 2007
    Date of Patent: July 7, 2009
    Assignee: The Aerospace Corporation
    Inventor: William H. Ailor, III
  • Patent number: 10377500
    Abstract: To provide an electrified aircraft, and a method of controlling a regenerative electric power of the electrified aircraft where a path angle and a descending rate can be controlled with a good response independently from a speed while controlling the drag force of the propulsion drive system and where it is possible to maximize safely a generated electric power in each flight status at the time of descent or ascent. The electrified aircraft includes a propeller or a fan for propulsion; an electric drive motor for rotary-driving the propeller or the fan and for generating an electric power by the rotation of the propeller or the fan; and an estimation unit for estimating a drag force of the propeller or the fan or an electric power generation amount of the electric drive motor based on propulsion system parameters of the electric drive motor.
    Type: Grant
    Filed: March 12, 2015
    Date of Patent: August 13, 2019
    Assignee: Japan Aerospace Exploration Agency
    Inventors: Hiroshi Kobayashi, Akira Nishizawa, Tomoko Iijima, Takeshi Tagashira
  • Patent number: 4566699
    Abstract: A novel and improved heavier-than-air flying craft (20) is the subject matter of this patent application. The craft (20) includes an airfoil (22), over an upper wall (28) of which multiple fluid streams are directed. The craft (20) can include a multiplicity of main engines (54) for directing the fluid streams. Vertical ascent and horizontal translational flight can be controlled by modulating the flow of exhaust from these engines (54). The craft (20) can further include auxiliary engines (58) for facilitating horizontal translational flight and yaw control engines (56) to augment yawing of the craft (20). None of the engines (54, 56, 58) have moving parts, and the airfoil (22) has no moving parts in the external air stream.
    Type: Grant
    Filed: December 27, 1982
    Date of Patent: January 28, 1986
    Assignee: Richards Aerospace Research Corporation
    Inventor: Joseph R. Cucuzza
  • Publication number: 20100243816
    Abstract: 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. Produced energy is stored within craft oscillatory circuit and plasma vortices. When energy from craft capacitance system is depleting, energy can be obtained from craft inductance system from craft magnetic field. Said craft is capable of space flight, use as a submersible craft, boring device, or lifting device. Particle propulsion in space will be accomplished utilizing metal ions stored within craft capacitor plates. Said craft is opaque to electromagnetic radiation, and also absorbs radiation directed at craft. Said craft is capable of verticle ascent, descent and landing, and is lenticular in shape. Said aircraft can operate within earth radiation belts safely.
    Type: Application
    Filed: March 19, 2010
    Publication date: September 30, 2010
    Inventor: Gary Richard Gochnour
  • Patent number: 4473199
    Abstract: A one-man helicopter comprising a fuselage having a rotor shaft attached thereto but offset therefrom, rotor blades having rocket engines in the tips thereof, a hub on the shaft and means on the hub between the rotor blades and the rotor shaft to change the vertical displacement of the rotor blades, said means comprising a housing pivotable about a hinged joint; the outer portion of the housing is a swash plate which is rotatable about the rotor shaft, and linkages interconnect the swash plate and the rotor blades.
    Type: Grant
    Filed: January 26, 1984
    Date of Patent: September 25, 1984
    Assignee: Aerospace General Co.
    Inventor: Gilbert W. Magill
  • Publication number: 20050001100
    Abstract: A cryogenic fuel tank adapted for attachment to an aerospace vehicle includes an exterior layer of reinforced composite insulating foam. The insulating foam is reinforced with an aramid fiber mesh or a closed cell foam may be reinforced with one or more of carbon nanotubes, graphite whiskers, silicon carbide fibers or graphite fibers. The improved composite insulating structure disclosed herein provides a remedy for insulating material breaking off the large external fuel tank attached to the space shuttle during launch and ascent into space.
    Type: Application
    Filed: March 30, 2004
    Publication date: January 6, 2005
    Inventors: Kuang Hsi-Wu, Milton Torres
  • Publication number: 20170327249
    Abstract: 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.
    Type: Application
    Filed: November 3, 2016
    Publication date: November 16, 2017
    Inventors: Mark Featherstone, John Michael Sanders, Roger E. Ramsey, Eric David Wetzel
  • Publication number: 20140263841
    Abstract: 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.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Applicant: Blue Origin, LLC
    Inventors: Mark Featherstone, John Michael Sanders, Roger E. Ramsey, Eric David Wetzel
  • Patent number: 10266282
    Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods. 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.
    Type: Grant
    Filed: November 3, 2016
    Date of Patent: April 23, 2019
    Assignee: Blue Origin, LLC
    Inventors: Mark Featherstone, John Michael Sanders, Roger E. Ramsey, Eric David Wetzel
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