With Shield Or Other Protective Means (e.g., Meteorite Shield, Insulation, Radiation/plasma Shield) Patents (Class 244/171.7)
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Patent number: 7484690Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™)(10) includes 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: GrantFiled: January 10, 2007Date of Patent: February 3, 2009Assignee: Iostar CorporationInventors: Robert F. D'Ausilio, James R. Stuart, Roger X. Lenard, Franklin H. Williams, Jr.
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Patent number: 7484691Abstract: There is provided a radiation shield device for providing radiation protection to an area, such as a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The magnetic field generator preferably comprises at least one trapezoidal portion to provide substantially isotropic protection to the area. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device may also be provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator.Type: GrantFiled: June 30, 2005Date of Patent: February 3, 2009Assignee: The Boeing CompanyInventor: Gary A. Kinstler
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Patent number: 7464901Abstract: There is provided a radiation shield device for providing radiation protection to an area, such as a manned vehicle. The radiation shield device comprises a magnetic field generator, such as a solenoid, of superconductive material that provides a magnetic field around the area to shield the area from radiation. The solenoid preferably defines an axial length that is substantially smaller than a diameter of the solenoid. A thermal control system, comprising a limited amount of coolant or a refrigeration cycle, is included to control a temperature of the superconductive material during operation of the magnetic field generator. A magnetic shield device is also provided between the magnetic field generator and the area to be shielded from radiation to substantially shield the area from the magnetic field generated by the magnetic field generator.Type: GrantFiled: January 28, 2005Date of Patent: December 16, 2008Assignee: The Boeing CompanyInventor: Gary A. Kinstler
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Patent number: 7464900Abstract: A folding, retractable dome for protecting a feature, such as a docking mechanism, a hatch or other equipment at an exterior surface of a space vehicle, includes a plurality of arcuate ribs, each having opposite ends respectively pinioned at opposite sides of the feature at the surface of the vehicle for rotational movement about an axis of rotation extending through the opposite ends and through an arcuate path of revolution extending over the feature, and a flexible cover attached to each of the ribs such that, in a deployed configuration of the dome, in which adjacent ribs are rotated apart from each other at a maximum relative angle therebetween, the cover is stretched generally tangentially between the adjacent ribs to form a generally arcuate shield over the feature, and in a retracted position of the dome, in which adjacent ribs are rotated together at a minimum relative angle therebetween, the cover is collapsed to define folded pleats between the adjacent ribs.Type: GrantFiled: October 20, 2004Date of Patent: December 16, 2008Assignee: The Boeing CompanyInventors: Paul R. Clark, Ross H. Messinger
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Patent number: 7461818Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™)(10) includes 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 fully deployed spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.Type: GrantFiled: February 7, 2007Date of Patent: December 9, 2008Assignee: Iostar CorporationInventors: Robert F. D'Ausilio, Roger X. Lenard, James R. Stuart, Franklin H. Williams, Jr.
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Patent number: 7401752Abstract: A protective shield assembly capable of being deployed from a launch vehicle is provided, and methods for assembling and deploying the protective shield assembly are also provided. The protective shield assembly includes a shroud, and a flexible sheet of material within the shroud. The flexible sheet of material is capable of substantially conforming to a contour of at least a portion of the launch vehicle to provide a protective barrier.Type: GrantFiled: September 14, 2004Date of Patent: July 22, 2008Assignee: The Boeing CompanyInventors: Mark Andrew Lundgren, Henry K. Shu, Carl Frederick Dadson
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Patent number: 7381459Abstract: A composite thermal protection structure, for applications such as atmospheric re-entry vehicles, that can withstand temperatures as high as 3600° F. The structure includes an exposed surface cap having a specially formulated coating, an insulator base adjacent to the cap with another specially formulated coating, and one or more pins that extend from the cap through the insulator base to tie the cap and base together, through ceramic bonding and mechanical attachment. The cap and insulator base have corresponding depressions and projections that mate and allow for differences in thermal expansion of the cap and base.Type: GrantFiled: February 12, 2004Date of Patent: June 3, 2008Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration (NASA)Inventors: David A. Stewart, Daniel B. Leiser
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Patent number: 7377469Abstract: The invention discloses systems for mounting heat shields onto a spacecraft. It shows a number of ways to attach heat shield tiles in a way that allows for and accommodates the thermal expansion and contraction of the tiles without overstressing them and without loosing them due to delamination of adhesives. Shown also are various fasteners, which are flexible in several directions and which should preferably be oriented to provide the least resistance to the expected deformations of the tiles.Type: GrantFiled: November 12, 2004Date of Patent: May 27, 2008Inventor: Gabe Cherian
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Publication number: 20080078884Abstract: An apparatus for heat shielding and deceleration of a spacecraft comprises an unfoldable shield of individual panels made of a high temperature resistant fiber reinforced ceramic and pivotally mounted on the outer structure of the spacecraft. An unfolding ring slides axially along the body of the spacecraft. The panels are pivotally connected to the unfolding ring by compression struts acting as toggle levers. Tension springs pull the unfolding ring axially along the spacecraft body to toggle out the compression struts so as to outwardly pivotally deploy the panels. The unfoldable shield can be arranged on the forward end or the rear end of the spacecraft relative to its flight direction upon entry into the atmosphere.Type: ApplicationFiled: September 20, 2007Publication date: April 3, 2008Inventors: Ulrich Trabandt, Manfred Schmid
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Publication number: 20080048069Abstract: The present invention relates to a vibration attenuation/isolation device. An implementation of the invention provides an improved whole-spacecraft vibration attenuation/isolation by separating the vibration load on the spacecraft that arise from the launch vehicle and fairing into longitudinal and lateral components, and effectively attenuates and/or isolates those components. The invention also provides a general method for reducing vibrations in an assembly by using a vibration control device that separates the vibrational forces into perpendicular components that can be separately damped or attenuated.Type: ApplicationFiled: November 16, 2006Publication date: February 28, 2008Inventors: Gangtie Zheng, Likun Liu, Lu Liang, Ling He
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Patent number: 7309049Abstract: An orbital debris shield for protecting the hull of a spacecraft. The shield is comprised of a number of flexible and releasably attached gores that substantially cover the hull. Interleafed between layers of the gores are layers of a spacing material. As debris collides with the gores, the material is shocked and breaks up to some degree. As the shocked debris disperses through a layer of the gore, the spacing material interacts with the debris. After dispersing through a number of layers of the gores and the spacing material, the debris transfers a significant portion of kinetic energy and the probability of the remaining particles piercing the hull is significantly decreased.Type: GrantFiled: August 3, 2006Date of Patent: December 18, 2007Assignee: Bigelow AerospaceInventor: Robert T. Bigelow
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Patent number: 7296769Abstract: A cryogenic fuel tank assembly 10 is provided comprising a cryogenic fuel tank wall 22. A foam assembly 24 is affixed to the cryogenic fuel tank wall 22, the foam assembly 24 having an inner surface 30 and an outer surface 32. A first solid film 40 bonded to the outer surface 32 to provide a uniform outer bonding surface 42. A thermal protection system assembly 38 is bonded to the uniform outer bonding surface 42.Type: GrantFiled: October 11, 2003Date of Patent: November 20, 2007Assignee: The Boeing CompanyInventors: Peter A. Hogenson, Keith Chong, Peter Duong
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Patent number: 7281688Abstract: A self-transpiring hot skin for a hypersonic or reusable space vehicle that can provide protection to the vehicle during short periods of abnormally high heat flux (either planned in the flight profile or an off-nominal event). The hot skin includes a ceramic composite structure having an internal cavity that is coupled either to the insulating layer or directly to the support structure of the hypersonic vehicle. The internal cavity includes a material system that vaporizes, sublimes or decomposes into a gas when the temperature exceeds the upper temperature capability of the composite material. The gas transpires through the outer layer of the composite material to provide cooling to the outer layer below the upper temperature capability. Cooling may occur both by conduction of heat from the composite material to the transpiring gas and by the interaction of the transpiring gas with the boundary layer of hypersonic flow over the outer surface, leading to a reduction of the heat flux entering the surface.Type: GrantFiled: April 27, 2006Date of Patent: October 16, 2007Assignee: The Boeing CompanyInventors: Brian Nelson Cox, Janet B. Davis, Julia Mack, David Bruce Marshall, Peter E. Morgan, Olivier H. Sudre
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Patent number: 7278609Abstract: A nose cap and control strut assembly for supersonic aircraft is disclosed. In one embodiment, the nose cap extends forward from the nose of the aircraft to deflect shock waves and decrease draft during supersonic flight. In another embodiment, control struts extending from the nose of the aircraft have control surfaces which provide yaw and pitch control for the aircraft. The control struts may be rotatable around axes substantially parallel with the longitudinal axis of the aircraft. The control struts may also be retractable into the aircraft. The nose cap may be mounted at the forward ends of the control struts in such a manner that the nose cap remains in a stationary position with respect to the aircraft when the control struts are rotated.Type: GrantFiled: August 5, 2005Date of Patent: October 9, 2007Assignee: Northrop Grumman CorporationInventor: Allen A. Arata
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Patent number: 7275720Abstract: An apparatus and method for thermal protection is provided. A thermal protection apparatus includes a porous layer attached to an inner structural member requiring thermal protection. The porous layer serves as both a cooling air plenum and a transpiring medium. The porous layer may include a low strength ceramic foam layer. Thermal protection may be achieved by flowing cooling air the length of the porous layer. The voids in the porous layer may be sized to less than 50 ?m, producing uniquely efficient thermal protection due to micro-fluidic effects in the air flowing through the layer. A semi-permeable layer may be attached to the outer surface of the porous layer. The semi-permeable layer may prevent erosion of the porous layer and may transform the porous layer into a plenum by making the majority of the cooling air flow the length of the porous layer before exiting through small holes drilled or punched through the semi-permeable layer.Type: GrantFiled: June 9, 2003Date of Patent: October 2, 2007Assignee: The Boeing CompanyInventors: William W. Behrens, Andrew R. Tucker, Gayl J. Miller
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Patent number: 7270301Abstract: Optical surface reflector, for a spacecraft such as a geostationary satellite. The exterior surface (10) of the reflector comprises a plurality of facets (14) inclined to each other and to the interior surface (12) of the reflector. The facets (14) advantageously form a pyramid with a square base in which the angle at the apex is equal to 90°. However, other arrangements are possible without departing from the scope of the invention. The invention increases radiative capacity without significantly increasing mass and overall size.Type: GrantFiled: September 30, 2002Date of Patent: September 18, 2007Assignee: ThalesInventor: Gilles Maurel
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Patent number: 7219859Abstract: A reentry vehicle includes a nose section, a modular section comprised of two or more connected modules, a flared section. The nose section is connected to a first end of the modular section, and the flared section is positioned proximate a second end of the modular cylindrical section.Type: GrantFiled: April 1, 2005Date of Patent: May 22, 2007Assignee: Spacehab, IncorporatedInventors: Michael D. Johnson, James D. Baker, Frank T. Eichstadt, Michael E. Bain
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Patent number: 7216833Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10). 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: GrantFiled: December 15, 2003Date of Patent: May 15, 2007Assignee: Iostar CorporationInventors: Robert F. D'Ausilio, Bari M. Southard, James R. Stuart, Franklin H. Williams, Jr.
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Patent number: 7198231Abstract: A method of forming ablative insulation coatings on aerospace structures and articles produced thereby. The method includes forming a mold having a cavity configured to complementarily receive at least a portion of the structure and directly molding the ablative coating to a surface of the structure by introducing a prepared ablative mixture, such as an epoxy resin, into the mold. The process may desirably include curing at atmospheric pressures to reduce the expense and equipment required in carrying out the process. The method of applying the ablative coating further includes features such as varying the thickness of the ablative coating from one portion of the component to another. Control of the thickness may be effected through use of spacers embedded into the ablative coating and formed of the same or similar material previously cured prior to placement in the mold.Type: GrantFiled: March 28, 2005Date of Patent: April 3, 2007Assignee: Alliant Techsystems, Inc.Inventors: Bradford P. Packer, Roy E. Bronson, Russell Montgomery, Roger D. Holstein
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Patent number: 7159824Abstract: A device for verifying the calibration of an infrared sensor includes a body configured to be placed in orbit. The body defines a spin axis and an outer surface. The outer surface has an infrared radiant intensity that is substantially independent of the viewing angle between the spin axis of the body and the infrared sensor. The device may be used for on-orbit verification of the calibration coefficients associated with each pixel of an infrared sensor, including linearity calibration and verification of the resolution capability of the sensor. The calibration coefficients may be verified over the entire sensing capability range of the infrared sensor. After a thermal model of the device is developed, the device operates passively and provides a known source of infrared radiation observable during the device's entire orbital lifetime. The device may be designed to automatically de-orbit from space after a predictable time in orbit.Type: GrantFiled: September 4, 2003Date of Patent: January 9, 2007Assignee: Analex CorporationInventors: David W. Geyer, Russell Shea Ferring, Richard D. Nielsen
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Patent number: 7093799Abstract: A guided missile having a longitudinally extending airframe with a tip, a seeker head arranged in the tip and a window located in front of the seeker head for closing the airframe at the tip so as to protect the seeker head. A jettisonable protective cap consisting of at least two separable parts is attached to the airframe in front of the window for protection of the window.Type: GrantFiled: August 5, 2003Date of Patent: August 22, 2006Assignee: Bodenseewerk Gerätetechnik GmbHInventors: Bernd Dulat, Hubert Kuppel, Wolgang Grosshardt, Alexander Stengele, Jens Wallrabe
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Patent number: 7070151Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) 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: GrantFiled: January 9, 2004Date of Patent: July 4, 2006Assignee: IOSTAR CorporationInventors: Robert F. D'Ausilio, Roger X. Lenard, Chauncey W. Uphoff, Franklin H. Williams, Jr.
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Patent number: 6974109Abstract: The present invention provides a sealing and restraint apparatus to establish a pressure boundary for inflatable or expandable spacecraft. The apparatus is capable of connecting the flexible pressure boundary of an inflatable spacecraft to the rigid structure of the spacecraft. The flexible pressure boundary of the present invention comprises a gas membrane and a restraint layer. The gas membrane minimizes air leakage. The restraint layer carries the forces created by the internal pressurization of the spacecraft. This apparatus provides a hermetic seal and the structural integrity necessary to resist internal pressurization forces.Type: GrantFiled: January 31, 2001Date of Patent: December 13, 2005Assignee: Bigelow AerospaceInventors: John Mezits, Russell J. Common, John A. Rusi