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| Application No. | Application Title | Issue Date |
| 20120012711 | DUAL EVOLVED EXPENDABLE LAUNCH VEHICLE (EELV) SECONDARY PAYLOAD ADAPTOR (ESPA) PORT SMALL SATELLITE DESIGN An apparatus and method are disclosed for dual Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) port small satellite designs. The apparatus and method provide payload volume for larger satellites. In one or more embodiments, the apparatus and me... | 01/19/2012 |
| 20110309200 | Apparatus, Satellite and Method for Trapping High-Speed Particles An apparatus for trapping high-speed particles, such as space debris, is provided. The apparatus includes a first front tapping surface and at least one rear trapping surface. The front and rear trapping surfaces are arranged substantially parallel to each other and are... | 12/22/2011 |
| 20110210209 | SELF DEPLOYING SOLAR ARRAY A deployable structure that may include a slit-tube longeron and a flat panel coupled with the slit-tube longeron. The slit-tube longeron may include a tubular member having a slit that runs along the longitudinal length of the slit-tube longeron. The deployable structu... | 09/01/2011 |
| 20110011983 | MULTIJUNCTION PHOTOVOLTAIC CELL GROWN ON HIGH-MISCUT-ANGLE SUBSTRATE The present invention provides a photovoltaic cell comprising a GaInP subcell comprising a disordered group-III sublattice, a Ga(In)As subcell disposed below the GaInP subcell, and a Ge substrate disposed below the Ga(In)As subcell comprising a surface misoriented from ... | 01/20/2011 |
| 20100187365 | CRYOGENIC PROPELLANT DEPOT AND DEPLOYABLE SUNSHIELD A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solu... | 07/29/2010 |
| 20100116942 | HIGH-EFFICIENCY SOLAR CELL STRUCTURES Solar cells include a substrate consisting essentially of silicon, a first junction disposed over the substrate, the first junction comprising at least one III-V material and having a threading dislocation density of less than approximately 107 cm−2 05/13/2010 | |
| 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 place... | 12/10/2009 |
| 20090250555 | Solar Powered Excess Electron Emission Device The chassis of a spacecraft has one side exposed to ultraviolet photons and another side shielded from the ultraviolet photons. An electrically conductive surface is disposed on the exposed side of the chassis and is electrically isolated from the chassis. A field-emiss... | 10/08/2009 |
| 20090230250 | SOLAR ARRAY MOMENTUM CONTROL One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The s... | 09/17/2009 |
| 20090224105 | Satellites and Satellite Fleet Implementation Methods and Apparatus A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separat... | 09/10/2009 |
| 20090173831 | Method for manufacturing a solar module in orbit A geosynchronous Solar Power Satellite System is created by an artificial gravity, closed ecology, multiple use structure in low earth orbit that manufactures modular solar power panels and transmitter arrays. This facility takes empty fuel tanks and expended rocket boo... | 07/09/2009 |
| 20090145476 | ISOELECTRONIC SURFACTANT SUPPRESSION OF THREADING DISLOCATIONS IN METAMORPHIC EPITAXIAL LAYERS A method of reducing propagation of threading dislocations into active areas of an optoelectronic device having a III-V material system includes growing a metamorphic buffer region in the presence of an isoelectronic surfactant. A first buffer layer may be lattice match... | 06/11/2009 |
| 20090101758 | FORMATION FLIGHT DEVICE INTENDED FOR A SOLAR CORONAGRAPHY MISSION The present invention relates to a device making it possible to study the solar corona on a space mission requiring the formation flight of two satellites: an occulting satellite (OCC), the role of which is to create an artificial eclipse of the sun from the point of vi... | 04/23/2009 |
| 20080272240 | Active vibration damping (AVD) system for precision pointing spacecraft An active vibration damping (AVD) control system for spacecraft provides a simple-to-implement and robust formulation that provides a novel damping control method for reducing spacecraft structural vibrations and improving antenna and instrument pointing. The AVD contro... | 11/06/2008 |
| 20080237399 | SATELLITES AND SATELLITE FLEET IMPLEMENTATION METHODS AND APPARATUS A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separat... | 10/02/2008 |
| 20080078885 | Canted solar array and method for using same A method and apparatus for deploying a fixed and canted solar array of a satellite. The solar array is rotated in a first plane and about a first axis from a stowed position to a first position, rotated about a second axis orthogonal to the first axis from the first pos... | 04/03/2008 |
