Patent application number | Description | Published |
20080272236 | SPACE FRAME FUSELAGE STRUCTURE AND RELATED METHODS - An aircraft for carrying cargo in one or more containers. The aircraft includes a fuselage structure having a plurality of nodes and a plurality of elements connecting the nodes to form a space frame in which to carry cargo. At least some of the nodes are positioned in the space frame based on dimensions of the one or more containers. The fuselage structure is more compact, lighter and less expensive compared to conventional semi-monocoque fuselages. | 11-06-2008 |
20080308142 | SOLAR COLLECTOR DEVICES AND METHODS OF ASSEMBLY - In one embodiment, a method of assembling optical elements is provided. At least a portion of each optical element is disposed against at least a portion of a high precision surface. A structural frame is disposed adjacent the optical elements. At least two portions of the structural frame are aligned relative to each other and to the high precision surface with high precision. Adhesive is applied to adhere the structural frame to the optical elements. The adhesive is cured. In other embodiments, optical element assemblies are provided. | 12-18-2008 |
20080308152 | SOLAR COLLECTOR WITH ANGLED COOLING FINS - In one embodiment, a solar collector includes a heat pipe and at least one cooling fin. The at least one cooling fin is attached to the heat pipe at a non-perpendicular first angle relative to the heat pipe. In further embodiments, methods of transferring heat are disclosed, in addition to methods of manufacturing solar collectors. | 12-18-2008 |
20080308153 | RESTRAINED SOLAR COLLECTOR AND METHOD - In one embodiment, a solar collector comprises a solar cell attached with a heat exchanger, and a restraining member attached to the heat exchanger. The restraining member at least partly restrains the heat exchanger when heated. In further embodiments, restraining members and methods are disclosed for at least partly restraining the thermal expansion of a solar collector. | 12-18-2008 |
20090025712 | STRUCTURALLY ISOLATED THERMAL INTERFACE - In one embodiment, an assembly having bodies of different thermal expansion rates comprises a first body, a second body having a different thermal expansion rate than the first body, and a plurality of high conductivity members attached to both the first and second bodies. The high conductivity members are more flexible than the first and second bodies in order to allow for varied thermal expansion of the first and second bodies. The assembly may comprise a solar collector assembly, wherein the first body is a solar cell attached to a substrate, and the second body is a heat sink. | 01-29-2009 |
20090236473 | PROVIDING SKINS FOR AIRCRAFT FUSELAGES - An aircraft including a space frame fuselage structure. A plurality of panels are connected with the structure and configured to form a skin over the structure. The panels are movable relative to one another so as to prevent loading of the structure from inducing loading in the skin. | 09-24-2009 |
20100275972 | Enclosed, Off-axis Solar Concentrator - A solar concentrator including a housing having a receiving wall, a reflecting wall and at least two end walls, the receiving, reflecting and end walls defining a three-dimensional volume having an inlet, wherein a vertical axis of the housing is generally perpendicular to the inlet, a receiver mounted on the receiving wall of the housing, the receiver including at least one photovoltaic cell, wherein a vertical axis of the receiver is disposed at a non-zero angle relative to the vertical axis of the housing, at least one clip disposed on the reflecting wall, an optical element received within the three-dimensional volume, the optical element including at least one tab, the tab being engaged by the clip to align the optical element with the receiver, and a window received over the inlet to enclose the housing. | 11-04-2010 |
20110017876 | Shape-Changing Control Surface - A method and apparatus for controlling the shape of a control surface. A structure is rotated about an axis. The structure is located between a flexible skin and a skin located substantially opposite of the flexible skin. An assembly is moved to change the shape of the control surface in response to a rotation of the structure. The assembly is movably connected to the structure and is configured to move such that the flexible skin forms a plurality of curvatures. | 01-27-2011 |
20110226232 | Solar Energy System With Wind Vane - A solar energy system including a pedestal defining a longitudinal axis, a frame that is supported by the pedestal and that is rotateable relative to the pedestal about the longitudinal axis, the frame including at least one solar device, and a wind vane operatively connected to the frame to urge the frame relative to the pedestal about the longitudinal axis in response to wind acting on the wind vane. | 09-22-2011 |
20130227952 | SANDWICH STRUCTURE WITH SHEAR STIFFNESS BETWEEN SKINS AND COMPLIANCE IN THE THICKNESS DIRECTION - A sandwich structure includes a first skin, a second skin, a first hinge member, and a second hinge member. The first hinge member may be movably coupled to the first skin and a first skin joint. The second hinge member may be movably coupled to the second skin and second skin joint. The first hinge member and the second member may be movably coupled to one another and a member joint located between the first and second skin joint. | 09-05-2013 |
20140298635 | PRELOADING A FASTENER OF A MECHANICAL FITTING - A system for preloading a fastener of a mechanical fitting includes a strain measuring device to measure a strain on the fastener as the fastener is tightened. The mechanical fitting may include a base structure and a plate member. A support structure supports the plate member at a predetermined spacing from the base structure. The support structure may include a first sloping plate and a second sloping plate each extending between the plate member and the base structure. The fastener extends through a first hole in the plate member and a second hole in the base structure. The fastener is accessible through an opening on each side of the support structure. At least a portion of the strain measuring device is positioned relative to the fastener through a first opening of the openings to measure the strain on the fastener correlating to the preload as the fastener is tightened. | 10-09-2014 |