Patent application number | Description | Published |
20130206926 | AIRCRAFT ELECTRICAL CABLE RACEWAY - An electrical cable raceway for an aircraft, the electrical cable raceway being formed at least in part from a ceramic material. | 08-15-2013 |
20130209764 | COMPOSITE LAMINATE WITH SELF-HEALING LAYER - A composite structure comprising: a first stack comprising a plurality of plies of composite material and at least one ply of self-healing material, the ply of self-healing material comprising a plurality of containers each containing a curable healing liquid; and a second stack comprising a plurality of plies of composite material, the stacks being joined together at a bond line. By placing a ply of self-healing material in one of the stacks (preferably relatively close to the bond line) the ply of self-healing material can resist the propagation of cracks between the first stack and the second stack. Preferably the global strength of the first stack is greater than the global strength of the second stack. | 08-15-2013 |
20130209854 | BATTERY CASE - A battery case for a power tool, comprising a body defining a cavity configured to receive a battery, a body surface of the battery case being formed to have a curved outward profile. | 08-15-2013 |
20130214100 | CLAMP BLOCK ASSEMBLY - A clamp block assembly for securing hydraulic pipes, the clamp block assembly comprising one or more unitary clamp blocks of deformable material each having a through hole for receiving a respective pipe, and a clamp adapted to apply a predetermined load around the clamp block(s). | 08-22-2013 |
20130220024 | TEST APPARATUS FOR PROVIDING AXIAL STRESSES IN A STRUCTURE - The invention provides a test apparatus for providing axial stresses in a structure, comprising a first set of formations for abutting a first surface of the structure at a first plurality of locations, a second set of formations for abutting a second surface of the structure at a second plurality of locations, and a force actuator, and wherein each set of formations comprises at least three formations and wherein at least two formations in each set of formations are aligned with a notional alignment line along the structure and at least one formation in each set of formations is out of alignment along the structure with said notional alignment line, such that when the force actuator applies a force, loads are applied at different locations, causing the structure to bend biaxially and thereby providing biaxial stresses in the structure. | 08-29-2013 |
20130220124 | FILTER FOR A PIPE - The invention provides a filter for a pipe, the filter comprising an attachment portion for attaching to the pipe, and a filter surface for presentation to and filtering of an oncoming flow of the pipe, wherein the filter surface has at least one pointed apex for protruding into the oncoming flow. The invention also provides a pipe for transporting an oncoming flow, wherein the pipe is provided with a filter surface across the cross-sectional area of the pipe and wherein the filter surface has at least one pointed apex protruding along the longitudinal axis of the pipe. The invention also provides an aircraft with such a filter or pipe and a method of filtering an oncoming flow of a pipe. | 08-29-2013 |
20130264002 | INTEGRAL STIFFENER - An integral composite wing spar ( | 10-10-2013 |
20130269421 | SENSOR DEVICE AND METHOD FOR COMMUNICATING WITH SENSOR DEVICES - A sensor device for a fuel system, the sensor device comprising sensing means configured to sense a property of fuel within the fuel system, and transmitting means configured to wirelessly transmit a signal representative of the sensed fuel property to a remote receiver. Also a sensor device comprising a photo-diode which is operable to function as an antenna or part of an antenna for the device. Also a method for communicating with a plurality of sensor devices. | 10-17-2013 |
20130320141 | SEAL ASSEMBLY FOR AN AIRCRAFT WING - A wing assembly for an aircraft comprising a spar, a wing cover and a rib; wherein the spar has a web portion and a flange portion joined by a radius corner; wherein a gap is formed at an interface between the spar, the wing cover and the rib; wherein the assembly further comprises a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap. Also a method for sealing a gap in an aircraft wing assembly. | 12-05-2013 |