| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 073802000 | Aircraft structure | 12 |
| 20090090192 | Test Device - A test structure for dynamic seat tests comprises a load cell, a seat rail with a bar and a upper chord, a load transfer device, which comes into contact with opposite sides of the bar of the seat rail and is fixed to the load cell and an integrated floor plate which is fixed to the upper chord of the seat rail and to the load transfer device. | 04-09-2009 |
| 20090139341 | Apparatus for indicating loading in a structure having exceeded a predetermined threshold - Apparatus for indicating loading in a structure having exceeded a predetermined threshold is disclosed in which deformation of a structural element is identified by the torque required to rotate a gauge assembly integrated in the structure. | 06-04-2009 |
| 20090260449 | DEVICE FOR TEST LOADING - The present invention provides a device for test loading a fuselage barrel, in particular in the aviation and aerospace industry. The device comprises a first and a second pressure bulkhead for sealing the fuselage barrel at the end faces thereof in a pressure-tight manner. The device further comprises a support device which may be coupled to the first pressure bulkhead, on the one hand, and to the second pressure bulkhead, on the other hand, extending through the fuselage barrel. Moreover, the device comprises a loading device which may be coupled to the support device, on the one hand, and to a portion of the fuselage barrel, on the other hand, for introducing loads into the fuselage barrel. The resulting advantage is that gravitational force and/or acceleration forces acting on the masses arranged in the fuselage barrel, for example cargo, in particular during the flight phase may be simulated by means of components which are exclusively arranged within the fuselage barrel, which is pressurised during the test. Thus a provision of through-holes in the fuselage skin for passing through hydraulic cylinders and the sealing of said holes relative to the fuselage skin, as in the device known to the applicant, are avoided. | 10-22-2009 |
| 20100126281 | REINFORCED PANEL - A reinforced panel ( | 05-27-2010 |
| 20100186519 | APPARATUS FOR TESTING FUSELAGE PANELS - Gripping claws and pairs of arched angular profiles are arranged along the perimeter of a cylindrical surface segment so as to grip the edges of a fuselage panel, closing the opening of a pressurizable chamber. | 07-29-2010 |
| 20100313669 | METHOD OF DETERMINING OVERSPEED RELIABILITY - A method and system for determining the reliability of a rotating component compares a normalized stress curve with a normalized strength curve. The resulting overlap corresponds with the reliability of the rotating component. | 12-16-2010 |
| 20110107843 | ELECTRICAL CIRCUIT ASSEMBLIES AND STRUCTURAL COMPONENTS INCORPORATING SAME - A structural health monitoring arrangement includes a component formed of fibre reinforced composite material with a plurality of electrical conducting fibres intrinsic to the composite defining electrical paths that run through the composite. The paths act as sensing paths running through the material and a detector watches for changes in electrical property indicative of a structural event. The paths may be configured as an open or a closed node grid whose electrical continuity is monitored directly or indirectly. Alternatively they may be fibres having a piezoresistive property and the changes in resistance may be monitored. | 05-12-2011 |
| 20130192381 | MONITORING DEVICE FOR REPAIR PATCHES, REPAIR KIT, AND METHOD FOR MONITORING A REPAIR PATCH - A monitoring device for a repair patch that can be placed on or in a wall of an aircraft to repair a defect has a sensor device for detecting properties of the repair patch placed in the wall, an energy supply device for supplying energy at least to the sensor device, and a communication device so as to read out the sensor data. A repair kit that can be placed in or on a wall of an aircraft to repair defects comprises a repair patch for repairing a defect in or on a wall of an aircraft and also comprises a monitoring device. A method for monitoring a repair patch in or on a wall of an aircraft by means of a monitoring device comprises the steps of detecting a measurement phase on the basis of the amount of energy provided by the energy supply device, measuring load parameters in and/or on the repair patch during the measurement phase, and reading out the load parameters. | 08-01-2013 |
| 20130213141 | Method and an arrangement for purposes of determining an incidence of loading of an aircraft structure - A method and an arrangement to determine an incidence of loading of an aircraft structure. A true reality of at least one aircraft structural section is superposed with the virtual reality of the aircraft structural section, and any deviation is established by means of a comparison of the two realities; this deviation is evaluated with reference to its consequences in terms of the structural mechanics involved. | 08-22-2013 |
| 20140000381 | PLANKING PANEL FOR A STRUCTURAL COMPONENT, FLOW BODY COMPRISING SUCH A PLANKING PANEL AND DEVICE FOR MONITORING MATERIAL DAMAGE ON SUCH A PLANKING PANEL | 01-02-2014 |
| 20140318266 | FLIGHT CONTROL SYSTEM LOADING TEST APPARATUS AND METHOD - A flight control system loading test apparatus includes a surface-mounted sector, a cam profile sector, a dummy weight, and a cable. The surface-mounted sector attaches to an aircraft flight control system body such that the surface-mounted sector pivots along with the body about a pivot axis. The cam profile sector is configured to rotate about a rotational axis among a plurality of loading positions. The cam profile sector includes a profile surface having a plurality of curves. Each curve follows a different radius emanating from a respective axis substantially parallel to the rotational axis of the cam profile sector. The cable contacts the cam profile sector along the profile surface. An applied hinge moment using the dummy weight varies as the cam profile sector rotates about the rotational axis. | 10-30-2014 |
| 20150040679 | ACTIVE RESISTANCE DYNAMOMETER FOR WHEEL TESTING - A wheel testing system and method are provided that simulates realistically conditions likely to be encountered during operation of vehicle wheels, especially powered drive wheels and wheel-connected structures. The system may include an integral support frame designed to adjustably mount wheels or wheel-connected structures to be tested, a load motor drivingly connected to an inertial load, and an adjustable mounting sled configured to adjustably mount a test wheel or a wheel-connected structure with an hydraulic system actuatable to adjust the location of the test wheel relative to the inertial load to vary or fix the load on the test wheel desired. Speed of the test wheel can be varied or fixed by controlling the speed of the load motor. System measurement and data collection electronics measure a range of selected wheel parameters and gather data for transmission to a processor or non-transitory storage medium for processing and evaluation. | 02-12-2015 |
