| Patent application number | Description | Published |
|---|
| 20100043450 | SYSTEM FOR ATTACHING AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT, SUCH AS A SAIL WING AIRCRAFT - System for attaching an engine to the structure of an aircraft, such as a sail wing aircraft. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure. The upper beam is in addition firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft ( | 02-25-2010 |
| 20100108802 | SAIL WING AIRCRAFT WHICH INCLUDES AN ENGINE MOUNTED ON A PYLON - Sail wing aircraft which includes a wing ( | 05-06-2010 |
| 20110036942 | ENGINE ATTACHMENT PYLON COMPRISING MEANS OF FASTENING SPARS AND PANELS LOCATED OUTSIDE THE INNER SPACE IN THE BOX - An engine attachment pylon for an aircraft including a rigid structure including a box including an upper spar and a lower spar, connected to each other through two lateral panels. At least one of the upper and lower ends of the web of at least one of the two lateral panels includes at least one assembly cleat projecting sideways from the web towards the outside of the box, and assembled to the spar on which it bears through an attachment mechanism located outside the inner space in the box. | 02-17-2011 |
| 20110036943 | AIRCRAFT ENGINE ATTACHMENT PYLON COMPRISING A BOX WITH A CIRCULAR OR ELLIPTICAL SHAPED SECTION - An engine attachment pylon for an aircraft, including a rigid structure including a box formed by one or plural hollow segments. The section of at least one hollow segment is circular or elliptical in shape. | 02-17-2011 |
| 20110290935 | METHOD OF MANUFACTURE BY SUPERPLASTIC FORMING AND BY FISHPLATING OF A RIB FOR AN AERODYNAMIC FAIRING OF AN AIRCRAFT ENGINE MOUNTING PYLON - The present invention relates to a method of manufacture of a stiffening transverse internal rib for an aerodynamic fairing of an engine mounting device, including:
| 12-01-2011 |
| 20110290936 | METHOD OF MANUFACTURE BY SUPERPLASTIC FORMING AND BY FISHPLATING OF A RIB FOR AN AERODYNAMIC FAIRING OF AN AIRCRAFT ENGINE MOUNTING PYLON - The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs ( | 12-01-2011 |
| 20130174572 | METHOD FOR COOLING A THERMAL PROTECTION FLOOR OF AN AFT AERODYNAMIC FAIRING OF A STRUCTURE FOR MOUNTING AN AIRCRAFT PROPULSION SYSTEM - A propulsion system for an aircraft, including a dual-flow turbojet and a mounting structure for mounting this turbojet on the wing surface or on the fuselage of an aircraft. The mounting structure includes an aft aerodynamic fairing including a thermal protection floor to protect the mounting structure from the heat of a primary airstream channelled by an exhaust nozzle of the turbojet, as well as an air inlet provided in a longitudinal aerodynamic wall washed by a secondary airstream of the turbojet and delimiting together with an other similar wall a cavity isolated from the secondary airstream for extracting a cooling airstream from the secondary airstream, and air circulation means fed by the air inlet and having at least one outlet aperture emerging in a space between the thermal protection floor and the exhaust nozzle. | 07-11-2013 |
| 20130320135 | AFT AERODYNAMIC FAIRING WITH IMPROVED THERMAL RESISTANCE FOR A PYLON FOR ATTACHING AN AIRCRAFT PROPELLING ASSEMBLY - An aft aerodynamic fairing for a pylon for attaching an aircraft propelling assembly, including a caisson structure, a heat-shield floor, as well as a support structure for this floor comprising linking parts arranged to link two side edges of this floor to the caisson structure. The linking parts of each side edge of the floor are configured so as to allow travelling motion of the side edge relative to the caisson structure in a corresponding direction included in a plane orthogonal to a longitudinal direction of the fairing. The linking parts form a sliding link between the floor and the caisson structure, reducing the stresses induced by the deformations of these elements in use. | 12-05-2013 |
