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101.发明申请公开(公告)号：US20190161211A1
公开(公告)日：2019-05-30
申请号：US16197719
申请日：2018-11-21
摘要： An aircraft with a system for rearward mounting and dismounting an engine, the engine being placed inside the rear part of the aircraft when mounted. The system for rearward mounting and dismounting the engine comprises a first removable attachment device arranged to attach the engine to the fuselage in the rear part of the aircraft, internal supports fixed in the rear part of the aircraft, at least two longitudinal detachable rails, to be placed on the internal supports and under the engine, and a slider to attach to the engine via a second removable attachment device, to be placed on the longitudinal detachable rails.
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公开(公告)号：US20190152616A1
公开(公告)日：2019-05-23
申请号：US16197726
申请日：2018-11-21
发明人： Olivier PAUTIS , Eric BOUCHET , Olivier BARBARA
IPC分类号： B64D27/26
摘要： To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.
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公开(公告)号：US20190136941A1
公开(公告)日：2019-05-09
申请号：US15989200
申请日：2018-05-25
发明人： Dongxu Li , Changping Yin , Dong Hao , Wang Liu
摘要： A non-limit multi-function viscoelastic support structure group, relating to a field of aerospace structural design, includes a basic structure, a supported structure and multiple viscoelastic support structure units. The multiple viscoelastic support structure units form a circular discontinuous group and are arranged between the basic structure and the supported structure. The viscoelastic support structure units are connected with the basic structure and the supported structure respectively in ways of pre-pressing and surface contact, and no fixed constrained relationship exists. The present invention absorbs a vibration energy through a viscoelastic effect of own structural material and forms a spring-oscillator vibration attenuation system with the supported structure. With a geometric topology boundary change of the structure group, the supported structure is allowed to have a relative motion, thereby consuming the external vibration energy through converting into a kinetic energy of an oscillator, which effectively improves a mechanical environment of the supported structure.
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公开(公告)号：US10266273B2
公开(公告)日：2019-04-23
申请号：US14907233
申请日：2013-07-26
申请人： MRA Systems, Inc.
发明人： Yanxiang Kang , Mingchao Yuan , Xueliang Fang
摘要： An aircraft engine pylon having an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting and the upper panel, and tension fasteners at least partially coupling the upper fitting and the upper panel with the shear pin defining a shear force load path and the tension fasteners defining tension force load paths.
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公开(公告)号：US20190100324A1
公开(公告)日：2019-04-04
申请号：US16150991
申请日：2018-10-03
发明人： Frederic JOURNADE , Eric BOUCHET , Olivier BARBARA , Pascal POME
摘要： An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.
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公开(公告)号：US20190071186A1
公开(公告)日：2019-03-07
申请号：US15695156
申请日：2017-09-05
申请人： X Development LLC
发明人： Raymond Gradwohl
摘要： Systems and methods for mounting a motor to a receiving device of a UAS are disclosed herein. The motor may include a number of protruding elements, each protruding element including a shank segment having a first diameter and a head segment having a second diameter that is larger than the first diameter. The receiving device may include a base configured to couple the receiving device to the UAS, a first sidewall extending upwardly from a first side of the base, and a second sidewall extending upwardly from a second side of the base. Both the first and second sidewalls may include at least one receptacle. The head segment of each protruding element may be configured to interlock with one or more of the receptacles of the first sidewall or the second sidewall when the protruding elements are inserted between the first sidewall and the second sidewall of the receiving device.
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公开(公告)号：US20190055888A1
公开(公告)日：2019-02-21
申请号：US16047634
申请日：2018-07-27
发明人： Gabriel L. Suciu , Ioannis Alvanos , Brian Merry
CPC分类号： F02C7/20 , B64D27/10 , B64D27/26 , B64D2027/262 , B64D2027/266 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y10T29/49947
摘要： A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
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公开(公告)号：US10202186B2
公开(公告)日：2019-02-12
申请号：US15585058
申请日：2017-05-02
摘要： Aerial vehicles may include propulsion units having motors with drive shafts that may be aligned at a variety of orientations, propellers with variable pitch blades, and common operators for aligning the drive shafts at one or more orientations and for varying the pitch angles of the blades. The common operators may include plate elements to which a propeller hub is rotatably joined, and which may be supported by one or more linear actuators that may extend or retract to vary both the orientations of the drive shafts and the pitch angles of the blades. Operating the motors and propellers at varying speeds, gimbal angles or pitch angles enables the motors to generate forces in any number of directions and at any magnitudes. Attributes of the propulsion units may be selected in order to shape or control the noise generated thereby.
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公开(公告)号：US10197128B2
公开(公告)日：2019-02-05
申请号：US15423719
申请日：2017-02-03
发明人： Iman Shahosseini , John Nall , Ivan Roson
IPC分类号： B64D27/00 , F16F13/10 , B60K5/12 , B64D27/12 , B64D27/26 , F02C7/20 , F16F9/28 , F16F15/02 , F16F15/023
摘要： A hydraulic torque compensation device comprises a pair of housings, a first housing including a first high pressure liquid chamber and a second low pressure liquid chambers, a second housing having a third high pressure liquid chamber, a fourth accumulator chamber, and a fifth low pressure chamber that is defined by a wall and an end of the second housing. A first main duct links the first chamber of the first housing to the third chamber of the second housing. A second main duct links the second chamber of the first housing to the fifth chamber of the second housing. Each housing also include a piston, the first chamber between a first piston body and an end of the first housing and the third chamber between a second piston body and the wall. The device ensures a counter action to engine loads when a positive torque is applied.
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公开(公告)号：US20190031361A1
公开(公告)日：2019-01-31
申请号：US16154326
申请日：2018-10-08
IPC分类号： B64D31/06 , B64D31/14 , B64C27/57 , B64C29/02 , B64C29/00 , B64C27/52 , B64C39/02 , B64D27/24 , B64D27/26 , G05D1/00 , B64C11/46
摘要： A propulsion assembly for an aircraft includes a nacelle having a rapid connection interface, at least one battery disposed within the nacelle, a speed controller coupled to the battery and a propulsion system coupled to the speed controller and the battery. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that are rotatable with the output drive of the electric motor in a rotational plane to generate thrust. The electric motor is operable to rotate responsive to power from the battery at a speed responsive to the speed controller. The rapid connection interface of the nacelle is couplable to a rapid connection interface of an airframe nacelle station to provide structural and electrical connections therebetween that are operable for rapid in-situ assembly.
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