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公开(公告)号：US11136114B2
公开(公告)日：2021-10-05
申请号：US16556651
申请日：2019-08-30
发明人： Martin Griffith Rowlands , Maxwell William Jones , Graham King , Trevor Anthony Brighton , Matthew Gadd
摘要： A control system has first and second processing modules for controlling retraction and extension of an aircraft landing gear assembly. The processing modules operate independently providing redundancy. Each processing module is configured to perform a first sequence of steps for retracting the landing gear assembly and a second sequence of steps for extending the landing gear assembly. A step of switching control from one processing module to the other (e.g. an avionics side changeover step) is performed (a) as part of the first sequence of steps, but only after the landing gear assembly has been retracted, or (b) as part of the second sequence of steps. By ensuring that the step of switching control is performed at such times, and not for example between initiation of the first sequence of steps and the retraction of the landing gear assembly, the landing gear assembly may be retracted sooner after such initiation.
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公开(公告)号：US20200086582A1
公开(公告)日：2020-03-19
申请号：US16132311
申请日：2018-09-14
申请人： The Boeing Company
摘要： A composite sandwich panel includes a first composite part and a second composite part. A plurality of stiffeners extend between the first and second composite parts. A fiberglass composite perimeter edge closeout is positioned along one or more edges of the first and second composite parts. The fiberglass composite perimeter edge closeout controls a magnetic flux to bond the first and second composite parts to the plurality of stiffeners.
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公开(公告)号：US10479472B2
公开(公告)日：2019-11-19
申请号：US15611425
申请日：2017-06-01
申请人： The Boeing Company
摘要： An aerodynamic cover panel for a landing gear wheel well in an undercarriage of an aircraft includes at least one embodiment having a peripheral lip that defines a plane. Movements of the cover panel to open and close the wheel well are confined to pivotal rotation within the plane, and occur within an aerodynamic boundary layer of the undercarriage about a pivot axis in one rotational direction to open the wheel well, and in an opposite rotational direction to close the wheel well. The cover panel includes a flange, to which a rotary shaft is secured at one end for rotation about the pivot axis. The other end of the rotary shaft is secured to an actuator fixed within the undercarriage. In one embodiment, the cover panel rotates about an arc of least 75° between fully opened and fully closed positions of the wheel well.
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公开(公告)号：US10287012B2
公开(公告)日：2019-05-14
申请号：US15241436
申请日：2016-08-19
摘要： A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.
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公开(公告)号：US20190112034A1
公开(公告)日：2019-04-18
申请号：US16161461
申请日：2018-10-16
发明人： Daniel BELLET , Francois LOYANT , Alexandre LEGARDEZ , Simon ROUX , Sebastien CROUZET , Laurent DUBREUIL , Alain PRUDENT
摘要： An aircraft landing gear bay roof for forming a pressurization barrier between an upper pressurized compartment and a landing gear bay for the housing of a landing gear. The roof comprises a main bulkhead extending in a longitudinal direction, an inclined forward bulkhead, rigidly connected to a forward edge of the main wall, and an inclined aft bulkhead, rigidly connected to an aft edge of the main bulkhead. The forward bulkhead and the aft bulkhead each form an obtuse angle with the main bulkhead. This configuration enables a better absorption of loads by the landing gear bay roof and a shorter and optimized path for transmission of the mechanical loads, in particular to the fuselage member to which the aft bulkhead is configured to be connected.
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公开(公告)号：US10137985B2
公开(公告)日：2018-11-27
申请号：US15182074
申请日：2016-06-14
IPC分类号： B64C39/02 , B64C39/10 , B64D7/00 , B64C25/10 , B64D1/06 , B64D7/06 , B64D27/14 , B64C25/16 , B64D7/02 , B64D27/10
摘要： An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side.
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公开(公告)号：US09957039B2
公开(公告)日：2018-05-01
申请号：US14920600
申请日：2015-10-22
发明人： Louis Peltier , Robin Allory , Maurice Ricci
摘要： The present disclosure provides a system for opening and closing, in a substantially longitudinal direction, at least one hatch of a landing gear bay of an aircraft. In particular, the system includes: a proximal guide rod and a distal guide rod, each having a first end pivotably attachable to the hatch, and a second end pivotably attachable to a stationary inner structure of the gear bay, and arranged such as to form a deformable parallelogram hinge; and at least one drive rod having a first end that is pivotably attachable to the hatch, and a second end that is pivotably attachable to a landing gear leg.
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公开(公告)号：US09868519B2
公开(公告)日：2018-01-16
申请号：US14892698
申请日：2014-08-20
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA., LTD , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
发明人： Jun Lv , Qinggong Meng , Pu Zhang , Hao Jiang , Shangxin Yang , Hengkang Zhang , Jian Ma
摘要： A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors.
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49.发明申请公开(公告)号：US20170166300A1
公开(公告)日：2017-06-15
申请号：US15374652
申请日：2016-12-09
摘要： A system for the control of the door assemblies of a bay of a landing gear of an aircraft, that is retractile and is able to be deployed, the opening of the bay for the landing gear being able to be closed by a forward door assembly and an aft door assembly, comprises a coupling mechanism of the forward door assembly and the aft door assembly, that is configured such that the aft door assembly is not completely closed, but is ajar, as soon as the forward door assembly is opened during the deployment of the landing gear and the aft door assembly is completely closed at the complete closing of the forward door assembly when the landing gear is retracted.
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50.发明申请REAR DOOR OF A LANDING GEAR BOX COMPRISING AN AIR PASSAGE ORIFICE AND A CLOSURE MEMBER OF THE LATTER 审中-公开一个包括空气通道和一个闭路器的闭路齿轮箱的后门公开(公告)号：US20170021919A1
公开(公告)日：2017-01-26
申请号：US15216141
申请日：2016-07-21
发明人： Francis Dazet
摘要： A landing gear box of an aircraft comprising a front door with independent opening and a rear door with opening mechanically connected to the landing gear, including an orifice in the rear door provided with a closure member and a drive mechanism allowing movement of this closure member independently of any movement of the rear door.
摘要翻译： 飞机的起落架包括具有独立开口的前门和具有机械连接到起落架的开口的后门，包括在后门中的孔，其设置有闭合构件和允许该闭合构件独立地移动的驱动机构 后门的任何运动。
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