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1. 发明授权

US09079669B2 Icing detector probe and icing detector with the same 有权
标题翻译：结冰检测器探头和结冰探测器相同
公开(公告)号：US09079669B2
公开(公告)日：2015-07-14
申请号：US13809934
申请日：2011-06-30
申请人： Yingchun Chen , Lin Ye , Miao Zhang , Junfeng Ge , Lijuan Feng , Tiejun Liu , Feng Zhou
发明人： Yingchun Chen , Lin Ye , Miao Zhang , Junfeng Ge , Lijuan Feng , Tiejun Liu , Feng Zhou
IPC分类号： B64D15/20
CPC分类号： B64D15/20
摘要： An icing detector probe includes three sections arranged sequentially along the direction of air flow, namely, a first section, a second section and a third section. The shape of the outer surface of the first section is suitable for collecting droplets in the air flow. The shape of the outer surface of the second section is suitable for full decelerating and releasing latent heat of large droplets during their movements. The outer surface of the third section is suitable for icing of large droplets. The probe detects icing by distinguishing and identify large droplets icing. The probe effectively detects types of traditional icing, thus being helpful for exact detection of icing thickness. An icing detector including said icing detector probe is also provided.
摘要翻译：结冰检测器探头包括沿空气流动方向依次布置的三个部分，即第一部分，第二部分和第三部分。第一部分的外表面的形状适合于在空气流中收集液滴。第二部分的外表面的形状适合于在其运动期间完全减速和释放大液滴的潜热。第三部分的外表面适用于大液滴的结冰。探测器通过识别和识别大型液滴结冰来检测结冰。探头有效地检测传统结冰的类型，有助于精确检测结冰厚度。还提供了包括所述结冰检测器探针的结冰检测器。

2. 发明授权

US11319057B2 Electric pedal control device for aircraft 有权
公开(公告)号：US11319057B2
公开(公告)日：2022-05-03
申请号：US16310058
申请日：2017-11-30
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD. , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD. SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
发明人： Dianhuang Xie , Zhengqiang Li , Yefei Dai , Jian Li , Junhui Liao , Desheng Xu , Shenghui Yu
IPC分类号： B64C13/04 , B64C13/12 , B64C13/30
摘要： An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

3. 发明申请

US20190382101A1 ELECTRIC PEDAL CONTROL DEVICE FOR AIRCRAFT 审中-公开
公开(公告)号：US20190382101A1
公开(公告)日：2019-12-19
申请号：US16310058
申请日：2017-11-30
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD. , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD. SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
发明人： Dianhuang XIE , Zhengqiang LI , Yefei DAI , Jian LI , Junhui LIAO , Desheng XU , Shenghui YU
IPC分类号： B64C13/04 , B64C13/30 , B64C13/12
摘要： An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

4. 发明授权

US09950803B2 Airplane suspension cowling structure with wing-mounted arrangement 有权
公开(公告)号：US09950803B2
公开(公告)日：2018-04-24
申请号：US14893717
申请日：2014-08-28
申请人： Commercial Aircraft Corporation of China, Ltd , Commercial Aircraft Corporation of China, Ltd Shanghai Aircraft Design and Research Institute
发明人： Zhehui Yu , Miao Zhang , Meihong Zhang , Fei Xue , Tiejun Liu , Dongyun Zhang , Junhong Wang , Pan Cheng , Yong Lu , Xiaoyan Liu
IPC分类号： B64D29/02 , B64C7/02 , B64D27/26
CPC分类号： B64D29/02 , B64C7/02 , B64D2027/264
摘要： Provided is an airplane suspension (20) fairing structure with a wing-mounted arrangement, the fairing structure comprising a front fairing located in front of the leading edge (31) of a wing and a rear fairing located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front fairing is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front fairing of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the fairing aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.

5. 发明授权

US10773809B2 Dewatering device for an air conditioning system of a plane 有权
公开(公告)号：US10773809B2
公开(公告)日：2020-09-15
申请号：US15310029
申请日：2015-09-22
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
发明人： Xuede Sun , Geping Li , Xizhong Jian , Xudong Yan , Zhan Cheng
IPC分类号： B64D13/06 , B01D46/00 , B01D46/10 , B01D46/46 , B64D13/02 , G05D22/02 , F24F3/14 , B64D13/00 , F24F13/04
摘要： The present invention provides a dewatering device for an air-conditioning system of a plane, comprising: one or more filter plates disposed within a mixing cavity of an air-conditioning system of a plane, for filtering liquid-state water in mixed air in the mixing cavity, wherein the filter plates are configured to be inclinable relative to an axis of the mixing cavity, and an inclination angle thereof is adjustable so as to change a filtering amount of the mixed air.

6. 发明申请

US20170267333A1 AIRCRAFT WING ASSEMBLY 审中-公开
公开(公告)号：US20170267333A1
公开(公告)日：2017-09-21
申请号：US15309933
申请日：2015-09-29
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD , SHANGHAI AIRCRAFT MANUFACTURING CO., LTD.
发明人： WEI LIAN , MING LI , JIANGANG LIU , CHENTAO WENG , DEHONG SHEN , YANKAI LIU , RUI HE , YUANQING ZHANG , MENGMENG XU
IPC分类号： B64C23/06 , B64C3/18
CPC分类号： B64C23/069 , B64C3/187 , B64C3/52 , B64F5/00 , Y02T50/164
摘要： An airplane wing assembly includes a wing, a winglet and a connection element. The wing has a wing box. The wing box is located at a wing tip of the wing and the winglet is connected with the wing by the wing box. The connection element includes a butt joint rib, which is assembled with the wing box, and a center connection, which is assembled with the winglet. The butt joint rib has a first shearing pin hole and a second shearing pin hole, into which are press fitted a corresponding first and a second shearing pin respectively to form interference fit. The center connector has a first sleeve hole and a second sleeve hole.

7. 发明授权

US10272990B2 Aircraft wing assembly 有权
公开(公告)号：US10272990B2
公开(公告)日：2019-04-30
申请号：US15309933
申请日：2015-09-29
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE , SHANGHAI AIRCRAFT MANUFACTURING CO., LTD.
发明人： Wei Lian , Ming Li , Jiangang Liu , Chentao Weng , Dehong Shen , Yankai Liu , Rui He , Yuanqing Zhang , Mengmeng Xu
IPC分类号： B64C3/52 , B64C23/06 , B64C3/18 , B64F5/00
摘要： An airplane wing assembly includes a wing, a winglet and a connection element. The wing has a wing box. The wing box is located at a wing tip of the wing and the winglet is connected with the wing by the wing box. The connection element includes a butt joint rib, which is assembled with the wing box, and a center connection, which is assembled with the winglet. The butt joint rib has a first shearing pin hole and a second shearing pin hole, into which are press fitted a corresponding first and a second shearing pin respectively to form interference fit. The center connector has a first sleeve hole and a second sleeve hole.

8. 发明授权

US09868519B2 Linkage mechanism for driving aircraft landing gear bay door 有权
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
IPC分类号： B64C25/20 , B64C25/16 , B64C25/10
CPC分类号： B64C25/20 , B64C25/10 , B64C25/16
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.

9. 发明授权

US09856028B2 Integrated pylon structure for propulsion system 有权
公开(公告)号：US09856028B2
公开(公告)日：2018-01-02
申请号：US14407497
申请日：2013-12-12
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
发明人： Guanghui Wu , Kecen Han , Liangdao Zhou , Qifeng Yu , Guozheng Lin , Hongjie Zhang , Shibiao Zhang , Haojie Weng , Haisha Guo , Pengfei Zhang , Xiaonan Li , Shiwei Ma , Yinyin Hu , Sen Peng , Honggang Tang , Mingpeng Yan
IPC分类号： B64D27/26 , F02K1/72 , B64D27/18
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , F02K1/72 , Y02T50/44 , Y02T50/672
摘要： An integrated pylon structure for a propulsion system is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure includes a pylon box section (110) formed from an upper and a lower bean, a frame (100) and a side wall panel. The pylon structure has a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood having a front fixed hood (301) and a rear movable hood (302). A guide rail allows the rear movable hood to slide and open relative to the pylon box section. The engine thrust reverser hood is directly connected to the side wall of the pylon box section and a guide rail on the side wall guides the opening of the thrust reverser hood.

10. 发明授权

US09745072B2 Front installation node integrated with aircraft pylon 有权
公开(公告)号：US09745072B2
公开(公告)日：2017-08-29
申请号：US14407545
申请日：2013-12-06
申请人： COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD , COMMERCIAL AIRCRAFT CORPORATION OF CHINA, LTD SHANGHAI AIRCRAFT DESIGN AND RESEARCH INSTITUTE
发明人： Guozheng Lin , Yinyin Hu , Sen Peng , Qifeng Yu , Yaoyu Fan
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/266 , Y02T50/44
摘要： A front installation node is suitable for integral forming with a front end frame of an aircraft pylon and includes a first lug and a second lug, each respectively protruding outwardly from one of the two sides of the frond end frame; a first connecting rod and a second connecting rod, one end thereof being respectively connected to the first lug and the second lug, and the other end thereof being respectively suitable for connecting to an aircraft engine. The first connecting rod can pivotally connect to the first lug at a first connection point. The second connecting rod and the second lug are respectively connected at a second connecting point and a third connecting point. Using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.

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