后缘襟翼相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
61	铰链式单缝后缘襟翼	CN201720453502.9	2017-04-26	CN207208456U	2018-04-10	田甘霖; 韩卓伟; 刘枭; 刘玉强
本实用新型公开了铰链式单缝后缘襟翼，包括有固定机翼，所示固定机翼的后缘上设有襟翼，还包括有驱动装置，所示驱动装置括有底座、转杆与摇臂，所述底座固定在固定机翼的底面，所述转杆的一端与底座铰接、另外一端与襟翼铰接；所述摇臂安装在底座上，所述摇臂通过一连杆与襟翼驱动连接，所述连杆与襟翼铰接，且所述连杆与襟翼的铰接点跟转杆与襟翼的铰接点不重叠。相对简单襟翼，通过驱动装置使得襟翼在打开的时候，襟翼与机翼之间留有缝隙，通过这种结构可以增加襟翼附面层的能量，延迟机翼后缘气流分离，因此增升效果好于简单襟翼。
62	一种后缘襟翼增升装置支撑机构	CN201120327942.2	2011-09-02	CN202213714U	2012-05-09	张瑞华; 黄衫; 田云; 刘沛清; 屈秋林
本实用新型提供一种后缘襟翼增升装置支撑机构，属于航空气动结构领域，包括丝杠、滑轨和滑轨架；丝杠与推动块螺纹连接，通过电机带动丝杠旋转；连接架与飞机后缘襟翼固定连接；滑轨架内部安装有上下两个滚轮架，滑轨穿叉在上下两个滚轮架的中间，滑轨的轨道包括水平轨道和沿圆弧弯曲向下轨道两部分，并在沿圆弧弯曲向下的轨道部分的底部安装有止动块；将滑轨固定安装于飞机机翼的加强翼肋上；滑轨架的一端通过耳片与后缘襟翼连接。本实用新型采用直线-圆弧形滑轨为基本型，其直线段，后退量大，向下偏转角度小适用于飞机起飞时的要求。滑轨圆弧段后退行程短，向下偏转角度大，适于飞机着陆时大升力和大阻力的要求。
63	带折叠后缘襟翼的折叠式机翼	CN202021502508.9	2020-07-27	CN213083484U	2021-04-30	及兰平; 及佳; 王旭
本实用新型属于航空技术领域，具体涉及一种带折叠后缘襟翼的折叠式机翼，其包括主翼和折叠后缘襟翼，其中多根曲柄形襟翼支撑肋，通过连接轴和对应的蒙皮支撑肋下表面铰接连接，构成依托蒙皮支撑肋的折叠后缘襟翼支撑骨架，复位弹簧使曲柄形襟翼支撑肋长边上表面紧贴蒙皮支撑肋下表面，柔性襟翼蒙皮附着连接在折叠后缘襟翼支撑骨架上表面。在现有折叠式机翼的基础上，本实用新型设计能够随机翼折叠、展开，且可调节的机翼后缘襟翼，构成带折叠后缘襟翼的折叠式机翼，能够很好地解决现有折叠式机翼没有机翼后缘襟翼，机翼调节能力受限的问题，配合折叠式机翼副翼，使得折叠式机翼具有现代固定翼机翼的主要功能。
64	一种飞机后缘襟翼的悬挂装置	CN202020716751.4	2020-04-30	CN212243789U	2020-12-29	李云鹏; 王俊朋; 李刚; 姜立峰
本申请提供一种飞机后缘襟翼的悬挂装置，所述装置包括轴承1、悬挂接头2、垫板3、梁4、内侧加强肋6、外侧加强肋7、下蒙皮8、加强板9，其中：悬挂接头2为竖直方向上的单耳结构，悬挂接头2的连接区包括竖直面和底面，悬挂接头2的竖直面通过垫板3和梁4分别与内侧加强肋6和外侧加强肋7连接，悬挂接头2的底面通过下蒙皮8和加强板9分别与内侧加强肋6和外侧加强肋7连接，悬挂接头2的上端设置有结构优化孔，悬挂接头2的下端设置有轴承孔，悬挂接头2腹板区的厚度从轴承孔至远端依此减薄；轴承1内置于悬挂接头2的轴承孔内。
65	一种农业轻型飞机后缘襟翼控制机构	CN201621073904.8	2016-09-23	CN206125410U	2017-04-26	蔡畅岚; 屈霞; 许志林; 叶蕾; 朱辉杰; 曾嵘; 彭金京; 郭丹; 邰瑞雪; 邓欢
本实用新型提供一种农业轻型飞机后缘襟翼控制机构，包括电动机构、支架Ⅰ、操纵拉杆Ⅰ、直角摇臂Ⅰ、连杆Ⅰ、丁字摇臂、支座、连杆Ⅱ、直角摇臂Ⅱ、操纵拉杆Ⅱ、支架Ⅱ和支臂，襟翼控制盒与电动机构连接，电动机构与丁字摇臂铰接，丁字摇臂与支座连接。连杆Ⅰ、连杆Ⅱ一端与丁字摇臂连接，另一端分别与直角摇臂Ⅰ、直角摇臂Ⅱ连接。直角摇臂Ⅰ、直角摇臂Ⅱ分别与支架Ⅰ、支架Ⅱ连接，操纵拉杆Ⅰ、操纵拉杆Ⅱ一端分别与直角摇臂Ⅰ、直角摇臂Ⅱ连接，另一端分别与左、右襟翼操纵接头铰接。本实用新型公开一种农业轻型飞机后缘襟翼控制机构，通过一套机械传动机构实现交联，使左、右两块独立的襟翼同时偏转，很好地解决了舵面同步性问题。
66	飞机后缘襟翼操纵系统的软轴驱动装置	CN200620118141.4	2006-06-02	CN2913182Y	2007-06-20	黎国荣; 王莉; 张立圣; 姜曼琳; 高洁; 印正峰; 哈晓春
本实用新型涉及一种采用马达作为驱动装置操纵飞机后缘襟翼操纵系统的软轴驱动装置。在马达驱动装置与下一级传动装置之间使用软轴连接，软轴的一端内壁有内齿，另一端的外壁有外齿，内齿端与马达输出轴的外齿啮合，并用护套紧固件固定；外齿与下一级传动装置的内齿啮合，并用护套紧固件固定。本实用新型解决了在较小空间进行功率传递问题，由于没有采用硬轴进行功率传递所必须的多杆连接，及所必须的杆间连接装置，故传递精度得到提高。在航空工程里，有使用软轴操纵负载的先例，但均属较小负载的操纵。而本实用新型通过软轴传递高转速、低扭矩给下一级设置了合理的减速比的传动装置，既可由该传动装置输出低转速、高扭矩，其输出功率足以克服飞机较大的气动载荷。
67	用于飞机后缘襟翼全尺寸试验的支撑装置	CN201820535848.8	2018-04-16	CN208393643U	2019-01-18	王春寿; 袁坚锋; 刘杨; 黄海峰; 杨志丹
本实用新型涉及用于飞机后缘襟翼全尺寸试验的支撑装置，其特征在于，所述支撑装置包括：用于调整飞机后缘襟翼以实现不同卡位的调整机构；传动机构，所述传动机构与所述调整机构形状锁合连接并且和与飞机后缘襟翼连接的构件不可相对转动地连接；将飞机后缘襟翼载荷传递到机翼后缘上的连接机构，其中，所述连接机构在一侧与调整后的调整机构连接且在与该侧相对的一侧和与机翼后缘连接的构件固定连接。
68	基于无缝后缘襟翼机构的直升机旋翼桨叶	CN201921987960.6	2019-11-18	CN211869690U	2020-11-06	杨卫东; 周金龙; 董凌华
本实用新型公开了一种基于无缝后缘襟翼机构的直升机旋翼桨叶，包含桨叶本体和若干后缘襟翼模块；后缘襟翼模块包含壳体、驱动器、推拉杆、驱动杆、安装平台、第一柔性铰链、第二柔性铰链、后缘襟翼和密封片。驱动器产生动态直线位移输出；驱动器、推拉杆、驱动杆、后缘襟翼依次相连，驱动器产生的力和位移输出传递到后缘襟翼；后缘襟翼通过第二柔性铰链与安装平台相连，并通过第二柔性铰链将推拉杆的直线往复运动转换为后缘襟翼偏转运动。本实用新型用于直升机后缘襟翼主动控制旋翼，通过后缘襟翼动态偏转，动态改变桨叶气动载荷分布，抑制直升机旋翼振动载荷，或通过声场对消的方法抑制旋翼噪声。(ESM)同样的发明创造已同日申请发明专利
69	一种用于B737NG机队后缘襟翼的数据采集装置	CN201921620828.1	2019-09-25	CN210882690U	2020-06-30	朱晓炜; 赵红华; 程伟; 沈凯杰
本实用新型涉及一种用于B737NG机队后缘襟翼的数据采集装置，包括壳体，所述壳体包括手持部和探测部，所述手持部与所述探测部一体成型，所述手持部的顶部位置设有显示屏，所述显示屏的下方设有操作按钮板，所述手持部的底部内置有锂电池仓，所述探测部设有多个用于发射和接收探测波的信号发射孔及信号接收孔，所述壳体内部还内置有用于分析对应探测波波形并转化成数据的信号分析电路板及用于控制所述操作按钮板和所述显示屏的开发板，所述的开发板上设有存储信号转化数据的存储卡。与现有技术相比，本实用新型具有操作简便，自动化程度高，实时监控，降低危险等优点。
70	采用柔性铰链的直升机桨叶后缘襟翼驱动机构	CN201822201292.1	2018-12-26	CN210101968U	2020-02-21	杨卫东; 董凌华; 周金龙
本实用新型公开了一种采用柔性铰链的直升机桨叶后缘襟翼驱动机构，包括固定框、驱动器、后缘襟翼、襟翼柔性铰链、轴承、驱动杆及驱动杆柔性铰链。驱动器产生高频直线位移输出用以驱动后缘襟翼偏转运动；襟翼柔性铰链一端与后缘襟翼相连，另一端安装在固定框上，在旋翼旋转状态下襟翼柔性铰链承受襟翼离心载荷；后缘襟翼与固定框之间安装轴承，作用在于对后缘襟翼的浮沉运动进行约束；驱动杆将驱动器直线位移输出传递到后缘襟翼，通过襟翼柔性铰链、驱动杆柔性铰链以及轴承，将驱动器的直线位移转换为后缘襟翼的偏转运动。本实用新型用于驱动后缘襟翼动态偏转，产生附加气动载荷以抑制旋翼振动，从而实现直升机旋翼振动主动控制。(ESM)同样的发明创造已同日申请发明专利
71	用于改善电动垂直起降飞机翼面流动特性的后缘襟翼结构	CN202222061833.1	2022-08-08	CN217945496U	2022-12-02	王继明; 姚远; 杨万里; 党铁红; 董明
本实用新型公开了用于改善电动垂直起降飞机翼面流动特性的后缘襟翼结构，包括主翼，所述主翼后侧设有襟翼，所述襟翼与主翼之间存在襟翼缝道，所述襟翼缝道的宽度设置在0.8％～1.5％，所述襟翼的转轴位于襟翼翼面之下，所述襟翼偏转时襟翼缝道宽度随之增加。本结构增加了升力系数，改善了翼面的流动分离，提升了飞机的失速裕度，增加飞机低速飞行的安全性。
72	Trailing edge flap system	US12946075	2010-11-15	US08511608B1	2013-08-20	Mark Steven Good; Alan Keith Prichard
A method and apparatus for controlling a movement of a control surface comprises a first linkage system, a second linkage system, and an actuator system. The first linkage system is connected to a first location of a control surface. The second linkage system is connected to a second location of the control surface. The first location is closer to a leading edge of the control surface than the second location. The actuator system is configured to move the first linkage system and the second linkage system.
73	Trailing-edge flap system	US13468099	2012-05-10	US08602364B2	2013-12-10	Tom Dostmann; Bernhard Schlipf; Jochen Eichhorn
A trailing-edge flap system is described. The trailing-edge flap system includes a trailing-edge flap and a movement device. The movement device includes at least a translatory mover for the translation of the trailing-edge flap and at least a rotational mover for the rotation of the trailing-edge flap.
74	Folding truss mechanism for trailing edge flaps	US463455	1982-09-29	US4448375A	1984-05-15	Gerald F. Herndon
A swinging drive link (10) is pivotally connected at its lower end (18) to a forward support (16) for a flap (20). The flap rear support is provided by a pivotal connection (24) between a rear support point and the lower end of a swing link (22). The upper end of the swing link (22) is pivotally connected (31) to the upper end of a support link (26) and the rear end of a slave link (30). The lower end of the support link (26) is attached (27) to a beam structure (28) projecting rearwardly from the main wing section (13, 29). The forward end of the slave link (30) is pivotally attached (40) to an intermediate portion of the drive link (10). Rearward rotation of drive link (10) causes the flap (20) to translate rearwardly with a small amount of downward rotation until the flap (20) is essentially completely extended. Then, further extension of the mechanism rotates the flap (20) a substantial amount downwardly. In a double slot embodiment (FIGS. 7-9), similar linkage is provided between a forward main flap (66) and an aft flap (64).
75	Method for predicting a trailing edge flap fault	US14065893	2013-10-29	US08989953B2	2015-03-24	Christopher Joseph Catt; Julia Ann Howard
A method of predicting a trailing edge flap failure, the method includes receiving a position signal from the position sensor indicative of the position of at least one of the trailing edge flaps, comparing the position signal to a reference position value to define a position comparison, defining a variation comparison and providing an indication of a prediction of a trailing edge flap failure based on the variation comparison.
76	트레일링 에지 플랩을 갖는 헬리콥터 에어로포일	KR1020177001390	2016-04-21	KR1020170141182A	2017-12-22	케이브앤드류; 스테이시시몬
에어로포일은에어로포일단면의주요부와작동장치에의해주요부에대해이동가능한트레일링에지부를가지며, 트레일링에지부는굴곡지점/영역(A)에서또는그 주위에서이동가능하고, 굴곡지점/영역(A)은에어로포일의압력또는흡입표면에또는그에인접위치되고, 트레일링에지부는제1 및제2 연결부재들에의해주요부에연결되고, 제1 연결부재는굴곡지점/영역(A)으로부터안쪽으로연장되고주요부에직접적으로또는간접적으로연결되는단부를가지며제1 및제2 연결부재는가요성을갖는다.
77	Slotted cruise trailing edge flap	EP04075105.9	1997-10-15	EP1407964A2	2004-04-14	Siers, Geoffrey L.
A slotted cruise trailing edge flap (16) having a single-slotted configuration during cruise, and a double-slotted configuration during takeoff and landing is disclosed. The slotted cruise trailing edge flap (16) includes a flap assembly (18) positioned along the trailing edge of an aircraft wing (30). The flap assembly (18) includes a vane element (22) and a main element (24) mounted in a fixed relation to one another that defines a slot (25) therebetween. The slotted cruise trailing edge flap also includes an extension assembly (20) that includes a support structure (23) from which the flap assembly (18) is translatably connected via a track (44) and carriage (46) arrangement. The flap assembly (18) is rotatably connected to the support structure (23) using a cam follower (52) and cam slot (50). An actuation mechanism (28) including a rotary actuator (56) moves the flap assembly (18) relative to the support structure (23). In a stowed position, the vane element (22) preferably nests into the wing (30) such that the slot (25) remains available to direct airflow from the wing lower surface to the wing upper surface. In an extended position, the vane and main elements (22), (24) form a double-slotted arrangement created by the flap assembly translating rearward and rotating downward relative to the wing (30).
78	Gekrümmtes Flügelprofil mit einer schwenkbaren Hinterkantenklappe	EP13197105.3	2013-12-13	EP2743177B1	2016-09-14	Dipl.-Ing. Storm, Stefan; Dr.-Ing. Wildschek, Andreas

79	Hinged panel operation systems and methods	EP13194967.9	2013-11-28	EP2738087A2	2014-06-04	Beyer, Kevin W.; Sakurai, Seiya; Stephenson, Martin F.
A hinged panel operation system (10) is provided having a mechanical linkage assembly (90) coupled between a fixed structure (96) and a trailing edge device (36). The mechanical linkage assembly has a first link (118) operatively coupled to the trailing edge device, a second link (130) pivotably connected at a first end to the first link and pivotably connected at a second end to a third link (142), and an eccentric attachment (154) connecting the second link to the third link. The hinged panel operation system further has a hinged panel (162) positioned forward of the trailing edge device and being operatively coupled to the mechanical linkage assembly. The hinged panel is movable by the mechanical linkage assembly between a stowed position and a drooped position. The mechanical linkage assembly provides a load path to the hinged panel.
80	Trailing-edge flap system for a wing of an aircraft and aircraft comprising a wing and at least one such trailing-edge flap system	EP13198114.4	2013-12-18	EP2886451A1	2015-06-24	Gemilang, Atra, Surya; Vöge, Wolfgang
A trailing-edge flap system (2) for a wing of an aircraft is proposed, the wing having a wing structure, the trailing-edge flap system (2) comprising a trailing-edge flap (4), a guide rail (6) attached to the trailing-edge flap (4), a carriage (12) slidably engaging the guide rail (6) and rotatably attachable to a fixed position on the wing structure, and a drive means (14) couplable with the wing structure and coupled with a first joint (28) on the guide rail (6). The drive means (14) is adapted for moving the trailing-edge flap (4) relative to the wing structure by moving the guide rail (6) along the carriage (12) through moving the first joint (28) relative to the wing structure, such that the trailing-edge flap (4) translates and rotates, wherein the trailing-edge flap (4) is at least movable into a cruise position, a high-lift position and an air brake position. The system is space effective and allows an air-brake function besides the high-lift functions without sacrificing the aerodynamics of the wing in cruise flight.

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