CN102642616B - Airplane high lift device with fixed double slotted flaps - Google Patents
Airplane high lift device with fixed double slotted flaps Download PDFInfo
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Abstract
本发明属于设计领域，涉及一种用于飞机起飞和着陆时增加飞机升力的带固定双缝襟翼的飞机增升装置。增升装置包括主襟翼、后襟翼、Y形支架、主翼后梁固定杆、作动筒、第一联动杆、第二联动杆、第三联动杆、扰流板、下挡板、密封胶皮。本发明的增升装置的结构重量是带非固定主/后双缝襟翼的飞机增升装置的重量的60%～75%。相对于非固定主/后双缝襟翼的飞机增升装置，采用本发明的增升装置，飞机的生产成本可以降低1.5%～3.5%，乘客或货物装载量增加0.5%～1.5%，飞机的单位装载的燃油消耗量降低0.5%～1.5%，飞机的运营成本降低0.5%～1.5%。与传统的滑轨运动机构相比。
The invention belongs to the field of design, and relates to an aircraft lift-increasing device with fixed double-slotted flaps used for increasing the lift of the aircraft during take-off and landing. The lifting device includes main flaps, rear flaps, Y-shaped brackets, main wing rear beam fixing rods, actuators, first linkage rods, second linkage rods, third linkage rods, spoilers, lower baffles, and rubber seals . The structural weight of the lift increasing device of the present invention is 60% to 75% of the weight of the aircraft lift increasing device with non-fixed main/rear double slit flaps. Compared with the aircraft high-lift device with non-fixed main/rear double-slot flaps, the high-lift device of the present invention can reduce the production cost of the aircraft by 1.5% to 3.5%, and increase the passenger or cargo loading by 0.5% to 1.5%. The fuel consumption per unit load is reduced by 0.5% to 1.5%, and the operating cost of the aircraft is reduced by 0.5% to 1.5%. Compared with the traditional slide rail movement mechanism.
Description
技术领域： Technical field:
本发明属于设计领域，涉及一种用于飞机起飞和着陆时增加飞机升力的带固定双缝襟翼的飞机增升装置。The invention belongs to the field of design, and relates to an aircraft lift-increasing device with fixed double-slotted flaps used for increasing the lift of the aircraft during take-off and landing.
背景技术 Background technique
现有的带非固定主襟翼/后襟翼的飞机增升装置（如图1所示），由于主襟翼和后襟翼是相互独立的，为了保证在受到最大的气动载荷时，它们的结构变形能满足设计要求，它们的结构重量都需要比较大；它们的运动机构的强度和刚度也都必须满足设计要求，从而他们的运动机构重量也比较大。带非固定主襟翼/后襟翼的飞机增升装置的重量是带单缝襟翼的飞机增升装置的重量的1.8～2.4倍，增加的这部分重量是飞机起飞重量的1%～2%，这导致飞机的生产成本增加2%～5%，乘客或货物装载量减少1%～2%，飞机的单位装载的燃油消耗量增加1%～2%。The existing aircraft high-lift device with non-fixed main flaps/rear flaps (as shown in Figure 1), since the main flaps and rear flaps are independent of each other, in order to ensure that they are under the maximum aerodynamic load, The structural deformation can meet the design requirements, and their structural weight needs to be relatively large; the strength and stiffness of their kinematic mechanisms must also meet the design requirements, so their kinematic mechanisms are also relatively heavy. The weight of the aircraft high-lift device with non-fixed main flaps/rear flaps is 1.8 to 2.4 times the weight of the aircraft high-lift device with single-slot flaps, and the added weight is 1% to 2% of the take-off weight of the aircraft. %, which leads to an increase in the production cost of the aircraft by 2% to 5%, a reduction in the passenger or cargo load by 1% to 2%, and an increase in the fuel consumption per unit load of the aircraft by 1% to 2%.
发明内容 Contents of the invention
本发明的目的是提出一种在提高增升能力的同时，保证襟翼运动机构相对简单的带固定双缝襟翼的飞机增升装置。本发明的技术解决方案是，增升装置包括主襟翼、后襟翼、Y形支架、主翼后梁固定杆、作动筒、第一联动杆、第二联动杆、第三联动杆、扰流板、下挡板、密封胶皮，主翼后梁固定杆的一端固定在主翼上的后梁下缘条处，主翼后梁固定杆的这一端的宽度与后梁的下缘条宽度相同，主翼后梁固定杆的另一端通过主铰链与Y形支架的一端铰接，主翼后梁固定杆的宽度光滑渐变至与主铰链的直径相同；Y形支架的另外两个端面分别固定在主襟翼中的主襟翼梁下部和后襟翼中的后襟翼梁下部，Y形支架固定在主襟翼中的主襟翼梁下部的端面宽度是主襟翼梁下缘条宽度的2倍，Y形支架固定在后襟翼中的后襟翼梁下部的端面宽度是后襟翼梁下缘条宽度的2.5倍；连杆的一端固定在主翼后梁固定杆上靠近主铰链处，此固定位置到主铰链的距离为主翼后梁固定杆长度的10%～25%，连杆的另一端与第一联动杆的一端铰接；第一联动杆的另一端同时与第二联动杆的一端、第三联动杆的一端铰接，第二联动杆的另一端铰接在Y形支架上的主襟翼一侧的内壁上，此铰接位置到主襟翼下表面的距离是主襟翼后梁下缘条到主铰链的距离的15%～25%，第三联动杆的另一端铰接在下挡板的下表面；The purpose of the present invention is to propose an aircraft lift-increasing device with fixed double-slotted flaps while improving the lift-increasing capacity and ensuring that the flap motion mechanism is relatively simple. The technical solution of the present invention is that the high-lift device includes a main flap, a rear flap, a Y-shaped bracket, a main wing rear beam fixing rod, an actuator, a first linkage lever, a second linkage lever, a third linkage lever, a spoiler plate, lower baffle, sealing rubber, one end of the main wing rear beam fixing rod is fixed at the lower edge of the rear beam on the main wing, the width of this end of the main wing rear beam fixing rod is the same as the width of the lower edge of the rear beam, and the other end of the main wing rear beam fixing rod One end is hinged with one end of the Y-shaped bracket through the main hinge, and the width of the main wing rear beam fixing rod smoothly and gradually changes to the same diameter as the main hinge; the other two end surfaces of the Y-shaped bracket are respectively fixed on the lower part of the main flap beam in the main flap and the The lower part of the rear flap spar in the rear flap, the Y-bracket is fixed in the main flap. The end face width of the lower part of the rear flap beam is 2.5 times the width of the lower edge of the rear flap beam; one end of the connecting rod is fixed on the main wing rear beam fixed rod close to the main hinge, and the distance from this fixed position to the main hinge is the main wing rear beam 10% to 25% of the length of the fixed rod, the other end of the connecting rod is hinged with one end of the first linkage rod; the other end of the first linkage rod is also hinged with one end of the second linkage rod and one end of the third linkage rod, and the second The other end of the linkage rod is hinged on the inner wall of the main flap on the Y-shaped bracket. The distance from the hinged position to the lower surface of the main flap is 15% to 25% of the distance from the lower edge of the rear beam of the main flap to the main hinge. , the other end of the third linkage rod is hinged on the lower surface of the lower baffle;
此铰接位置与主襟翼铰链的距离为下挡板长度的25%～50%；The distance between this hinge position and the main flap hinge is 25% to 50% of the length of the lower fender;
下挡板的一端通过主襟翼铰链铰接在主襟翼上主襟翼梁下缘条的后方，下挡板的另一端固定有一个密封胶皮,密封胶皮与后襟翼前缘贴合，将后襟翼舱下部分密封；One end of the lower baffle is hinged to the rear of the lower edge of the main flap beam on the main flap through the main flap hinge, and the other end of the lower baffle is fixed with a sealing rubber, which is attached to the front edge of the rear flap. The lower part of the rear flap compartment is sealed;
作动筒的固定端铰接在主翼后梁固定杆上，此铰接位置到主翼上的后梁下缘条的距离为后梁固定杆长度的5%～30%，作动筒的活动端铰接在Y形支架上，此铰接位置到主襟翼梁下缘条的距离为主铰链到主襟翼梁下缘条的距离的20%～60%；The fixed end of the actuator is hinged on the fixed rod of the rear beam of the main wing. The distance from the hinged position to the lower edge of the rear beam on the main wing is 5% to 30% of the length of the fixed rod of the rear beam. The movable end of the actuator is hinged on the Y-shaped bracket , the distance from the hinge position to the lower edge of the main flap beam is 20% to 60% of the distance from the main hinge to the lower edge of the main flap beam;
主翼上的扰流板的尾部搭在后襟翼中的后襟翼梁上缘条处，将后襟翼舱遮住，扰流板与主襟翼的尾部有间隙。The tail of the spoiler on the main wing rides on the upper edge of the rear flap beam in the rear flap to cover the rear flap cabin, and there is a gap between the spoiler and the tail of the main flap.
本发明具有的优点和有益效果，本发明采用的是带定轴转动后缘固定主/后双缝襟翼的飞机增升装置，本发明的增升装置的增升能力，不低于带非固定主/后双缝襟翼的飞机增升装置的增升能力。本发明的增升装置的结构重量是带非固定主/后双缝襟翼的飞机增升装置的重量的60%～75%。相对于非固定主/后双缝襟翼的飞机增升装置，采用本发明的增升装置，飞机的生产成本可以降低1.5%～3.5%，乘客或货物装载量增加0.5%～1.5%，飞机的单位装载的燃油消耗量降低0.5%～1.5%，飞机的运营成本降低0.5%～1.5%。与传统的滑轨运动机构相比，本发明采用的定轴转动运动机构更轻、可靠性更高、操纵反应更快。The present invention has the advantages and beneficial effects. What the present invention adopts is an aircraft lift-increasing device with fixed main/rear double-slotted flaps with a fixed-axis rotation trailing edge. The lift-increasing capacity of the lift-increasing device of the present invention is not lower than that Increased lift capacity of aircraft with fixed main/rear double-slotted flaps. The structural weight of the lift increasing device of the present invention is 60% to 75% of the weight of the aircraft lift increasing device with non-fixed main/rear double slit flaps. Compared with the aircraft high-lift device with non-fixed main/rear double-slot flaps, the high-lift device of the present invention can reduce the production cost of the aircraft by 1.5% to 3.5%, and increase the passenger or cargo loading by 0.5% to 1.5%. The fuel consumption per unit load is reduced by 0.5% to 1.5%, and the operating cost of the aircraft is reduced by 0.5% to 1.5%. Compared with the traditional slide track motion mechanism, the fixed-axis rotation motion mechanism adopted by the present invention is lighter, has higher reliability and faster manipulation response.
附图说明 Description of drawings
图1现有技术的结构示意图；The structural representation of Fig. 1 prior art;
图2是本发明结构示意图；Fig. 2 is a structural representation of the present invention;
图3是本发明起飞状态示意图；Fig. 3 is a schematic diagram of the take-off state of the present invention;
图4是本发明着陆状态示意图。Fig. 4 is a schematic diagram of the landing state of the present invention.
具体实施方式 Detailed ways
下面结合附图对本发明作详细说明。The present invention will be described in detail below in conjunction with the accompanying drawings.
如图所示，增升装置包括主襟翼2、后襟翼3、Y形支架8、主翼后梁固定杆9、作动筒10、第一联动杆11、第二联动杆15、第三联动杆16、扰流板4、下挡板6、密封胶皮7，As shown in the figure, the high-lift device includes a main flap 2, a rear flap 3, a Y-shaped bracket 8, a main wing rear beam fixing rod 9, an actuator 10, a first linkage lever 11, a second linkage lever 15, and a third linkage lever. Rod 16, spoiler 4, lower baffle 6, sealing rubber 7,
主翼后梁固定杆9的一端固定在主翼1上的后梁12下缘条处，主翼后梁固定杆9的这一端的宽度与后梁7的下缘条宽度相同，主翼后梁固定杆9的另一端通过主铰链13与Y形支架8的一端铰接，主翼后梁固定杆9的宽度光滑渐变至与主铰链13的直径相同；Y形支架8的另外两个端面分别固定在主襟翼2中的主襟翼梁下部和后襟翼3中的后襟翼梁下部，Y形支架8固定在主襟翼2中的主襟翼梁下部的端面宽度是主襟翼梁下缘条宽度的2倍，Y形支架8固定在后襟翼3中的后襟翼梁下部的端面宽度是后襟翼梁下缘条宽度的2.5倍；连杆14的一端固定在主翼后梁固定杆9上靠近主铰链13处，此固定位置到主铰链13的距离为主翼后梁固定杆9长度的10%～25%，连杆14的另一端与第一联动杆11的一端铰接；第一联动杆11的另一端同时与第二联动杆15的一端、第三联动杆16的一端铰接，第二联动杆15的另一端铰接在Y形支架8上的主襟翼2一侧的内壁上，此铰接位置到主襟翼下表面的距离是主襟翼后梁下缘条到主铰链13的距离的15%～25%，第三联动杆16的另一端铰接在下挡板6的下表面；One end of the main wing rear beam fixed rod 9 is fixed on the rear beam 12 lower edge strips on the main wing 1, the width of this end of the main wing rear beam fixed rod 9 is the same as the lower edge width of the rear beam 7, and the other end of the main wing rear beam fixed rod 9 passes through the main wing. The hinge 13 is hinged with one end of the Y-shaped bracket 8, and the width of the main wing rear beam fixing rod 9 smoothly gradually changes to the same diameter as the main hinge 13; the other two end surfaces of the Y-shaped bracket 8 are respectively fixed on the main flaps in the main flap The lower part of the beam and the lower part of the rear flap beam in the rear flap 3, the Y-shaped bracket 8 is fixed in the main flap 2. The end face width of the lower part of the main flap beam in the main flap 2 is twice the width of the lower edge strip of the main flap beam, Y-shaped The end face width of the lower part of the rear flap beam in which the support 8 is fixed in the rear flap 3 is 2.5 times the width of the lower edge of the rear flap beam; one end of the connecting rod 14 is fixed on the main wing rear beam fixed rod 9 near the main hinge 13, The distance from this fixed position to the main hinge 13 is 10% to 25% of the length of the main wing rear beam fixed rod 9, and the other end of the connecting rod 14 is hinged with an end of the first linkage rod 11; One end of the second linkage rod 15 and one end of the third linkage rod 16 are hinged, and the other end of the second linkage rod 15 is hinged on the inner wall of the main flap 2 side on the Y-shaped bracket 8, and the hinged position is to the lower surface of the main flap. The distance is 15% to 25% of the distance from the lower edge of the main flap rear beam to the main hinge 13, and the other end of the third linkage rod 16 is hinged on the lower surface of the lower baffle 6;
此铰接位置与主襟翼铰链17的距离为下挡板6长度的25%～50%；The distance between this hinged position and the main flap hinge 17 is 25% to 50% of the length of the lower baffle 6;
下挡板6的一端通过主襟翼铰链17铰接在主襟翼2上主襟翼梁下缘条的后方，下挡板6的另一端固定有一个密封胶皮7,密封胶皮7与后襟翼3前缘贴合，将后襟翼舱5下部分密封；One end of the lower baffle 6 is hinged behind the lower edge of the main flap beam on the main flap 2 through the main flap hinge 17, and the other end of the lower baffle 6 is fixed with a sealing rubber 7, which is connected with the rear flap 3. The front edge is attached to seal the lower part of the rear flap compartment 5;
作动筒10的固定端铰接在主翼后梁固定杆9上，此铰接位置到主翼1上的后梁12下缘条的距离为后梁固定杆9长度的5%～30%，作动筒10的活动端铰接在Y形支架8上，此铰接位置到主襟翼梁下缘条的距离为主铰链13到主襟翼梁下缘条的距离的20%～60%；The fixed end of the actuator 10 is hinged on the main wing rear beam fixed rod 9. The distance from the hinged position to the lower edge of the rear beam 12 on the main wing 1 is 5% to 30% of the length of the rear beam fixed rod 9. The movement of the actuator 10 The end is hinged on the Y-shaped bracket 8, and the distance from the hinge position to the lower edge of the main flap beam is 20% to 60% of the distance from the main hinge 13 to the lower edge of the main flap beam;
主翼1上的扰流板4的尾部搭在后襟翼3中的后襟翼梁上缘条处，将后襟翼舱5遮住，扰流板4与主襟翼2的尾部有间隙。The afterbody of the spoiler 4 on the main wing 1 rides on the rear flap beam upper edge place in the rear flap 3, and the rear flap cabin 5 is covered, and the afterbody of the spoiler 4 and the main flap 2 has a gap.
本发明可以分6步来实现：The present invention can be realized in 6 steps:
（1）如图所示，按照总体设计要求，分别确定主翼1及扰流板4的长度，确定主襟翼2前缘到后襟翼3后缘的总长度；(1) As shown in the figure, according to the overall design requirements, determine the lengths of the main wing 1 and the spoiler 4 respectively, and determine the total length from the leading edge of the main flap 2 to the trailing edge of the rear flap 3;
（2）扰流板4的长度以扰流板4可以完全覆盖主襟翼2和后襟翼间的后襟翼舱5上部为标准，确定主襟翼2和后襟翼3的尺寸；(2) The length of the spoiler 4 is based on the fact that the spoiler 4 can completely cover the upper part of the rear flap compartment 5 between the main flap 2 and the rear flap, and the dimensions of the main flap 2 and the rear flap 3 are determined;
（3）设计出主襟翼2和后襟翼3的剖面外形，将主襟翼2和后襟翼3都固定在Y形支架8上，Y形支架8通过主铰链13铰接在主翼后梁固定杆9上；(3) Design the cross-sectional shape of the main flap 2 and the rear flap 3, fix the main flap 2 and the rear flap 3 on the Y-shaped bracket 8, and the Y-shaped bracket 8 is hinged to the main wing rear beam through the main hinge 13 and fixed on pole 9;
（4）连杆14的一端固定在主翼后梁固定杆9上，另一端与第一联动杆11铰接，第一联动杆11的另一端与第二联动杆15的一端、第三联动杆16的一端铰接，第二联动杆15的另一端铰接在Y形支架8上，第三联动杆16的另一端铰接在下挡板6上；(4) One end of the connecting rod 14 is fixed on the main wing rear beam fixed rod 9, and the other end is hinged with the first linkage rod 11, and the other end of the first linkage rod 11 is connected with one end of the second linkage rod 15 and the third linkage rod 16. One end is hinged, the other end of the second linkage rod 15 is hinged on the Y-shaped bracket 8, and the other end of the third linkage rod 16 is hinged on the lower baffle plate 6;
（5）密封胶皮7固定在下挡板6的靠近后襟翼3头部的一端。(5) The sealing rubber 7 is fixed on the end of the lower baffle 6 close to the head of the rear flap 3 .
（6）作动筒10的固定端铰接在主翼后梁固定杆9上，作动筒10的活动端铰接在Y形支架8上，通过作动筒10的活动端的伸缩运动，驱动Y形支架8、主襟翼2和后襟翼3同时转动，Y形支架8带动第二联动杆15、第一联动杆11和第三联动杆16转动，第三联动杆16带动下挡板6绕着主襟翼铰链17进行偏转。(6) The fixed end of the actuator 10 is hinged on the fixed rod 9 of the main wing rear beam, the movable end of the actuator 10 is hinged on the Y-shaped bracket 8, and the Y-shaped bracket 8 is driven by the telescopic movement of the movable end of the actuator 10 , the main flap 2 and the rear flap 3 rotate at the same time, the Y-shaped bracket 8 drives the second linkage lever 15, the first linkage lever 11 and the third linkage lever 16 to rotate, and the third linkage lever 16 drives the lower baffle plate 6 around the main The flap hinge 17 is deflected.
本发明通过以下步骤实现飞机襟翼的偏转运动：The present invention realizes the deflection motion of aircraft flap by following steps:
(1)飞机在巡航状态时，主襟翼2和后襟翼3处于收起状态，下挡板6和密封胶皮7封闭后襟翼舱5；(1) When the aircraft is in the cruising state, the main flap 2 and the rear flap 3 are in the retracted state, and the lower baffle 6 and the sealing rubber 7 seal the rear flap compartment 5;
(2)飞机在起飞状态时，作动筒10的活动端向外伸出，推动Y形支架8、主襟翼2、后襟翼3和下挡板6同时偏转，直到主襟翼2偏转到起飞状态预定的角度，作动10的活动端停止运动；(2) When the aircraft is in the take-off state, the movable end of the actuator 10 protrudes outward, pushing the Y-shaped bracket 8, the main flap 2, the rear flap 3 and the lower baffle 6 to deflect at the same time until the main flap 2 deflects To the predetermined angle of the take-off state, the movable end of the actuator 10 stops moving;
(3)飞机在着陆状态时，作动筒10的活动端继续向外伸出，推动Y形支架8、主襟翼2、后襟翼3和下挡板6同时偏转，直到主襟翼2偏转到着陆状态预定的角度，作动10的活动端停止运动；(3) When the aircraft is in the landing state, the movable end of the actuator 10 continues to protrude outward, pushing the Y-shaped bracket 8, the main flap 2, the rear flap 3 and the lower baffle 6 to deflect at the same time until the main flap 2 Deflection to a predetermined angle in the landing state, the movable end of the actuator 10 stops moving;
(4)飞机在停止前的地面滑跑时，作动筒10的活动端向内缩进，推动Y形支架8、主襟翼2、后襟翼3和下挡板6同时偏转，直到主襟翼2偏转到收起状态，作动10的活动端停止运动。(4) When the aircraft is taxiing on the ground before stopping, the movable end of the actuator 10 is retracted inwardly, pushing the Y-shaped bracket 8, the main flap 2, the rear flap 3 and the lower baffle 6 to deflect at the same time until the main The flap 2 is deflected to the retracted state, and the movable end of the actuator 10 stops moving.
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9580168B2 (en) * | 2014-12-19 | 2017-02-28 | The Boeing Company | Cove lip door slaved to trailing edge control device |
| CN109018300B (en) * | 2018-08-16 | 2020-02-04 | 晨龙飞机（荆门）有限公司 | Adjustable wing slat on aircraft wing |
| CN110294102B (en) * | 2019-04-26 | 2023-05-23 | 庆安集团有限公司 | Compound kinematic mechanism of integrated flaperon |
| CN112339987B (en) * | 2020-10-29 | 2022-06-28 | 中电科芜湖通用航空产业技术研究院有限公司 | Double-slit wing flap with wing flap fixedly connected with additional wing |
| CN112678150B (en) * | 2020-12-31 | 2024-04-26 | 中国商用飞机有限责任公司 | Aircraft trailing edge flap |
| CN113104196B (en) * | 2021-05-28 | 2022-05-24 | 中国商用飞机有限责任公司 | High-lift device and high-lift method for aircraft |
| CN115384757B (en) * | 2022-10-31 | 2023-01-24 | 北京启时智航科技有限公司 | Flaperon actuating mechanism and wing structure |
| CN115817795B (en) * | 2022-12-27 | 2023-08-01 | 江苏华阳重工股份有限公司 | High-performance flap rudder body |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1982157A (en) * | 2005-11-21 | 2007-06-20 | 波音公司 | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
| WO2009067319A3 (en) * | 2007-11-16 | 2009-07-23 | Boeing Co | Method and apparatus for a multi-segment flap fence |
| CN101678893A (en) * | 2007-04-24 | 2010-03-24 | 空中客车运营有限公司 | Aircraft |
| CN102137793A (en) * | 2008-08-28 | 2011-07-27 | 空中客车营运有限公司 | High lift system for an aircraft with a high lift flap and method for adjusting the high lift flap |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102007020870A1 (en) * | 2007-05-04 | 2008-11-13 | Airbus Deutschland Gmbh | High-lift system on the wing of an aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1982157A (en) * | 2005-11-21 | 2007-06-20 | 波音公司 | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
| CN101678893A (en) * | 2007-04-24 | 2010-03-24 | 空中客车运营有限公司 | Aircraft |
| WO2009067319A3 (en) * | 2007-11-16 | 2009-07-23 | Boeing Co | Method and apparatus for a multi-segment flap fence |
| CN102137793A (en) * | 2008-08-28 | 2011-07-27 | 空中客车营运有限公司 | High lift system for an aircraft with a high lift flap and method for adjusting the high lift flap |
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