阅读说明：本技术 襟翼系统、机翼以及飞行器 (Flap system, wing and aircraft ) 是由 安德烈亚斯·格里明格尔 马库斯·吉贝特 伯恩哈德·施利普夫 布拉任科·科斯科维奇 于 2019-07-10 设计创作，主要内容包括：本发明涉及襟翼系统、机翼以及飞行器,该襟翼系统(2)用于在缩回位置与伸展位置之间驱动前缘襟翼(28),该襟翼系统(2)包括具有第一襟翼接头(34)和第二襟翼接头(36)的前缘襟翼(28)、第一剪刀式杆(8)、第二剪刀式杆(24)、第一连接杆(18)、以及致动器(48)。致动器(48)与第一剪刀式杆(8)联接或者与第一连接杆(18)联接,其中,第一剪刀式杆(8)包括用于将第一剪刀式杆(8)以可旋转的方式支承在第一结构固定点(10)上的第一支承接头(14),并且其中,致动器(48)、第一剪刀式杆(8)、第二剪刀式杆(24)和第一连接杆(18)布置成主动地将前缘襟翼(28)从缩回位置置于伸展位置。(The invention relates to a flap system, a wing and an aircraft, the flap system (2) being used for driving a leading edge flap (28) between a retracted position and an extended position, the flap system (2) comprising the leading edge flap (28) with a first flap joint (34) and a second flap joint (36), a first scissor lever (8), a second scissor lever (24), a first connecting rod (18) and an actuator (48). An actuator (48) is coupled with the first scissor lever (8) or with the first connecting rod (18), wherein the first scissor lever (8) comprises a first support head (14) for rotatably supporting the first scissor lever (8) on the first structure fixing point (10), and wherein the actuator (48), the first scissor lever (8), the second scissor lever (24) and the first connecting rod (18) are arranged to actively bring the leading edge flap (28) from the retracted position into the extended position.)

1. A flap system (2) for driving leading edge flaps (28) between a retracted position and an extended position, the flap system (2) comprising:

-a leading-edge flap (28) having a first flap joint (34) and a second flap joint (36);

-a first scissor lever (8);

-a second scissor lever (24);

-a first connecting rod (18); and

-an actuator (48),

wherein the actuator (48) is coupled with the first scissor lever (8) or with the first connecting lever (18),

wherein the first scissor lever (8) comprises a first support head (14) for rotatably supporting the first scissor lever (8) on a first structure fixing point (10), wherein an end of the first scissor lever (8) opposite the first support head (14) is coupled with the first flap joint (34),

wherein the first connecting rod (18) comprises a second bearing joint (22) for rotatably supporting the first connecting rod (18) on a second structure fixing point (20), and wherein an end (26) of the first connecting rod (18) opposite the second bearing joint (22) is rotatably coupled with an end of the second scissor rod (24),

wherein an end of the second scissor lever (24) opposite the end coupled with the first connecting lever (18) is coupled with the second flap joint (36),

wherein, in addition, the first scissor lever (8) and the second scissor lever (24) are rotatably coupled to each other to form a scissor arrangement, and

wherein the actuator (48), the first scissor lever (8), the second scissor lever (24) and the first connecting lever (18) are arranged to actively place the leading edge flap (28) from a retracted position into an extended position.

2. The flap system (2) of claim 1,

wherein the first scissor lever (8) is coupled to the flap (28) by a second connecting rod (30), the second connecting rod (30) being rotatably supported to the first scissor lever (8) and rotatably supported to the first flap joint (34).

3. The flap system (2) of claim 2,

wherein the length of the second connecting rod (30) is shorter than the length of the first connecting rod (18).

4. The flap system (2) of claim 3, wherein the length of the second connecting rod (30) is less than one third of the length of the first connecting rod (18).

5. The flap system (2) of one of the preceding claims,

wherein one of the first and second scissor levers (8, 24) comprises a recess (70) along a main extension direction, the other of the first and second scissor levers (8, 24) passing through the recess (70), and

wherein the first scissor lever (8) and the second scissor lever (24) are rotatably coupled in the region of the recess (70).

6. The flap system (2) of one of the preceding claims,

wherein the first and second scissor levers (8, 24) comprise a rotary scissor joint (38) for coupling the first and second scissor levers (8, 24), wherein the scissor joint (38) is arranged in a central region of each scissor lever (8, 24).

7. The flap system (2) of one of the preceding claims,

wherein the second scissor lever (24) is directly coupled with the flap (28).

8. The flap system (2) of one of the preceding claims,

wherein only a single actuator (48) is used.

9. The flap system (2) of one of the preceding claims,

wherein the actuator (48), the first scissor lever (8), the second scissor lever (24), and the first connecting lever (18) are arranged to actively bring the leading edge flap (28) from a retracted position to an intermediate position in which a chord axis (56) of the flap (28) is adjusted to a desired angle, and the actuator (48), the first scissor lever (8), the second scissor lever (24), and the first connecting lever (18) are arranged to provide a translational movement subsequently along the chord axis (56) of the flap (28).

10. A wing (6), the wing (6) having a leading edge region (4) and a trailing edge region and having at least one flap system (2) according to one of claims 1 to 9, the flap system (2) being mounted in the wing (6).

11. The wing (6) of claim 10, wherein the flap system (2) is arranged in the leading edge region (4).

12. The wing (6) of claim 10 or 11, wherein the flap system (2) is designed to move the flap (28) below a leading edge point (60) of the wing until an angle between a local flap chord (56) and a local wing chord (54) is 117 °.

13. The wing (6) of any of claims 10 to 12, wherein the flap system is further designed to limit a gap (58) between a trailing edge (42) of the flap (28) and a leading edge point (60) of the wing (6) to 2% of the local wing chord (54).

14. An aircraft (76) with at least one wing (6) according to any of claims 10 to 13.

Technical Field

The invention relates to a system for driving a flap arrangement between a retracted position and an extended position, a wing with such a system, and an aircraft.

Background

In commercial aircraft, so-called high-lift systems are usually provided on the wings, so that the lift-generating area of the wings can be increased and the camber of the wings can be increased. Mainly, these high lift systems comprise trailing edge flap arrangements and leading edge flap arrangements. For example, the leading edge flap arrangement comprises the following flaps: the flap extends from a recess at the underside of the wing to a position upstream of the wing. For such so-called krueger flaps, there are many different actuating mechanisms.

Krueger flaps are typically stored at the underside of the wing with the trailing edge pointing in the forward direction and the leading edge pointing in the aft direction. During deployment of the flap, the flap generally follows a rotational movement to reach a position in front of the leading edge of the wing with a gap to the leading edge of the wing, wherein the leading edge of the flap points in the flight direction and wherein the trailing edge points in the aft direction.

DE102011018906a1 shows an exemplary leading-edge flap system with krueger flaps. Here, an additional retaining element is attached to the trailing edge of the flap to influence the gap between the flap and the leading edge of the wing.

EP2509859B1 shows a high lift system which may also comprise a krueger flap which has a specific design which shapes the gap created between the flap and the leading edge of the wing into a strict convergence.

Disclosure of Invention

A common kinematics for extending a leading-edge flap in the form of a krueger flap generally provides a strict movement of the leading-edge flap attached to a lever which is turned about a rotational axis. Thus, the angle between the flap chord axis and the wing chord axis is substantially proportional to the position of the lever. However, it may be advantageous to provide different motions to optimize the gap between the leading edge flap and the leading edge of the wing and to optimize the airflow over the flap and the wing.

It is therefore an object of the present invention to propose an improved flap system for providing movement of leading-edge flaps, which improves the airflow in the flap region, while the system should be as simple as possible.

This object is met by a flap system according to the application. Advantageous embodiments and further developments can be gathered from the following description.

A flap system for driving a leading edge flap between a retracted position and an extended position is proposed, which system comprises a leading edge flap having a first flap joint and a second flap joint, a first scissor lever, a second scissor lever, a first connecting lever, and an actuator, wherein the actuator is coupled with the first scissor lever or with the first connecting lever, wherein the first scissor lever comprises a first support joint for rotatably supporting the first scissor lever on a first structural fixing point, wherein an end of the first scissor lever opposite the first support joint is coupled with the first flap joint, wherein the first connecting lever comprises a second support joint for rotatably supporting the first connecting lever on a second structural fixing point, and wherein an end of the first connecting lever opposite the second support joint is rotatably coupled with an end of the second scissor lever, and wherein an end of the second scissor lever opposite to the end coupled with the first link lever is coupled with the second flap joint, wherein additionally the first scissor lever and the second scissor lever are rotatably coupled with each other to form a scissor arrangement, and wherein the actuator, the first scissor lever, the second scissor lever and the first link lever are arranged to actively place the leading edge flap from the retracted position to the extended position.

The main advantage of the flap system according to the invention is that the proportional or strict coupling of the leading edge flap angle and the flap deployment state is eliminated. A scissor device coupled to the first structure-fixed point on only one end of one of the scissor levers will rotate about the first structure-fixed point and will change the angle between the flap and the wing chord until a specific relationship between the scissor device's rotational position and the scissor device's closed state. This may be considered an intermediate position. In this regard, a scissor arrangement is "closed" if the scissor levers generally do not enclose an angle and are positioned flush with each other. The closed state is considered to be the degree to which the scissor is closed. After reaching the intermediate position, the flap angle may remain substantially constant or change only slightly. This means that the desired flap deployment angle can be almost reached before the flap is fully deployed. After this, the flap may provide a substantially translational movement. This improves the shape of the gap at an earlier stage of deployment compared to conventional krueger flap arrangements.

The main flap may be a flow body having an elongated shape and having a leading edge and a trailing edge. The main flap may be curved in a similar manner to a conventional krueger flap or another type of airflow influencing control surface of an aircraft. A main flap is a leading-edge flap intended to be moved relative to the leading edge of the wing. In the retracted state, the flap is arranged in a recess at the underside of the wing. The movements referred to in this application relate to deployment movements from the recess to a position in front of the leading edge of the wing.

The flap system according to the invention is based on a scissor arrangement consisting of two scissor levers, wherein one of the scissor levers is rotatably supported on a structural fixing point and wherein the other scissor lever is supported on a first connecting rod. The first connecting rod is in turn rotatably connected to another structure-fixing point. By moving the first connecting rod, the end of the second scissor lever rotates about the first structural fixed point. Depending on the length of the first connecting rod, the distance of the first structure fixing point from the second structure fixing point and the dimensions of the two scissor levers, a movement of the flap is caused. In the following, the components are described in more detail.

The actuator may be a rotary actuator, which is illustratively coupled directly to the first connecting rod. The actuator may also be coupled to a structural fixing point in the mounted state on the wing. By rotating the actuator, the first connecting rod rotates around the second structure-fixing point and thus moves the second scissor rod. However, the actuator may also be coupled with the first scissor lever and the structural fixation point to rotate the first scissor lever in a circular path.

The first scissor lever includes two ends, wherein one of the ends is rotatably coupled with the first structure fixation point. The first scissor lever is thus able to pivot about the first structure fixation point. An end of the first scissor lever opposite the first structure fixation point is coupled with the first flap joint. Thus, the first scissor lever does not have to be directly coupled with the first flap joint. Instead, intermediate parts or components can also be provided between the first flap joint and the first scissor lever.

The second scissor lever also includes two ends, wherein one of the ends is rotatably coupled with the first connecting rod, and wherein the other end is rotatably coupled with the second flap joint. The second scissor lever is thus able to pivot about the end of the first connecting lever opposite the end connected to the first structural fixing point. Thus, when the first connecting rod is turned by the action of the actuator, the second scissor rod is also pushed into motion.

Both scissor levers are equipped with another joint, which will be referred to as scissor joint. The scissor joint is arranged in a region between two ends of each of the scissor levers and causes the creation of a scissor arrangement. This means that the two scissor levers cross each other and may assume different angles with respect to each other.

By moving the first connecting rod, the entire scissor device is thus pushed into rotation about the end of the first scissor rod that is rotatably coupled with the first structure fixation point. The dimensional relationship between the rods and the links of the rods determines the final movement of the scissor rods, i.e. the angle between the two scissor rods, and determines the rotation of the first scissor rod about the inner end of the first scissor rod that is linked to the first structural fixing point. Thus, the flap system according to the invention can be adjusted such that: even in the case where the trailing edge of the flap is located below the chord axis of the wing to which the flap system can be attached, the leading edge of the flap is in a relatively far forward position. Thus, a gap between the flap and the leading edge of the wing can be achieved while the flap is still just below the wing chord axis when in the neutral position.

Subsequent movement of the flap to the fully extended position maintains a particular gap size as the position of the flap is changed to the desired extended position. This may include a slight rearward movement and a slight further rotation.

In a preferred embodiment, the first scissor lever is coupled with the flap by a second connecting rod which is rotatably supported to the first scissor lever and to the first flap joint. This enables the flap angle to remain substantially constant over a particular range of deployed conditions. Preferably, the second connecting rod has a length shorter than that of the first connecting rod. In particular, the second connecting rod is significantly shorter than the first connecting rod, and the length of the second connecting rod is equal to one third or less of the length of the first connecting rod. This can generally increase the compactness of the flap system, since in case of a considerable angle between the scissor levers, the leading edge flaps fit closely at the underside of the wing with all levers folded onto or into each other. Still further, the flap system allows for over-locking of the second connecting rod, which ensures that more translational movement, rather than more rotational movement, of the flap from the neutral position to the final fully deployed setting is achieved.

Preferably, one of the first and second scissor levers comprises a recess along the main direction of extension, wherein the other of the first and second scissor levers passes through the recess, and wherein the first and second scissor levers are rotatably coupled in the region of the recess. The recesses may illustratively comprise the shape of slots or slits and the recesses may extend through a major portion of the respective scissor levers. The main part of the respective scissor lever can thus be designed in the form of a fork head, wherein the two limbs of the fork head enclose a gap through which the other of the scissor levers extends. A joint for coupling the scissor levers may be arranged in the space between the limbs.

The first and second scissor levers may each include a scissor joint for coupling the first and second scissor levers, wherein the scissor joint is disposed in a central region of each scissor lever. The term "central region" is to be understood as the following regions of the respective rod: this region is located between the two ends and extends along about 50% of the total length of the single scissor lever, i.e. along about 25% of the respective length from the center of the lever to both directions. The scissor joint may be disposed at any point of the central region. The dimensional relationship is related to the center axis of the scissor joint.

In a preferred embodiment, the second scissor lever is directly coupled with the second flap joint. By directly coupling, i.e. rotatably coupling, the second scissor lever with the flap, the second flap joint is moved only by the movement of the second scissor lever. Therefore, no additional guide such as a linear guide is required. This simplifies the mechanical design of the system according to the invention.

Furthermore, only a single actuator may be used. Thus, the advantages of the flap system can be achieved by moving only one of the levers, without having to utilize a second actuator for, for example, changing the angular or translational position of the flap relative to the wing on which the flap system is mounted. The flap system according to the invention provides the desired movement of the flap simply but effectively.

Preferably, the actuator, the first scissor lever, the second scissor lever and the first connecting lever are arranged to actively bring the leading edge flap from a retracted position to an intermediate position in which the chord axis of the flap is adjusted to a desired angle, and the first scissor lever, the second scissor lever and the first connecting lever are arranged to provide a subsequent substantially translational movement along the chord axis of the flap, while the orientation of the chord axis remains substantially constant or increases slightly, for example by about 10 ° to 15 °. Therefore, all of the levers used in the flap system should be designed in such a way that this property can be achieved. Thus, the flap presented in the above description will be moved to a forward position in which the local flap chord has assumed the desired angle just before the local chord axis of the wing is reached. The flap may then be moved in a substantially translational manner along the chord axis into a fully extended position with a certain gap between the leading edge of the wing and the leading edge flap.

As set forth further below, the particular angle in the intermediate position may be about 117 °. In the extended position, the angle may be about 130 °. However, these angles may vary slightly, for example by about ± 2 °.

The invention also relates to a wing having a leading edge region and a trailing edge region and having at least one flap system according to the above description.

Advantageously, the system is arranged in the leading edge region.

Preferably, the flap system is designed to move the flap to an intermediate position below the wing leading edge point until the angle between the local flap chord and the local wing chord is 117 °. This prevents flow separation on the upper side of the wing. The position of the flap just below the leading edge point of the wing is considered to be the intermediate position mentioned above and further mentioned below.

In a subsequent extension from the intermediate position to the extended position, the local flap chord and the local wing chord attain an exemplary angle of 130 °. The flap then has been moved in a substantially translatory motion along the leading edge of the wing, with the gap maintained.

The flap system is also designed to define a gap between the trailing edge of the flap and the leading edge point of the wing of 2% of the local wing chord. This allows for a coordinated airflow from the flap to the upper side of the wing. The gap between the trailing edge of the flap and the leading edge of the wing should be no more than 2% of the local wing chord. This prevents flow separation on the wing during deployment of the flap. This may include intermediate positions. Further, this may include an extended position.

Finally, the invention relates to an aircraft having at least one such wing.

Drawings

Further features, advantages and potential applications of the invention result from the following description of exemplary embodiments illustrated in the drawings. In this respect, all described and/or graphically illustrated features also form the object of the invention both individually and in any combination, irrespective of the constitution of the features in a single claim or the reference of the features to other claims. Further, in the drawings, the same or similar objects are identified by the same reference numerals.

Fig. 1 shows, in a schematic side view, a flap system according to the invention in a retracted state at the leading edge of a wing.

Fig. 2 shows a flap system according to the invention in a schematic side view in an intermediate state at the leading edge of a wing.

Fig. 3 shows, in a schematic side view, a flap system according to the invention in an extended state at the leading edge of a wing.

Fig. 4 shows a flap system according to the invention in three dimensions in an extended state at the leading edge of a wing.

Fig. 5 shows an aircraft with a wing comprising at least one flap system according to the invention.

Detailed Description

Fig. 1 shows a flap system 2 mounted in a leading edge region 4 of a wing 6. The flap system 2 comprises a first scissor lever 8, which first scissor lever 8 is mounted on a first structure fixing point 10 in a rotatable manner or in a rotatable manner. For example, inner end 12 of first scissor lever 8 includes a rotary joint 14, and rotary joint 14 is connected to first structure fixing point 10 of wing 6. First scissor lever 8 also includes an outer end 16, where outer end 16 is opposite first end 12.

Flap system 2 further comprises a first connecting rod 18, which first connecting rod 18 is rotatably or rotatably mounted on a second structure fixing point 20. To this end, the first connecting rod 18 comprises a rotary joint 22.

The first connecting rod 18 and the first scissor lever 8 are coupled by a second scissor lever 24. An outer end 26 of the first connecting rod 18 is rotatably coupled with the second scissor lever 24, which outer end 26 is arranged at the end of the second scissor lever 24. The other end of the second scissor lever 24 opposite the outer end 26 is rotatably coupled with a flap 28. The outer end 16 of the first scissor lever 8 is in turn coupled to a second connecting rod 30 by a rotary joint 32. The end of the second connecting rod 30 opposite the outer end 16 is coupled to the flap 28 by means of a further rotary joint 34. In the following, the connection point of the second connecting rod 30 to the flap 28 is referred to as first flap joint 34. Similarly, the rotary joint 36 between the second scissor lever 24 and the flap 28 is referred to as a second flap joint 36.

Further, first scissor lever 8 and second scissor lever 24 include scissor joint 38, with both scissor lever 8 and scissor lever 24 being rotatably supported relative to each other by scissor joint 38.

Fig. 1 shows the flap 28 in a fully retracted position. Here, the leading edge 40 of the flap 28 is in a rearward position and the trailing edge 42 of the flap 28 is in a forward position. The flap 28 provides a continuous surface for the surrounding part of the wing 6. To this end, the wing 6 comprises a recess 44 at its lower side 46.

When the flap system 2 is moved according to fig. 2, the actuator 48, which is exemplarily identified at the second structure fixing point 22, moves the first connecting rod 18 in the clockwise direction. Thus, the outer end 26 of the first connecting link 18 pushes the second scissor lever 24 in a forward direction. In this case, the second flap joint 36 also moves in the forward direction. Due to the bearing on the first structure fastening point 10, the first scissor lever 8 follows the movement of the second scissor lever 24, since the two scissor levers are connected to each other by the scissor joint 38. The angle γ, denoted γ, between the extension direction 50 of the first scissor lever 8 and the extension direction 52 of the second scissor lever 24 decreases with increasing movement of the first connecting link 18. In the position shown in fig. 2, the direction of extension of the second connecting rod 30 is substantially parallel to the direction of extension 50 of the first scissor lever 8. When the first connecting rod 18 is moved further in the clockwise direction, the angle γ will decrease and the second connecting rod 30 will be over-locked. The dimensional relationships of all the rods in fig. 2 are dimensioned such that: the trailing edge 42 of the flap 28 is approximately at the same height as the local wing chord 54, while the angle α between the local flap chord 56 and the wing 6 is approximately 117 °. This is considered the neutral position. The gap 58 between the trailing edge 42 of the flap 28 and the leading edge 60 of the wing 6 amounts to a maximum of 2% of the local wing chord.

FIG. 3 shows: with further movement of the first connecting rod 18, the angle γ decreases and thus the second connecting rod 30 is rotated about the outer end of the first scissor lever 8, which results in a further upward, substantially translational movement of the leading edge flap 28, maintaining the gap 58 between the leading edge 60 of the wing 6 and the lower side 62 of the flap 28. In this position, the angle α between the local flap chord 56 and the wing 6 is about 130 °, which position is considered to be the extended position. Thus, a simple mechanism can provide a very advantageous movement of the flap 28 by providing a considerable angle between the local flap chord 56 and the local wing chord 54, and can provide the flap 28 already in the middle of the extended movement and maintain the gap 58 between the middle position and the extended position, which improves the airflow and prevents flow separation on the upper side of the wing 6.

Fig. 4 shows the design of the flap system 2 in a three-dimensional view. Here, it is apparent that the first connecting rod 18 may comprise two separate sub-rods 64 and 66, the sub-rods 64 and 66 together forming the first connecting rod. The first scissor lever 8 is designed at its outer end 16 as a fork head 68, so that a recess 70 is formed, through which recess 70 the second scissor lever 24 extends. Furthermore, the second connecting rod 30 is fitted between the two limbs 72 and 74 of the first scissor lever 8. Thus, a symmetrical arrangement of the rods is provided, which eliminates tilting or binding stresses etc.

Finally, fig. 5 shows an aircraft 76 with two wings 78 and 80: such flap systems 2 may be mounted to the wings 78 and 80 at the leading edge region 4.

Furthermore, it should be noted that "comprising" does not exclude other elements or steps and "a" or "an" does not exclude a plurality. Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments can also be used in combination with other characteristics or steps of other exemplary embodiments described above. Reference signs in the claims shall not be construed as limiting.