阅读说明：本技术 襟翼系统、机翼和飞行器 (Flap system, wing and aircraft ) 是由 马库斯·吉贝特 布拉任科·科斯科维奇 于 2019-05-31 设计创作，主要内容包括：本发明提供一种襟翼系统、一种机翼和一种飞行器,该系统包括：主襟翼、覆盖襟翼、具有将主连杆支承在第一结构固定点上的第一主连杆接合部和与主襟翼联接的第二主连杆接合部的主连杆、具有在距第一主连杆接合部一距离处与主连杆联接的第一辅助连杆接合部和与覆盖襟翼联接的第二辅助连杆接合部的辅助连杆、以及具有将连接连杆支承在第二结构固定点上的第一连接连杆接合部以及在第三辅助连杆接合部处与辅助连杆联接以用于将连接连杆支承在辅助连杆上的第二连接连杆接合部的连接连杆,连接连杆、辅助连杆和主连杆设置成：在主襟翼的缩回位置以活动的方式将覆盖襟翼放置在主襟翼的前方,以及在主襟翼的至少一个伸出位置将覆盖襟翼放置在主襟翼的后方。(The invention provides a flap system, a wing and an aircraft, the system comprising: a main flap, a covering flap, a main link with a first main link joint supporting the main link at a first structural fixing point and a second main link joint coupled with the main flap, an auxiliary link with a first auxiliary link joint coupled with the main link at a distance from the first main link joint and a second auxiliary link joint coupled with the covering flap, and a connecting link with a first connecting link joint supporting the connecting link at a second structural fixing point and a second connecting link joint coupled with the auxiliary link at a third auxiliary link joint for supporting the connecting link on the auxiliary link, the connecting link, the auxiliary link and the main link being arranged such that: the cover flap is movably placed in front of the main flap in its retracted position and in rear of the main flap in at least one extended position of the main flap.)

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

-a main flap (8),

-a covering flap (10),

-a main link (12),

-an auxiliary link (16), and

-connecting rod (14)

Wherein the main link (12) comprises a first main link joint (26) and a second main link joint (27), the first main link joint (26) being used for rotatably supporting the main link (12) on a first structure fixing point (24), the second main link joint (27) being rigidly coupled with the main flap (8),

Wherein the connecting link (14) comprises a first connecting link joint (36), the first connecting link joint (36) being used to rotatably support the connecting link (14) on a second structure fixing point (38), the second structure fixing point (38) being located behind the first structure fixing point (26), and the connecting link (14) further comprises a second connecting link joint (32),

wherein the auxiliary link (16) comprises a first auxiliary link joint (32), the first auxiliary link joint (32) being coupled with the main link (12) at a distance from the first main link joint (26), and the auxiliary link (16) further comprises a second auxiliary link joint (30) being coupled with the covering flap (10),

Wherein the second connecting link joint (32) is coupled with the auxiliary link (16) at a third auxiliary link joint (34) located between the first auxiliary link joint (32) and the second auxiliary link joint (30) for rotatably supporting the connecting link (14) on the auxiliary link (16), and

Wherein the connecting link (14), the auxiliary link (16) and the main link (12) are arranged to: the cover flap (10) is movably placed in front of the main flap (8) in a retracted position of the main flap (8), and the cover flap (10) is placed behind the main flap (8) in at least one extended position of the main flap (8).

2. The system (2) according to claim 1,

Wherein the main link (12) has an L-shape.

3. The system (2) according to claim 1 or 2,

Wherein the master link (12) has a first master link section (44), the first master link section (44) extending from the first master link joint (26) in the direction of the second master link joint (27) up to a transition region (45),

Wherein the main link (12) has a second main link section (46), the second main link section (46) extending from the transition region (45) in the direction of the second main link joint (27), and

Wherein the second main link segment (46) has a width (w2) in a direction parallel to the axis of rotation (48) of the first main link joint (26), the width (w2) being greater than the width (w1) of the first main link segment (44).

4. System (2) according to one of the preceding claims,

Wherein the master link (12) comprises a recess (50), the recess (50) extending perpendicular to the axis of rotation (48) of the first master link joint (26), and

Wherein the recess (50) is designed to move at least the connecting link (14) and the cover flap (10) through the recess (50) when moving the main flap (8).

5. System (2) according to claims 3 and 4,

wherein the recess (50) extends into the second main link section (46).

6. System (2) according to one of the preceding claims,

Wherein the cover flap (10) has a width in a direction parallel to the rotational axis (48) of the first main link joint (44) that exceeds the width (w1, w2) of at least a part of the main link (12).

7. System (2) according to one of the preceding claims,

wherein the second auxiliary link joint (30) comprises a rigid connection with the covering flap (10).

8. system (2) according to one of the preceding claims,

Wherein the third auxiliary link joint (34) is disposed less than 25% away from a center of the auxiliary link (16).

9. System (2) according to one of the preceding claims,

Wherein the connecting link (14) extends in the direction of the first main link joint (26) when the main flap (8) is in the retracted position.

10. An airfoil (6), the airfoil (6) having a leading edge region (4) and a trailing edge region, and at least one system (2) according to any one of claims 1 to 9 mounted within the airfoil (6).

11. The wing (6) as claimed in claim 10, the system (2) being arranged in the leading edge region (4).

12. Wing (6) according to claim 10 or 11, wherein the wing (6) comprises a cutout (42) for receiving at least a part of the main link (12), and wherein the cover flap (10) is designed to cover the cutout (42) in the retracted position of the main flap (8).

13. An aircraft having at least one wing (6) according to any of claims 10 to 12.

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 wing to allow for an increase in the lift generating area of the wing and the camber (camber) of the wing, mainly these high lift systems comprise trailing edge flap devices and leading edge flap devices.

Depending on the stowed position of the krueger flap in its retracted position and the actuation mechanism used to extend the krueger flap to the desired deployed position, an additional cut-out or recess is required in the fixed leading edge to allow the actuation mechanism to reach the maximum deployed position. The cut needs to be sealed to maintain a smooth outer surface for cruise flight conditions. Typically, these cuts are closed by a resilient seal.

In an alternative solution, the gap is at least partially sealed by a gap covering flap which is moved between an open position and a closed position by the action of the main flap.

DE 102008056655 a1 shows a gap covering device which is actuated by means of a device comprising a prestressed rod moved by a flap, and an adjusting mechanism for the gap covering device.

Disclosure of Invention

a device to close a cut-out in a leading edge of a wing for an actuation mechanism coupled with a leading edge krueger flap may be helpful: the device requires neither elastomeric seals nor complex mechanisms for deploying the cover flap.

It is therefore an object of the invention to propose a system for driving a flap arrangement which allows the extension and retraction of flaps and the sealing of the required cut-outs for the flap actuator, while the covering of the flap actuator should be as simple as possible.

This object is met by a flap system for driving a flap arrangement between a retracted position and an extended position having the features of the appended claim 1. Advantageous embodiments and further developments can be gathered from the dependent claims and the following description.

a flap system for driving a flap arrangement between a retracted position and an extended position is presented. The system includes a main flap, a cover flap, a main link, an auxiliary link, and a connecting link. The main link comprises a first main link joint for rotatably supporting the main link on a first structural fixing point and a second main link joint rigidly coupled with the main flap. The connecting link comprises a first connecting link joint for rotatably supporting the connecting link on a second structure fixing point located behind the first structure fixing point, and a second connecting link joint. The auxiliary link comprises a first auxiliary link joint coupled with the main link at a distance from the first main link joint, and the auxiliary link further comprises a second auxiliary link joint coupled with the cover flap. The second connecting link joint is coupled with the auxiliary link at a third auxiliary link joint located between the first and second auxiliary link joints for rotatably supporting the connecting link on the auxiliary link. Further, the connecting link, the auxiliary link, and the main link are provided: the cover flap is movably placed in front of the main flap in its retracted position and in rear of the main flap in at least one extended position of the main flap.

The main flap may be a flow body (flow body) having an elongated shape and a leading edge and a trailing edge. The main flap may be curved in a similar manner to a krueger flap or other types of flow affecting control surfaces of aircraft. In a preferred embodiment, the main flap is a leading-edge flap intended to be moved relative to the leading edge of the wing.

The main link is rigidly attached to the main flap and adapted to move the main flap between a retracted position and one or more extended positions by rotation of the main link about a first main link joint. When placing the main flap at the leading edge region of the wing, it is intended to fit the main flap tightly into the recess on the underside of the wing to completely close the recess and provide a continuous surface. However, because the main flap is moved between positions that are typically spaced very significantly apart using the main link, the wing also has a cutout for allowing the main link to move between the retracted position and the fully extended position. The cover flap is arranged for closing the additional incision by placing the cover flap over said incision. When the main flap is in its retracted position, the cover flap is directly adjacent to the main flap, i.e. directly in front of the main flap. The cover flap is thus part of the aerodynamic surface in the retracted position of the main flap. The master link may be curved or straight.

According to the invention, the covering flap is moved exclusively by means of a kinematic arrangement comprising a secondary link, a connecting link and attachments of the secondary link and the connecting link to the main flap and to the second structural fixing point. This means that the covering flap is driven only by the main flap and no special drive is required.

The covering flap is connected to a secondary link which follows the movement given by the connection with the main link and follows the movement constraint by means of a connecting link which can rotate about a second structure fixed point. Since the second structure-fixing point is located behind the first structure-fixing point, the movement of the covering flap relative to the main flap also depends on the arrangement of the two flaps in the retracted position of the main flap. Preferably, the cover flap is located in front of the main flap in the retracted position of the main flap. Thus, the main link and the connecting link cross each other when the main flap is in the retracted position.

As shown, the auxiliary link is moved by the induced motion of the first and third auxiliary link joints, thereby defining motion at the second auxiliary link joint. If the main link is moved into the extended position in a first rotational orientation, the auxiliary link is moved in the opposite rotational direction at least in a certain movement phase. Thus, by moving the main flap in a forward direction, the cover flap is moved backwards and releases the additional cut-out for allowing the movement of the main link into a forward direction into the cut-out.

In this respect, a "forward" direction should be understood as a first direction, which may be considered as a flight direction when the flap system is attached to an aircraft.

Therefore, the backward direction should be considered to be the opposite direction.

Furthermore, the term "rigidly" should be understood as securely holding the main flap or the cover flap without allowing a rotational or translational movement of the respective cover relative to the respective link.

In addition, flap arrangements are to be understood as meaning main flaps and covering flaps.

No additional elastomeric seals are required due to the use of the cover flap to close the additional cut for accommodating the motion of the master link in a movable manner (activery). The cover flap can be designed such that it fits tightly into the additional cutout. Furthermore, the cut-out may comprise a rest surface at least partially surrounding the additional cut-out to allow circumferential contact of the rest surface of the cover flap when covering the additional cut-out.

It may also be preferred to arrange the rest surface of the cover flap and the corresponding contact surface such that the cover flap is subjected to a certain pretension between the rest surface and the edge section of the cover flap. The pre-tension support covers precise alignment of the flap relative to the cutout.

In an advantageous embodiment, the main link has an L-shape. The L-shape may include a first leg and a second leg connected to each other at substantially a right angle. The first leg and the second leg may comprise different lengths. For example, the first leg may include a first master link joint. The first leg may include a greater length than the second leg. By this arrangement, the first structure fixing point can be placed in an upward, forward position of the flap system, wherein the main link extends in a rearward direction. At the rearwardmost position, the second leg may be extended in a downward direction. As a result, the main link can carry the main flap in an upside-down position at the lowermost space of the flap system. The L-shaped main link is commonly found in many leading edge high lift systems of aircraft. However, such a shape of the main link is not mandatory, and any shape is suitable as long as the main link is able to hold the main flap and provide a rotational movement of the main flap.

In an advantageous embodiment, the main link has a first main link section which extends from the first main link joint up to the transition region in the direction of the second main link joint, wherein the main link has a second main link section which extends from the transition region in the direction of the second main link joint, and wherein the second main link section has a greater width in a direction parallel to the axis of rotation of the first main link joint than the width of the first main link section. The second main linkage joint on the main flap therefore extends along a course which significantly exceeds the course of the first main linkage joint in a direction parallel to the axis of rotation. However, the cutout for accommodating the movement of the main link covered by the cover flap is dimensioned to conform to the first main link section. It is therefore advantageous to dimension the first main link section as narrow as possible.

The main link comprises a recess which extends perpendicularly to the axis of rotation of the first main link joint and through which recess at least the connecting link and the covering flap can be moved when moving the main flap. As mentioned above, the auxiliary link and the main link cross each other due to the spaced-apart position of the first and second structure-fixing points and the relative position of the main flap and the cover flap in the retracted state. Thus, the auxiliary link and connecting link must transmit the motion of the main link in a side-by-side relationship, or as suggested, pass through the main link through the recess. Thereby, a symmetrical introduction of the load between the main link, the connecting link and the auxiliary link is achieved.

in this respect, it is mentioned that the auxiliary link may exemplarily be connected to the main link from within the recess. Thus, the first auxiliary link joint may be coupled with a surface facing in a direction parallel to the axis of rotation defined by the first auxiliary link joint. Advantageously, two opposing attachment points may be used to couple the auxiliary link with the main link.

In an advantageous embodiment, the recess extends into the second main link section. Since the second main link section advantageously has a greater width than the width of the first main link section, the covering flap can simply pass through the recess in the region in the second main link section. Since the cover flap is intended for covering the additional cutout for accommodating the first main link section, the width of the cover flap is significantly smaller than the second main link section.

as mentioned above, the covering flap has a width in parallel with the rotational axis of the first main link joint that exceeds the width of at least a part of the main link. The cover flap has a width in the region around the first main link joint which at least slightly exceeds the width of the main link. In addition, the cover flap has a width in a direction parallel to the rotational axis of the first main link joint that is smaller than the width of at least a portion of the main link. In examples where the second main link section has a width greater than the width of the first main link section, the cover flap has a width between the two widths of the main link sections.

Preferably, the second auxiliary link joint comprises a rigid connection with a covering flap. The position of the covering flap is thus clearly defined by the movement of the auxiliary link. To compensate for temperature or motion induced deformations or dimensional changes, the covering flap may comprise a certain deformability. Alternatively, the connection with the auxiliary link may allow a slight angular rotatability.

in an advantageous embodiment, the third auxiliary link joint is arranged less than 25% away from the centre of the auxiliary link. Therefore, the third auxiliary link joint portion is provided substantially in the center of the auxiliary link. Thus, the auxiliary link may provide a significant rotational movement through the connecting link induced by the connection with the main link.

The connecting link can also be extended in the direction of the first main link joint when the main flap is in the retracted position.

The invention also relates to a wing for an aircraft, the wing comprising a leading edge region and a trailing edge region, the wing further comprising at least one system according to the above description.

obviously, when introducing the system into a wing, the main flap is preferably supported by at least two main links, which results in an integral combination of at least two auxiliary links and two connecting links for carrying two covering flaps.

Furthermore, it is obvious that the wing can be equipped with a plurality of flap systems.

preferably, the system according to the invention is arranged in the leading edge region of the wing.

It is also preferred that the wing comprises a cut-out for receiving at least a part of the main link, wherein the cover flap is designed to cover the cut-out in the retracted position of the main flap. When the main flap is in the retracted position, the cover flap forms part of the aerodynamic surface of the wing. Furthermore, the cut-out is preferably provided at the lower side of the leading edge region.

The invention also 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 which are shown in the drawings. In this respect, all described and/or visually illustrated features also form the object of the invention, both individually and in any combination, irrespective of their composition in the respective claims or their reference to other claims. Further, the same or similar objects are identified by the same reference numerals in the drawings.

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, in a schematic side view, a flap system according to the invention in a half-extended state at the leading edge of a wing.

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

Fig. 4 shows in a three-dimensional view a flap system according to the invention 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 arranged in a leading edge region 4 of a wing 6 of an aircraft. The flap system 2 comprises a main flap 8, a cover flap 10, a main link 12, a connecting link 14 and an auxiliary link 16. The main flap 8 has a profile with a flap leading edge 18 and a flap trailing edge 20. The main flap 8 can be designed similarly to a plain Krueger flap, and the illustration in the figure is merely schematic.

In fig. 1, the main flap 8 is fully retracted and placed on the underside of the wing 6. Here, the main flap 8 is in an upside-down orientation, i.e. with the leading edge 18 pointing backwards, the trailing edge 20 pointing forwards, and the upper side 22 pointing downwards. The main flap 8 can be moved into the extended position by rotating the main link 12 about a first structure-fixing point 24, at which first structure-fixing point 24 a first main link joint 26 is disposed. This movement is indicated by the curved arrow about the first structure fixation point 24. The main flap 8 is attached to the main link 8 at a second main link joint 27, the second main link joint 27 being opposite the first main link joint 26.

The master link 12 illustratively includes an L-shape. Here, the first main link section 44 extending up to the first main link joint 26 represents a first leg of the L-shape. The second main link section 46, which is arranged substantially at right angles to the first main link section 44 and extends up to the second main link joint 27, represents the second leg of the L-shape. A transition region 45 is provided between the two main link sections 44 and 46, the transition region 45 connecting the two main link sections 44 and 46 in a tangentially continuous manner.

The covering panel 10 has a crescent-shaped profile and is thinner than the main flap 8. In the retracted position, the cover flap 10 is placed in front of the main flap 8 and is directly connected to the trailing edge 20 of the main flap 8. As shown in the other figures, the cover flap 10 is intended for covering the cutout 28, the cutout 28 being intended to accommodate the main link 12 during the extension movement. This is further illustrated in fig. 3.

The covering flap 10 is connected to the auxiliary link 16 by means of a second auxiliary link joint 30, while in the illustration a first auxiliary link joint 32 is concealed by the main link 12. Preferably, the second auxiliary link joint 30 is intended to rigidly hold the covering flap 10 in a fixed geometric relationship.

The auxiliary link 16 includes a third auxiliary link joint 34, and the connecting link 14 is attached to the third auxiliary link joint 34. Further, the connecting link 14 includes a first connecting link joint 36 attached to a second structure securing location 38. The second structure securing location 38 is rearward of the first structure securing location 24.

The auxiliary link 16 rotates about the first auxiliary link joint 32 by moving the master link 12 about the first structure fixation point 24 and holding the connecting link 14 at the second structure fixation point 38. In the retracted position, i.e., the initial position, the connecting link 14 and the master link 12 cross each other.

in fig. 2, the main flap 8 is actuated from the retracted (initial) position in fig. 1 and is in the process of moving into the extended position. The fully extended position is shown in fig. 3, whereas in fig. 2 the main flap 8 is placed between the retracted position and the fully extended position. Here, the main link 12 is moved approximately 70 ° from the retracted position, and the main flap 8 is moved significantly out of the recess 40, the recess 40 being provided for accommodating the main flap 8 at the underside of the wing 6. Since the connecting link 14 is held at the second structure fixing point 38 by the first connecting link joint 36, the auxiliary link 16 is urged to rotate counterclockwise. However, the master link 12 rotates in a clockwise direction. During this movement, the covering flap 10 moves backwards and passes the main link 12. Further, the auxiliary link 16 is provided to conform (conform) to the position of the main link 12. In this state, the main flap 8 and the cover flap 10 have changed their sequence of positions along the longitudinal axis, i.e. in the forward or rearward direction. The main flap 8 is located almost completely in front of the covering flap 10.

In fig. 3, the extension movement of the main flap 8 is completed. Here, it can be seen that the master link 12 is located forward of the trailing edge 20 in the retracted position of the master link 8 (see fig. 1). Here, the additional cut-outs 42 required in the leading edge region 4 of the wing 6 are indicated by dashed lines. In the retracted position of the main flap 8, the cutout 42 will be closed by the cover flap 10, but the cutout 42 is now completely open to accommodate the main link 12.

In fig. 3, the spatial relationship between the connecting link 14 and the auxiliary link 16 is further illustrated. Illustratively, the connecting link 14 has a curved shape similar to the curved shape of the auxiliary link 16. The fixed length of the connecting link 14 results in pulling the third auxiliary link joint 34 back away from the main link 12, placing the cover flap 10 in a rearward position. The auxiliary link 16, the connecting link 14 and the second structure-fixing point 38 are selected such that the covering flap 10 is placed in a position as far upwards and as far inwards as possible, so that the additional aerodynamic drag caused by the covering flap 10 in the extended position of the main flap 8 is reduced.

It may also be preferred to arrange the rest surface of the cover flap and the corresponding contact surface such that the cover flap is subjected to a certain pretension between the rest surface and the edge section of the cover flap. The pre-tension support covers precise alignment of the flap relative to the cutout.

Fig. 4 provides a good overview of the flap system 2 from below the flap system 2 in a three-dimensional view. Here, the different sections 44 and 46 of the master link 12 are apparent. The first and second main link segments 44, 46 have different widths in a direction parallel to the axis of rotation 48 of the first main link joint 26. Here, the first main link segment 44 includes a width w1 that is significantly smaller than the second main link segment 46 having a width w 2. Illustratively, w2 may be twice as large as w 1.

A recess 50 is evident in the master link 12, the recess 50 extending through the master link 12 perpendicular to the axis of rotation 48. The recess 50 is designed to have a T-shape due to the different widths of the main link segments 44 and 46. The wider portion of the T-shape is disposed in second main link section 46 and the narrower portion of the T-shape is disposed in first main link section 44. Since the cutout 42 for accommodating the main link 12 only has to receive the first main link section 44, the covering flap 10 only has to cover a width that is slightly greater than the width w1 of the first main link section 44. This allows the covering flap 10 to pass through the recess 50. However, the auxiliary link 16 can pass through the portion of the recess 50 disposed at the first main link section 44.

Due to the symmetrical design of the main link 12, the auxiliary link 16 and the covering flap 10, it is advantageous to use two connecting links 14 instead of only one connecting link 14. The connecting links 14 may be disposed parallel to each other to symmetrically enclose the auxiliary links 16. The arrangement of two connecting links 14 and one auxiliary link 16 can also pass through the recess 50. However, a single connecting link 14 and two auxiliary links 16 may also be used. In this case, two auxiliary links 16 enclose the connecting link 14.

The first auxiliary link joint 32 can be placed in the recess 50 and further allows for a very space-saving design. To this end, the first main link section 44 may include two inner surfaces 47 that face each other. Here, two means for coupling the two first auxiliary link joint portions 32 are provided. The device may be a threaded bore or other suitable device.

Finally, fig. 5 shows an aircraft 52 with a wing 6, the wing 6 being equipped with a flap system 2 according to the preceding figures. For the sake of simplicity, only possible mounting positions are shown, but the recesses or cutouts remain open.

In addition, 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 features in the claims should not be construed as limiting.