Wing leading edge device and wing with same
阅读说明:本技术 机翼前缘装置和具有这种机翼前缘装置的机翼 (Wing leading edge device and wing with same ) 是由 斯特凡·本斯曼 马库斯·埃尔班 马丁·费斯 于 2020-02-28 设计创作,主要内容包括:提出了一种机翼前缘装置,所述机翼前缘装置包括流动本体,所述流动本体具有:前侧,所述前侧由第一展向边缘和第二展向边缘界定;后侧,所述后侧由所述第一展向边缘和所述第二展向边缘界定;前蒙皮,所述前蒙皮被布置在所述前侧上;后蒙皮,所述后蒙皮被布置在所述后侧上;以及至少一个加强组件,所述至少一个加强组件在所述第一展向边缘的区域中在所述前蒙皮和所述后蒙皮之间,其中,所述前蒙皮连续延伸并且在所述第一展向边缘和所述第二展向边缘之间没有中断,并且覆盖所述至少一个加强组件。(A wing leading edge device is presented, the wing leading edge device comprising a flow body having: a front side bounded by a first spanwise edge and a second spanwise edge; a rear side defined by the first spanwise edge and the second spanwise edge; a front skin disposed on the front side; a rear skin disposed on the rear side; and at least one stiffening component between the front skin and the rear skin in the region of the first spanwise edge, wherein the front skin extends continuously and without interruption between the first spanwise edge and the second spanwise edge and covers the at least one stiffening component.)
1. A flow body (4, 35, 49, 57, 65, 71, 81) for an aircraft, in particular for a wing leading edge device, the flow body (4, 35, 49, 57, 65, 71, 81) having
-a front side (6) delimited by a first spanwise edge (8) and a second spanwise edge (10),
-a rear side (14) delimited by the first spanwise edge (8) and the second spanwise edge (10),
a front skin (12) arranged on the front side (6),
-a rear skin (16) arranged on the rear side (14), and
-at least one stiffening component (18, 36, 50, 58, 72) between the front skin (12) and the rear skin (16) in the region of the first spanwise edge (8),
wherein the front skin (12) extends continuously without interruption between the first spanwise edge (8) and the second spanwise edge (10) and covers the at least one stiffening assembly (18, 36, 50, 58, 72).
2. Flow body (4, 35, 49, 57, 65, 71, 81) according to claim 1,
wherein the at least one stiffening component (18, 36, 50, 58, 72) extends between the front skin (12) and the rear skin (16) in the region of the first spanwise edge (8).
3. Flow body (4, 35, 49, 57, 65, 71, 81) according to claim 1 or 2,
wherein the at least one reinforcement assembly (18, 36, 50, 58, 72) comprises at least one spar (26, 28, 30).
4. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the at least one stiffening assembly (18, 36, 50, 58, 72) comprises a tip profile body (32, 74) attached to the front skin (12) adjacent to the first spanwise edge (8) at a side of the front skin (12) facing the rear skin (16) for stiffening the flow body (4, 35, 49, 57, 65, 71, 81) in the region of the first spanwise edge (8).
5. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the rear skin (16) is engaged in a spanwise section adjacent to the first spanwise edge (8).
6. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the at least one stiffener assembly (18, 36, 50, 58, 72) includes a stiffener (52) extending between the front skin (12) and the rear skin (16).
7. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the at least one stiffening component (18, 36, 50, 58, 72) comprises a plurality of spanwise stiffening profile bodies (61).
8. Flow body (4, 35, 49, 57, 65, 71, 81) according to claim 7,
wherein the spanwise reinforcing profile body (61) is part of a sheet (60) of corrugated material.
9. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the at least one reinforcement assembly (18, 36, 50, 58, 72) comprises a honeycomb core (20) extending between the front skin (12) and the rear skin (16).
10. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the at least one stiffening assembly (18, 36, 50, 58, 72) comprises a tip profile body (32, 74) arranged at the first spanwise edge (8), wherein the rear skin (16) terminates on or at the tip profile body (32, 74) within a distance from the first spanwise edge (8).
11. Flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims,
wherein the flow body (4, 35, 49, 57, 65, 71, 81) is a leading-edge slat, and
wherein the first spanwise edge (8) is a trailing edge of the slat.
12. An airfoil (86) having a fixed airfoil body and an airfoil leading edge device having a flow body (4, 35, 49, 57, 65, 71, 81) according to any one of the preceding claims.
13. An aircraft (84) with at least one flow body (4, 35, 49, 57, 65, 71, 81) according to any one of claims 1 to 12.
14. The aircraft (84) according to claim 13, wherein the flow body (4, 35, 49, 57, 65, 71, 81) is part of a wing leading edge device arranged on a fixed wing body of a wing (86).
Technical Field
The invention relates to a flow body of an aircraft, in particular for a wing leading edge device, to a wing with a stationary wing body and a wing leading edge device, and to an aircraft with at least one such flow body.
Background
High lift systems are known which are used to increase the lift coefficient of the wings of commercial aircraft. These systems may include trailing edge flaps and leading edge devices. During take-off and landing, they are usually activated, i.e. moved from a retracted position to an extended position.
Leading-edge slats typically include a front skin, a rear skin, and a mechanical interface for coupling with the slat track. A separate trailing edge is typically used at the end of the slat, which may be constructed from a metal honeycomb with a top and bottom cover and an extruded profile for the tip. For a hybrid slat, the rear skin and the trailing edge are integral parts, but need to be attached to the front skin by fasteners.
Disclosure of Invention
A common design results in a design gap between the leading skin and the trailing edge of the slat. Natural laminar flow studies indicate that even if the gap is sealed, the airflow may separate at the gap and become turbulent.
It is therefore an object of the present invention to propose a flow body, in particular for an airfoil leading edge device, which comprises a simple design but provides a flow which is as smooth as possible.
This object is achieved by a flow body, in particular for an airfoil leading edge device having the features of independent claim 1. Advantageous embodiments and further developments can be gathered from the dependent claims and the following description.
A flow body for an aircraft, in particular for a wing leading edge device, is proposed, having: a front side bounded by a first spanwise edge and a second spanwise edge; a rear side defined by the first spanwise edge and the second spanwise edge; a front skin disposed on the front side; a rear skin disposed on the rear side; and at least one stiffening component between the front skin and the rear skin in the region of the first spanwise edge, wherein the front skin extends continuously and without interruption between the first spanwise edge and the second spanwise edge and covers the at least one stiffening component.
The flow body may be arranged in a spanwise direction at least in the retracted state. Accordingly, the flow body may comprise an elongated shape extending in a spanwise direction and comprising a specific contour profile. The profile is determined primarily by the desired aerodynamic properties. It is preferred that the flow body is strong enough for the intended purpose, as it is directly exposed to strong airflow during flight conditions.
A front skin is disposed on the front side and includes a leading edge of the flow body. In the example of the wing leading edge device, this is the case at least in the extended state of the wing leading edge device. The front skin is therefore designed primarily according to aerodynamic requirements. The front skin includes a first spanwise edge and a second spanwise edge, both the first spanwise edge and the second spanwise edge running in a spanwise direction and defining both the front side and the front skin. The front skin extends between these edges, preferably in a concave shape at least in the extended position.
The flow body can be designed according to a number of different concepts. For example, the flow body may be a leading-edge slat comprising a substantially fixed shape. The slat may be coupled with a drive assembly including a slat track such that the slat moves substantially in a forward direction between a retracted state in which the slat is directly forward of the fixed leading edge and several extended positions. The path of motion of the slat may also include a component that rotates slightly downwards. The flow body may also be a Krueger flap which moves from a retracted position at the bottom side of the fixed leading edge to a position forward of the fixed leading edge with a gap created. For extension movements a rotation of substantially more than 90 is required. Such flaps may be deformed from a substantially flat shape to a more curved shape during extension. Still further, the flow body may constitute a droop or droop nose comprising a substantially fixed position on the fixed leading edge of the airfoil, but rotating about a substantially span-wise axis.
Hereinafter, the first spanwise edge and the second spanwise edge may be arbitrarily selected. However, it may be preferred that the first spanwise edge is a trailing edge of the flow body, which may be arranged above a fixed leading edge of the wing in the retracted position. The second spanwise edge may thus be a lower spanwise edge of the flow body.
At least one stiffening element is arranged at least in the region of the first spanwise edge and serves to improve the structural stability of the flow body at least in the region of the first spanwise edge. The at least one stiffening element thus particularly stabilizes the trailing edge of the flow body. As further noted below, the at least one stiffening component may be implemented by a number of different techniques.
The gist of the invention is to provide a completely closed surface on the front side by providing a continuous front skin. Any gaps can be prevented so that also minor turbulences can be eliminated. Embodiments of different implementations of the at least one stiffening assembly support the provision of a continuous front skin.
In addition to wing leading edge devices (e.g., slat or drooping nose devices), other types of flow bodies may also benefit from the present invention. These flow bodies may include many different flow bodies with trailing edges, such as flaps, ailerons, flaperons, spoiler horizontal and vertical tails, rudders, and many other flow bodies.
In an advantageous embodiment, the at least one stiffening component extends between the front skin and the rear skin in the region of the first spanwise edge. The hollow space inside the flow body in the region of the first spanwise edge is therefore fitted with the reinforcement assembly or reinforcement element. In this design, no additional trailing edge portion is required to be attached to the skin.
Advantageously, the at least one reinforcing assembly comprises at least one spar. The spar may have a spanwise extension with a web and flanges on opposite sides of the web for attachment to the skin. The spar may be arranged substantially perpendicular to one of the front skin and the rear skin. Preferably, the spar is arranged perpendicular to the front skin. However, the spar may also be arranged parallel to a vertical axis of the aircraft, to which vertical axis the flow body is coupled.
Still further, the at least one stiffening assembly may comprise a tip profile body attached to the front skin adjacent to the first spanwise edge at a side of the front skin facing the rear skin for stiffening the flow body in the region of the first spanwise edge. The tip profile body may comprise a rigid elongate body extending in a spanwise direction. However, the tip profile body may also have a hollow shape with a closed circumferential profile or an open profile. By providing a dedicated tip profile body, the position and shape of the flow body in the section of the first spanwise edge can be more easily maintained. It is possible that the tip profile body directly adjoins the front skin and follows in the rearward direction. Thus, there may be a slight step or gap between the first spanwise edge and the tip profile body, however, as far as possible at the trailing edge and thus not affecting the aerodynamic behaviour of the flow body.
In another advantageous embodiment, the rear skin engagement (joggle) is in a spanwise section adjacent to the first spanwise edge. In particular in this example, a spar may also be arranged between the front skin and the rear skin. By providing a joggled rear skin, an improved connection can be achieved in the region of the first spanwise edge. Further, a thickness step for a more flexible tip may be achieved. In order to achieve a flush transition between the flow body and the fixed leading edge downstream of the flow body in the extended position, the first spanwise edge and thus the tip profile needs to be thin at the end. Thus, if the front skin is also arranged at the tip, i.e. at the first spanwise edge, this edge may also be chamfered.
Further, the at least one reinforcement assembly includes a rib extending between the front skin and the back skin. The ribs may extend over a section of the hollow space between the front skin and the rear skin. Thus, it may extend only partially in the contour of the hollow space. However, it may also extend across the entire contour of the hollow space. By providing the ribs, a complicated autoclave cycle for bonding the reinforcing elements can be avoided. The ribs and the skin may be connected by rivets. Furthermore, the tip profiles mentioned further above may be riveted to the skin. By providing a multi-ribbed trailing edge design, a dedicated route for hot air for anti-icing and/or de-icing may be created.
The at least one reinforcing component may comprise a plurality of spanwise reinforcing profile bodies. Thus, the at least one stiffening component may also provide a stiffening function in the spanwise direction. The flow body may comprise a substantial extension in the spanwise direction. Thus, a stiffening element running in the spanwise direction is provided, resulting in an improved structural stability of the flow body.
Still further, the spanwise reinforcing profile body may be part of a sheet of corrugated material. The corrugated material sheet can be manufactured by a relatively simple manufacturing process. The corrugated sheet may be attached to the skin by riveting or gluing. It may be made of a material compatible with the material of the top and rear skins, such as a composite part or a metallic material.
In another embodiment, the at least one reinforcement assembly may include a honeycomb core extending between the front skin and the rear skin. Honeycomb cores are very feasible in providing reinforcement functions. The honeycomb core may be glued to the skin or may be directly bonded. No additional joggles (joggles) or steps are required.
According to another embodiment, the at least one stiffening assembly comprises a stiffening profile body arranged at the first spanwise edge, wherein the rear skin terminates on or at the stiffening profile body within a distance from the first spanwise edge. As mentioned above, the reinforcing profile body may be arranged at the first spanwise edge and may provide a simple and effective way to improve the structural stability directly at the first spanwise edge.
In this case it is further noted that the use of a pointed profile body at the trailing edge is applicable in most of the above-mentioned cases. However, a chamfered front skin may also be used if such a tip profile body is not desired. Thus, in the embodiments presented above and in the illustrations provided further below, it is also possible to provide a chamfered front skin instead of using a tip profile body. For example, in these cases, the rear skin may terminate slightly further forward than the front skin, and may be attached to the front skin at the ends of the rear skin. Thus, the front skin may constitute one type of tip. To improve such a front skin tip, it may be chamfered, as described above and further below.
As already noted above, it may be preferred that the device is a leading-edge slat, wherein the first spanwise edge is a trailing edge of the leading-edge slat.
The invention also relates to an airfoil having a stationary airfoil body and an airfoil leading edge device having a flow body according to the above description.
Finally, the invention also relates to an aircraft having at least one such wing.
Drawings
Further features, advantages and potential applications of the invention emerge from the following description of exemplary embodiments illustrated in the drawings. In this respect, all features described and/or illustrated form the object of the invention both individually and in any combination, irrespective of their composition in the independent claims or their reference to other claims. Further, in the drawings, the same or similar objects are identified by the same reference numerals.
Fig. 1-8 illustrate various exemplary embodiments of an airfoil leading edge device having a flow body.
Fig. 9 shows an aircraft with a wing with such a wing leading edge device.
Detailed Description
Fig. 1 shows a first exemplary embodiment of a wing leading
In this exemplary embodiment, the
In the retracted position facing the fixed leading edge of the wing, the flow body 4 comprises a rear side 14 with a
In the area around the first
In fig. 2, a very similar airfoil leading
Additionally, a
FIG. 3 illustrates yet another airfoil leading
The
Fig. 4 shows a very advantageous embodiment of an airfoil leading
Fig. 5 shows a wing leading
In FIG. 6, the wing leading
Fig. 7 shows a yet further embodiment in the form of a wing leading
In fig. 8 this concept is modified by increasing the size of the
Finally, fig. 9 shows an
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.
Reference numerals
2 wing leading edge device
4 flow body
6 front side
8 first spanwise edge
10 second spanwise edge
12 front covering
14 rear side
16 rear covering
18 reinforcing component
20 honeycomb core
22 wing leading edge device
23 flow body
24 reinforcing assembly
26 spar
28 spar
30 spar
32 tip section bar body
34 wing leading edge device
35 flow body
36 reinforcing component
38 spar
40 Flexible tip
42 rear skin
44 first step
46 end of the rear skin
48 wing leading edge device
49 flow body
50 strengthen the assembly
52 stiffening ribs
54 hollow space
56 leading edge device
57 flow body
58 reinforcement assembly
60 corrugated sheet
61 spanwise reinforcing body
62 folding piece
64 wing leading edge device
65 flow body
66 corrugated sheet
68 folder
70 wing leading edge device
71 flow body
72 reinforcing assembly
74 tip section bar body
76 rear skin
78 tip
80 wing leading edge device
81 flow body
82 rear skin
84 aircraft
86 wing
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