Aircraft drag flap

FIELD: transport.

SUBSTANCE: aircraft drag flap arranged either atop wing or on fuselage is fitted at angle to airflow flowing there over. Flap 20 comprises free edge 21 arranged at angle is shifted from aircraft outer skin create wing-tip vortex in said airflow. Said free edge 21 comprises some separate sections 22 with their edges dividing edge vortex into some partial vortices and are formed with the help of recesses on free edge 41 of drag flap 40 that do not penetrate thought flap.

EFFECT: reduced noise.

6 cl, 3 dwg

 

The present invention relates to the brake flap for an aircraft, with the specified plate for braking the aircraft may be installed at an angle to the air stream flowing around it (ambient), while the flap includes an edge, which when installed at an angle offset from the outer shell of the aircraft.

To improve the resistance when approaching the ground and landing on modern civil aircraft use brake flaps. Typically, such panels are located on top of the wing, between the landing flaps and the rear spar, and they are generally called interceptors. Such panels can also be used to control roll and to reduce the lifting force. Less likely to use solution, in accordance with which the brake flaps are provided on the fuselage, usually in the back. In both cases we use mainly simple sheet metal, which are set at an angle to the air stream, flowing the plane.

By increasing the resistance by using speed brakes or spoilers aircraft can more steeply closer to the earth, that among other things can be used to reduce noise on the trajectory approach. However, it should be borne in mind that achieved this by reducing the noise is partially cancelled by the noise generated by the brake flap. Brake flaps are also used for braking in the planting scheme.

Noise generation on the brake flap is caused mainly by the fact that only a pronounced vortex is formed at the edge of the flap, as shown in figure 1. Usually one end flap hinged to the aircraft, while edge vortex is formed at the free edge, which is opposite to the pivotally connected end and/or side edges. The purpose of this invention is to provide a brake for an aircraft, which is mainly the same efficiency, as previously known, the flap, makes less noise.

In accordance with the present invention serves the brake flap for an aircraft, which is set at an angle to the air stream flowing around it, and the flap includes a free edge, which when installed at an angle offset from the outer shell of the aircraft, and edging creates a vortex in the air stream flowing around the aircraft. The free edge contains several individual edge sections that divide the edge vortex into several partial vortexes.

Individual sections of the edges that divide the edge vortex into several partial vortices, formed by recesses which do not pass through the shield.

Mainly, one end sitesonline attached to the aircraft, while individual sections of the edges that divide the edge vortex into several partial vortices, provided on the free edge, which is opposite the hinge attached to the end flap.

In accordance with another preferred variant of the present invention, one end flap pivotally attached to the aircraft, while the individual sections of the edges that divide the edge vortex into several partial vortices, provided on one side edge or both side edges of the flap.

In accordance with another preferred variant of the present invention, one end flap pivotally attached to the aircraft, while the individual sections of the edges that divide the edge vortex into several partial vortices, provided on the free edge, which is opposite the hinge attached to the end flap and one side edge or both side edges of the flap.

In accordance with a preferred embodiment of the present invention, a flap is provided on the top of the wing of the plane.

In accordance with another preferred embodiment of the present invention, a flap is provided on the fuselage of the aircraft.

Mainly, the flap can also be used to control roll of the aircraft.

Then var is the preferable implementation of the present invention will be described with reference to the drawings.

Figure 1 shows a perspective view of part of the previously known brake for an aircraft, with the specified brake plate can be installed at an angle relative to the air stream flowing around it.

Figure 2 shows a perspective view of part of a brake for an aircraft in accordance with a preferred variant of the present invention.

On figa-e shows the species in the long term, each of which shows a portion of the brake flap for an aircraft for the case of known brake (figa) and for the case of various preferred exemplary variants of the present invention (fig.3b-e), and figs shows the approximate variant, already shown in figure 2,

Figure 1 shows a perspective view of part of the previously known brake for an aircraft, with the specified brake plate for braking the aircraft, can be installed at an angle relative to the air stream flowing around it. The shield 10 includes a free edge 11, which when installed at an angle offset from the outer shell of the aircraft and creates (generates) edge vortex in the air stream flowing around the aircraft. This edge vortex is a significant source of noise, which is generated when the brake plate is angled, and which may be invalid when approaching to land.

On Fig shows a perspective view of the brake flap 20 for an aircraft in accordance with an exemplary variant of the present invention, with the specified brake plate for braking the aircraft, can be installed at an angle relative to the air stream flowing around it. The flap 20 has a free edge 21, which when installed at an angle offset from the outer shell of the aircraft and which creates edge vortex in the air stream flowing around the aircraft. The free edge 21 contains several individual sections 22 edges that divide the edge vortex into several partial vortices. In the exemplary embodiment shown in figure 2, the individual sections 22 of the edge formed at the expense of the zigzag designs free edge 21.

On figa shows a perspective view of part of the previously known brake 10 for an aircraft, with the specified brake flap has already been shown in figure 1. On fig.3b-e shows the views in perspective of the parts 20; 30; 40; 50 brake for an aircraft, in accordance with various preferred variants of the present invention, in which the free edge 21; 31; 41; 51 there are several individual sections 22; 32; 42; 52 edges that divide the edge vortex into several partial vortexes.

In the exemplary embodiment shown in fig.3b, individual sections of the edges that divide the edge vortex into several partial vortexes 32 obtained due to the structure of the waveform (in wave form) is free to the OMCI 31.

On figs again shows the approximate variant, shown in figure 2, in which the individual sections 22 edges obtained by zigzag designs free edge 21.

In the exemplary embodiment shown in fig.3d, individual sections of the edges that divide the edge vortex into several partial vortices received through openings or apertures 42 which are provided near the free edge 41 in the brake flap 40. Holes or recesses 42, which are provided in the brake flap 40 may be made in the form of through holes in the plate 40, as in the exemplary embodiment shown in fig.3d, or can be made in the form of recesses on the outer side of the flap 40, which do not pass through the specified cluster.

In the exemplary embodiment shown in fige, individual sections of the edges that divide the edge vortex into several partial vortices, formed by ledges or projections 52 provided near the free edge 51 on the surface of the brake plate 50.

Instead of the shown exemplary options section edges provided on the free edge of the brake flap that divide the edge vortex into several partial vortices can also be performed in other ways, provided that instead of a single noise-edge vortex, shown in figure 1, are a few indiv the dual lower edge vortices, which create less noise and can even be mutually weaken or suppress the generated noise. In the context of the present invention, the term "partition edges" refers to the sections that are formed in the vicinity of edges. They do not necessarily have to be formed by the edge of the flap, as in the case of approximate variants shown in fig.3b and 3C, but instead can be formed close to the edges as in the case of approximate variants shown in fig.3d and 3E.

Usually one end of the flap 20; 30; 40; 50 pivotally attached to the aircraft, while the individual sections 22; 32; 42; 52 edges that divide the edge vortex into several partial vortices, can be provided on the free edge 21; 31; 41; 51 plate 20; 30; 40; 50), and specified the free edge 21; 31; 41; 51 is opposite the hinge attached to the end, i.e. opposite the rear longitudinal edge, as shown in figure 2 and 3b-e, however, be mind that, alternatively or additionally, these individual sections 22; 32; 42; 52 edges can also be provided on the side edges of the brake flap.

The flap 20; 30; 40; 50 may be located on the upper part of the wing, which is typical for modern civil aircraft. However, the flap 20; 30; 40; 50 may also be located on the fuselage of the aircraft. The flap 20; 30; 40; 50 can be additionally used to control roll of the aircraft.

1. Brake flap for an aircraft, which is located on the upper part of the wing or on the fuselage of the aircraft and for braking of the aircraft is set at an angle relative to the air stream flowing around it, and the shield (20; 30; 40; 50) includes a free edge(21; 31; 41; 51), which when installed at an angle offset from the outer shell of the aircraft and edging creates a vortex in the air stream flowing around the aircraft, with the specified free edge (21; 31; 41; 51) contains several individual sections(22; 32; 42; 52), edges which divide the edge vortex into several partial vortices and which is formed with recesses at the free edge (41) of the brake plate (40)which do not pass through the shield.

2. Brake plate according to claim 1, in which the free edge (31) has a wave shape.

3. Brake plate according to claim 1, in which the free edge (31) has a zigzag shape.

4. Brake plate according to claim 1, in which one end of the shield (20; 30, 40; 50) is pivotally attached to the aircraft, and individual sections(22; 32; 42; 52), edges which divide the edge vortex into several partial vortices, provided on the free edge (21; 31; 41; 51) flap(20; 30; 40; 50), and specified the free edge (21; 31; 41; 51) is located opposite the pivotally attached end.

5. Brake plate according to claim 1, in which one end of the shield (20; 30; 40; 50) churn the RNO attached to the aircraft, while individual sections(22; 32; 42; 52), edges which divide the edge vortex into several partial vortices, are provided on both side edges of the flap(20; 30; 40; 50).

6. Brake plate according to claim 1, in which one end of the shield (20; 30; 40; 50) is attached to the aircraft, and individual sections(22; 32; 42; 52), edges which divide the edge vortex into several partial vortices, provided on the free edge(21; 31; 41; 51), which is located opposite the pivotally attached end panel(20; 30; 40; 50), and on one side edge or both side edges of the flap(20; 30; 40; 50).



 

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