Guide of landing flap of aircraft

FIELD: air transport.

SUBSTANCE: guide element is connected to landing flap supported with guide rail with possibility of being moved between takeoff and landing positions. Guide of landing flap of aircraft is supported with guide rail and moves along it between takeoff and landing positions by means of a carriage. In the guide there are two grooves having the section close to U-shaped one. On carriage there fixed are sliding elements entering the above grooves, the cross section shape of which repeats the groove profile. The guide is equipped with side guide elements intended for preventing the carriage movement perpendicular to rail.

EFFECT: improving reliability and decreasing overall dimensions.

3 cl, 2 dwg

 

The invention relates to guides landing flaps for aircraft, in which the guide element is connected with the landing flaps resting on the guide rail for movement between positions takeoff and landing.

Landing flaps, making proportional to the translational movement, usually goes carriage flap, which sent him packing device. Carrier landing flap should absorb any forces acting on it in the vertical and lateral directions with respect to the rollers of the carriage.

To solve this task may require the use of expensive design with numerous guide rollers, the disadvantages which are associated with high cost, weight, and need for maintenance.

Thus, the present invention is to create a guide landing flaps for aircraft, which has a simple structure, high safety features and reliability.

This problem is solved due to the fact that the guide element is in the form of a carriage which can move in a bearing device for a landing flap, having mostly straight configuration, with men whom she least one guide mechanism of the sliding bearing device for a flap.

The advantage of this solution is determined by the fact that it uses a small number of moving parts that are subject to wear. The design, which can be made in accordance with this decision, has a light weight and economical in manufacture, and in the process of maintenance. In addition, it is assumed that depending on the forces that must be taken into account, the number of additional guide rollers may be reduced. The reduction in the number of the guide rollers may be significant.

The figures shown:

figure 1 is a view of a partial cross section along the line AA' guide landing flap presented in figure 2;

figure 2 is a side view of the guide of the landing flap.

In a variant implementation of the invention, represented in figure 1 and 2, the landing flaps 1 mounted on the carriage 4 is supported and guided bearing device 3 for flap placed on the wing. Figure 1 shows the schematic view of a partial cross section along the line AA' guide landing flap presented in figure 2.

For extension and retraction of landing flaps 1 it is connected with a sliding carriage 4 and is supported and guided by guide elements 42 and 44 of the bearing device 3 for the flap.

When the carriage 4 absorbs the forces acting on it in perpendi usrnam and lateral directions relative to the guide rail 3.

Figure 1 shows the schematic view of the landing flap 1, which is connected to the carriage 4 by means of a hinge 45, 46, which is shown in the figure only schematically, and the axis of rotation of the hinge 45 lies in the plane of the drawing.

The slide elements 41, 43, mounted on the carriage 4 landing flaps provide movement of the carriage 4 in the guide elements 42, 44 of the bearing device 3. The carriage 4 directs all the forces acting on the landing flaps 1 in vertical and lateral directions relative to the guide, through a pair of slide 41, 42 and 43, 44. This means that each rail slide includes a slide elements 41, 43, which are mounted on the carriage, and guide members 42, 44 that are installed on the host device for the flap.

The slide elements 41, 43 and guiding elements 42, 44 form a rail system that provides movement essentially only along the guide elements. Thus, in accordance with an illustrative embodiment of the implementation of the invention, the slide elements 41, 43 and guiding elements 42, 44 form a rail system, which provides translational motion with essentially only one degree of freedom.

To ensure safe and reliable operation of the guide sliding in almost any possible operating conditions kadapra slip must be able to withstand high surface pressure and have relatively low coefficients of static and dynamic friction. In addition, each pair of slide should have a high resistance to temperature fluctuations and humidity to freezing and to the action of chemical reagents and tpol addition, the wear should be predictable as possible. Based on these requirements for the sliding surfaces of the pairs of sliding can be selected from the following materials (list not exhaustive):

metals coated or uncoated, ceramic materials, synthetic materials with fillers made of ceramics or metals, synthetic materials, fiber-reinforced (for example, textile materials reinforced with carbon fiber), ceramic materials, fiber-reinforced (for example, textile materials reinforced with carbon with silicon carbide), and the multi-layer composite materials obtained by the deposition of carbon on the basis of plasma, and in the latter case, the strength can be varied by known methods from the strength of the graphite to the strength of the diamond.

In accordance with an illustrative embodiment of the implementation of the present invention, the slide elements 41, 43, which interact with the guide elements 42, 44, may have a cross-sectional mostly oblong or rectangular shape. That is, the slide elements 41 and 43, shown in figure 1, can be flat is th figure 1, having essentially a rectangular shape. Preferably the slide elements 41 and 43 are generally parallel rails or guide elements carrying device 3 for the flap.

As you can see in figure 1, the guide elements 42 and 44 may be generally U-shaped profile. Preferably the cross-sectional shape of the guide elements 42 and 44 corresponds exactly to the cross-sectional shape of the slide elements. Thus, on both sides of the carriage 4, you can use the slide elements 41 and 43 different forms, which interact with the guide elements 42 and 44, with the appropriate conjugated form, to account for conditions differences loads or spatial distribution.

Figure 2 presents a view of a partial section of the wing, which shows a side view of the guide device of the landing flap in accordance with an illustrative embodiment of the implementation of the present invention.

As you can see in figure 2, the landing flaps 1 can move along the rail 3 by using slides or sliding device 4. The direction of the flap 1 and the rail 3 with the carrier provides positioning at release or harvesting of the flap.

As mentioned above with reference to figure 1, the carriage 4 is directed along the rail 3 with the help of slide elements 41 and 43, which interact with the guide elements 42 and 44. However, as you can see from figure 2, in accordance with another illustrative implementation of the present invention can be used, and other guiding elements. As shown in figure 2, can be used lateral guiding elements 52 and 54, which are designed to prevent the movement of the carriage 4 in the lateral direction, generally perpendicular to the rail 3. That is, the guide members 52 and 54, which can be used guide rollers interacting with the rail 3 can be used for the lateral direction of the carriage 4 on the rail 3. These guide elements can be attached to the carriage 4 by means of appropriate fasteners 50. Further, in another guide element 56 can be used a guide roller that rolls, as shown in figure 2, along the rail 3. These guiding elements used in addition to the slide elements 41, 43 and the guide elements 42, 44 may further restrict the displacement of the carriage 4 in the direction parallel to the cutting line AA'. These guide elements 52, 54 and 56 can even improve the movement of the carriage 4 in the guide elements 42 and 44, as may be prevented tilt and rotation of the slide elements 41, 43 in the guide elements 42, 44. This can provide a smooth and reliable the direction of the flap. the moreover, the use of guide elements 52, 54 and 56 in combination with the guides 42 and 44 can provide a more secure and reliable guide system for the flaps, which is characterized by a smaller volume of maintenance work.

1. Guide landing flaps of an aircraft, based on the guide rail and moving it between the provisions of the take-off and landing with the carriage, the guide has two notches close to the U-shaped profile, and fixed on the carriage included in the said recess of the slide elements, the cross-sectional shape which follows the profile of the recess, and a guide provided with side guide elements designed to prevent the movement of the carriage perpendicular to the rail.

2. Guide landing flap according to claim 1, in which the two notches and the constituent slide elements have different shapes.

3. Guide landing flap according to claim 1, in which the sliding surface of the kinematic pairs made of a material selected from the following group: metals coated, uncoated metals, ceramic materials, synthetic materials with a filler made of ceramics or metals, synthetic materials, fiber-reinforced, ceramic materials, fiber-reinforced, and that the same multi-layer composite materials, obtained by applying carbon based plasma.



 

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