RU2715249C1 - Helicopter stabilizer - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering and can be used in helicopter design to provide required stability and controllability. Stabilizer has a symmetrical profile and consists of right (1) and left (2) trapezoid-shaped consoles in plan symmetrically located relative to tail boom. Each stabilizer arm of the rivet structure consists of one side member (3), eight ribs (4), steel bands (5), diaphragms (6, 7, 8), front duralumin skin (9), tail stringer (10), removable end fairing (11), upper rifted duralumin sheath (12), lower rifted duralumin skin (13) with hatch (14), fittings with axes (15, 16), fittings (17, 18) for attachment of two stabilizer cantilevers. Each cantilever is equipped with plate with holes to provide required angle of stabilizer installation.

EFFECT: reduced weight, increased manufacturability of the unit, reduced load on personnel during repair.

3 cl, 5 dwg

Description

The invention relates to the field of aircraft construction, and may find application in the design of helicopters to provide the necessary stability and controllability.

Known aircraft hatch (patent RU 2482996, B64C 1/14, publ. 10.02.2012), and a cover for the access hole of the aircraft (patent RU 2469908, B64C 1/14, publ. 10.08.2011), which are used in the stabilizers and wings of the aircraft. The manhole cover for the access hole in the structure of the aircraft made of composite material contains the following elements: outer and inner cover; an adjusting washer between an internal cover and a covering; sealing profiles between the inner cover and the adjusting washer and between the outer cover and casing; the plate between the casing and the outer cover. The technical result consists in improving the fastening of the cover for the access hole of the aircraft.

The above-described cover design is designed specifically for placement in stabilizers and wings made of composite materials, while carbon fiber is difficult to machine.

The design of the helicopter stabilizer is known (Danilov V.A. Mi-8 helicopter: - M .: Transport, 1988, pp. 24-25, Fig. 2.13.), Which consists of two halves located symmetrically on the tail boom, each of which includes a spar, ribs, a tail stringer, a diaphragm, a frontal fairing made of duralumin sheet, a removable end fairing made of fiberglass and a sheathing of the stabilizer with a drainage hole.

The disadvantage of this analogue, taken as a prototype, is the fragility of linen sheathing made from the canvas, due to low resistance to climatic and biological influences, especially on helicopters operating in a marine or tropical climate.

A known helicopter stabilizer design closest to the claimed technical solution (patent RU 2220882, B64C 1/00, publ. 10.01.2004), which consists of two halves located symmetrically on the tail boom, each of which includes two spars, ribs , a tail stringer, a diaphragm, a frontal fairing made of duralumin sheet, a removable end fairing made of fiberglass and a sheathing of the stabilizer with at least one drainage hole, while the sheathing of the stabilizer is made of a metal sheet and connected to the shelf spar, ribs and a tail stringer through rivets butt with frontal and end fairings, and drainage holes are made in each compartment formed between the stabilizer ribs.

The disadvantage of this design is the presence of two spars, which increases the weight of the unit, while the stabilizer area is small, which affects the stability and controllability of the helicopter, limits its use on new models of helicopters with increased carrying capacity. In the process of replacing the axles of the stabilizer linkage, when working out, one of the skins must be fully riveted to gain access to the dismantling of the axles, which increases the workload on personnel, and labor costs increase. Also in this design there is no possibility of inspection of the internal stabilizer power set during operation.

A technical problem that has not been solved in the known device, the solution of which is provided by the claimed invention, consists in creating a stabilizer of an increased area to improve the controllability and stability of the helicopter during flight, with the possibility of internal access for inspection and repair.

The technical result consists in improving controllability, reducing weight, increasing the manufacturability of the unit, reducing the load on personnel during the repair process.

The technical result is achieved due to the fact that in the stabilizer of the helicopter containing two consoles symmetrically located on the tail boom, each of which includes a spar, ribs, tail stringer, diaphragm, fairing, in accordance with the claimed invention, the lower and upper skins are made rifts, and a hatch is installed on the lower skin; in addition, each console is equipped with a plate with holes.

Also, fringes are fixed on the lower casing in places of a cut for placement of hatches.

Moreover, one spar is installed in the design.

The implementation of the casing with the rifts is aimed at reducing weight, improving the manufacturability of the unit, because allows to exclude from the design a second spar or additional ribs.

The presence of a hatch on the lower casing allows inspection, repair and replacement of the hinge axes without dismantling the casing, which generally increases the adaptability of the stabilizer and reduces the load on personnel during operation and repair.

The design of the helicopter stabilizer is illustrated by the drawings:

in FIG. 1 - stabilizer, top view;

in FIG. 2 - view A, docking of the stabilizer consoles;

in FIG. 3 is a section BB of FIG. 1, view of the 1st rib;

in FIG. 4 - hatch, section BB of FIG. 1;

in FIG. 5 - rift, section GG of FIG. 1.

To ensure the necessary stability and controllability, a stabilizer is installed on the helicopter, the installation angle of which changes on the ground.

The stabilizer has a symmetrical NACA-0012 profile and consists of the right 1 and left 2 trapezoidal consoles in plan, symmetrically located relative to the tail boom.

Each stabilizer console is a riveted structure, consists of one spar 3, eight ribs 4, steel strips 5, diaphragms 6, 7, 8, frontal duralumin sheathing 9, tail stringer 10, removable end fairing 11, upper rift-shaped duralumin sheathing 12, lower rift duralumin sheathing 13 with a hatch 14, fittings with axles 15, 16, fittings 17, 18 for mounting two stabilizer consoles (Fig. 1, 2).

The nose of the stabilizer, the upper 12 and lower 13 of the casing are riveted to the spar 3, diaphragms and ribs with rivets. Two round-shaped hatches 14 of a small size on the lower 13 skins are installed using screws 19 and nuts. To ensure structural rigidity in the cutout of the lower casing 13 under the hatches 14, fringes 20 are made, which are installed on the casing 13 with countersunk rivets. Through hatches 14 provides access to the dismantling of the axles of the stabilizer. Also, through these hatches, you can inspect the internal stabilizer power set. This design allows inspection, repair and replacement of the hinge axes without dismantling the casing, which generally increases the adaptability of the stabilizer and reduces the load on personnel during operation and repair.

To ventilate the structure from the inside and drain the condensate, drainage holes in the amount of 7 pieces on each (not shown) were made on the lower casing.

Spar 3 - beam type, riveted construction. Its upper and lower belts are made of duralumin corner profiles. Fittings with metal axles 15, 16 are installed on the spar near rib No. 1 for mounting the stabilizer on the tail boom. Docking of the right 1 and left 2 stabilizer consoles is done with bolts using fittings 17, 18.

On the toe of rib No. 1 of each stabilizer console, a plate 21 is riveted, with which you can change the stabilizer installation angles on the ground from + 9 ° to -9. Holes 22 are provided in the plate 21 for fastening the stabilizer to the tail boom. Mounting the stabilizer through the holes 22 changes the angle of its installation. Additionally, a special adapter (not shown) is used, which allows to achieve accuracy in setting a given angle.

On the lower 13 and upper 12 casing rifts 23 are made (Fig. 5), which are located between the ribs 4. The rifts 23 provide structural rigidity in the transverse direction, which allows you to abandon the second spar in the structure, resulting in weight reduction. Also, the rifts 23 remove the longitudinal load from the stabilizer sheathing, which prevents its deformation in the presence of aerodynamic loads (the formation of claps). Thus, due to the implementation of the rifts 23 reduces the weight of the structure and increases manufacturability.

According to the results of static, dynamic and flight tests, it was found that the increased stabilizer area positively affects the stability and controllability of the helicopter during flight.

The developed design is universal and can be installed on helicopters of various modifications.

Claims (3)

1. The helicopter stabilizer, containing two consoles symmetrically located on the tail boom, each of which includes a spar, ribs, tail stringer, diaphragms, fairing, characterized in that rifts are made on the lower and upper panels, and a hatch is installed on the lower panels , each console is provided with a plate with holes. 2. The stabilizer according to claim 1, characterized in that the fringing is fixed on the lower skin in the places of the cut for the placement of hatches. 3. The stabilizer according to claim 1, characterized in that one spar is installed in the structure.

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