RU2228283C1 - Aircraft - Google Patents

Abstract

FIELD: flying vehicles. SUBSTANCE: proposed aircraft includes fuselage with tail unit consisting of fin with rudder and stabilizer with elevator, folding wing, hydraulic folding mechanism, two wheeled landing gears and rear support. Aircraft is provided with four stiffness mechanisms mounted in pairs nose and tail sections of outer wing panels. Each mechanism is made in form of two guides with longitudinal hole in center. One guide is secured in root part of slide block received by oblong hole of root part. Aircraft is also provided with hydraulic cylinder which is rigidly connected root part and its rod is connected with slide block. Longitudinal holes of guides are located coaxially relative to each other. Slide block has form of circle in cross section. EFFECT: enhanced strength of root part and tips at joint area. 8 dwg

Description

The invention relates to aircraft, in particular to airplanes.

A well-known aircraft, consisting of a fuselage with a tail in the form of a keel with a rudder and a stabilizer with a elevator, two wings located one above the other, two landing gears with wheels and floats are attached to the lower one (Magazine "Wings of the Motherland", 1999 , No. 10, - p. 19).

The disadvantage of the aircraft is the inability to use for parking areas limited in size due to the large wingspan.

The closest analogue of the invention is an aircraft comprising a fuselage with a tail unit in the form of a keel with a rudder and a stabilizer, with a folding wing, which consists of a radical part rigidly connected to the fuselage and two end parts that are pivotally connected to each other, and mono-nacelles, in which mounted wheeled chassis, rear support (Journal of Aviation and Cosmonautics, 1999, No. 12, Fig. Grumman F7 G-2N, - p.25).

The disadvantage of the aircraft is the need for a significant increase in the strength of the root and end parts at the junction.

The technical result achieved by the aircraft, according to the invention, is to increase the strength of the root and end parts at the junction.

The specified result is achieved in that the aircraft containing the fuselage with the tail in the form of a keel with a rudder and a stabilizer with a rudder, a folding wing, a hydraulic folding mechanism, two wheeled landing gears, two landing gears, according to the invention, in pairs in the cavity of the nose and tail sections of the wing consoles in pairs mounted four hydraulic stiffness mechanisms, each made in the form of two guides with a longitudinal hole in the center, one of which is fixed in the root part, and the other in the end part, crawled una placed in the longitudinal hole of the guide root part, the hydraulic cylinder, the body is rigidly connected to the root part, and the rod with the slider, while the longitudinal holes of the guides are aligned with each other, and the depth of the input of the slider into the hole of the guide end part is determined by the ratio

C = (2 ... 3)

where C is the length of the section of the slider introduced into the hole of the guide end part;

D is the diameter of the slider,

moreover, the slider in cross section is made in the shape of a circle.

The proposed aircraft is illustrated by drawings, where

figure 1 shows an airplane, side view;

figure 2 is the same, a top view in plan according to A in figure 1;

figure 3 is the same, with folded end parts, front view;

figure 4 shows the hydraulic stiffness mechanism with a horizontal arrangement of the end part of the wing consoles;

figure 5 is the same with the folded end parts of the wing;

figure 6 shows the stiffness mechanism, a cross section along BB in figure 4;

7 shows a slider;

in Fig.8 shows the stiffness mechanism with the folded end part, a cross section along BB in Fig.5.

The aircraft includes a fuselage 1 with a tail in the form of a keel with a rudder and a stabilizer with a elevator. The wing 2 consists of the root part "a" and two end parts "b". Four hinges 3 pairwise connect the root “a” and the end “b” of the wing. Two hydraulic cylinders 4 are located on the sides of the fuselage 1, each of which is pivotally connected to the root part “a” by the body, and the rod to the end part “b” by the rod. Four hydraulic stiffening mechanisms are mounted in pairs in the nasal and tail sections of the left and right wing console 2. Each mechanism consists of a guide 5 with a longitudinal hole in the center, fixed in the end part “b”, a guide 6 with the same hole made along the longitudinal axis in the center located in the root part "a", the slider 7, made in the form of a round rod placed in the hole of the guide 6, the hydraulic cylinder 8, located on the side of the fuselage 1, rigidly connected to the root part "a" by the body, and stock - with slider 7.

The plane operates as follows.

For parking on a site of unlimited width, as well as for movement in air, the end parts "b" are positioned horizontally, Figs. 1, 2. At the same time, the rods exit the hydraulic cylinders 4, act on the end parts "b" and hold them in horizontal position. For a more reliable fixation of the position of the end parts "b" in a horizontal position, sliders 7 are inserted into the longitudinal hole of the guides 5 by an amount equal to C = (2 ... 3) · D, where C is the length of the section of the slide introduced into the hole of the guide 5, D is the diameter of the slider. Thanks to what increase the rigidity of the connection of the end parts "b" with the root part "a". This significantly reduces the vibration of the end parts "b" when moving in the air.

To place the aircraft in a section limited by the width, the end parts "b" of the wing consoles 2 are moved to a vertical position, possibly with a blockage to the longitudinal axis of the fuselage, 1, Fig. 3, the sliders 7 are removed from the hole of the guides 5, Fig. 5. In this case, the rods are pulled into the hydraulic cylinders 8, and the sliders 7 enter the hole of the guides 6. Then, the end parts "b" of the wing consoles 2 are moved to the vertical position. While the rods are pulled into the hydraulic cylinders 4, and the end parts "b" rotate on hinges 3. Due to this, the wingspan 2 is reduced, Fig.3.

 Providing the aircraft with a stiffness mechanism ensures reliable fixation of the end part of the wing consoles in a horizontal position.

In addition, significantly reduces the vibration of the end parts when moving in the air.

The introduction of sliders into the guides of the 5 end parts to a depth equal to its 2nd ... 3rd diameters provides sufficient bond strength between the root and end parts of the wing consoles; the penetration of the slider into the guide 5 by more than three of its diameter significantly increases the cost of the mechanism. When you enter the slider into the guide 5 less than two of its diameters does not provide sufficient strength of the joints of the mentioned parts of the wing console.

The device according to the invention can be used in the construction of medium and heavy types of aircraft with folding end parts of the wing consoles.

Claims (1)

An airplane containing a tail fuselage in the form of a keel with a rudder and a stabilizer with a elevator, a folding wing, a hydraulic folding mechanism, two wheeled landing gears, a rear support, characterized in that four hydraulic mechanisms are mounted in pairs in the cavity of the nose and tail sections of the wing consoles stiffnesses, each of which is made in the form of two guides with a longitudinal hole in the center, one of which is fixed in the root part, and the other in the end part, of a slider placed in the longitudinal bore stie directing root portion of the hydraulic cylinder, the housing is rigidly connected with the root portion, and a rod - the slide, which in cross section is shaped circle, that the longitudinal guide holes are coaxial with each other, and the insertion length of the slide into the opening end portion of the guide is defined by the relation C = (2 ÷ 3) D, where C is the length of the section of the slider introduced into the hole of the guide end part of the wing console; D is the diameter of the slider.

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