RU2549999C1 - Folding airfoil with two lines of folding - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: folding airfoil with two folding lines comprises centre section, root and end panels. Folding lines of the latter are parallel with aircraft airframe. Root panel drive is arranged at centre section. Length-adjustable rod is arranged at root panel to interact with end panel. Said rod is arranged for rectilinear displacement and contact by its end with shaped groove made at centre section. Its opposite skewed end contacts with shaped tooth made at end panel.

EFFECT: simplified design.

3 dwg

Description

The claimed technical solution relates to aviation and rocket technology and can be used to install folding aerodynamic surfaces on aircraft (LA), starting from a transport and launch container of a limited volume.

Known folding aerodynamic body of a guided projectile (patent RU 2280230, IPC F42B 10/14) containing a steering wheel, a pin with an axis, a folding axis, an opening mechanism in the form of a torsion spring located along the folding axis and connected at one end with the steering wheel and the other with a pin , the locking mechanism in the form of a compression spring with two latches included in the open position in the holes of the axle.

The disadvantages of this device:

- the rudders are opened in air, but not in water due to insufficient drive power (a powerful torsion spring will require unacceptable dimensions for a folding aerodynamic body);

- for a given opening angle of the rudders and subject to the specified dimensions into which the torsion spring can be placed, it is necessary to design a spring with high tangential stresses at the opening angle, which can lead to a weakening of its moment characteristics during prolonged storage;

- with a sufficiently powerful torsion spring, the translation of the steering wheel from the open position to the folded without special equipment will be difficult;

- with one folding line, the placement of aircraft in the launch container is not always ensured.

Folding aerodynamic surfaces with two folding lines are known. Their classification is presented in the book "V. Grushchansky, A. Dergachev Design and efficiency of aircraft. M., 2008, pp. 26-27. "

Fig. 1.3.7b of the above book shows a diagram when the root and end panels in the folded position sequentially encircle the body of the aircraft. In this case, the most compact folding is obtained, while the root panel rotates by an angle of more than 90 ° when opening, and the end panel relative to the root panel by an angle of less than 90 °.

For the closest analogue, the authors adopted the design of a folding stabilizer with two folding lines, given in the book "Golubev I.S. and others. Design and design of aircraft. M., 1995, p. 276, fig. 11.31. "

The stabilizer consists of a center section, a middle part and an end part. In the folded position, the middle part covers the aircraft body, and the end part is located between the aircraft body and the middle part, that is, the angle of rotation of the end part relative to the middle part is 180 °. This can be seen from Fig. 11.31b and 11.31c.

The power drive is a pneumohydraulic mechanism for unfolding the middle part of the stabilizer, which, when activated, rotates the middle part of the stabilizer relative to its folding axis. In the middle part of the stabilizer, an eccentricity relative to the axis of folding of the middle part is installed, the rod 2 is adjustable in length (see Fig. 11.31a, b, c), connected on the one hand with the folding mechanism of the middle part, and on the other hand, with the folding mechanism of the end part the stabilizer by means of the earrings 5 and the rocker 4. During the rotation of the middle part of the stabilizer, the rod 2 due to the given eccentricity starts using the earrings 5 and the rocker 4 to rotate the end part of the stabilizer, making a complex plane motion.

The advantages of this device include the fact that the disclosure of the middle and end parts of the stabilizer is ensured by one power drive due to the kinematic connection between the middle and end parts.

The disadvantages of this device:

- irrational folding stabilizer from the point of view of fitting into a limited size;

- irrational folding scheme of the stabilizer from the point of view of energy - the end part must be rotated through an angle of 180 °;

- irrational kinematics of the disclosure in the form of a complex planar movement of the mechanism elements, including traction, when it is necessary to ensure a delay in the disclosure of the end part relative to the middle part to avoid impact of the end part on the aircraft body;

- to ensure a flat movement of the elements of the mechanism for opening the end panel, a large construction height of the root panel in which it is placed is required;

- due to the complexity of the mechanism, its reliability is reduced, and the presence of a large number of articulated joints leads to additional backlashes in the mechanism.

The purpose of the proposed technical solution is to simplify the design of a folding aerodynamic surface with two folding lines and increase its reliability, as well as increase its manufacturability in the manufacture, assembly and operation.

The goal is achieved in that the root and end panels in the folded position are adjacent to the body, while the folding angle of the root panel is greater than 90 °, and the end panel relative to the root panel does not exceed 90 °. To ensure the opening of the end panel using the power drive of the root panel, a spring-loaded rod that is adjustable in length is installed in the root panel, while the rod is mounted with the possibility of rectilinear movement (in the prototype, the rod makes a plane movement and has articulated joints with several parts) and has its own contact an end face under the action of a compression spring with a profiled groove made in the center section, and with its other end face, having a bevel, with a profiled tooth made in the end panel.

The proposed technical solution is illustrated by drawings.

Figure 1 is a plan view of an aerodynamic surface 1 with two folding lines, comprising a center section 2, a root panel 3, an end panel 4, a power drive 5 mounted on an arm 6 of a center section 2 and providing rotation of the root panel 3 around its folding axis 7 , as well as a rod 8, adjustable in length, installed in the root panel 3 and providing rotation of the end panel 4 around its folding axis 9. The bracket 6 of the center section 2 is mounted on the aircraft body 10.

Figure 2 shows the aerodynamic surface in the folded sectional position. Aa. In this case, the root panel 3 and the end panel 4 sequentially encircle the body of the aircraft. The rod 8 is installed in the root panel 3 with the possibility of rectilinear movement under the action of the spring 11 and abuts on the one hand in the profiled groove 12 of the bracket 6, and on the opposite side the rod 8 is in contact with the profiled tooth 14 of the end panel 4. It can be seen that the root and the end panels in the folded position do not extend beyond the inner contour of the container 15, and the folding angle of the end panel relative to the root panel does not exceed 90 °.

Figure 3 shows the aerodynamic surface in the open position along the cross section. Aa. In this position, the end panel 4 is fixed relative to the root panel 3, in turn, the root panel is fixed relative to the bracket 6 of the center section 2.

The device operates as follows. When the actuator 5 is activated, the root panel 3 rotates around the axis of folding of the root panel 7. The rod 8, abutting against the profiled groove 12 of the bracket 6, is pressed inside the root panel by the action of the spring 11 during the rotation of the root panel 3 and acts on the profiled tooth 14 with its bevel 13 end panel 4, forcing the end panel to rotate around the folding axis of the end panel. During simultaneous rotation, the root and end panels are moved to the open position. The root and end panels are secured by spring-loaded clips (not shown).

The proposed design has successfully passed laboratory-bench and flight design tests in the composition of the aircraft in the temperature range of ± 50 ° C.

Using the proposed technical solution will simplify the design of the folding aerodynamic surface with two folding lines and increase its reliability, as well as increase its manufacturability in the manufacture, assembly and operation.

Claims (1)

A folding aerodynamic surface with two folding lines, containing a center section, a root and an end panel, the folding axes of which are parallel to the axis of the aircraft body, a root panel power drive installed in the center section and a rod adjustable in length installed in the root panel to interact with the end panel, characterized the fact that the rod is installed with the possibility of rectilinear movement and contact with its end face under the action of a compression spring with a profiled groove made in the center section , And at the other end having a bevel, with profiled teeth formed in the end panel.

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