RU2336489C2 - Folding wing of aircraft - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention is related to rocket engineering in particular to aircrafts exposed to strong wind waves. Folding wing of aircraft contains base with indent that is rigidly fixed in aircraft body, blade that is arranged with possibility of turn on axes in relation to base and connected to movable elements. Opening device installed in indent is equipped with leaf spring that is fixed with base in its medium portion and connected with elastic elements with its ends. Fixing devices are installed on both ends of leaf spring and interact with movable elements. Opening device is equipped with torsion installed on blade rotation axis and fixed with its one end to blade and with other end to base element. Every fixing device is equipped with lock device, which interacts with slots of bushing that is installed on corresponding axis of blade. Bushing slots are reamed in relation to each other at angle of blade opening.

EFFECT: increase of folding wing operation reliability by provision of reliability of opening and fixation of blade in preset time interval under effect of strong wind waves.

3 cl, 4 dwg

Description

The invention relates to the field of rocketry, in particular to aircraft under the influence of strong wind disturbances.

Currently, folding wings are widely used in aircraft (LA), because they allow to reduce the dimensions of the aircraft during storage.

A device is known under the name "Folding rocket rudders" [US patent No. 3650496, F42B 13/32, 1972]. This device contains a base with a recess, a rotary blade and an opening device rigidly fixed to the aircraft body. The opening device is made in the form of a drive rod loaded with a set of Belleville springs. The stem tends to move the blade from the folded to the open position, in which it constitutes a continuation of the base.

The disadvantage of this device is that the use of Belleville springs in such a design for wings experiencing the effects of high aerodynamic and centrifugal forces will require significant hardening of the structure for reliable coupling.

The closest in technical essence and adopted for the prototype is a device called "Folding wing of a small-sized rocket" [RF patent No. 2184339, F42B 10/14, publ. June 27, 2002].

This device comprises a base with a recess rigidly fixed on the aircraft (rocket) body, a blade made with the possibility of rotation on the axes relative to the base and connected to movable elements (inserts), an opening device located in the recess, having a leaf spring fixed in its middle part with the base and connected at its ends with liners, and latches installed on both ends of the springs and interacting with the liners.

To fold the wing, it is necessary to remove, overcoming the spring force, the blade from the recess of the base and fold it in one direction or another. When the folded blade is released (for example, when the rocket leaves the launcher), it automatically returns to the working position under the action of the leaf spring, entering the recess of the base and fixing itself in this position by the latches.

This device has a simple design. However, sufficient force is needed to effect translational-rotational motion when the folded blade is released, which can lead to unstable wing opening, especially under the influence of strong wind disturbances.

In addition, the above structures provide reliable opening of the blade only in a certain time interval, at start, when the velocity head together with atmospheric disturbance from the wind is up to 10 m / s. However, with an increase in the speed of the oncoming flow to 50 m / s, such designs do not provide reliable opening and fixing of the blade at a given time interval.

The objective of the invention is to increase the reliability of operation of the expanding wing by ensuring the reliability of the disclosure and fixation of the blade in a given time interval under the influence of strong wind disturbances.

It is proposed to solve this problem in such a way that a folding wing of an aircraft containing a base with a recess rigidly fixed to the aircraft body, a blade made with the possibility of rotation on the axes relative to the base and connected to movable elements located in the recess of the disclosure having a leaf spring fixed in its middle part with the base and connected at its ends with movable elements, and fixation devices installed on both ends of the spring and interacting with movable elements, according to the invention, the opening device is provided with a torsion bar located on the axis of rotation of the blade, fixed at one end with the blade and the other end with the base element, and each fixing device is equipped with a locking device that interacts with the grooves of the sleeve mounted on the corresponding axis of the blade.

Such a constructive solution provides:

- increase in the total moment of opening of the blade,

- reliable disclosure and fixation of the blade in a predetermined time interval at high speed pressures.

Comparison of the claimed technical solution with the prototype made it possible to establish its compliance with the criterion of "novelty."

When studying other known technical solutions in this technical field, signs that distinguish the claimed solution from the prototype were not identified, which allows us to consider the claimed technical solution meets the criterion of "inventive step".

The proposed solution is illustrated by drawings,

Where

figure 1 shows the wing in the folded position;

figure 2 - wing in the open position;

figure 3 is a view of the wing in the folded position (side view);

figure 4 - view of the element of the device for fixing the blades in the folded position.

The proposed folding wing consists of a base 2 rigidly fixed to the body 1 of the aircraft with a recess "a", a folding blade 3, pivotally mounted using eyes 4, 5 mounted on the axles 6 at the junction of the base 2 and the blade 3. The eye 4 is fixed to the blades 3, and the eye 5 is fixed on the base 2. In the recess "a" there is a device for opening the blades 3 and a device for fixing the blades 3 (Figs. 1, 2).

The device for opening the blade 3 contains a torsion bar 7 and a leaf spring 8, fixed in its middle part with an element of the base 9 and connected at its ends with movable elements-levers 10, 11. The lever 10 is made with a stop 12 (for example, in the form of a L-shaped plate ), which serves to fix the blade in the folded position, and the lever 11 is made in the form of a rod with eyelets at the ends, connected to the blade 3 through the eye 13 and the lever 10 using the axes 14 (Fig.3). The torsion bar 7 is fixed at one end 15 with the blade 3, and the other end 16 with the base element 9. The spring 8 is made with preliminary pressing in the direction of the aircraft body 1 and is installed with the support of the concave part (Fig. 1) in the base element 9 to which is attached its middle part with the help of fastening elements 17. The introduction of the base element 9, located between the torsion 7 and the spring 8 fixed with its middle part on it, allows to further improve the reliability of operation of the expanding wing while maintaining weight and size characteristics. Rigid fastening of the middle part of the spring 8 gives freedom of movement to its ends connected with levers 10, 11, with the help of which the transmission of the opening force from the spring 8 to the blade 3 is carried out. Torsion 7, untwisting and acting simultaneously with the spring 8, creates a sufficient total moment for opening blades 3, providing reliable disclosure of the blades 3 in a certain time interval at high speed heads.

The locking device consists of two electromagnetic locks 18 with spring-loaded stoppers 19 installed on both ends of the spring 8 and interacting with the stops 12 of each of the levers 10 and two electromagnetic locks 20 with spring-loaded stoppers 21, each of which interacts with the grooves 22, 23 of the sleeve 24, mounted on the corresponding axis 6 at the junction of the base 2 and the blade 3 (Fig.3, 4). The grooves 22, 23 of the sleeve 24, deployed at an angle α of the opening of the blade, ensure the fixation of the blade 3 both in the folded and in the open position.

To improve the aerodynamic flow around the wing and increase its stiffness after the opening of the blade 3, the wing is equipped with an aerodynamic shield 25 (figure 3), which is a closed thin-walled shell installed with the possibility of movement along the blade 3 under the action of a spring (not shown) towards the body 1, closing the cavity of the disclosure device and forming a continuous surface of the wing.

The disclosure of the wing is as follows.

In the folded position of the aircraft wing, the stopper 21 of each of the locks 20 is inserted into the groove 22 of each of the bushings 24, thereby holding the torsion 7 and the blade 3 from a turn, and the stopper 19 of each of the locks 18, interacting with the stop 12 of each of the levers 10, holds the end spring 8 from moving (figure 1).

When a signal is supplied from the control system (not shown) to the opening of the blade 3, the electromagnets (not shown) compress the springs (not shown) of the locks 18, 20 with the stops 19, 21, respectively. In this case, the stopper 19 of each of the locks 18 releases the spring 8, which is straightened, transmitting the opening force through the levers 10, 11. At the same time, the stopper 21 of each of the locks 20 comes out of the groove 22 of each of the bush 24. This also releases the torsion 7, which is untwisted, increases the torque created by the spring 8, acting on the blade 3 (figure 2), to a value sufficient to ensure reliable disclosure of the blade under the influence of strong wind disturbances.

After the rotation of the blade 3 around the axes 6 at the angle α of the opening of the blade, the stopper 21 of each of the locks 20 falls into the groove 23 of each of the bushings 24 and blocks them, fixing the blade 3 in the open position (Fig.3). Thus, the reliable opening of the blade 3 is ensured by the simultaneous action of the spring 8 and the torsion 7. Then the aerodynamic shield 25 under the action of a spring (not shown), moving, closes the blade opening device and forms a continuous wing surface. The process of opening the blade is veiled.

So, the information presented indicates that when using the claimed invention, the following combination of conditions:

- ensuring reliability in operation of the expanding wing in a given time interval at high speed heads;

- further improving the reliability in operation of the aircraft wing while maintaining weight and size characteristics;

- improving the aerodynamic flow around the wing and increasing its stiffness after opening the blades;

- for the claimed device in the form in which it is described in the claims, the possibility of its implementation using the means and methods described in the application and known prior to the priority date is confirmed.

Therefore, the claimed invention meets the condition of "industrial applicability".

Claims (3)

1. A folding wing of an aircraft, comprising a base with a recess fixed to the body of the aircraft, a blade made to rotate on the axes relative to the base and connected to movable elements located in the recess of the disclosure having a leaf spring fastened in its middle part with the base and connected at its ends with movable elements, and fixation devices installed on both ends of the springs and interacting with movable elements, characterized by The opening device is equipped with a torsion bar located on the axis of rotation of the blade, fastened at one end with the blade and the other end with the base element, and each fixing device is equipped with a locking device that interacts with the grooves of the sleeve mounted on the corresponding axis of the blade, and the grooves of the sleeve are deployed relative to each other at the angle of the blade. 2. The folding wing according to claim 1, characterized in that the base element is located between the torsion bar and the spring fixed to its middle part on it, made with preliminary compression towards the hull of the aircraft. 3. The folding wing according to claim 2, characterized in that the wing is equipped with an aerodynamic shield, which is a closed thin-walled shell installed with the possibility of movement along the blade.

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