RU207835U1 - VIBRATION DAMPER FOR SUSPENSION OF TARGET LOAD TO AIRCRAFT - Google Patents

Abstract

The utility model relates to the field of vibration reduction devices (shock absorbers) and can be used in the design of vibration protection for a target load installed on an aircraft. The technical results of the utility model consist in the reduction of vibration and shock effects from the aircraft on the established target load in all planes, in increasing the rigidity of the fastening elements of the target load installed on the aircraft along the Y and Z axes, in increasing the stability of operational properties under conditions of prolonged static and dynamic load, in increasing durability. The technical results are achieved due to the fact that the vibration absorber for suspending the target load to the aircraft contains the upper and lower mounting plates connected to each other by a rigid detachable connection, a streamlined casing, upper corner connectors located symmetrically relative to the center of the upper plate and relative to each other, lower corner connectors located symmetrically relative to the center of the bottom plate and relative to each other, middle connectors located symmetrically relative to the centers of the upper and lower plates and relative to each other, cable vibration isolators located symmetrically relative to the upper and lower plates. Moreover, each cable vibration isolator contains two strips and a cable between them, which is an elastic element of the cable vibration isolator. At the same time, cable vibration isolators are installed at the corners of the upper and lower mounting plates at an angle of 45 ° with respect to each other using the upper and lower corner connectors. To increase the rigidity of fastening along the vertical Z axis along the edges of the mounting plates perpendicular to the plates using medium connectors, vibration isolators are installed opposite each other, in the middle between the angular vibration isolators. The vibration damper for suspending the target load to the aircraft also contains shock-absorbing supports located in pairs symmetrically relative to the centers of the upper and lower plates and relative to each other, and each shock-absorbing support contains rubber-metal buffers to limit movement along the vertical and horizontal Y and Z axes. a pair of shock-absorbing supports is installed in such a way that it is possible to engage them while simultaneously breaking cable vibration isolators: the first shock-absorbing support in each pair is rigidly fixed with a stop on the upper plate, the second shock-absorbing support in a pair is rigidly fixed with a stop on the lower plate. Moreover, the protrusion of the stop installed on the upper plate enters the cavity of the stop installed on the lower plate, forming a zigzag connection. At the ends of the stops, rubber-metal buffers are installed, which soften the impact and limit the range of motion under dynamic load. 1 wp f-ly, 12 ill.

Description

The utility model relates to the field of devices for reducing vibration effects (shock absorbers) and can be used in the design of vibration protection for a target load installed on an aircraft.

A known vibration damper for an aircraft nacelle (RF patent No. 2467221 with a priority date of 08/01/2008), placed between the electronic unit and the fixed structure of the aircraft nacelle, containing a unit of elastic material, a screw for fastening this unit on the specified fixed structure and means of fastening the specified unit on the specified node. Moreover, the shock absorber is equipped with means for limiting the travel of said fastening means relative to said fastening screw in at least two directions in space. The specified means of limiting include, firstly, a cuvette mounted with the possibility of attachment to the specified fixed structure, and, secondly, a stop freely moving inside the specified cuvette and rigidly connected with the specified means of fastening, and said means of limiting have such dimensions to prevent the transfer of loads to the specified propeller, which could lead to its fatigue and / or failure.

A disadvantage of the known vibration damper for an aircraft nacelle is the design complexity.

Known vibration isolating suspension, disclosed on the page "Research and Production Company" Astron "(access mode: https://dempfer.ru/cases/cnizhenie-vibratsii-pri-ustanovki-optiko-elektronnoy-sistemy-na-vertolet/, access date : June 2021) - prototype. The described vibration-isolating suspension is intended for installation in an optoelectronic system (hereinafter - OES) on an EMERCOM BO-105 helicopter. Structurally, the suspension is made of two identical supports. The support includes fastening elements and two cable vibration isolators. Cable vibration isolators are designed to reduce the impact of vibration from a helicopter on an OES in a certain frequency range on the installed optoelectronic system.

The disadvantages of the known vibration-isolating suspension are

low degree of applicability: the device is intended for use only on an EMERCOM BO-105 helicopter, while it cannot be used on other helicopters;

low rigidity of attachment to the elements of the helicopter;

low reliability due to the fact that there are no safety elements in case of breakage of the vibration isolator, and there is no protection against atmospheric precipitation;

instability of operational properties under conditions of prolonged static and dynamic loading caused by partial irreversible deformation of cable spring-damping elements, which return the cable elements to their original state and prevent irreversible deformation from occurring.

The technical problem to be solved by the claimed utility model is the reduction of vibration and shock effects on the target load from the aircraft while simplifying, reducing the size, material consumption and increasing the strength of the structure.

The technical results of the utility model consist in the reduction of vibration and shock effects from the aircraft on the set target load in all planes, in increasing the rigidity of the fastening elements of the target load installed on the aircraft along the vertical and horizontal axes Y and Z, in increasing the stability of operational properties under conditions of prolonged static and dynamic loading, in increasing the durability.

To achieve the indicated technical results, the claimed vibration absorber for suspending the target load to the aircraft comprises upper and lower mounting plates, a streamlined casing, upper corner connectors located symmetrically relative to the center of the upper plate and relative to each other, and lower corner connectors connected by a rigid detachable connection. , located symmetrically relative to the center of the lower plate and relative to each other, middle connectors, located symmetrically relative to the centers of the upper and lower plates and relative to each other, cable vibration isolators, located symmetrically relative to the upper and lower plates.

In this case, each cable vibration isolator contains two strips and a cable between them, which is an elastic element of the cable vibration isolator.

In this case, cable vibration isolators are installed at the corners of the upper and lower mounting plates at an angle of 45 ° with respect to each other with the help of upper and lower corner connectors.

At the same time, to increase the rigidity of fastening along the vertical Z axis, vibration isolators are installed opposite each other at the edges of the mounting plates perpendicular to the plates using medium connectors, opposite each other, in the middle between the angular vibration isolators.

The vibration damper for suspending the target load to the aircraft also contains shock-absorbing supports, located in pairs symmetrically relative to the centers of the upper and lower plates and relative to each other, each of which contains rubber-metal buffers to limit movement along the vertical and horizontal Y and Z axes.

In this case, each pair of shock-absorbing supports is installed in such a way that it is possible to engage them while simultaneously breaking cable vibration isolators: the first damping support in each pair is rigidly fixed by means of a stop on the upper plate, the second damping support in a pair is rigidly fixed by means of a stop on the lower plate. Moreover, the projection of the stop installed on the upper plate enters the cavity of the stop installed on the lower plate, forming a zigzag connection. At the ends of the stops, rubber-metal buffers are installed, which soften the impact and limit the range of motion under dynamic load.

The rigid detachable connection can be made with screws.

The claimed solution is illustrated by drawings.

FIG. 1 shows the external view of the shock absorber for suspension of the target load to the aircraft, where

1 - top plate;

2 - bottom plate;

3 - casing;

4 - upper corner connector;

5 - lower corner connector;

6 - middle connector;

7 - cable vibration isolator;

8 - depreciation support.

Fig. 2 shows the upper plate, Fig. 3 - the lower plate, Fig. 4 - the casing, Fig. 5 - the upper corner connector, Fig. 6 - the lower corner connector, Fig. 7 - the middle connector, on Fig. 8 - cable vibration isolator, Fig. 9 - damping support, where

9 - emphasis;

10 - rubber-metal buffer.

Figure 10 shows a vibration damper for suspending a target load to an aircraft assembled with an optoelectronic system (hereinafter referred to as OES).

Figure 11 shows the attachment of a vibration damper for suspending the OES to an aircraft.

Figure 12 shows the principle of operation of a vibration damper for suspending a target load to an aircraft.

The description of the implementation of the utility model can be used as an example for a better understanding of its essence and is set forth with reference to the figures attached to the present description. At the same time, the details given below are intended not to limit the essence of the utility model, but to make it clearer.

A vibration damper for suspending the target load to the aircraft ensures the installation of a target load on the aircraft, for example, an optoelectronic system (hereinafter referred to as OES) (Figs 10, 11), as well as protection of the target load from vibration and shock effects in a stationary and mobile state ...

The vibration damper for suspension of the target load to the aircraft (Fig. 1) contains the upper (Fig. 1 - Pos. 1, Fig. 2) and the lower (Fig. 1 - Pos. 2, Fig. 3), connected by a rigid detachable connection. rectangular mounting plates, a streamlined casing (Fig. 1 - pos. 3, Fig. 4), four upper corner connectors (Fig. 1 - pos. 4, Fig. 5), four lower corner connectors (Fig. 1 - pos. . 5, Fig. 6), two middle connectors (Fig. 1 - pos. 6, Fig. 7), six cable vibration isolators (Fig. 1 - pos. 7, Fig. 8), four shock-absorbing supports (Fig. 1 - item 8, figure 9), each of which contains rubber buffers to limit movement along the vertical and horizontal axes Y and Z (figure 9 - item 10).

Four cable vibration isolators (Fig. 8) are installed at the corners of the mounting plates and at an angle of 45 ° (Fig. 12) on the upper and lower plates (Fig. 12 - items 1 and 2), symmetrically relative to the center of the upper and lower plates, respectively, and relative to each other, using the corner connectors of the upper and lower (Fig. 12 - items 4 and 5). Also, to increase the rigidity along the vertical Z axis, two cable vibration isolators (Fig. 12 - pos. 7) are installed perpendicular to the plates using middle connectors (Fig. 12 - pos. 6) symmetrically relative to the centers of the upper and lower plates.

Each damping support (Fig. 9, Fig. 12 - pos. 8) is equipped with rubber-metal buffers (Fig. 9 - pos. 10), which limit the amplitude of movement along the vertical and horizontal axes Y and Z, increasing the rigidity of the system along these axes. The shock-absorbing supports (Fig. 12 - pos. 8) in a pair are installed so that they provide the possibility of engagement with simultaneous breakage of the vibration isolators of the cable (Fig. 12 - pos. 7), which increases the reliability of the system and protects the target load from falling and impact.

FIG. 12 shows a diagram of the installation of depreciation supports. Each pair of damping supports is installed as follows. The first support in a pair (Fig. 12 - pos. 8) is rigidly fixed with a stop (Fig. 9 - pos. 9) on the upper plate (Fig. 12 - pos. 1). The second support in a pair (Fig. 12 - pos. 8) is rigidly fixed with a stop (Fig. 9 - pos. 9) on the lower plate (Fig. 12 - pos. 2). The protrusion of the stop (Fig. 9 - pos. 9) of the first support installed on the upper plate (Fig. 12 - pos. 1) enters the cavity of the stop of the second support installed on the lower plate (Fig. 12 - pos. 2), forming zigzag connection. At the ends of the stops (Fig. 9 - pos. 9), rubber-metal buffers are installed through the threaded holes (Fig. 9 - pos. 10). Rubber-metal buffers (Fig. 9 - pos. 10) on the stops (Fig. 9 - pos. 9) are installed in such a way that there is sufficient clearance between the supports, shock-absorbing and mounting plates to prevent collision under loads.

To protect against external influences, the ingress of foreign objects and increase reliability, the vibration absorber for suspending the target load to the aircraft along the entire contour is closed with a streamlined casing (Fig. 4, Fig. 12 - pos. 3), which is rigidly fixed to the end part of the upper plate (Fig. .12 - pos. 1), providing the possibility of free movement of the lower plate (Fig. 12 - pos. 2) with the target load installed on it. The casing forms a streamlined surface of the shock absorber contour to reduce the likelihood of air stalling.

The rigid detachable connection can be made with screws.

The vibration isolator cable can be made of zinc-chromated steel, anodized aluminum alloy, polymer-carbon nanocomposites based on organosilicon resins.

The functioning of the inventive shock absorber for suspension of the target load to the aircraft is as follows.

The target load is attached to the bottom plate of the shock absorber for suspension (Fig. 3) using a rigid detachable connection (Fig. 12).

The upper plate of the shock absorber for suspending the target load (Fig. 2) using a rigid detachable connection is attached to the aircraft (Fig. 12).

Under the influence of gravity, the arcuate sections of cable vibration isolators perceive vertical loads and ensure the balance of the system.

When the aircraft vibrates during flight, the arcuate sections of cable vibration isolators perceive both vertical and horizontal loads, thereby weakening the dynamic effect on the target load, i.e. provides spatial vibration and shock protection. Due to the friction between the cable strands, the vibrational energy is dissipated and the transfer of forces to the target load is reduced. Vibration damping occurs in all planes.

Installation of four cable vibration isolators using the upper and lower head connectors at an angle of 45 °, symmetrically relative to the center of the plates and relative to each other, ensures the operation of the vibration isolator system in all directions, since with this installation vibration isolators work both in compression (vertical loads) and in shear (horizontal loads). The installation diagram of vibration isolators at an angle to the axes of symmetry of the target load (Fig. 12) is most suitable for isolating spatial vibrations, but at the same time it is the most complicated, since with a slight violation of symmetry, all six associated modes of natural vibrations arise in the system. In such a scheme, all external forces are balanced in the direction of the center of gravity, which reduces the effect of vibrational vibrations.

Damping supports limit the range of motion when passing through resonance, prevent the impact of random dynamic loads on cable vibration isolators and prevent the target load from falling while the cables break. Rubber-metal buffers installed on the ends of the stops soften the impact and limit the amplitude of movement along the vertical and horizontal axes Y (shear) and Z (compression) under dynamic load. The amplitude of movement along the horizontal X-axis (in the direction of flight) has no limiters and is determined only by the rigidity of the cable vibration isolators, to reduce the stiffness of the vibration-isolating system in the direction of flight, to mitigate the effect of random increased shock loads along this axis on the target load.

Vibration isolators installed through a rigid connection with a middle connector to the upper plate symmetrically about the center are located towards each other. This double-sided arrangement provides protection against external forces acting in all directions.

The streamlined shape of the casing significantly reduces the effect of airflow during wind loads, thereby reducing vibration and shock effects on the target load. In case of lateral loads, in order to avoid collisions, a sufficient gap is provided between the casing and the bottom plate.

Thus, the reduction of vibration and shock effects from the aircraft on the set target load in all planes, an increase in the rigidity of the attachment elements of the target load installed on the aircraft along the vertical and horizontal axes Y and Z, an increase in the stability of operational properties under conditions of prolonged static and dynamic loading, an increase in durability is achieved by the fact that the vibration damper for suspending the target load to the aircraft contains interconnected rigid detachable connection upper and lower mounting plates, a streamlined casing, upper corner connectors located symmetrically relative to the center of the upper plate and relative to each other, lower corner connectors located symmetrically relative to the center of the lower plate and relative to each other, middle connectors located symmetrically about the centers the upper and lower plates and relative to each other, cable vibration isolators, located symmetrically relative to the upper and lower plates. In this case, each cable vibration isolator contains two strips and a cable between them, which is an elastic element of the cable vibration isolator. In this case, cable vibration isolators are installed at the corners of the upper and lower mounting plates at an angle of 45 ° with respect to each other with the help of upper and lower corner connectors. To increase the rigidity of fastening along the vertical Z axis along the edges of the mounting plates perpendicular to the plates using medium connectors, vibration isolators are installed opposite each other, in the middle between the angular vibration isolators. The vibration damper for suspending the target load to the aircraft also contains shock-absorbing supports located in pairs symmetrically relative to the centers of the upper and lower plates and relative to each other, and each shock-absorbing support contains rubber-metal buffers to limit movement along the vertical and horizontal Y and Z axes. a pair of shock-absorbing supports is installed in such a way that it is possible to engage them while simultaneously breaking cable vibration isolators: the first damping support in each pair is rigidly fixed by means of a stop on the upper plate, the second damping support in a pair is rigidly fixed by means of a stop on the lower plate. Moreover, the projection of the stop installed on the upper plate enters the cavity of the stop installed on the lower plate, forming a zigzag connection. At the ends of the stops, rubber-metal buffers are installed, which soften the impact and limit the range of motion under dynamic load.

Claims (2)

1. A vibration damper for suspending the target load to the aircraft, containing connected to each other by a rigid detachable connection, the upper installation plate, upper and lower corner connectors, cable vibration isolators, each of which contains two strips and a cable between them, which is an elastic element of cable vibration isolator, characterized by,which additionally contains a lower mounting plate, a streamlined casing, middle connectors located symmetrically relative to the centers of the upper and lower plates and relative to each other, shock-absorbing supports; moreover, the upper and lower corner connectors are located symmetrically relative to the center of the upper plate and the lower plate, respectively, and relative to each other, while cable vibration isolators are located symmetrically relative to the upper and lower plates, while cable vibration isolators are installed at the corners of the upper and lower mounting plates at an angle of 45 ° in relation to each other using corner connectors top and bottom; at the same time, vibration isolators are installed opposite each other along the edges of the mounting plates perpendicular to the plates using medium connectors, in the middle between the angular vibration isolators; damping supports are arranged in pairs symmetrically relative to the centers of the upper and lower plates and relative to each other, each damping support contains rubber-metal buffers to limit movement along the vertical and horizontal axes Y and Z; each pair of shock-absorbing supports is installed in such a way that it is possible to engage them while simultaneously breaking the cable vibration isolators: the first shock-absorbing support in each pair is rigidly fixed with a stop on the upper plate, the second shock-absorption support in a pair is rigidly fixed with a stop on the lower plate, and the protrusion of the stop installed on the upper plate enters the cavity of the stop installed on the lower plate, forming a zigzag compound; rubber-metal buffers are installed on the ends of the stops, which soften the impact and limit the range of motion under dynamic load. 2. A vibration damper for suspending the target load to the aircraft according to claim 1, characterized in that the rigid detachable connection is made using screws.

Images