RU2283469C1 - Device for fixing of folded flight vehicle aerodynamic surfaces - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the device has an assembly providing adjoining of folded aerodynamic surfaces to the flight vehicle fuselage, and an actuating locking mechanism linked with the assembly provided adjoining of folded aerodynamic surfaces to the flight vehicle fuselage with a probability of detachment. The assembly providing adjoining of folded aerodynamic surfaces to the flight vehicle fuselage consists of the first catching member positioned on the tip of the folding aerodynamic surface, and the second catching member, whose one end is linked with the first catching member, and the other - with the actuating locking mechanism and made in the form of a stopper having a body with a union and a spring-loaded rod installed in the body for axial translation and engaged with the second catching member.

EFFECT: enhanced reliability of device operation.

4 dwg

Description

The invention relates to fixation devices, in particular to devices for fixing folding aerodynamic surfaces of aircraft (LA) in the folded position.

A device for fixing the folded aerodynamic surfaces of an aircraft (see US patent No. 3921498, 1974.24.05., NKI 244-3.28) containing a fork-shaped element that holds the aerodynamic surfaces of the aircraft in the folded position, and a stopper in the form of a flag.

The disadvantages of this device include the fact that it does not provide vibration resistance of aerodynamic surfaces in the folded position due to their free fastening, which leads to a reduction in the shelf life of the aircraft. Also disadvantages include the bulkiness of the device, which imposes additional requirements for the placement of the aircraft.

It is also known a device for fixing the folding aerodynamic surfaces of an aircraft (see US patent No. 2977880, 1959.07.04, NKI 244-3.29), containing a node for securing the fit of the folded aerodynamic surfaces to the aircraft body, made in the form of a flag, as well as an actuating locking mechanism, associated with the node, ensuring the fit of the folded aerodynamic surfaces to the aircraft body, made in the form of a burning check. This device is the closest analogue to the claimed proposal and is selected as a prototype.

The disadvantages of the prototype include: low vibration resistance of the fixed aerodynamic surfaces, poor controllability of the aircraft at start in case of icing, low reliability of the device when the engine fails at the time of starting the aircraft, the unsynchronism of such operation, as well as the increased cost of the device due to its multi-component nature.

The present invention is aimed at solving the following problems:

- improving the reliability of the device, especially when working in icing conditions, as well as in case of emergency situations in the operation of the aircraft engine;

- ensuring synchronization of the disclosure of fixed aerodynamic surfaces of the aircraft;

- optimization of the overall mass characteristics of the device;

- reducing the impact of vibration loads on the folded aerodynamic surfaces of the aircraft.

The tasks are solved due to the fact that in the proposed device for fixing the folded aerodynamic surfaces of the aircraft, which consists of a node that ensures the fit of the folded aerodynamic surfaces to the body of the aircraft, and an executive locking mechanism connected to the node that ensures the fit of the folded aerodynamic surfaces to the body of the aircraft, with with the possibility of detachment, the assembly ensuring the fit of the folded aerodynamic surfaces to the aircraft body consists of the first engagement element, located laid on the tip of the folding aerodynamic surface, and the second engagement element, one end connected to the first engagement element, and the other to the executive locking mechanism, made in the form of a stopper containing a housing with a fitting and a spring-loaded rod mounted in the housing with axial movement and entering meshing with the second engagement element, wherein the actuating locking mechanism is mounted on the aircraft in such a way that the direction of the action force of the second engagement element Ia was close to perpendicular to the middle surface of the folded lockable airfoil LA.

This design makes it possible to increase the vibration resistance of the aerodynamic surfaces of the aircraft in the folded position due to the tight fit to the aircraft body, to increase the reliability of locking and the density of the layout of the aircraft, to ensure the reliability of operation of the device in conditions of possible icing due to a simpler device design than the prototype, as well as in case of emergency situations in the operation of the aircraft engine at startup.

The invention is illustrated by drawings, where

figure 1 shows a General view of the aircraft from the side with folded aerodynamic surfaces and a device for their fixation;

figure 2 shows the device for fixing the folded aerodynamic surfaces of the aircraft with the first and second engagement elements;

figure 3 shows the aerodynamic surface of the aircraft, rear view;

figure 4 - Executive locking mechanism with a second engagement element, section bb.

Figure 1-4 shows the position in the following order:

1 - upper aerodynamic surface;

2 - tip of the upper aerodynamic surface;

3 - lower aerodynamic surface;

4 - node, ensuring the fit of the folded aerodynamic surfaces to the aircraft body;

5 - executive locking mechanism;

6 - the first element of engagement;

7 - the second element of engagement;

8, 9 - screw;

10 - adjusting clutch;

11.12 - lock nut;

13 - loop;

14 - stock;

15 - spring;

16 - aircraft body;

17 - housing executive locking mechanism;

18 - fitting;

19 - gargrot.

The device for fixing the folded aerodynamic surfaces of the aircraft consists of a node that ensures the fit of the folded aerodynamic surfaces to the body of the aircraft (4), and the executive locking mechanism (5). The assembly ensuring the fit of the folded aerodynamic surfaces to the body of the aircraft (4) can be configured to control the degree of fit, while it includes a first engagement element (6) and a second engagement element (7).

The first engagement element (6) is mounted on a folding aerodynamic surface, for example, on the upper aerodynamic surface (1), and can be made either as a separate part or integrally with the aerodynamic surface, for example, as shown in FIGS. 1-2, at the tip (2) the upper aerodynamic surface (1).

The second engagement element (7) can be made, for example, as shown in FIG. 2, in the form of two screws (8, 9), with the opposite direction of the thread, connected by an adjusting sleeve (10), with locknuts (11,12), with In this case, the free ends of the screws (8.9) pass into the loops (13). The second engagement element (7) can also be made in the form of a cable, rubber band or other design that can withstand a given tensile force.

The first gearing element (6) and the second gearing element (7) are interconnected, and their connection can be either detachable or one-piece, depending on the specific conditions. If it is necessary to make a one-piece connection, the first gearing element (6) can be made, for example, in the form of a loop, and the first end of the second gearing element (7), which is involved in connecting with the first gearing element (6), can also be made in the form loops. If it is necessary to make the connection detachable, the first engagement element (6) can be made, for example, in the form of a hook, as shown in figures 1 and 2.

The actuating locking mechanism (5) can be made, for example, as shown in Fig. 4, in the form of a stopper with a housing (17), in which a rod (14) is installed that can move inside the housing (17) along the axis of the housing (17), for example , under the influence of the working fluid entering through the fitting (18). The rod (14) of the actuating locking mechanism (5) is in contact with one end with the spring (15), and the other end is engaged with the loop (13) of the second engagement element (7).

The executive locking mechanism (5) is mounted on the aircraft and can be installed both on the body of the aircraft (16) and on the garrot (19), as shown in Fig. 1. A necessary condition for choosing the installation location of the executive locking mechanism (5) is that the direction of action of the second engagement element (7) should be close to the perpendicular direction relative to the middle surface of the folded fixed aerodynamic surface (1) of the aircraft. The median surface is the surface of the wing chords — a surface (in a particular case, a plane) containing all wing chords (see AVIATION: Encyclopedia. / Ed. By GP Svishchev. - M.: Big Russian Encyclopedia, 1994. - 736 p., P. 642).

The stopper of the actuating locking mechanism (5) can be either pneumatic, hydraulic or another type.

A device for fixing the folded aerodynamic surfaces of an aircraft operates as follows.

After folding the aerodynamic surfaces (1,3), for example, as shown in Fig. 1, the first engagement element (6) is connected to one end of the second engagement element (7), and the other end of the second engagement element (7) is connected to the rod (14 ) executive locking mechanism (5). To lock the second engagement element (7), the rod (14) is retracted while compressing the spring (15), a loop (13) is inserted into the groove of the stopper housing of the actuating locking mechanism (5), as shown in Fig. 4, and the rod (14) is released ) Under the action of the force of the compressed spring (15), the rod (14) moves and fixes the loop (13) of the second engagement element (7). To create the necessary degree of fit of the folded aerodynamic surfaces (1, 3) to the aircraft body, the adjusting sleeve (10) of the second engagement element (7) is wrapped with a moment of a certain value in the direction of decreasing the length of the second engagement element (7). To prevent spontaneous unwinding of the adjusting sleeve (10), it is locked with locknuts (11,12).

The second gearing element (7) is disconnected from the actuating locking mechanism (5) as follows. The working fluid through the fitting (18) is fed into the inner cavity of the housing of the actuating locking mechanism (17). Under the influence of the pressure of the working fluid due to the difference in the diameters of the working surfaces of the rod (14), the rod (14) moves, compressing the spring (15), disengages from the loop (13), thus freeing the second engagement element (7).

When the first engagement element (6) and the second engagement element (7) are detachable during the unfolding of the aerodynamic surfaces (1, 3) under the action of inertial forces and the incoming flow, the second engagement element (7) is separated from the first engagement element (6) and carried away flow.

When the first engagement element (6) and the second engagement element (7) are inseparably, after the second engagement element (7) is disconnected from the actuating locking mechanism (5), the latter remains hanging, connected to the first engagement element (6), on the aerodynamic surface (7) .

After depressurizing the working fluid, the rod (14) of the actuating locking mechanism (5) under the action of the compressed spring (15) returns to its original position.

Thus, the invention compared with the prototype allows to increase the reliability of the device for fixing the folded aerodynamic surfaces of the aircraft, especially when working in icing conditions, due to the optimal placement of its components. The invention also allowed to obtain optimal overall mass characteristics, which improves the layout of the aircraft and reduces its cost. In addition, as a result of reducing the impact of vibration loads on the folded aerodynamic surfaces of the aircraft, it became possible to increase the shelf life of the aircraft.

Claims (1)

The device for fixing the folded aerodynamic surfaces of the aircraft, consisting of a node that ensures the fit of the folded aerodynamic surfaces to the body of the aircraft, and an actuating locking mechanism connected to a node that ensures the fit of the folded aerodynamic surfaces to the body of the aircraft, with the possibility of disconnection, characterized in that the node , ensuring the fit of the folded aerodynamic surfaces to the body of the aircraft, consists of the first engagement element located at the tip of the folding aerodynamic surface, and the second engagement element, one end connected to the first engagement element, and the other with the actuating locking mechanism, made in the form of a stopper containing a housing with a fitting and a spring-loaded rod mounted in the housing with the possibility axial movement and engaging with the second engagement element, while the actuating locking mechanism is mounted on the aircraft in such a way that the direction of action of force of the second engagement member was close to perpendicular to the middle surface of the folded lockable aerodynamic surface of an aircraft.

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