RU2785298C1 - Turntable for safe separation of goods - Google Patents

Abstract

FIELD: aviation technology.

SUBSTANCE: invention relates to aviation technology. The turntable for separating cargo contains a frame (1) designed to accommodate cargo (2). The frame (1) with its rear edge is hinged on the inner surface of the cargo compartment of the aircraft, and on its front edge on the upper side there is a rotary mechanism (4) made in the form of two links (5, 6). On the upper side of the frame (1) there is a drive (8) that provides folding, unfolding and fixation in the unfolded position of the links (5, 6) of the rotary mechanism (4), attached to one of the links of the rotary mechanism. The frame (1) is designed to be fixed inside the aircraft body during transportation. The unfolded position of the links of the rotary mechanism is the arrangement of the links in a straight line.

EFFECT: expansion of the area of altitudes and aircraft flight speeds, at which safe cargo separation is possible.

3 cl, 2 dwg

Description

The invention relates to aeronautical engineering and is intended, in particular, for use as a movable support for an ejection device equipped with a power drive for suspension, transportation and combat use on missile weapons aircraft.

When separating cargo from an aircraft, the initial conditions of separation, such as speed, height, velocity head, cargo mass, significantly affect the separation trajectory. If the critical level of velocity pressure is exceeded, the separation trajectory may become unsafe for the aircraft or cargo.

From the prior art, a unified intra-fuselage ejection device is known, equipped with a power drive (source RU 2381146 C2, 10.02.2010), which is intended for use as an ejection device for suspension of missile weapons on aircraft. The known device contains a housing with attachment points to the aircraft, an ejection mechanism, a power drive for launching a rocket, an onboard electrical connector for electrical connection of the rocket board with the aircraft board. The ejection mechanism is made in the form of front and rear output levers mounted for rotation on axles fixed in the housing. The axis of the front output lever is located in the zone of the rear yoke of the rocket, and the axis of the rear output lever is located in the zone of the front yoke of the rocket, respectively. Said output levers are connected in the middle part by a rocking chair synchronizing their movement and carried on free end sections by hinged carriages for attaching the rocket. The carriage fixed on the rear lever has a ejector placed in the carriage guides and interconnected by a rod with the front output lever, and both the front output lever and the rear output lever are equipped with stops. The power drive comprises a body with attachment points, a hollow plunger with a squib placed in it, a combustion chamber, an electrical harness for supplying an electric pulse to the squib. The squib is equipped with an electric igniter with two glow bridges and is made in the form of a cylindrical sleeve with relative elongation λ=3…5, which makes it possible to equip with a variable amount of fuel.

The disadvantage of the known device is the inability to adapt in flight to various modes of cargo release, due to the impossibility of changing the angle and speed of cargo separation, which leads to the fact that safe cargo separation can not be carried out in all areas of altitudes and flight speeds.

Also known from the prior art is a method for ensuring the safe separation of cargo from the intra-fuselage compartments by lowering the platform together with missiles, bombs and a launcher outside the contour of the aircraft for subsequent launching into the cargo stream (source WO 2011081579 A1, 07.07.2011).

The disadvantages of this technical solution are its large mass, sufficiently large strokes of the actuators, the complexity of the design and the lack of safe separation of cargo at any heights and speeds.

Thus, the objective of the claimed invention is to eliminate the shortcomings of the prior art.

The technical result, to which the claimed invention is directed, is the expansion of the area of altitudes and aircraft flight speeds, at which safe cargo separation is possible.

This technical result is fully achieved by a combination of features of an independent claim.

The turntable for separating the load contains a frame designed to accommodate the load. The frame is hinged with its rear edge on the inner surface of the cargo compartment of the aircraft, and on its front edge on the upper side there is a rotary mechanism made in the form of two upper and lower links. On the upper side of the frame, a drive is installed that provides folding, unfolding and fixing in the unfolded position of the links of the rotary mechanism, attached to the lower link of the rotary mechanism. The frame is made with the possibility of fixation inside the aircraft body during transportation. The unfolded position of the links of the rotary mechanism is the arrangement of the links in a straight line.

In the transport position, the frame with the load is located within the outer contour of the aircraft.

The fixing device, installed on the inner surface of the cargo compartment, ensures the fixation of the frame in the transport position and is a transport position lock that interacts with the frame in its transport position.

In the unfolded position of the rotary mechanism, the frame is located in the starting position, in which the rear edge of the frame is located within the outer contour of the aircraft, and the front edge of the frame is located outside the outer contour of the aircraft.

Further, the claimed invention is explained in more detail by the drawings, in which:

Fig. 1 - transport position of the declared platform.

Fig. 2 - starting location of the declared platform.

SUBSTANCE: turntable for separating cargo contains a frame (1) for placing cargo (2) installed at one end on a fixed axle (3), and a rotary mechanism (4) made in the form of two links. The first link (5) of the swivel mechanism (4) is pivotally fixed on the frame (1) with its lower end, its upper end is pivotally attached to the lower end of the second link (6) of the swivel mechanism (4). The upper end of the second link (6) is pivotally attached to the body (7) of the aircraft. The rotary mechanism (4) is made with the possibility of folding, unfolding and fixing in the required position due to the drive (8) placed on the upper side of the frame (1), attached to the first link of the rotary mechanism (4). On the body (7) of the aircraft there is a lock (9) for the transport position of the frame (1), which ensures its reliable fixation inside the body (7) of the aircraft during transportation. The design of the transport position lock is not within the scope of the applicant's claims and can be made in any known manner.

The claimed platform works as follows.

During transportation, the cargo is located in the transport position, which is characterized by the location of the cargo inside the fuselage along the longitudinal axis of the aircraft. When a command is received, the lock (9) of the transport position is opened, energy is supplied to the drive (8), which changes its length, while the kinematic connection causes the links of the rotary mechanism to decompose into a line. During the unfolding process, the swivel mechanism (4) turns the frame (1) with the load (2) into the starting position.

The starting position is characterized by the location of the front part of the cargo outside the fuselage (external contour of the aircraft (10)) of the aircraft and with an angle that does not coincide with the longitudinal axis of the aircraft. In this position, an additional dive moment of the cargo is provided due to the influence of the oncoming flow, which allows you to safely separate the cargo in the entire range of altitudes and flight speeds.

When laying out the links in a line, the rotary mechanism becomes on the kinematic lock, and the rotary platform with the load moves to the starting position, while the front part of the load goes beyond the outer contour of the aircraft (10).

After separating the load, the platform moves to the transport position in reverse order.

Unfolding the links of the rotary mechanism in a line allows you to get a rigid thrust in the starting position, which eliminates the impact of starting loads on the drive.

The claimed platform is made quick-detachable.

Thus, due to the implementation of the turntable in the above manner, it is possible to safely separate cargo over the entire range of altitudes and aircraft flight speeds.

Claims (3)

1. A turntable for separating cargo, containing a frame designed to accommodate cargo, characterized in that the frame is hinged with its rear edge on the inner surface of the cargo compartment of the aircraft, and on its front edge from the upper side there is a rotary mechanism made in the form of two upper and lower links, while on the upper side of the frame there is a drive that provides folding, unfolding and fixing in the unfolded position of the links of the rotary mechanism, attached to the lower link of the rotary mechanism, and the frame is made with the possibility of fixing inside the aircraft body during transportation, while the unfolded position of the links The swivel mechanism is an arrangement of links in a straight line. 2. A turntable for separating the load according to claim 1, characterized in that in the transport position the frame with the load is located within the outer contour of the aircraft. 3. A turntable for separating cargo according to claim 1, characterized in that in the unfolded position of the rotary mechanism, the frame is located in the starting position, in which the rear edge of the frame is located within the outer contour of the aircraft, and the front edge of the frame is located outside the outer contour of the aircraft.

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