RU2765523C1 - Launching unit in a closed compartment - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aviation equipment, namely, to launching units placed in closed compartments of aircrafts. The launching unit in a closed compartment comprises the body of a cargo compartment, located longitudinally in the lower part of the fuselage of the aircraft, a launch container placed within the body of the cargo compartment, equipped in the back part thereof with a unit for mechanical coupling with the back wall of the cargo compartment, and in the front part thereof with a rotary apparatus connecting said body with the front wall of the cargo compartment and bringing the launch container into a position for launching cargo and returning said container to the travel position. A body with a U-shaped cross-section is made on the outside of the launch container. Said body acts as a flap of the cargo compartment, forming an integral plane with the surface of the fuselage of the aircraft in the travel position of the launch container.

EFFECT: invention provides a reduction in the time of cargo launch and a reduction in the radio location visibility of the aircraft at the time of cargo launch.

2 cl, 4 dwg

Description

The present invention relates to aviation technology, namely to launchers placed in closed compartments of aircraft.

From the prior art, a cargo compartment with flaps is known, placed inside the fuselage of an aircraft (patent RU No. 2583824, publ. 10.05.2016). The disadvantage of this technical solution is that before pushing the cargo placed inside the cargo compartment by the launcher, it takes a certain time to open the doors of the compartment and bring the launcher into position for launching the cargo. The compartment doors themselves and their mechanization complicate the cargo compartments and, together with the launchers placed in them, take up a lot of space in the cross section of the compartment.

Also known from the prior art is a transport and launch container according to RF patent No. 2350885 (publ. 27.03.2009). This container is used as part of sea and land complexes, and a launcher is required to bring it into the cargo launch position, which makes it impossible to use it on aircraft due to the limited space inside the cargo compartment.

The objective of the present invention is to reduce the launch time of the cargo, reduce the radar visibility of the aircraft at the time of the launch of the cargo, the creation of a launcher in the closed compartment of the aircraft, which combines bringing the specified installation into position for launching the cargo with opening the cargo compartment.

The technical result of the claimed invention is the simplification of the design and, as a result, the reduction of the time required to launch the cargo from the closed compartment.

The claimed technical result is achieved by a launcher in a closed compartment, containing a cargo compartment body longitudinally located in the lower part of the fuselage of the aircraft, a launch container located inside the cargo compartment body, which in its rear part is equipped with a mechanical interface unit with the rear wall of the cargo compartment, and in its front part is equipped with a rotary device connecting it to the front wall of the cargo compartment and carrying out bringing the launch container to the position for launching the cargo and returning to the stowed position; , forming a single plane with the surface of the fuselage of the aircraft in the stowed position of the launch container.

The launcher in the closed compartment may consist of at least two independent launch containers placed parallel to each other in the body of the cargo compartment.

Due to the fact that the body of the launch container acts as the cargo compartment hatch flap, the process of opening the flap and bringing the launch container into position for launching the cargo is combined, which simplifies the design and significantly reduces the launch time of the cargo.

In FIG. 1 shows a general view of the launcher in the stowed position.

In FIG. 2 shows a diagram of the launcher in the stowed position in cross section.

In FIG. 3 shows a general view of the launcher in position for launching cargo.

In FIG. 4 shows a diagram of the launcher in the position for launching the load in cross section.

The launcher in a closed compartment contains a cargo compartment body 1, a launch container 2 located inside the cargo compartment, which is a hollow cylindrical body with a "blind" bottom, in the rear part from the bottom side, the launch container 2 is equipped with a mechanical interface assembly 3 with the rear wall (not shown ) cargo compartment 1, made in the form of shock-absorbing suspension. In front of the launch container 2 is equipped with a rotary device 4, connecting it with the front 5 wall of the cargo compartment 1. The rotary device 4 is driven by a drive 6, which can be hydraulic or electric. On the upper wall 7 of the cargo compartment 1 there is a cover 8 with a drive, which is pressed against the end of the front part of the launch container 2 in the stowed position, providing its additional fixation. On the outer side of the launch container 2, a housing 9 of U-shaped cross section is made, while the outer wall of the housing acts as a cargo compartment flap, in the stowed position forming a single plane with the surface of the aircraft fuselage.

In the stowed position, the launch container is located inside the cargo compartment coaxially with the axis of the aircraft. When a signal is received to launch the cargo, the drive 6 through the rotary device 4 extends the front part of the launch container 2 from the cargo compartment, ensuring its location at the angle necessary for launching the cargo relative to the axis of the aircraft. Simultaneously with the extension of the launch container 2, the cargo compartment door opens, the role of which is played by the body 9 of a U-shaped cross section, made on the outer side of the launch container 2. When the launch container 2 reaches the angle necessary for launching the cargo, a powder charge is activated, located inside the back of the launch container behind the payload (not shown). The cargo is released in the direction of movement of the aircraft, while undermining the powder charge, a force arises that acts in the direction opposite to the direction of the launch of the cargo and acts on the bottom of the launch container. The specified force is extinguished by the node 3 of the mechanical interface of the rear part of the launch container 2 with the rear wall of the cargo compartment, made in the form of a shock-absorbing suspension. After the release of the load, the drive 6 through the rotary device 4 brings the launch container to the stowed position, placing it inside the cargo compartment coaxially with the axis of the aircraft. In the stowed position, the body 9 of U-shaped cross section, made on the outer side of the launch container 2, forms a single plane with the surface of the fuselage.

Claims (2)

1. A launcher in a closed compartment, containing a cargo compartment body longitudinally located in the lower part of the fuselage of the aircraft, a launch container located inside the cargo compartment body, which in its rear part is equipped with a mechanical interface with the rear wall of the cargo compartment, and in its front part it is equipped with a rotary device connecting it to the front wall of the cargo compartment and carrying out bringing the launch container to the position for launching the cargo and returning to the stowed position, on the outer side of the launch container there is a U-shaped cross-sectional body, while the said body acts as a cargo compartment flap, forming a single plane with the surface of the fuselage of the aircraft in the stowed position of the launch container. 2. A launcher in a closed compartment according to claim 1, characterized in that it consists of at least two independent launch containers placed parallel to each other in the cargo compartment housing.

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