DE3236584C2 - Device for suspending and releasing external loads on aircraft - Google Patents

Abstract

Device for hanging and releasing external loads on aircraft, in which, in addition to an automated hanging process for the external load, its secure locking is guaranteed and the necessary small or large forces can be applied to the hook for its release.

Description

25th

The invention relates to a device for suspending and releasing external loads on aircraft the generic term of the claim.

Devices of the type mentioned are used to carry external loads on aircraft and to to bring these to dropping despite the large forces occurring during the flight. In addition to this large tensile forces are to be transmitted by a suspension device, as the external loads to avoid Self-movements are usually firmly braced against fixed points on the aircraft.

Furthermore, for reasons of simplified and quick operation, this device is the actual one Automate the hanging process for the external load as far as possible, but it must be ensured under all circumstances that that the suspension cannot come loose unintentionally. On the other hand, it must also be ensured that despite the high forces already mentioned, the dropping of the external load from the aircraft to the Release time can take place.

GB-PS 10 19 828 describes a device in which the hanging process is automated, but is through a wedge load and through the links held in line by means of a spring action, as well as through its asymmetrical loading of the hooks exposed to the risk that it can come loose in an uncontrolled manner, or on the other hand, the links and / or the hook become wedged or eat due to the aforementioned high forces and the hook for dropping the external load cannot be opened.

DE-OS 27 58 131 a device according to the generic term of the claim has become known, which, however, requires a manual adjustment and a high level of component and component costs requires a large amount of space.

The object of the invention is a device for suspending and releasing external loads on aircraft to create that only takes up a small amount of space in the airframe and is still reliable Load release guaranteed.

This object is achieved by the features listed in the characterizing part of the patent claim.

An embodiment of the invention is shown in the drawing and is described in more detail below:

The only figure of the drawing shows a schematically simplified side view of the device.

On a bearing 7 fixed to the aircraft, an angle lever 5 and a tie rod 14 are provided Rocker 4 rotatably mounted, which has a stop 8 to a surface 16 on the angle lever 5 and to a support 2 on a coupling lever 3.

The coupling lever 3, which is connected to the rocker 4 via a knee joint 9, is supported with one on its End located recess 15 against a roller 6 on the angle lever 5 and engages with his other End via a pivot point 12 on the hook 1, which is pivotable on a further bearing 11 fixed to the aircraft is stored.

The way the device works is as follows:

As shown in the drawing, the support of the coupling lever 3 with its recess 15 on the roller 6 of the angle lever 5 of the hook 1 automatically locked after he lifted the outer glass ;, About the eyelet 10 was set in a closing pivoting movement.

The hook 1 is released by means of a pulling movement de; · Pull rod 14 on the angle lever 5, whereby the roller 6 moves out of the recess 15 of the coupling lever 3 and first unlocks the hook 1.

Subsequently, the continued movement of the angle lever 5 by means of the pull rod 14 causes its surface 16 exerts a sliding movement on the stop 8 of the rocker 4. The stop 8 moves thereby Via the support 2 on the coupling lever 3 this around the knee joint 9 with the rocker 4 and pulls it over the pivot point 12 on the pivotable about another aircraft-fixed bearing 11 hook 1 until it is completely is resolved.

1 sheet of drawings

Claims (1)

Claim: Device for attaching and releasing an external load on an aircraft with one on one aircraft-mounted bearing consisting of a swiveling hook which is connected to a toggle mechanism from a coupling lever articulated to the hook and one on a bearing fixed to the aircraft mounted rocker arm and with an angle lever rotatably mounted in its apex, with its one leg, the triggering movement of the toggle mechanism can be locked and with the other Leg, the triggering movement can be initiated, characterized in that the aircraft most bearings (7) of the rocker arm (4) of the angle lever (5) is mounted and that the coupling lever (3) is provided with an extension beyond the knee joint (9) is that when the load is suspended in the release direction against one leg of the angle lever (5) and against the triggering direction against a stop (8) arranged on the rocker arm (4).