RU220486U1 - UAV PAYLOAD DISCHARGE DEVICE - Google Patents

Abstract

The utility model relates to equipment for an unmanned aerial vehicle, in particular to a payload release device. The technical results that the utility model is aimed at achieving are to increase the reliability of fastening and releasing the payload and increasing the safety of operation of the UAV with a payload release device. The specified technical results are achieved in a UAV payload release device, which includes a base with a fixed half-ring and an electric drive located on the base, as well as a movable half-ring, the first end of which is connected to the first end of the fixed half-ring by an axis with the possibility of rotation, and the second end is detachably connected to the second end of the fixed half-ring. half rings by means of a locking element. Technical results are achieved in that the locking element is equipped with a first cylindrical spring to hold the locking element in the closed position, the movable half-ring is equipped with a second cylindrical spring to hold the movable half-ring in the open position, and the base is equipped with a transverse wall to which a thrust plate is attached using a detachable threaded connection with cutouts designed to accommodate different payload shapes. 4 salary f-ly, 6 ill.

Description

The utility model relates to additional equipment for an unmanned aerial vehicle (hereinafter referred to as UAV), in particular to a UAV payload release device.

A device for releasing the payload of a UAV, namely grenades, is known, see the description of the patent RU 174729 U1, IPC B64D 1/02, publ. 01/18/2021, including a container in the cavity of which an actuator with two cables and a fastening unit are located.

The disadvantages of the device are:

excessive design complexity due to the use of cables for removing the safety pin with a ring from the grenade and for attaching the grenade body;

high labor intensity of manufacturing;

insufficient reliability of the device;

unsuitability for dropping ammunition of a different design from a UAV, for example, VOG-17 and VOG-25 rounds for grenade launchers.

A device for releasing a UAV payload is known, see the description of the patent RU 201868 U1, IPC B64D 1/02, publ. 01/18/2021, including a monolithic body with a groove, a pin installed in the groove, an electric drive and a double-armed lever that converts the rotation of the electric drive shaft into the forward movement of the pin.

The device, known from patent RU 201868 U1, allows for the release of payload in the form of mines and ammunition.

The disadvantages of the device are:

limited scope of application due to execution without taking into account the design and shape of ammunition;

unsuitability for dropping grenades F1, RGD5;

unsuitability for discharging VOG-17, VOG-25 rounds for grenade launchers without modifying their design.

A device for releasing the payload of a UAV, namely six RGD-5 or F-1 grenades, is known, see the description of the patent RU 2733904 C1, IPC V64S 39/02, B64D 1/02, publ. 10/08/2020, including vertically oriented cylindrical barrels for placing grenades, with side holes for extending the antennae of the safety pin and removing the ring, grenade body latches located inside the barrels and equipped with rubber pads, and electric drives for moving the latches.

The location of the grenade in the cylindrical barrel prevents the trigger lever of the hand grenade from being folded back after the antennae of the safety pin are unbent and the ring is removed.

The disadvantages of the device, known from patent RU 2733904 C1, are:

excess weight due to the implementation of trunks in the form of pipe sections;

significant height of the UAV equipped with a release device, due to the presence of vertical trunks.

The closest analogue is a device for dropping a UAV payload, in particular, a bomb for extinguishing a fire, known from the description of the patent CN 108371767 A, IPC A62S 3/02, A62S 31/00, A62S 37/00, V64S 25/10, V64S 25 /62, B64D 45/00, pub. 07/08/2018 The analogue includes a base, a fixed and movable half-ring, the first ends of which are connected by an axis with the possibility of rotation, and the second ends are removably connected by a locking element, an electric drive for moving the locking element.

The disadvantages of the device are:

excess weight due to the manufacture of half rings from a hollow cylinder of considerable length;

unsuitability for dropping grenades F1, RGD5;

limited scope of application due to execution without taking into account the design and shape of the ammunition.

The objective of the proposed technical solution is to create a UAV payload release device that provides:

safe equipment of the UAV with a payload in the form of F1, RGD5 grenades;

reliable mounting of the payload on the UAV;

reliable release of payload from a UAV;

the ability to use F1, RGD5 grenades and VOG-17, VOG-25 rounds for grenade launchers as a payload.

The technical results that the utility model is aimed at achieving are to increase the reliability of attaching and releasing the payload and increasing the safety of operation of the UAV with a payload release device.

The above technical results are achieved in a device for attaching and releasing a UAV payload, including:

a base with a fixed semi-ring and an electric drive located on the base, as well as

a movable half-ring, the first end of which is connected to the first end of the fixed half-ring by an axis with the possibility of rotation, and the second end is detachably connected to the second end of the fixed half-ring by means of a locking element.

Technical results are achieved by:

the locking element is provided with a first coil spring for holding the locking element in a closed position;

the movable half-ring is equipped with a second cylindrical spring to hold the movable half-ring in the open position;

the base is equipped with a transverse wall, to which a thrust plate with cutouts made to accommodate different payload shapes is attached using a detachable threaded connection.

In this case, the threaded connection may include a wing nut for fastening the thrust plate without tools.

In this case, on the thrust plate to the left of the cutouts there are inscriptions indicating the type of payload.

In this case, each half-ring can be made in the form of a frame of two plates and partitions connecting the plates.

The base, cross wall, semi-ring plates and partitions can be made of D16 aluminum alloy.

In FIG. 1 shows the device, general view.

In FIG. Figure 2 shows the device, side view.

In FIG. Figure 3 shows the device, front view.

In FIG. Figure 4 shows the details of the base and the fixed half ring.

In FIG. 5 shows a locking element.

In FIG. 6 shows a plate of a movable half ring.

Reference numbers in FIG. 1-6 are marked:

1 - UAV payload release devices; 2 - base;

3 - fixed half ring; 4 - electric drive; 5 - movable half ring;

6 - first cylindrical spring; 7 - second cylindrical spring;

8 - transverse wall; 9 - thrust plate with cutouts;

10 - inscription on the thrust plate; 11 - wing nut;

12 - plate of a fixed half ring; 13 - plate of the movable half ring;

14 - partition of a fixed semi-ring in the form of a plate;

15 - partition of a fixed semi-ring in the form of a sleeve;

16 - partition of a movable half ring in the form of a sleeve; 17 - locking element.

The utility model can be successfully implemented in the UAV payload release device 1 (Fig. 1-3), which includes a base 2 with a fixed semi-ring 3 and an electric drive 4 located on the base 2, as well as a movable semi-ring 5, the first end of which is connected to the first end of the fixed one. the half ring 3 has a rotatable axis, and the second end is detachably connected to the second end of the fixed half ring 3 by means of a locking element 17.

To implement the utility model, the following changes are made to the design of the UAV payload release device 1.

A cam is installed on the motor shaft of electric drive 4 to interact with the locking element.

The locking element 17 (Fig. 5) is connected to the fixed half-ring 3 by an axis and is equipped with a first cylindrical spring 6 to hold it in the closed position.

Spring 6 makes it possible to increase the reliability of holding the payload in the UAV payload release device 1 and the safety of UAV operation.

The movable half-ring 5 is equipped with a second cylindrical spring 7 to hold the movable half-ring 5 in the open position.

The spring 7 is guaranteed to move the end of the movable half-ring 5 away from the locking element 17, increasing the reliability of payload release and the safety of UAV operation.

The base 2 (Fig. 4) is equipped with a transverse wall 8, to which a thrust plate 9 with cutouts made to accommodate different payload shapes is attached using a detachable threaded connection.

The presence of a thrust plate 9 makes it possible to increase the reliability of fastening the payload in the release device and the safety of UAV operation.

Fastening the thrust plate 9 using a threaded connection allows you to select a cutout on the plate 9 that matches the shape of the payload.

In addition to ensuring the reliability of payload mounting by taking into account the shape of the payload, it becomes possible to use both F1 and RGD5 grenades and VOG-17, VOG-25 rounds for grenade launchers as payloads.

To increase the safety of operation of a UAV with a payload release device, inscriptions 10 are made on the thrust plate 9 to the left of the cutouts, indicating the type of payload.

To increase the reliability of payload mounting and increase the operational safety of a UAV with a payload release device, each half-ring 3, 5 is made in the form of a frame of two plates and partitions connecting the plates.

To increase operational safety, the base, transverse wall, half-ring plates and partitions are made of durable and lightweight aluminum alloy D16.

Device 1 is attached to the bottom of the UAV using threaded connections.

Before installing the payload, its type is determined and the thrust plate 9 is rotated relative to the base 2 so that the corresponding cutout in the plate 9 is located opposite the base 2. The inscription 10 on the plate 9 to the left of the cutout corresponds to the designation of the payload being used. The thrust plate 9 is fixed using a threaded connection.

The payload in the form of an RGD-5, F-1 grenade is installed on a fixed half-ring 3 with the grenade lever to the base 2 of device 1 and is fixed using a movable half-ring and a locking element 17. The grenade fuse is pressed against the cutout in the plate 9.

The payload in the form of a VOG-17, VOG-25 shot for a grenade launcher is installed on a fixed half-ring 3 and is fixed using a movable half-ring and a locking element 17. The front part of the shot is pressed against the cutout in plate 9.

On one UAV, depending on the type of the latter, can be installed from one to four payload release devices 1, equipped with RGD-5, F-1 grenades or VOG-17, VOG-25 rounds for a grenade launcher.

Device 1 as part of the UAV is used as follows.

When the UAV hovers over the drop site, upon command from the radio control panel, supply voltage is supplied to the electric drive 4 of one of the devices 1.

The cam mounted on the motor shaft of the electric drive 4 rotates and, overcoming the resistance of the first cylindrical spring 6, removes the locking element 17 from engagement with the movable half-ring 3. The freed end of the movable half-ring 5, under the action of the second cylindrical spring 7 and the mass of the payload, moves away from the locking element 17 , and the payload falls from the UAV device 1 from a height of 30-40 meters to the drop site.

When using the RGD-5, F-1 grenade, the grenade lever changes its position, the fuse hits the primer and ignites the powder retarder. After the moderator burns out, after 3-4 seconds, the detonator capsule is triggered and the main charge of the grenade explodes.

In the case of using a VOG-17, VOG-25 shot for a grenade launcher, the fuse is triggered by an impact on a hard surface when dropped from a height of more than 3 meters.

Conducted patent research confirms the world novelty of the utility model.

The operation of prototypes of the utility model confirmed its industrial applicability and compliance with the stated technical results.

Claims (5)

1. A UAV payload release device, including a base with a fixed half-ring and an electric drive located on the base, as well as a movable half-ring, the first end of which is connected to the first end of the fixed half-ring by an axis with the possibility of rotation, and the second end is detachably connected to the second end of the fixed half-ring by means of a locking element, characterized in that the locking element is equipped with a first cylindrical spring to hold the locking element in the closed position, the movable half-ring is equipped with a second cylindrical spring to hold the movable half-ring in the open position, and the base is equipped with a transverse wall to which a thrust plate is attached using a detachable threaded connection with cutouts designed to accommodate different payload shapes. 2. The device according to claim 1, characterized in that the threaded connection includes a wing nut. 3. The device according to claim 1, characterized in that on the thrust plate to the left of the cutouts there are inscriptions indicating the type of payload. 4. The device according to claim 1, characterized in that each half-ring is made in the form of a frame of two plates and partitions connecting the plates. 5. The device according to claim 1, characterized in that the base, transverse wall, half-ring plates and partitions are made of D16 aluminum alloy.