CN113086207B - Low-cost airborne hanging rack mechanism - Google Patents

Abstract

The invention discloses a low-cost airborne hanger mechanism, which comprises: a base; the embracing unit comprises a first embracing frame and a second embracing frame; the outer support is fixed on the outer side of the first holding frame; the safety plate is connected with the outer side support in an elastic and rotating mode through a fulcrum shaft of the safety plate; the safety component is arranged on the outer side of the first holding frame; one end of the binding belt is connected with the second holding frame; the other end of the binding belt is sleeved on the bottom hook part of the safety plate in a state that the missile is not released, so that the first holding frame and the second holding frame clamp the missile, and the safety part locks the flat plate part of the safety plate; the safety component unlocks the flat plate part of the safety plate in the state of releasing the missile, and the safety plate outwards rotates under the elastic force of the elastic rotating connection part of the safety plate so that the bottom hook part is completely separated from the other end of the binding belt. By adopting the scheme of the invention, the missile can be reliably clamped and released, and the cost is lower.

Description

A low-cost airborne pylon mechanism

technical field

The invention relates to the technical field of airborne auxiliary equipment, in particular to a missile pylon clamping mechanism for low-cost unmanned aerial vehicles.

Background technique

The main task of the UAV is to provide close air support to ground forces, and it can also perform persistent surveillance and reconnaissance missions in mountainous and dangerous areas. UAVs are more and more widely used in local conflicts, and missile-borne UAVs are a cost-effective weapon. In order to reduce costs, in addition to UAVs, missiles are also a huge consumable. Traditional missile pylons are provided with slide rails or lifting lugs, while small missiles are short due to their short shape, and the lugs or slide rails will occupy the missile’s space after installation. Part of the installation space affects the strength of small missiles and other technical indicators, and the cost of traditional missile pylons is relatively high. Therefore, it is necessary to design a small missile pylon suitable for multi-rotor or fixed-wing UAVs. release mechanism.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a low-cost airborne pylon mechanism, which can reliably clamp and release the missile, and has low cost.

The object of the present invention is achieved in this way: a low-cost airborne pylon mechanism, comprising:

Suspended and fixedly attached to the underside of the wing;

An embracing unit, which includes a first embracing frame and a second embracing frame that are rotatably connected to the base, the first embracing frame and the second embracing frame are relatively rotatable and the rotation axes of the two are on the upper side, the first embracing frame, The rotating shafts of the second holding frame are all coaxially provided with opening and closing gears, and the opening and closing gears of the first holding frame and the opening and closing gears of the second holding frame mesh with each other;

The outer support is fixed on the outer side of the first holding frame;

A rotatable safety plate, the safety plate has a fulcrum shaft as its central axis of rotation, the safety plate is elastically rotatably connected with the outer support through its fulcrum shaft, and the safety plate is divided into its main body based on the fulcrum shaft. part of the flat plate portion, and the bottom hook portion forming its bottom;

The safety part is installed on the outer side of the first holding frame and is used to lock and unlock the flat plate part of the safety board;

an elastic binding belt, one end of the binding belt is connected to the second holding frame;

Wherein, in the state where the missile is not released, the other end of the binding belt covers the bottom hook of the safety plate so that the first holding frame and the second holding frame clamp the missile, and the safety part locks the flat plate part of the safety plate; In the state of releasing the missile, the safety part unlocks the flat plate portion of the safety plate, and the safety plate is rotated outward by the elastic force of its elastic rotating connection to make the bottom hook part completely disengage the other end of the binding belt.

Further, there are two outer supports, the insurance plate is movably placed between the two outer supports, the fulcrum shaft is fixedly connected to the insurance plate, and the two shaft ends of the fulcrum shaft are respectively elastically rotatably connected to the two outer supports. an outer support.

Further, the insurance component includes:

A safety pin for locking the safety plate, the safety pin movably penetrates the outer support, the safety pin abuts against and locks the flat plate portion of the safety plate when the missile is not released, and the safety pin is in the state of releasing the missile. The pin is released from the flat portion of the safety plate;

A linear drive assembly that drives the safety pin to extend and retract axially.

Further, the first and second armatures are both set as V-shaped plate structures, and the V-shaped groove of the first armature is opposite to the V-shaped slot of the second armature, and the missile is not released when the missile is not released. It is clamped by the V-shaped groove of the first holding frame and the V-shaped groove of the second holding frame.

Further, the linear drive assembly of the safety component includes a drive motor, a drive gear, a rack and a rack sliding bearing seat, the drive motor is controlled by the airborne control system and the missile's electronic control system, and the drive motor and the gear are controlled by the electronic control system of the missile. The rack sliding bearing seat is installed on the outer side of the first bracket, the driving gear is sleeved on the main shaft of the driving motor, the toothed side of the rack is meshed with the driving gear, and the toothless side of the rack is slidably connected to the rack. In the support seat, one end of the safety pin is fixedly connected to the rack, and the length direction of the safety pin is parallel to the length direction of the rack.

Further, the drive motor is set as a worm gear motor.

The beneficial effects of the present invention are:

1. The missile can be released reliably and safely. In the state of releasing the missile, the drive motor is started through the onboard control system, and the safety pin is retracted through the transmission of the drive gear and rack, thereby releasing the safety component from the safety plate. Locked, the safety plate is rotated outwards by the elastic force of its elastic rotating connection so that the bottom hook is completely separated from the binding belt, so that the first and second brackets are in an active state, and then the missile's own weight is used to push the first and second brackets away. The second holding frame makes the first holding frame and the second holding frame rotate outward in opposite directions, thereby entering the open state, so that the missile can be released quickly and reliably;

2. The missile can be clamped reliably and safely without damaging the missile. In the state where the missile is not released, the belt is bound to cover the bottom hook of the insurance plate, so that the first and second arms remain stationary. The state of the first arm and the second arm is driven to hold the missile stably. Since the safety part can lock the safety plate, it can ensure that the first arm and the second arm can clamp the missile reliably and safely;

3. Simple structure, easy to use, convenient for lightweight design and compatible with small multi-rotor or fixed-wing drones.

Description of drawings

FIG. 1 is a perspective view of the present invention.

Figure 2 is a state diagram of an unreleased missile.

Figure 3 is a state diagram of a missile being released.

Detailed ways

The present invention will be further described below with reference to the accompanying drawings 1-3 and specific embodiments. The missiles 14 mentioned in this embodiment are small missiles specially installed on low-cost UAVs.

As shown in Figures 1-3, a low-cost airborne pylon mechanism, which is used for low-cost UAVs, includes:

Suspended and fixedly connected base 1 on the underside of the wing;

The embracing unit, which includes a first embracing frame 2 and a second embracing frame 3 that are rotatably connected to the base 1, the first embracing frame 2 and the second embracing frame 3 are relatively rotatable and the rotating shafts of the two are on the upper side, and the first embracing frame 2. The rotating shafts of the second holding frame 3 are coaxially provided with opening and closing gears 4, and the opening and closing gears 4 of the first holding frame 2 and the opening and closing gears 4 of the second holding frame 3 mesh with each other, so that the first holding frame 2 and the second frame 3 can maintain a synchronized state when rotating;

The outer support 8 is fixed on the outer side of the first holding frame 2;

A rotatable safety plate 6, the safety plate 6 has a fulcrum shaft 7 as its central axis of rotation, and the safety plate 6 is elastically rotatably connected with the outer support 8 through its fulcrum shaft 7, and the safety plate 6 is divided into components based on the fulcrum shaft 7. The flat plate portion of its main body, and the bottom hook portion 6a that constitutes its bottom;

The safety part is installed on the outside of the first bracket 2 to lock and unlock the flat plate part of the safety board 6;

An elastic binding belt 5 is provided, and one end of the binding belt 5 is connected to the second holding frame 3 .

Wherein, in the state where the missile 14 is not released, the other end of the binding belt 5 covers the bottom hook 6a of the safety plate 6 so that the first holding frame 2 and the second holding frame 3 clamp the missile 14, and the safety part locks the safety plate 6 In the state of releasing the missile 14, the safety part unlocks the flat plate part of the safety plate 6, the safety plate 6 is rotated outward by the elastic force of its elastic rotating connection so that the bottom hook part 6a is completely separated from the other end of the binding belt 5.

The above-mentioned first armature 2 and second armature 3 are both set as V-shaped plate structures, and the V-shaped groove of the first armature 2 is opposite to the V-shaped slot of the second armature 3, in the state that the missile 14 is not released The missile 14 is clamped by the V-shaped groove of the first carrier 2 and the V-shaped groove of the second carrier 3 , so as to form a better clamping effect on the missile 14 .

The above-mentioned outer supports 8 are provided with two, the insurance plate 6 is movably placed between the two outer supports 8, the fulcrum shaft 7 is fixedly connected to the insurance plate 6, and the two shaft ends of the fulcrum shaft 7 are respectively elastically rotatably connected to the two outer supports. 8.

The above insurance components include:

The safety pin 12 for locking the safety plate 6, the safety pin 12 movably passes through the outer support 8, and in the state where the missile 14 is not released, the safety pin 12 abuts against the outer side of the flat plate portion of the safety plate 6, thereby locking the safety plate 6, In the state of releasing the missile 14, the safety pin 12 is separated from the flat plate portion of the safety plate 6 to realize unlocking;

A linear drive assembly that drives the safety pin 12 to expand and contract axially.

Among them, the above-mentioned linear drive assembly includes a drive motor 9, a drive gear 10, a rack 11 and a rack sliding bearing seat 13. The drive motor 9 is controlled by the airborne control system and the electronic control system of the missile 14, and the drive motor 9 is set as a worm gear and worm. The deceleration motor, the drive motor 9 and the rack sliding support 13 are installed on the outside of the first bracket 2, the drive gear 10 is sleeved on the main shaft of the drive motor 9, the toothed side of the rack 11 meshes with the drive gear 10, the rack 11 The toothless side is slidably connected to the rack sliding support base 13 , one end of the safety pin 12 is fixedly connected to the rack 11 , and the length direction of the safety pin 12 is parallel to the length direction of the rack 11 .

As shown in FIG. 2 , in the state where the missile 14 is not released, the binding belt 5 is wrapped around the bottom hook 6a of the safety plate 6, so that the first holding frame 2 and the second holding frame 3 are in a stationary state, thereby driving the first holding frame 2 and the second holding frame 3. The holding frame 2 and the second holding frame 3 hold the missile 14 stably. Since the safety pin 12 can lock the safety plate 6, the safety pin 12 abuts against the outer side of the flat plate portion of the safety plate 6, and can lock the safety plate 6 well. It is ensured that the first carrier 2 and the second carrier 3 can hold the missile 14 reliably and safely.

Figure 3 shows the principle of releasing the missile 14. When the drone or the missile 14 receives the target locking signal, the mechanical separation signal of the drone and the missile starts to activate, and the forward rotation delay circuit of the drive motor 9 operates. The transmission of the gear 10 and the rack 11 makes the safety pin 12 retract, thereby releasing the locking of the safety member to the safety plate 6, and the safety plate 6 is rotated outward by the elastic force of its elastic rotational connection to make the bottom hook 6a completely disengage from the binding belt 5. Make the first armature 2 and the second armature 3 in an active state, and then use the self-weight of the missile 14 to push the first armature 2 and the second armature 3, through the mutual meshing effect of the two opening and closing gears 4, The first holding frame 2 and the second holding frame 3 are simultaneously rotated outward in opposite directions, thereby entering the open state, so that the missile 14 can be released quickly and reliably.

The above are the preferred embodiments of the present invention, and those of ordinary skill in the art can also carry out various transformations or improvements on this basis. Without departing from the general concept of the present invention, these transformations or improvements should belong to the claimed protection of the present invention. within the range.

Claims (6)

1. A low-cost airborne pylon mechanism, comprising a base (1) suspended and fixedly connected to the underside of a wing, characterized in that it also includes: An embracing unit, which includes a first embracing frame (2) and a second embracing frame (3) that are rotatably connected to the base (1), the first embracing frame (2) and the second embracing frame (3) are relatively rotatably arranged and the two The rotation axis of the first bracket (2) and the rotation axis of the second bracket (3) are coaxially provided with opening and closing gears (4), and the opening and closing gears (4) of the first bracket (2) are arranged on the upper side. The closing gear (4) and the opening and closing gear (4) of the second holding frame (3) mesh with each other; The outer support (8) is fixed on the outer side of the first holding frame (2); A rotatable safety plate (6), the safety plate (6) has a fulcrum shaft (7) as its central axis of rotation, the safety plate (6) is connected to an outer support (8) through its fulcrum shaft (7) Elastic rotation connection, the safety plate (6) is divided into a flat plate part constituting its main body part and a bottom hook part (6a) constituting its bottom according to the fulcrum axis (7); a safety component, installed on the outside of the first bracket (2), for locking and unlocking the flat plate portion of the safety board (6); an elastic binding belt (5), one end of the binding belt (5) is connected to the second holding frame (3); Wherein, when the missile (14) is not released, the other end of the binding belt (5) covers the bottom hook (6a) of the safety plate (6) so that the first holding frame (2) and the second holding frame ( 3) The missile (14) is clamped, and the safety member locks the flat plate portion of the safety plate (6); when the missile (14) is released, the safety member unlocks the flat plate portion of the safety plate (6), and the safety member unlocks the flat plate portion of the safety plate (6). The plate (6) is rotated outward by the elastic force of its elastic rotating joint so that the bottom hook (6a) is completely disengaged from the other end of the binding belt (5). 2 . The low-cost airborne hanger mechanism according to claim 1 , wherein there are two outer supports ( 8 ), and the safety plate ( 6 ) is movably placed on the two outer supports. 3 . Between the seats (8), the fulcrum shaft (7) is fixedly connected to the insurance plate (6), and the two shaft ends of the fulcrum shaft (7) are respectively elastically rotatably connected to the two outer supports (8). 3. The low-cost airborne pylon mechanism according to claim 1, wherein the safety component comprises: The safety pin (12) for locking the safety plate (6), the safety pin (12) movably passes through the outer support (8), and the safety pin (12) contacts the outer support (8) when the missile (14) is not released. leaning against and locking the flat plate portion of the safety plate (6), the safety pin (12) is separated from the flat plate portion of the safety plate (6) in the state of releasing the missile (14); A linear drive assembly that drives the safety pin (12) to expand and contract axially. 4. A low-cost airborne hanger mechanism according to claim 1, wherein the first holding frame (2) and the second holding frame (3) are both set as V-shaped plate structures, and the first holding frame (2) and the second holding frame (3) are both set as V-shaped plate structures. The V-shaped groove of the first carrier (2) is opposite to the V-shaped groove of the second carrier (3). When the missile (14) is not released, the missile (14) is caught by the V-shaped groove of the first carrier (2). It is clamped by the V-shaped groove of the second holding frame (3). 5. A low-cost airborne pylon mechanism according to claim 3, wherein the linear drive assembly of the safety component comprises a drive motor (9), a drive gear (10), a rack (11) and The rack sliding bearing seat (13), the drive motor (9) is controlled by the airborne control system and the electronic control system of the missile (14), the driving motor (9) and the rack sliding bearing seat (13) are mounted on the On the outside of the first holding frame (2), the drive gear (10) is sleeved on the main shaft of the drive motor (9), the toothed side of the rack (11) is meshed with the drive gear (10), and the rack The toothless side slidingly connected to the rack sliding bearing seat (13) of (11), one end of the safety pin (12) is fixedly connected to the rack (11), and the length direction of the safety pin (12) is parallel to the rack (11). ) in the length direction. 6 . The low-cost airborne hanger mechanism according to claim 5 , wherein the drive motor ( 9 ) is set as a worm gear reduction motor. 7 .

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