CN219077492U - Folding target aircraft catapult - Google Patents

Abstract

The utility model discloses a folding target aircraft ejector rack, which comprises an ejector rack capable of being folded and unfolded, wherein a trolley is connected in a sliding manner in the length direction of the unfolded ejector rack; a winch is arranged at the tail end of the ejection frame, an elastic band is wound on the winch, one end of the elastic band is tied at an elastic band connecting port on the trolley, and the other end of the elastic band is wound on the winch after bypassing the front end of the ejection frame; the tail end of the ejection frame is provided with a trolley locking mechanism for locking the trolley, and the trolley locking mechanism comprises a locking piece rotatably connected to the tail end of the ejection frame and a trolley hook fixed on the trolley; and rotating the locking piece to enable one end of the locking piece to slide out of the groove of the trolley hook, unlocking the trolley, pulling the trolley to the front end of the ejection frame by the rubber band, and ejecting the target drone arranged on the trolley. The utility model solves the problem of difficult transportation, and can be used for launching the target machine at the place where the rocket boosting cannot be used, and has wide application range.

Description

Folding target aircraft catapult

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle equipment, and particularly relates to a folding type target aircraft ejection frame.

Background

With the increasing maturity of unmanned aerial vehicle technology, its application in each field is also becoming more extensive, and unmanned aerial vehicle plays extremely important effect in both military and civilian field. The fixed wing unmanned aerial vehicle has higher applicability in the military field, is called a target aircraft, but has higher requirements on the field during take-off, can not play a role in some scenes without take-off conditions, and severely limits the application of the fixed wing unmanned aerial vehicle in wider fields.

Most of the existing target aircraft catapult adopts rocket boosting, and has higher requirements on ground conditions. Because the danger of rocket boosting is high, rocket boosting is not allowed to be adopted in some places, or because the ground condition is complex, the rocket boosting is not suitable for rocket boosting. The existing ejection rack has larger volume and is inconvenient to transport and carry.

Disclosure of Invention

Based on the defects in the prior art, the technical problem solved by the utility model is to provide the folding target aircraft catapult frame which can solve the problem that the rocket can not be used for boosting take-off and is difficult to transport.

In order to solve the technical problems, the utility model is realized by the following technical scheme: the utility model provides a folding target aircraft catapulting frame, which comprises a foldable and unfolding catapulting frame, wherein a trolley is connected in a sliding manner in the length direction of the unfolded catapulting frame; a winch is arranged at the tail end of the ejection frame, an elastic band is wound on the winch, one end of the elastic band is tied at an elastic band connecting port on the trolley, and the other end of the elastic band is wound on the winch after bypassing the front end of the ejection frame; the tail end of the ejection frame is provided with a trolley locking mechanism for locking the trolley, and the trolley locking mechanism comprises a locking piece rotatably connected to the tail end of the ejection frame and a trolley hook fixed on the trolley; and rotating the locking piece to enable one end of the locking piece to slide out of the groove of the trolley hook, unlocking the trolley, pulling the trolley to the front end of the ejection frame by the rubber band, and ejecting a target drone arranged on the trolley.

Further, the ejection frame is divided into a first section ejection frame, a second section ejection frame and a third section ejection frame, the first section ejection frame and the second section ejection frame are connected through a first hinge, the second section ejection frame and the third section ejection frame are connected through a second hinge, the first section ejection frame, the second section ejection frame and the third section ejection frame are unfolded to form a straight line, the unfolded first section ejection frame and the unfolded second section ejection frame are fixed through a first hasp, and the unfolded second section ejection frame and the unfolded third section ejection frame are fixed through a second hasp.

Further, the other end of the locking piece is connected with a transmitting deflector rod, and a transmitting deflector rod lengthening rod is inserted into the transmitting deflector rod.

Optionally, a first circular ring is arranged on the transmitting deflector rod, a second circular ring is fixed at the tail end of the ejection rack, and when the locking piece locks the trolley, the circle centers of the first circular ring and the second circular ring are overlapped in the vertical direction; the safety pin is inserted into the first circular ring and the second circular ring simultaneously to fix the transmitting deflector rod so as to prevent misoperation.

Further, the winch is electrically connected with a contraction handle, and a handle winch connecting wire on the contraction handle is connected with a winch connecting column of the winch; the handle battery connecting wire on the telescopic handle is connected with the battery connecting post on the battery; the retracting handle is provided with two buttons for controlling the winch to rotate clockwise and anticlockwise.

Further, the locking piece comprises two L-shaped steel plates which are parallel to each other and are arranged at intervals in an up-down symmetrical mode, a first rotating shaft connected between the same ends of the two L-shaped steel plates, and a second rotating shaft connected between right-angle ends of the two L-shaped steel plates; the second rotating shaft is rotationally connected to the tail end of the ejection frame, the emission deflector rod is connected between the other ends of the two L-shaped steel plates, which are far away from the first rotating shaft, through screws, acting force is applied to the emission deflector rod, so that the locking piece rotates clockwise by more than 90 degrees by taking the second rotating shaft as a circle center, and the first rotating shaft leaves a groove of the trolley hook, so that the locking of the trolley is released.

Preferably, the front end of the ejection rack is provided with a front supporting opening, and the tail end of the ejection rack is provided with a rear supporting rod; the front supporting rod is inserted into the front supporting opening and matched with the rear supporting rod to support and fix the ejection frame.

The first section ejection frame, the second section ejection frame and the third section ejection frame are connected in a folding manner through the first hinge and the second hinge, and the first section ejection frame, the second section ejection frame and the third section ejection frame after being unfolded are fixed into a straight line by adopting the first hasp and the second hasp; before the target drone is ejected, a trolley provided with the target drone is locked at the tail end of an ejection frame through a trolley locking mechanism, the trolley is pulled by an elastic band, and the elastic band is accumulated through a winch; during the transmission, through transmission driving lever extension bar and transmission driving lever rotation retaining member, make its slot disconnection with the dolly couple, the dolly is pulled to the front end of catapulting frame fast under the effect of rubber band, pops up the target aircraft through the dolly, and the transmission is successful. After launching, the first section ejection frame and the third section ejection frame are respectively folded along the directions of the first hinge and the second hinge to finish folding of the ejection frame, the whole structure is simple, the operation is convenient, the folding target aircraft ejection frame solves the problem of difficult transportation, and meanwhile, the ejection frame can be used for launching the target aircraft in places where rocket boosting cannot be used, and the application range is wide.

The foregoing description is only an overview of the present utility model, and is intended to be implemented in accordance with the teachings of the present utility model, as well as to provide further clarity and understanding of the above and other objects, features and advantages of the present utility model, as described in the following detailed description of the preferred embodiments, taken in conjunction with the accompanying drawings.

Drawings

In order to more clearly illustrate the technical solution of the embodiments of the present utility model, the drawings of the embodiments will be briefly described below.

FIG. 1 is a schematic view of a folding target ejector rack of the present utility model in a folded configuration;

FIG. 2 is a schematic view of a folding target ejector frame according to the present utility model in an unfolded state;

FIG. 3 is a schematic view of a folding target machine of the present utility model after a target machine is placed on an ejector rack;

FIG. 4 is a second schematic view of a folding target ejector rack according to the present utility model in a folded state;

FIG. 5 is a second schematic view of a foldable target ejector rack according to the present utility model in an unfolded state;

FIG. 6 is a schematic diagram of a locking dolly of the dolly locking mechanism of the present utility model;

fig. 7 is a top view of fig. 6.

Reference numerals: the device comprises a 1-target drone, 2, 3-front supporting rods, 4-storage batteries, 5-winches, 6-trolleys, 7-shrinkage handles, 8-rubber strings, 9-first hinges, 30-second hinges, 10-first buckles, 31-second buckles, 11-first hangers, 12-second hangers, 13-third hangers, 14-safety pins, 15-emission deflector rods, 16-emission deflector rod extension rods, 17, 18-rear supporting rods, 19, 20-winch connecting columns, 21, 22-storage battery connecting columns, 23, 24-handle winch connecting lines, 25, 26-handle storage battery connecting lines, 27-first-section ejection frames, 28-second-section ejection frames, 29-third-section ejection frames, 32, 33-front supporting ports, 34-trolley locking mechanisms, 35-trolley hooks, 36-locking pieces and 37-rubber string connecting ports.

Detailed Description

The following detailed description of the utility model, taken in conjunction with the accompanying drawings, illustrates the principles of the utility model by way of example and by way of a further explanation of the principles of the utility model, and its features and advantages will be apparent from the detailed description. In the drawings to which reference is made, the same or similar components in different drawings are denoted by the same reference numerals.

It should be noted that all directional indicators (such as up, down, outer, inner, front, and rear … …) in the embodiments of the present utility model are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.

As shown in fig. 1 to 7, the folding target aircraft ejector rack of the utility model comprises an ejector rack which can be folded and unfolded, a trolley 6 is connected in a sliding manner in the length direction of the unfolded ejector rack, a winch 5 is arranged at the tail end of the ejector rack, an elastic band 8 is wound on the winch 5, one end of the elastic band 8 is tied at an elastic band connection port 37 on the trolley 6, and the other end of the elastic band 8 is wound on the winch 5 after bypassing the front end of the ejector rack.

In addition, a trolley locking mechanism 34 for locking the trolley 6 is arranged at the tail end of the ejection frame, wherein the trolley locking mechanism 34 comprises a locking piece 36 rotatably connected to the tail end of the ejection frame and a trolley hook 35 fixed on the trolley 6, one end of the locking piece 36 slides out of a groove of the trolley hook 35 by rotating the locking piece 36, the trolley 6 is unlocked and pulled to the front end of the ejection frame by the rubber band 8, and the target drone 1 arranged on the trolley 6 is ejected.

Specifically, the locking member 36 includes two L-shaped steel plates that are parallel to each other and are arranged at intervals in a vertically symmetrical manner, a first rotating shaft that is connected between the same ends of the two L-shaped steel plates, and a second rotating shaft that is connected between right-angle ends of the two L-shaped steel plates, the second rotating shaft is rotatably connected to the tail end of the ejection rack, the ejection driving lever 15 is connected between the other ends of the two L-shaped steel plates, which are far away from the first rotating shaft, through screws, and an acting force is applied to the ejection driving lever 15, so that the locking member 36 rotates clockwise by more than 90 degrees with the second rotating shaft as the center of a circle, and the first rotating shaft leaves the groove of the trolley hook 35, thereby unlocking the trolley 6. In order to turn the locking element 36 more labor-saving, a firing lever extension 16 extending in the longitudinal direction of the firing lever 15 is inserted.

In the utility model, the ejector rack is divided into a first section ejector rack 27, a second section ejector rack 28 and a third section ejector rack 29, the first section ejector rack 27 and the second section ejector rack 28 are connected through a first hinge 9, the second section ejector rack 28 and the third section ejector rack 29 are connected through a second hinge 30, the first section ejector rack 27, the second section ejector rack 28 and the third section ejector rack 29 are unfolded to form a straight line, the unfolded first section ejector rack 27 and the unfolded second section ejector rack 28 are fixed through a first hasp 10, and the unfolded second section ejector rack 28 and the unfolded third section ejector rack 29 are fixed through a second hasp 31.

When the ejector rack is unfolded from the folded state shown in fig. 4 to the unfolded state shown in fig. 2, the first section of ejector rack 27 is unfolded along the first folding page 9 to form a straight line with the second section of ejector rack 28, then the third section of ejector rack 29 is unfolded along the second folding page 30 to form a straight line with the first section of ejector rack 27, the second section of ejector rack 28 and the third section of ejector rack 29, the first hasp 10 and the second hasp 31 are buckled, the front support rods 2 and 3 are inserted into the front support openings 32 and 33 at the front end of the first section of ejector rack 27 and are matched with the rear support rods 17 and 18 at the tail end of the third section of ejector rack 29 to support and fix the ejector rack.

The winch 5 is electrically connected with a shrinking handle 7, handle winch connecting wires 23 and 24 on the shrinking handle 7 are connected to winch connecting posts 19 and 20 of the winch 5, the model of the winch 5 is 2000LBS, handle battery connecting wires 25 and 26 on the shrinking handle 7 are connected to battery connecting posts 21 and 22 on the battery 4, then the shrinking handle 7 is used for controlling the winch 5 to rotate so that the rubber band 8 is retracted and released on the winch 5, the shrinking handle 7 is a controller of the winch 5, two buttons are arranged on the shrinking handle 7, one control winch 5 rotates clockwise, and the other control winch 5 rotates anticlockwise.

Before the target aircraft 1 is launched, determining whether the trolley 6 is at the tail part of an ejection frame, determining whether a trolley locking mechanism 34 locks the trolley 6, checking whether the launching deflector rod 15 is fixed through a safety pin 14, wherein a first circular ring is arranged on the launching deflector rod 15, a second circular ring is fixed at the tail end of the ejection frame, when the trolley locking mechanism 34 is in a locked state, the circle centers of the first circular ring and the second circular ring are overlapped in the vertical direction, simultaneously inserting the safety pin 14 into the two circular rings, and fixing the launching deflector rod 15 to prevent misoperation.

The trolley 6 is provided with a first hanging frame 11, a second hanging frame 12 and a third hanging frame 13, the target aircraft 1 is placed on the first hanging frame 11, the second hanging frame 12 and the third hanging frame 13, the launching deflector rod extension rod 16 is inserted into the launching deflector rod 15, the safety pin 14 is pulled out, the locking piece 36 is rotated clockwise by more than 90 degrees, the locking piece 36 is separated from the trolley hook 35, a clockwise rotating button on the shrinkage handle 7 is pressed, the winch 5 is rotated clockwise to shrink the rubber band 8 to pull the trolley 6 to the front end of the ejection frame, the target aircraft 1 is ejected, and the launching is successful.

After the launching frame is folded, firstly, a counterclockwise rotating button on the shrinkage handle 7 is pressed to enable the winch 5 to rotate, so that the rubber band 8 is retracted and released on the winch 5, the trolley 6 is pulled back to the tail part of the launching frame, the trolley 6 is locked by the trolley locking mechanism 34, and the launching deflector rod 15 is fixed by the safety pin 14 to prevent ejection. Then the handle winch connecting lines 23 and 24 and the handle battery connecting lines 25 and 26 on the retracting handle 7 are detached from the winch connecting columns 19 and 20 and the battery connecting columns 21 and 22 respectively, then the two front supporting rods 2 and 3 are detached, the first hasp 10 and the second hasp 31 are opened, and the first section ejection frame 27 and the third section ejection frame 29 are folded along the directions of the first folding page 9 and the second folding page 30 respectively, so that the folding is completed.

While the utility model has been described with respect to the preferred embodiments, it will be understood that the utility model is not limited thereto, but is capable of modification and variation without departing from the spirit of the utility model, as will be apparent to those skilled in the art.

Claims (7)

1. The utility model provides a folding target drone catapulting frame, includes the catapulting frame that can fold and expand, its characterized in that: a trolley (6) is connected in a sliding manner in the length direction of the unfolded ejection rack;

a winch (5) is arranged at the tail end of the ejection frame, an elastic band (8) is wound on the winch (5), one end of the elastic band (8) is tied at an elastic band connecting port (37) on the trolley (6), and the other end of the elastic band (8) is wound on the winch (5) after bypassing the front end of the ejection frame;

the tail end of the ejection frame is provided with a trolley locking mechanism (34) for locking the trolley (6), and the trolley locking mechanism (34) comprises a locking piece (36) rotatably connected to the tail end of the ejection frame and a trolley hook (35) fixed on the trolley (6); and rotating the locking piece (36) to enable one end of the locking piece (36) to slide out of a groove of the trolley hook (35), unlocking the trolley (6) and pulling the trolley to the front end of the ejection frame by the rubber band (8), and ejecting the target drone (1) arranged on the trolley (6).

2. The foldable target aircraft ejector rack according to claim 1, wherein the ejector rack is divided into a first section ejector rack (27), a second section ejector rack (28) and a third section ejector rack (29), the first section ejector rack (27) and the second section ejector rack (28) are connected through a first folding page (9), the second section ejector rack (28) and the third section ejector rack (29) are connected through a second folding page (30), the first section ejector rack (27), the second section ejector rack (28) and the third section ejector rack (29) are unfolded to form a straight line, the unfolded first section ejector rack (27) and the unfolded second section ejector rack (28) are fixed through a first hasp (10), and the unfolded second section ejector rack (28) and the unfolded third section ejector rack (29) are fixed through a second hasp (31).

3. The folding target ejector rack according to claim 1, characterized in that the other end of the locking member (36) is connected to a firing lever (15), and a firing lever extension bar (16) is inserted into the firing lever (15).

4. A folding target aircraft ejector rack according to claim 3, characterized in that the ejector lever (15) is provided with a first circular ring, the tail end of the ejector rack is fixed with a second circular ring, and when the locking piece (36) locks the trolley (6), the circle centers of the first circular ring and the second circular ring coincide in the vertical direction; the safety pin (14) is inserted into the first circular ring and the second circular ring simultaneously to fix the transmitting deflector rod (15) so as to prevent misoperation.

5. The folding target ejector rack according to claim 1, characterized in that the winch (5) is electrically connected with a retraction handle (7), a handle winch connection line (23, 24) on the retraction handle (7) being connected with a winch connection post (19, 20) of the winch (5); the handle battery connecting wires (25, 26) on the contraction handle (7) are connected with battery connecting posts (21, 22) on the battery (4); the retraction handle (7) is provided with two buttons for controlling the winch (5) to rotate clockwise and anticlockwise.

6. A folding target ejector rack according to claim 3, characterized in that the locking member (36) comprises two L-shaped steel plates arranged in parallel and vertically symmetrically spaced apart, a first rotation shaft connected between the same ends of the two L-shaped steel plates, and a second rotation shaft connected between right-angled ends of the two L-shaped steel plates;

the second rotating shaft is rotationally connected to the tail end of the ejection frame, the emission deflector rod (15) is connected between the other ends of the two L-shaped steel plates, which are far away from the first rotating shaft, by means of screws, acting force is applied to the emission deflector rod (15) to enable the locking piece (36) to rotate clockwise by more than 90 degrees by taking the second rotating shaft as a circle center, and the first rotating shaft leaves the groove of the trolley hook (35) to unlock the trolley (6).

7. The folding target ejector rack according to claim 1, characterized in that the front end of the ejector rack has a front support opening (32, 33) and the rear end of the ejector rack has a rear support bar (17, 18); front support rods (2, 3) are inserted into the front support openings (32, 33) and cooperate with rear support rods (17, 18) to support and fix the ejector rack.

Images