Miniature catapult

Abstract

The utility model relates to the technical field of catapults, in particular to a miniature catapult which comprises a front support and a rear support. The number of the ejection frames is multiple sets, the multiple sets of ejection frames are arranged at the top ends of the front support and the rear support, and every two adjacent ejection frames are fixedly connected through a connecting flange; the ejection assembly is used for ejecting the fixed-wing unmanned aerial vehicle, the ejection assembly comprises a rubber rope, a pre-tightening winch, an energy storage winch, an ejection trolley and a trigger, and the ejection assembly further comprises a first pulley, a guide wheel and a second pulley which are arranged on the inner wall of the ejection frame at the foremost end. By adopting the hollow H-shaped ejection frame, a plurality of strands of rubber ropes can be accommodated, the ejection tension can reach more than hundreds of kilograms by increasing the sections and the number of strands of the rubber ropes, and a hundreds of kilograms of unmanned aerial vehicles can be ejected to the maximum extent; the rubber rope is wound in a zigzag mode, it is guaranteed that the tension attenuation of the rubber rope is small along with increasing of the length, and ejection force is sufficient in the later ejection period.

Description

Technical Field

[0001] The utility model relates to the technical field of catapults, in particular to a miniature catapult. Background Art

[0002] With the improvement of UAV technology, its application in many fields is becoming more and more extensive. Among them, fixed-wing UAVs are suitable for some special needs because of their long flight distance, long hovering time, large load capacity and energy saving.

[0003] Medium and large fixed-wing UAVs have loose requirements on weight and volume, and can be equipped with wheels to take off and land like ordinary airplanes. Small and micro fixed-wing UAVs are restricted by weight and volume, cannot use wheeled takeoff and landing, and require assisted takeoff.

[0004] Rocket-assisted takeoff is widely used in the military. It has the advantages of being simple, fast, and having a high frequency of launch. Its disadvantages are that the tail flame produced by the rocket can easily expose the launch target and ablate the equipment. Rockets are disposable items, which causes serious waste. They are also explosive items and are dangerous to store and transport.

[0005] The use of cylinder catapult takeoff is widely used in civilian applications. It has the advantages of simple structure, fast speed and low-cost launch. The disadvantage is that it needs to be equipped with an air compressor or generator, plus a gas tank, etc., which is heavy, complex in structure, and has low gas conversion efficiency. It is necessary to wait for the air pressure to reach a certain value, which is not suitable for high-frequency launch.

[0006] The use of rubber bands and springs for catapult launch is currently the most widely used, but the disadvantages are that the elastic energy density of the rubber band is low and the effective stroke is short. Currently, kilogram-level catapults are more commonly used, and ten-kilogram to one-hundred-kilogram levels are rarely used. In view of this, the present application proposes a micro catapult. Utility Model Content

[0007] The purpose of the utility model is to provide a micro catapult to solve the problems raised in the above background technology.

[0008] In order to achieve the above-mentioned purpose, the utility model provides the following technical solution: a micro catapult, comprising:

[0009] front and rear brackets;

[0010] Ejection racks, the number of which is multiple, and the multiple groups of ejection racks are arranged at the top of the front bracket and the rear bracket, and two adjacent ejection racks are fixedly connected by connecting flanges;

[0011] An ejection assembly is used to eject a fixed-wing UAV, the ejection assembly includes a rubber rope, a pre-tensioning winch, an energy storage winch, an ejection trolley and a trigger, and the fixed-wing UAV is arranged on the top of the ejection trolley, the ejection assembly also includes a first pulley, a guide wheel and a second pulley respectively arranged on the inner wall of the frontmost ejection frame, and a third pulley arranged on the inner wall of the rearmost ejection frame, one end of the rubber rope is fixedly connected to the front end of the ejection trolley, and the other end of the rubber rope is fixedly connected to the pre-tensioning winch.

[0012] As a preferred technical solution, the top ends of the front bracket and the rear bracket are rotatably connected to the lower surface of the ejection frame through a first pin shaft, and the cross-sectional shape of the ejection frame is H-shaped.

[0013] As a preferred technical solution, a roller rollingly connected to the inner wall of the ejection frame is provided at the bottom of the ejection trolley, and a baffle for limiting the ejection trolley is provided at the end of the frontmost ejection frame.

[0014] As a preferred technical solution, one end of the rubber rope away from the ejection trolley passes through the first pulley, the guide wheel, the second pulley and the third pulley in a zigzag shape in sequence and is fixedly connected to the pre-tensioning winch.

[0015] As a preferred technical solution, the rear end of the ejection trolley is connected to the trigger, and the tail of the trigger is provided with a pull rope for facilitating the pulling operation of the trigger.

[0016] As a preferred technical solution, the tail of the ejection trolley is fixedly connected to the rope on the energy storage winch through a safety pin.

[0017] As a preferred technical solution, one end of the rubber rope away from the pre-tensioning winch is fixedly connected to the front end of the ejection trolley through a second pin shaft. Beneficial Effects

[0018] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0019] The utility model adopts a hollow H-shaped ejection frame to accommodate multiple rubber ropes. By increasing the cross-section and the number of strands of the rubber rope, the ejection pulling force can reach hundreds of kilograms or more, and a maximum ejection of a 100-kilogram class UAV is possible. The zigzag winding of the rubber rope ensures that the tension of the rubber rope decreases slightly as the length increases, and the ejection force is sufficient in the later stage of ejection.

[0020] The utility model ensures a sufficient acceleration distance and generates a maximum acceleration by adopting multiple groups of combined ejection frames; the bracket is easy to disassemble and the ejection frame is folded to ensure convenient transportation; the energy storage winch is mechanical and can be driven by a variety of power, which is suitable for field operations; the ejection installation and operation are simple and can be performed by a small number of people; the trolley is quickly and simply reset, and the ejection interval is short, which is suitable for high-frequency ejection; and a safety pin and a pull rope are adopted, which is safe and convenient to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 It is a schematic diagram of the three-dimensional structure of the utility model;

[0023] Figure 2 For this utility model Figure 1 The enlarged structural diagram at A in the middle;

[0024] Figure 3 For this utility model Figure 1 The enlarged structural diagram at B in the middle;

[0025] Figure 4 For this utility model Figure 1 Enlarged structural diagram at point C in the middle.

[0026] In the figure:

[0027] 100, front bracket;

[0028] 200, rear bracket;

[0029] 300, ejection frame; 301, connecting flange; 302, first pin shaft;

[0030] 400, ejection assembly; 401, rubber rope; 402, preload winch; 403, energy storage winch; 404, ejection trolley; 405, trigger; 406, first pulley; 407, guide wheel; 408, second pulley; 409, third pulley; 4010, roller; 4011, baffle; 4012, pull rope; 4013, safety pin; 4014, second pin shaft;

[0031] 500. Fixed-wing UAV. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0033] According to the attached Figure 1-4As shown, the embodiment of the utility model provides a micro catapult, comprising:

[0034] A front support 100 and a rear support 200;

[0035] The ejection rack 300 includes multiple groups of ejection racks 300. By using multiple groups of ejection racks 300, sufficient acceleration distance is ensured to generate maximum acceleration.

[0036] A plurality of ejection racks 300 are arranged at the top of the front bracket 100 and the rear bracket 200 , and two adjacent ejection racks 300 are fixedly connected via a connecting flange 301 . The brackets are easy to dismantle, and the ejection racks 300 are folded, so as to ensure convenient transportation.

[0037] The top ends of the front bracket 100 and the rear bracket 200 are rotatably connected to the lower surface of the ejection frame 300 through the first pin shaft 302, and the cross-sectional shape of the ejection frame 300 is H-shaped.

[0038] The ejection assembly 400 is used to eject the fixed-wing UAV 500 . The ejection assembly 400 includes a rubber rope 401 , a pre-tightening winch 402 , an energy storage winch 403 , an ejection trolley 404 and a trigger 405 .

[0039] By adopting a hollow H-shaped ejection frame 300, multiple rubber ropes 401 can be accommodated. By increasing the cross-section and number of rubber ropes 401, the ejection pulling force can reach hundreds of kilograms or more, and a maximum ejection of a 100-kilogram drone can be achieved.

[0040] The fixed-wing UAV 500 is arranged on the top of the ejection trolley 404, and the ejection assembly 400 also includes a first pulley 406, a guide wheel 407 and a second pulley 408 respectively arranged on the inner wall of the front end ejection frame 300, and a third pulley 409 arranged on the inner wall of the rear end ejection frame 300. One end of the rubber rope 401 is fixedly connected to the front end of the ejection trolley 404, and the other end of the rubber rope 401 is fixedly connected to the pre-tensioning winch 402.

[0041] A roller 4010 rollingly connected to the inner wall of the ejection frame 300 is disposed at the bottom of the ejection trolley 404 , and a baffle 4011 for limiting the ejection trolley 404 is disposed at the end of the frontmost ejection frame 300 .

[0042] One end of the rubber rope 401 away from the ejection trolley 404 passes through the first pulley 406 , the guide wheel 407 , the second pulley 408 and the third pulley 409 in a zigzag shape in sequence and is fixedly connected to the pre-tightening winch 402 .

[0043] The zigzag winding of the rubber rope 401 ensures that the tension of the rubber rope 401 decreases slightly as the length increases, and the ejection force is sufficient in the later stage of ejection.

[0044] The rear end of the ejection trolley 404 is connected to the trigger 405 , and a pull rope 4012 is provided at the tail of the trigger 405 for facilitating the pulling operation of the trigger 405 .

[0045] The tail of the ejection trolley 404 is fixedly connected to the rope on the energy storage winch 403 through a safety pin 4013, wherein the energy storage winch 403 is mechanical and can be driven by a variety of power, suitable for field operations, and the ejection installation and operation are simple and can be performed by a small number of people; the ejection trolley 404 is quickly and easily reset, and the ejection interval is short, which is suitable for high-frequency ejection; the safety pin 4013 and the pull rope 4012 are used, and the operation is safe and convenient.

[0046] One end of the rubber rope 401 away from the pre-tightening winch 402 is fixedly connected to the front end of the ejection trolley 404 through the second pin shaft 4014 .

[0047] When the micro catapult is ejected, the pre-tightening winch 402 pulls and pre-tightens the rubber rope 401; due to the tension on the rubber rope 401, the ejection trolley 404 is normally located at the position of the first pulley 406; the ejection trolley 404 is pulled by the energy storage winch 403 to the rear end of the ejection frame 300 and is hooked by the trigger 405; at the same time, the rubber rope 401 is stretched to store energy; the fixed-wing UAV 500 is installed on the ejection trolley 404 and enters the ejection state; when ejection is required, the safety pin 4013 is removed, and the elastic tension of the rubber rope 401 acts on the trigger 405 through the ejection trolley 404, and the ejection state is entered. state; the trigger 405 is pulled by the pull rope 4012, and the rubber rope 401 pulls the ejection cart 404, driving the fixed-wing UAV 500 to accelerate and glide; the ejection cart 404 exceeds the first pulley 406, and the forward pulling force of the rubber rope 401 on the ejection cart 404 changes to backward, and the ejection cart 404 decelerates until the baffle 4011 stops moving forward; the fixed-wing UAV 500 accelerates to a certain speed and continues to fly forward, completing the ejection; the ejection cart 404 stops near the first pulley 406 under the pulling force of the rubber rope 401; the traction rope of the energy storage winch 403 is connected to the safety pin 4013, and the next launch begins.

[0048] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the utility model and are not used to limit the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection of the utility model is defined by the attached claims and their equivalents.

Claims

1. A micro catapult, characterized in that: include, A front bracket (100) and a rear bracket (200); Ejection racks (300), the ejection racks (300) being provided in a plurality of groups, and the plurality of groups of ejection racks (300) being arranged at the top ends of the front bracket (100) and the rear bracket (200), and two adjacent ejection racks (300) being fixedly connected via a connecting flange (301); An ejection assembly (400) is used to eject a fixed-wing unmanned aerial vehicle (500). The ejection assembly (400) comprises a rubber rope (401), a pre-tightening winch (402), an energy storage winch (403), an ejection trolley (404) and a trigger (405). The fixed-wing unmanned aerial vehicle (500) is arranged on the top of the ejection trolley (404). The ejection assembly (400) further comprises a first pulley (406), a guide wheel (407) and a second pulley (408) which are respectively arranged on the inner wall of the frontmost ejection frame (300), and a third pulley (409) which is arranged on the inner wall of the rearmost ejection frame (300). One end of the rubber rope (401) is fixedly connected to the front end of the ejection trolley (404), and the other end of the rubber rope (401) is fixedly connected to the pre-tightening winch (402).

2. The micro catapult according to claim 1, characterized in that: The top ends of the front bracket (100) and the rear bracket (200) are rotatably connected to the lower surface of the ejection frame (300) via a first pin shaft (302), and the cross-sectional shape of the ejection frame (300) is H-shaped.

3. The micro catapult according to claim 1, characterized in that: A roller (4010) is provided at the bottom of the ejection trolley (404) and is rollingly connected to the inner wall of the ejection frame (300), and a baffle (4011) for limiting the ejection trolley (404) is provided at the end of the frontmost ejection frame (300).

4. The micro catapult according to claim 1, characterized in that: One end of the rubber rope (401) away from the ejection trolley (404) passes through the first pulley (406), the guide wheel (407), the second pulley (408) and the third pulley (409) in a zigzag shape in sequence and is fixedly connected to the pre-tightening winch (402).

5. The micro catapult according to claim 1, characterized in that: The rear end of the ejection trolley (404) is connected to the trigger (405), and a pull rope (4012) is provided at the tail of the trigger (405) for facilitating the pulling operation of the trigger (405).

6. The micro catapult according to claim 1, characterized in that: The tail of the ejection trolley (404) is fixedly connected to the winch rope on the energy storage winch (403) via a safety pin (4013).

7. The micro catapult according to claim 1, characterized in that: One end of the rubber rope (401) away from the pre-tightening winch (402) is fixedly connected to the front end of the ejection trolley (404) via a second pin shaft (4014).

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