Launching rack

Abstract

The utility model discloses a launching rack which comprises a launching platform (31), a rear supporting assembly (3) and a front supporting assembly (4). The front supporting assembly (4) is used for bearing a front supporting point of the aircraft; the rear supporting assembly (3) is used for bearing a rear fulcrum of the aircraft and limiting the rear fulcrum; the front supporting assembly (4) is hinged to the launching platform (31). A spring assembly (5) is arranged between the launching platform (31) and the front supporting assembly (4), and when the front supporting assembly (4) is in the vertical state, the spring assembly (5) provides acting force enabling the front supporting assembly (4) to rotate in the launching direction of the aircraft in the free state. When the unmanned aerial vehicle is separated from the launching rack, the front supporting assembly (4) is rapidly pulled to the horizontal state and locked through the spring assembly (5) arranged between the launching platform (31) and the front supporting assembly (4), and interference and collision between the unmanned aerial vehicle and the front supporting assembly are effectively avoided.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft launching, and in particular relates to a launching rack. Background Art

[0002] Small drones can be launched by human throwing, while drones with longer range and heavier mass need to be launched from a launcher. Existing drone launchers generally consist of a launch platform and front and rear support components installed on the launch platform. Before launch, the drone is fixed by the front and rear support components. During launch, when the drone is separated from the front and rear support components, it is easy to interfere with and collide with the front support component, causing scratches on the body or launch failure. Utility Model Content

[0003] The utility model aims to provide a launching stand to solve the problem that a UAV is easily interfered and collided with the launching stand during launching, thus causing scratches on the body or launch failure.

[0004] The utility model is realized by the following technical solutions:

[0005] A launching rack comprises: a launching platform, a rear supporting assembly and a front supporting assembly; the front supporting assembly and the rear supporting assembly are respectively arranged at the front and the middle of the launching platform; the front supporting assembly is used to bear the front fulcrum of an aircraft; the rear supporting assembly is used to bear the rear fulcrum of the aircraft and to limit the rear fulcrum of the aircraft; the front supporting assembly is hinged to the launching platform, a first locking mechanism is arranged between the front supporting assembly and the launching platform, the first locking mechanism is used to keep the front supporting assembly in a vertical state and limit the rotation of the front supporting assembly; a spring assembly is arranged between the launching platform and the front supporting assembly, when the front supporting assembly is in a vertical state, the spring assembly provides a force that enables the front supporting assembly to rotate in the launching direction of the aircraft in a free state.

[0006] In some embodiments, the spring assembly is a tension spring, and both ends of the tension spring are respectively connected to the front support assembly and the launching platform.

[0007] In some embodiments, the first locking mechanism includes a breakaway pin, both ends of which are connected to the front support assembly and the launching platform respectively.

[0008] In some embodiments, the first locking mechanism also includes a connecting assembly respectively arranged on the front support assembly and the launching platform, the connecting assembly includes a support and a pin shaft arranged on the support, and the two ends of the break pin respectively pass through the pin holes arranged on the pin shaft and connect the two connecting assemblies.

[0009] In some embodiments, when the front support assembly is in a vertical state, a safety pin is inserted between the front support assembly and the launching platform.

[0010] In some embodiments, a locking device is provided on the front support assembly, and the locking device is used to lock the front fulcrum of the aircraft; when the front support assembly rotates toward the launch direction of the aircraft, the locking device can release the lock on the front fulcrum of the aircraft.

[0011] In some embodiments, the locking device includes a locking hook, a pull rod assembly, a reset assembly, a switch and a slider; the locking hook is hinged to the front support assembly; one end of the locking hook extends out of the upper end surface of the front support assembly and cooperates with the front support assembly to lock the front fulcrum of the aircraft, and the other end of the locking hook is hinged to the upper end of the pull rod assembly; the switch is hinged to the front support assembly, and one end of the switch is hinged to the lower end of the pull rod assembly; the slider is arranged on the launch platform, and an inclined locking surface is arranged on the slider, and the other end of the switch abuts against the locking surface; the slider is configured to be able to adjust its position on the launch platform in a direction away from or close to the switch; one end of the reset assembly is connected to the front support assembly, and the other end is connected to the middle part of the pull rod assembly, and the reset assembly is used to provide the pull rod assembly with an upward force that can unlock the locking device.

[0012] In some embodiments, a second locking mechanism is provided between the launch platform and the front support assembly, and when the front support assembly rotates to a horizontal state along the launch direction of the aircraft, the second locking mechanism fixes the front support assembly in a horizontal state.

[0013] In some embodiments, a base frame is further included, and a launching platform is arranged on the base frame; an angle adjustment mechanism is arranged between the base frame and the launching platform, and the angle adjustment mechanism is used to adjust the pitch angle between the launching platform and the base frame.

[0014] In some embodiments, one end of the launching platform is hinged to the base frame, and the angle adjustment mechanism includes two groups of adjustment components. The adjustment component includes a transmission component and a screw rod. The transmission component is used to drive the screw rod to rotate, and the screw rod and the launching platform are connected in a transmission cooperation manner; the two groups of transmission components are connected by a transmission shaft to achieve synchronous transmission between the transmission components.

[0015] Compared with the prior art, the utility model has the following advantages and beneficial effects:

[0016] When the UAV is detached from the launch pad, the front support assembly is quickly pulled to a horizontal state and locked by a spring assembly arranged between the launch platform and the front support assembly, thereby effectively preventing interference and collision between the UAV and the front support assembly.

[0017] A break pin is used as the unlocking component, and its break force is more constant and less variable than the shear force of a traditional shear pin, making the launch of the launcher more stable.

[0018] A screw reducer is used as the launch angle adjustment mechanism. The adjustment process is stable and can achieve stepless adjustment. The launch angle can be locked at any angle by relying on the self-locking characteristics of the screw. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 This is a schematic diagram of the overall structure of the launch rack in Example 1.

[0021] Figure 2 Schematic diagram of the launch platform and rear support assembly structure of Example 1.

[0022] Figure 3 This is a schematic diagram of the front support assembly structure of Example 1.

[0023] Figure 4 It is a schematic diagram of the structure of the bullet-carrying mechanism of the first embodiment.

[0024] Figure 5 This is a schematic diagram of the structure of the flow guide mechanism of Example 1.

[0025] Description of reference numerals:

[0026] 1-bomb-supporting mechanism, 2-flow-guiding mechanism, 3-rear support assembly, 4-front support assembly, 5-spring assembly, 6-angle adjustment mechanism, 7-base, 8-leveling legs, 31-launching platform, 32-left rear guide rail, 33-right rear guide rail, 34-slider, 35-first pin shaft, 36-latch assembly, 37-safety pin, 41-ear shaft seat, 42-switch, 43-block, 44-lock hook, 45-front support rod, 46-pull rod assembly, 47-reset assembly, 48-screw sleeve, 49-connector, 410-rotating shaft, 11-third support, 12-lifting rod, 13-U-shaped bracket, 14-lifting assembly, 15-second angle adjustment mechanism, 16-fourth support, 21-flow-guiding bracket, 22-folding plate. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solutions and advantages of the embodiments of the utility model clearer, the technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings 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.

[0028] Embodiment 1

[0029] This embodiment is a launching frame, such as Figure 1 , Figure 2As shown, it includes a base frame 7, leveling legs 8, a launching platform 31, a front supporting assembly 4, a rear supporting assembly 3, a bullet-carrying mechanism 1, a flow-guiding mechanism 2, and an angle adjustment mechanism 6.

[0030] The launcher of this embodiment is suitable for launching various aircraft, and a drone is used as an example below.

[0031] The launch process of the drone: fix the front support assembly in a vertical position with a safety pin and a breakaway pin, hoist the drone and lock it on the launch pad, install the booster rocket, remove the safety pin, remotely ignite the drone and the booster rocket, push the breakaway pin, the front support assembly falls down, and the drone is launched.

[0032] The base frame 7 provides support for the entire launcher.

[0033] The leveling legs 8 are arranged under the base frame 7, and their height can be adjusted. Generally, the height of the leveling legs 8 can be adjusted according to the inclinometer placed on the reference plane of the launch platform 31 to ensure the horizontality of the launcher. The leveling legs 8 are connected and fixed to the ground to ensure that the launcher will not overturn or tip over during the launch process.

[0034] The launch platform 31 is mounted on the chassis 7, and an angle adjustment mechanism 6 is provided between the two, which is used to adjust the pitch angle between the launch platform 31 and the chassis 7. Specifically, the angle adjustment mechanism 6 includes two groups of adjustment components, the adjustment components include a transmission component and a screw rod, the transmission component is used to drive the screw rod to rotate, the screw rod and the launch platform 31 are connected in a transmission matching manner, and the two groups of transmission components are connected by a transmission shaft to achieve synchronous transmission between the transmission components. In this embodiment, one group of transmission components is driven by a rocker, and the other group of transmission components is driven by a transmission shaft. The transmission components synchronously drive the screw rod to rotate to achieve stable driving of the launch platform. The screw rod adopts a trapezoidal screw rod, which can realize stepless adjustment of the launch platform 31 between 10 degrees and 20 degrees and self-locking.

[0035] The front support assembly 4 and the rear support assembly 3 are used to carry the UAV and are respectively arranged at the front and middle of the launch platform 31, wherein the front support assembly 4 is used to carry the front fulcrum of the aircraft, and the rear support assembly 3 is used to carry the rear fulcrum of the aircraft and limit the rear fulcrum of the aircraft.

[0036] like Figure 2 , Figure 3 As shown, the front support assembly 4 is hinged to the launch platform 31. The specific connection mode is that the trunnion seat 41 is fixedly connected to the launch platform 31, and the front support assembly 4 is connected to the trunnion seat through the rotating shaft 410 to realize the hinge connection with the launch platform 31.

[0037] A first locking mechanism is provided between the front support assembly 4 and the launch platform 31, and the first locking mechanism is used to keep the front support assembly 4 in a vertical state and limit the rotation of the front support assembly 4. In this embodiment, the first locking mechanism includes a break pin and a connecting member respectively provided on the front support assembly 4 and the launch platform 31, and the connecting member includes a support and a pin shaft provided on the support, and the two ends of the break pin respectively pass through the pin holes provided on the pin shaft and connect the two connecting assemblies. Specifically, the first support is fixedly installed on the launch platform 31, and the first pin shaft 35 is provided on the first support, and the second support is fixedly installed on the front support assembly 4, and the second pin shaft 411 is provided on the second support, and the two ends of the break pin respectively pass through the pin holes provided on the first pin shaft 35 and the second pin shaft 411 to connect them.

[0038] The vertical state in the present application is a state perpendicular to the launch platform 31 , and the horizontal state in the present application is a state parallel to the launch platform 31 .

[0039] For safety, the front support assembly 4 is in a vertical state, and a safety pin 37 is inserted between the front support assembly 4 and the launch platform 31. Before hoisting the drone, the front support assembly 4 is fixed in a vertical state with the safety pin 37 and the breakaway pin.

[0040] During the launch of the aircraft, in order to prevent the UAV from interfering with and colliding with the front support assembly 4, causing scratches on the aircraft body or launch failure, the front support assembly 4 needs to be quickly dropped to a horizontal state and quickly locked to prevent rebound.

[0041] In this embodiment, a spring assembly 5 is arranged between the launch platform 31 and the front support assembly 4. When the front support assembly 4 is in a vertical state, the spring assembly 5 provides a force that enables the front support assembly 4 to rotate in the launch direction of the aircraft in a free state. In this way, when the front support assembly 4 falls down, the spring assembly 5 can quickly pull it to a horizontal state.

[0042] A second locking mechanism is provided between the launch platform 31 and the front support assembly 4. When the spring assembly 5 pulls the front support assembly 4 to a horizontal state, the second locking mechanism quickly fixes it in a horizontal state to prevent it from rebounding and damaging the body. In this embodiment, the second locking mechanism specifically includes a stopper 43 provided on the front support assembly 4 and a latch assembly 36 provided at the front end of the launch platform 31. The stopper 43 is welded to the front support assembly 4. When the front support assembly falls to a horizontal state, the stopper 43 is inserted into the latch assembly 36 to lock the front support assembly to a horizontal state.

[0043] The front support assembly 4 is provided with a locking device for locking the front fulcrum of the aircraft. When the UAV is launched and the front support assembly 4 is rotated in the launch direction of the aircraft, the locking device can release the lock on the front fulcrum of the aircraft.

[0044] like Figure 2 and Figure 3 As shown, the specific structure of the locking device includes a lock hook 44, a pull rod assembly 46, a reset assembly 47, a switch 42 and a slider 34, wherein the lock hook 44 is hinged to the front support assembly 4, one end of which extends out of the upper end surface of the front support assembly 4 and cooperates with it to lock the front fulcrum of the aircraft, the other end of the lock hook 44 is hinged to the upper end of the pull rod assembly 46, the lower end of the pull rod assembly 46 is hinged to one end of the switch 42 through a screw sleeve 48 and a connector 49, the switch 42 is hinged to the front support assembly 4, the slider 34 is arranged on the launch platform 31, and an inclined locking surface is arranged on it, the other end of the switch 42 abuts against the locking surface, and the slider 34 can adjust its position on the launch platform 31 in a direction away from or close to the switch 42. One end of the reset assembly 47 is connected to the front support assembly 4, and the other end is connected to the middle part of the pull rod assembly 46, which is used to provide the pull rod assembly 46 with an upward force that can unlock the locking device.

[0045] In this embodiment, the reset component 47 is a tension spring.

[0046] The threaded sleeve 48 is threadedly connected to the connector 49 and the lower end of the pull rod assembly 46, so that the connection length between the connector 49 and the pull rod assembly 46 is adjustable.

[0047] like Figure 2 As shown, the rear support assembly 3 is provided with a left rear rail 32 and a right rear rail 33, and both rails can be fine-tuned forward, backward, left and right, with an adjustment distance of 10 mm each, and the rear fulcrum of the drone can be locked on the left rear rail 32 and the right rear rail 33 through a third locking mechanism. When the drone is launched, under the force generated by the launch, the drone can release the lock of the third locking mechanism. This application does not involve improvements to the rear support assembly structure, and its structure is not described in detail here.

[0048] When hoisting the drone, the rear fulcrum of the drone is dropped into the left rear rail 32 and the right rear rail 33 respectively, and the front fulcrum is dropped into the U-shaped locking space at the upper end of the front support assembly 4. The position of the slider 34 is adjusted, and the switch 42 is pushed. The switch 42 pulls the pull rod assembly 46 to rotate the lock hook 44 to the locked state, that is, the front fulcrum of the drone is locked in the U-shaped locking space on the front support rod 45 of the front support assembly 4. In this way, the front support assembly 4 and the rear support assembly 3 together restrict all the freedom of the drone, ensuring the safety of the drone before launch.

[0049] like Figure 4As shown, the missile-carrying mechanism 1 is used to carry the booster rocket and is installed at the rear end of the launch platform 31. The booster rocket can be firmly pressed on the belly of the drone by adjustment. The missile-carrying mechanism 1 is composed of a lifting rod 12, a U-shaped bracket 13 and a second angle adjustment mechanism 15. The upper end of the lifting rod 12 is connected to the U-shaped bracket 13, and the lower end is hinged to the launch platform 31 through a nut shaft fixed on the third support 11 on the launch platform 31. A lifting assembly 14 composed of bolts and nuts is used to adjust the height of the U-shaped bracket 13 from the launch platform 31. One end of the second angle adjustment mechanism 15 is hinged to the lifting rod 12, and the other end is hinged to the launch platform 31 through a nut shaft fixed on the fourth support 16 on the launch platform 31. The angle of the lifting rod 12 is changed by adjusting its connection length through an external screw sleeve. The U-shaped bracket 13 has two notches, and one of the notches can be selected to fix the rocket as needed.

[0050] When installing the rocket, it is necessary to first adjust the second angle adjustment mechanism 15 to increase the installation gap. After the booster rocket is connected to the drone, the second angle adjustment mechanism 15 and the lifting rod 12 are adjusted to further enhance the reliability of the connection between the booster rocket and the drone.

[0051] like Figure 5 As shown, a guide mechanism 2 is provided in the UAV launch direction of the missile support mechanism 1, on which a high temperature resistant coating is sprayed, which can guide the wake generated by the booster rocket to protect the missile support mechanism 1. The guide mechanism 2 is composed of a folding plate 22 and a guide bracket 21. The upper end of the guide bracket 21 is fixedly connected to the folding plate 22, and the lower end is fixedly connected to the launch platform 31. The folding plate 22 is tilted downward, with the upper part close to the missile support mechanism 1 and the lower part away from the missile support mechanism 1.

[0052] After the installation of the UAV and the rocket is completed, they are powered on and debugged. After the inspection is completed, the launch platform 31 is erected to the specified launch angle through the angle adjustment mechanism 7, and the safety pin 37 is removed. Then the personnel evacuate to a safe area and remotely control the UAV engine to ignite. At this time, the UAV's own thrust cannot break the break pin, and the UAV is still locked on the launch pad. Then the booster rocket is ignited. The thrust of the booster rocket and the UAV's own thrust increase rapidly in a short time and break the break pin. The front support assembly 4 loses the rotation constraint and overturns in the launch direction around the rotation axis 410. During this movement, the reset assembly 47 in the locking device pulls the pull rod assembly 46 to move upward, pushing the lock hook 44 to unlock, and the UAV loses the freedom restriction and leaves the launch pad. Then the front support assembly 4 is quickly pulled to a horizontal state by the spring assembly 5, and the latch assembly 36 locks the block 43 to fix the front support assembly 4 in a horizontal state to prevent collision with the UAV or booster rocket and ensure the safety of the launch.

[0053] In the description of the present utility model, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. used to indicate the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the utility model product is usually placed when used. They are only for the convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model.

[0054] In addition, if the terms "horizontal" or "vertical" appear in the description of the present invention, it does not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0055] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0056] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A launching rack, characterized in that: include: A launching platform (31), a rear support assembly (3) and a front support assembly (4); The front support assembly (4) and the rear support assembly (3) are respectively arranged at the front and middle parts of the launching platform (31); The front support assembly (4) is used to support the front fulcrum of the aircraft; The rear support assembly (3) is used to support the rear fulcrum of the aircraft and to limit the position of the rear fulcrum of the aircraft; The front support assembly (4) is hinged to the launching platform (31), and a first locking mechanism is provided between the front support assembly (4) and the launching platform (31), the first locking mechanism being used to keep the front support assembly (4) in a vertical state and to limit the rotation of the front support assembly (4); A spring assembly (5) is provided between the launching platform (31) and the front supporting assembly (4); when the front supporting assembly (4) is in a vertical state, the spring assembly (5) provides a force that enables the front supporting assembly (4) to rotate in a free state in a direction of launching the aircraft.

2. The launcher according to claim 1, characterized in that: The spring assembly (5) is a tension spring, and two ends of the tension spring are respectively connected to the front support assembly (4) and the launching platform (31).

3. The launching rack according to claim 1, characterized in that: The first locking mechanism comprises a breaking pin, and two ends of the breaking pin are respectively connected to the front support assembly (4) and the launching platform (31).

4. The launching rack according to claim 3, characterized in that: The first locking mechanism also includes connecting components respectively arranged on the front support component (4) and the launching platform (31), the connecting components including a support and a pin shaft arranged on the support, and the two ends of the breaking pin respectively pass through the pin holes arranged on the pin shaft and connect the two connecting components.

5. The launching rack according to claim 1, characterized in that: When the front support assembly (4) is in a vertical state, a safety pin (37) is inserted between the front support assembly (4) and the launching platform (31).

6. The launching rack according to claim 1, characterized in that: The front support assembly (4) is provided with a locking device, and the locking device is used to lock the front fulcrum of the aircraft; When the front support assembly (4) rotates in the direction of launching the aircraft, the locking device can release the lock on the front fulcrum of the aircraft.

7. The launching rack according to claim 6, characterized in that: The locking device comprises a lock hook (44), a pull rod assembly (46), a reset assembly (47), a switch (42) and a slide block (34); The locking hook (44) is hinged to the front support assembly (4); One end of the locking hook (44) extends out of the upper end surface of the front support assembly (4) and cooperates with the front support assembly (4) to lock the front fulcrum of the aircraft, and the other end of the locking hook (44) is hinged to the upper end of the pull rod assembly (46); The switch (42) is hinged to the front support assembly (4), and one end of the switch (42) is hinged to the lower end of the pull rod assembly (46); The slider (34) is arranged on the launching platform (31), an inclined locking surface is arranged on the slider (34), and the other end of the switch (42) abuts against the locking surface; The slider (34) is configured to be able to adjust its position on the launch platform (31) in a direction away from or close to the switch (42); One end of the reset assembly (47) is connected to the front support assembly (4), and the other end is connected to the middle of the pull rod assembly (46). The reset assembly (47) is used to provide the pull rod assembly (46) with an upward force capable of unlocking the locking device.

8. The launching rack according to claim 1, characterized in that: A second locking mechanism is provided between the launch platform (31) and the front support assembly (4); when the front support assembly (4) is rotated to a horizontal state along the launch direction of the aircraft, the second locking mechanism fixes the front support assembly (4) in the horizontal state.

9. The launching rack according to claim 1, characterized in that: It also includes a base frame (7), and the launching platform (31) is arranged on the base frame (7); An angle adjustment mechanism (6) is provided between the base frame (7) and the launching platform (31), and the angle adjustment mechanism (6) is used to adjust the pitch angle between the launching platform (31) and the base frame (7).

10. The launching rack according to claim 9, characterized in that: One end of the launch platform is hinged to the base frame, the angle adjustment mechanism (6) comprises two groups of adjustment components, the adjustment components comprise a transmission component and a screw rod, the transmission component is used to drive the screw rod to rotate, and the screw rod is connected to the launch platform (31) in a transmission matching manner; The two sets of transmission components are connected by a transmission shaft to achieve synchronous transmission between the transmission components.

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