A selection lock mechanism for a drone catapult and methods of use thereof

Abstract

The application discloses a selecting and locking mechanism suitable for a UAV catapult, which comprises a locking holder with a C-shaped structure shell, an axle hole and an adapter are arranged on the shell, a horizontal axle is arranged in the axle hole, a locking ring is arranged at the end of the horizontal axle, a locking pin is arranged above the locking ring and connected with the shell, a dialing mechanism is arranged on the locking holder, the dialing mechanism is provided with a mounting seat, an unlocking plate and a dialing piece are arranged on the mounting seat, the dialing piece is connected with a servo lead screw and moves with the servo lead screw, the dialing mechanism is used for locking and unlocking the locking holder, the overall strength of the locking holder is greatly improved, the mechanism is suitable for a larger thrust place, the overall weight is further reduced, the overall action control is more accurate and reliable, the additional load of the catapult system is reduced, the catapult efficiency is improved, the overall structure is compact and simple and can be used in various catapult systems, the servo control is adopted, the mechanism action is more accurate and reliable, and the mechanism operation is more reliable.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical fields of mechanical manufacturing and unmanned aerial vehicle (UAV) selection locking mechanism, and particularly relates to a selection locking mechanism suitable for a UAV catapult and a use method thereof. BACKGROUND

[0002] At present, with the popularity of UAVs, UAV catapults have gradually developed. The UAV catapult is a device for assisting the rapid short-distance take-off of a UAV. The selection locking mechanism is a crucial device in the system, and is directly related to the smoothness of the catapulting process.

[0003] In the prior art, the UAV catapult generally adopts a one-to-one control form in which one thrust mechanism pushes one UAV. This form can avoid the use of the selection locking mechanism for the catapulting of multiple UAVs, but increases the number of thrust mechanisms, which greatly increases the complexity and cost of the overall catapult system. Or, the selection locking mechanism is only provided on a small-thrust UAV catapult. The overall strength of this mechanism is low, and it cannot be applied to large-thrust working conditions. Moreover, the weight of the mechanism is heavy, which greatly increases the catapult load.

[0004] In summary, there are at least the following technical problems:

[0005] The existing selection locking mechanism is only suitable for small-thrust catapults, has poor structural strength, and has a heavy mechanism. SUMMARY

[0006] The main purpose of the present application is to provide a selection locking mechanism suitable for a UAV catapult and a use method thereof, so as to solve the problems of the existing selection locking mechanism in the prior art, such as being only suitable for small-thrust catapults, having poor structural strength, and having a heavy mechanism.

[0007] In order to achieve the above-mentioned purpose, according to one aspect of the present application, a selection locking mechanism suitable for a UAV catapult is provided, comprising:

[0008] A locking holder has a C-shaped structure shell, an axle hole and an adapter are provided on the shell, a horizontal shaft is inserted into the axle hole, a locking ring is provided at the end of the horizontal shaft, a locking pin is provided directly above the locking ring, and the locking pin is connected with the shell;

[0009] A dialing mechanism has a mounting seat, an unlocking plate and a dialing piece are provided on the mounting seat, the dialing piece is connected with a servo lead screw and moves with the servo lead screw;

[0010] The dialing mechanism is used for locking and unlocking the locking holder.

[0011] Preferably, the locking holder is pushed by the catapult thrust mechanism in the launching channel and is accelerated with the UAV.

[0012] Preferably, the dialing mechanism is fixed in the unmanned aerial vehicle launching channel.

[0013] Preferably, the horizontal shaft slides left and right in the shaft hole.

[0014] Preferably, the adapter is installed around the shell.

[0015] Preferably, the unlocking plate is installed at the back of the mounting seat by screws.

[0016] Preferably, in the initial state, the horizontal shaft is inserted into the shaft hole, the locking bracket is locked in the launching channel, and the unlocking plate lifts the locking pin to make the locking pin in the unlocked state.

[0017] Preferably, when a selected unmanned aerial vehicle is needed, the servo lead screw moves right to drive the dialing piece to dial the locking ring, and the horizontal shaft is separated from the shaft hole and inserted into the thrust mechanism, that is, when a selected unmanned aerial vehicle is needed, a movement signal is given to the servo lead screw, the servo lead screw moves right to drive the dialing piece to dial the locking ring, thereby separating the horizontal shaft from the shaft hole and inserting it into the thrust mechanism to complete the selection action.

[0018] Preferably, when the selection is completed, the thrust mechanism drives the locking bracket and pushes the unmanned aerial vehicle out of the launching channel, the locking bracket moves forward to make the unlocking plate separate from the locking pin, and the locking pin is locked in the locking ring, and when the locking bracket approaches the dialing mechanism, the unlocking plate lifts the locking pin again to make the locking pin unlocked from the locking ring, then a movement signal is given to the servo lead screw, the servo lead screw moves left to drive the dialing piece to dial the locking ring, thereby separating the horizontal shaft from the thrust mechanism and inserting it into the shaft hole to complete the locking action.

[0019] According to another aspect of the present application, a method for using a selection and locking mechanism suitable for an unmanned aerial vehicle catapult is provided, comprising:

[0020] Inserting the horizontal shaft into the shaft hole, locking the locking bracket in the launching channel, and lifting the locking pin by the unlocking plate to make the locking pin in the unlocked state;

[0021] When a selected unmanned aerial vehicle is needed, a movement signal is given to the servo lead screw, the servo lead screw moves right to drive the dialing piece to dial the locking ring, thereby separating the horizontal shaft from the shaft hole and inserting it into the thrust mechanism to complete the selection action.

[0022] The thrust mechanism drives the locking bracket and pushes the unmanned aerial vehicle out of the launching channel, the locking bracket moves forward to make the unlocking plate separate from the locking pin, and the locking pin is locked in the locking ring to complete the catapult process and lock the shaft.

[0023] When the locking bracket returns, the unlocking plate lifts the locking pin again, and the locking pin is unlocked from the locking ring, and then a servo lead screw movement signal is given, and the servo lead screw moves left to drive the dial to dial the locking ring, thereby driving the horizontal shaft to separate from the thrust mechanism and complete the locking action with the insertion shaft hole.

[0024] The technical scheme of the present application has the following technical effects:

[0025] In this embodiment, the shell is made of 7075-T6 aviation aluminum material, the structure adopts a C-shaped structure, and a reinforcing rib is added to the inner side, which greatly improves the overall strength of the locking bracket, so that the present application can be applied to larger thrust places, and the hollow hole is opened in the outer wall to further reduce the overall weight. The dialing mechanism adopts servo drive lead screw transmission control, which makes the overall action control of the mechanism more accurate and reliable. The overall mechanism is divided into two parts, the locking bracket and the dialing mechanism, so that the locking bracket is directly driven by the thrust mechanism instead of the overall mechanism, which can reduce the additional load of the ejection system and improve the ejection efficiency. The overall structure is compact and simple and can be used in various ejection systems; the locking bracket adopts a C-shaped structure, which greatly increases the overall strength of the mechanism, so that the present application can be applied to larger thrust ejection systems; the mechanism of the present application adopts servo control, which can make the mechanism action more accurate and reliable. BRIEF DESCRIPTION OF DRAWINGS

[0026] The drawings accompanying the specification of this application form a part thereof, serve to provide further understanding of the present application, and together with the description of the exemplary embodiments of the present application and the explanation thereof, explain the present application, and do not constitute an improper limitation on the present application. In the drawings:

[0027] Figure 1 A structural schematic view of the selected machine locking mechanism suitable for the unmanned aerial vehicle ejector according to the present application is shown;

[0028] Figure 2 A locking bracket structure view of the selected machine locking mechanism suitable for the unmanned aerial vehicle ejector in Figure 1 ;

[0029] Figure 3 A dialing mechanism structure view of the selected machine locking mechanism suitable for the unmanned aerial vehicle ejector in Figure 1 ;

[0030] Figure 4 A working structure view of the selected machine locking mechanism suitable for the unmanned aerial vehicle ejector in Figure 1 ;

[0031] Figure 5 An unlocking plate lifting and locking pin action view of the selected machine locking mechanism suitable for the unmanned aerial vehicle ejector in Figure 1 ;

[0032] Figure 6 A shell view of a selection locking mechanism suitable for a UAV catapult is shown. Figure 1 A shell view of a selection locking mechanism suitable for a UAV catapult is shown.

[0033] Wherein, the above drawings include the following reference signs:

[0034] Locking bracket 1; toggle mechanism 2; shell 3; cross shaft 4; locking ring 5; locking pin 6; set screw 7; adapter 8; mounting seat 9; servo lead screw 10; unlocking plate 11; toggle piece 12; launch channel 13; shaft hole 14; thrust mechanism 15; UAV 16; reinforcing rib 17; hollow hole 18. DETAILED DESCRIPTION

[0035] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0036] As shown in Figures 1 to 6 The present application provides a selection locking mechanism suitable for a UAV 16 catapult, which includes a locking bracket 1. The locking bracket 1 has a C-shaped structure shell 3. The shell 3 is provided with a shaft hole 14 and an adapter 8. The shaft hole 14 is provided with a cross shaft 4. The end of the cross shaft 4 is provided with a locking ring 5. The locking ring 5 is provided with a locking pin 6 above. The locking pin 6 is connected with the shell 3.

[0037] The present application provides a selection locking mechanism suitable for a UAV 16 catapult, which includes a locking bracket 1. The locking bracket 1 has a C-shaped structure shell 3. The shell 3 is provided with a shaft hole 14 and an adapter 8. The shaft hole 14 is provided with a cross shaft 4. The end of the cross shaft 4 is provided with a locking ring 5. The locking ring 5 is provided with a locking pin 6 above. The locking pin 6 is connected with the shell 3.

[0038] The present application provides a selection locking mechanism suitable for a UAV 16 catapult, which includes a locking bracket 1. The locking bracket 1 has a C-shaped structure shell 3. The shell 3 is provided with a shaft hole 14 and an adapter 8. The shaft hole 14 is provided with a cross shaft 4. The end of the cross shaft 4 is provided with a locking ring 5. The locking ring 5 is provided with a locking pin 6 above. The locking pin 6 is connected with the shell 3.

[0039] The present application provides a selection locking mechanism suitable for a UAV 16 catapult, which includes a locking bracket 1. The locking bracket 1 has a C-shaped structure shell 3. The shell 3 is provided with a shaft hole 14 and an adapter 8. The shaft hole 14 is provided with a cross shaft 4. The end of the cross shaft 4 is provided with a locking ring 5. The locking ring 5 is provided with a locking pin 6 above. The locking pin 6 is connected with the shell 3.

[0040] In the present application, the locking bracket 1 is used to lock the UAV 16 in the launch channel 13. The locking bracket 1 has a C-shaped structure shell 3. The C-shaped structure has high strength. The shell 3 is provided with a shaft hole 14 and an adapter 8. The shaft hole 14 is used to install the cross shaft 4. The adapter 8 is installed around the shell 3 and is used to cooperate with the launch channel 13. The cross shaft 4 is inserted into the shaft hole 14 and slides left and right in the shaft hole 14. The end of the cross shaft 4 is provided with a locking ring 5. The locking ring 5 is provided with a locking pin 6 above and is used to lock the locking ring 5. The locking pin 6 is connected with the shell 3. The locking bracket 1 is pushed by the catapult thrust mechanism 15 in the launch channel 13 and is accelerated with the UAV 16.

[0041] In this embodiment, the dial mechanism 2 is used to realize the dial locking pin 6 and the locking ring 5, the dial mechanism 2 has a mounting seat 9, the mounting seat 9 is used to install the fixed servo lead screw 10 and the unlocking plate 11, the mounting seat 9 is provided with the unlocking plate 11 and the dial piece 12, the unlocking plate 11 is used to unlock the locking pin 6, the dial piece 12 is used to unlock the locking ring 5, the unlocking plate 11 is installed on the back of the mounting seat 9 by a screw, the dial piece 12 is connected with the servo lead screw 10 and moves with the servo lead screw 10, the servo lead screw 10 is given a movement signal, the right movement of the servo lead screw 10 drives the dial piece 12 to dial the locking ring 5, thereby driving the horizontal shaft 4 to be separated from the shaft hole 14 and to be inserted into the thrust mechanism 15 (simulating the thrust mechanism 15), that is, the selecting machine action is completed, then the thrust mechanism 15 drives the locking support 1 and pushes the unmanned aerial vehicle 16 (simulating the unmanned aerial vehicle 16) out of the launching channel 13, the forward movement of the locking support 1 makes the unlocking plate 11 separate from the locking pin 6, and the locking pin 6 is locked into the locking ring 5, that is, the ejection process is completed. The dial mechanism 2 is fixed in the unmanned aerial vehicle 16 launching channel 13.

[0042] In this embodiment, the dial mechanism 2 is used to lock and unlock the locking support 1. In the initial state, the horizontal shaft 4 is inserted into the shaft hole 14, the locking support 1 is locked in the launching channel 13, and the unlocking plate 11 lifts the locking pin 6, so that the locking pin 6 is in the unlocked state. When the unmanned aerial vehicle 16 needs to be selected, the right movement of the servo lead screw 10 drives the dial piece 12 to dial the locking ring 5, the locking ring 5 drives the horizontal shaft 4 to be separated from the shaft hole 14 and to be inserted into the thrust mechanism 15 to select the machine. When the machine selection is completed, the thrust mechanism 15 drives the locking support 1 and pushes the unmanned aerial vehicle 16 out of the launching channel 13, the forward movement of the locking support 1 makes the unlocking plate 11 separate from the locking pin 6, and the locking pin 6 is locked into the locking ring 5.

[0043] In this embodiment, the dial mechanism 2 is located behind the locking support 1 and works, the locking support 1 can be pushed by the ejector thrust mechanism 15 in the launching channel 13 to push the unmanned aerial vehicle 16 to accelerate, the dial mechanism 2 can be fixed in the unmanned aerial vehicle 16 launching channel 13 by a screw and does not accelerate with the unmanned aerial vehicle 16. The shell 3 is the main supporting structure, the horizontal shaft 4 is inserted into the center hole of the shell 3 and can slide left and right in the hole, the locking ring 5 is fixedly connected with the horizontal shaft 4 through the set screw 7, the locking pin 6 is fixedly connected inside the shell 3, and the adapter 8 is installed around the shell 3. The servo lead screw 10 is installed on the mounting seat 9 by a screw, the dial piece 12 is installed on the servo lead screw 10 and can move with the lead screw, and the unlocking plate 11 is installed on the back of the mounting seat 9 by a screw.

[0044] In this embodiment, the shell 3 is made of 7075-T6 aviation aluminum material, the structure adopts a C-shaped structure form, and a reinforcing rib 17 is added to the inside, as shown in Figure 6As shown, this greatly improves the overall strength of the locking bracket 1, so that the application can be applied to larger thrust places, while the outer wall is provided with a hollow hole 18, which further reduces the overall weight. The actuating mechanism 2 adopts a servo drive screw transmission control, which makes the overall action control of the mechanism more accurate and reliable. The overall mechanism is divided into two parts, the locking bracket 1 and the actuating mechanism 2, so that the thrust mechanism 15 directly drives the locking bracket 1 instead of the overall mechanism, which can reduce the additional load of the ejection system and improve the ejection efficiency. The overall structure is compact and simple and can be used in various ejection systems; the locking bracket 1 adopts a C-shaped structure, which greatly increases the overall strength of the mechanism, so that the application can be applied to larger thrust ejection systems; the mechanism of the application adopts servo control, which can make the mechanism operate more accurately and reliably.

[0045] In this embodiment, the application can be applied to various large-thrust unmanned aerial vehicle 16 ejection devices to assist in completing the ejection of the unmanned aerial vehicle 16. By adding a selection and locking mechanism to the unmanned aerial vehicle 16 ejection device, the mechanism can achieve the ejection of multiple unmanned aerial vehicles 16 by one set of thrust mechanisms 15 in the ejection device due to the selection function of the mechanism. For example, when a gas ejection device for unmanned aerial vehicles 16 is used to launch multiple unmanned aerial vehicles 16 at a high frequency, a set of thrust cylinders can only push one unmanned aerial vehicle 16, which is complex in structure and high in cost. The selection and locking mechanism of the application can be installed in the unmanned aerial vehicle 16 gas ejection device to reduce the number of thrust cylinders used, thereby reducing the cost of the ejection device.

[0046] The working principle is: the initial state is that the horizontal shaft 4 is inserted into the shaft hole 14, that is, the locking bracket 1 is locked in the launch channel 13 and cannot move, and at the same time the unlocking plate 11 lifts the locking pin 6, so that the locking pin 6 is in an unlocked state. When a selected unmanned aerial vehicle 16 is needed, a movement signal is given to the servo lead screw 10, the servo lead screw 10 moves right to drive the actuating piece 12 to actuate the locking ring 5, thereby driving the horizontal shaft 4 to separate from the shaft hole 14 and insert into the thrust mechanism 15 (simulated thrust mechanism 15), that is, the selection action is completed, and then the thrust mechanism 15 drives the locking bracket 1 and pushes the unmanned aerial vehicle 16 (simulated unmanned aerial vehicle 16) out of the launch channel 13, the locking bracket 1 moves forward to make the unlocking plate 11 separate from the locking pin 6, so that the locking pin 6 is locked into the locking ring 5, that is, the ejection process of the shaft locking is completed. When the thrust mechanism 15 returns, it will drive the locking bracket 1 to return, and when the locking bracket 1 approaches the actuating mechanism 2, the unlocking plate 11 will lift the locking pin 6 again, and the action is as follows Figure 5 As shown, a represents before lifting, b represents during lifting, and c represents after lifting, so that the locking pin 6 is unlocked from the locking ring 5, and then a movement signal is given to the servo lead screw 10, the servo lead screw 10 moves left to drive the actuating piece 12 to actuate the locking ring 5, thereby driving the horizontal shaft 4 to separate from the thrust mechanism 15 and insert into the shaft hole 14, that is, the locking action is completed.

[0047] In summary, the housing 3 of this invention adopts a C-shaped structure and reduces weight by removing materials from the internal structure, resulting in a simple, high-strength, and lightweight structure suitable for various high-thrust catapult applications. The mechanism employs a separate structure for the locking support 1 and the actuating mechanism 2. The locking and unlocking of the horizontal axis 4 is achieved by the separation and proximity movement of these two components, which controls the locking pin 6 via the unlocking plate. This mechanism is simple and reliable. Furthermore, this invention introduces servo drive into the drone 16-selector locking mechanism, making the overall control of the mechanism more precise and reliable.

[0048] Another embodiment of the present invention provides a method for using a selection and locking mechanism suitable for a UAV 16 catapult, comprising:

[0049] Insert the horizontal shaft 4 into the shaft hole 14, lock the locking bracket 1 in the launch channel 13, and lift the locking pin 6 through the unlocking plate 11 so that the locking pin 6 is in the unlocked state.

[0050] When it is necessary to select the drone 16, a motion signal is given to the servo screw 10. The servo screw 10 moves to the right, which drives the paddle 12 to move the locking ring 5, thereby driving the horizontal shaft 4 to disengage from the shaft hole 14 and engage with the insertion thrust mechanism 15 to complete the drone selection action.

[0051] The thrust mechanism 15 drives the locking support 1 and pushes the drone 16 out of the launch channel 13. The locking support 1 moves forward, causing the unlocking plate 11 to disengage from the locking pin 6 and the locking pin 6 to lock into the locking ring 5, thus completing the locking of the ejection process shaft.

[0052] When the thrust mechanism 15 returns, it drives the locking bracket 1 to return as well. When the locking bracket 1 approaches the actuating mechanism 2, the unlocking plate 11 lifts the locking pin 6 again, unlocking the locking pin 6 from the locking ring 5. Then, a motion signal is given to the servo screw 10, which moves to the left and drives the actuating plate 12 to actuate the locking ring 5, thereby causing the horizontal shaft 4 to disengage from the thrust mechanism 15 and complete the locking action with the insertion shaft hole 14.

[0053] As can be seen from the above description, the embodiments of the present invention achieve the following technical effects:

[0054] The shell 3 adopts 7075-T6 aviation aluminum material, the structure adopts C type structure form, and the reinforcing rib 17 is added to the inner side, the overall strength of the locking bracket 1 is greatly improved, the application can be applied to larger thrust places, at the same time, the hollow hole 18 is opened in the outer wall, the overall weight is further reduced. The driving mechanism 2 adopts servo driving screw transmission control, which makes the overall action control of the mechanism more accurate and reliable, the overall mechanism is divided into two parts, the locking bracket 1 and the driving mechanism 2, the thrust mechanism 15 directly drives the locking bracket 1 instead of the overall mechanism, the additional load of the ejection system can be reduced, and the ejection efficiency is improved. The overall structure is compact and simple and can be used in various ejection systems; the locking bracket 1 adopts C type structure form, which greatly increases the overall strength of the mechanism, so that the application can be applied to larger thrust ejection systems; the mechanism of the application adopts servo control, which can make the mechanism action more accurate and operation more reliable.

[0055] The above only describes the preferred embodiments of the application and is not used to limit the application. For those skilled in the art, the application can have various changes and variations. Any modification, equivalent replacement, improvement, etc. within the spirit and principle of the application shall be included in the protection scope of the application.

Claims

1. A selection and locking mechanism suitable for a UAV catapult, characterized in that, It comprises: A locking holder with a C-shaped structure shell, which is provided with an axle hole and an adapter, a cross axle is inserted into the axle hole, the end of the cross axle is provided with a locking ring, a locking pin is provided above the locking ring, and the locking pin is connected with the shell; the locking holder is pushed in the launching channel by the ejector thrust mechanism and is pushed and accelerated with the unmanned aerial vehicle; A dialing mechanism, which is provided with an installation seat, an unlocking plate and a dialing piece, the dialing piece is connected with a servo lead screw and moves with the servo lead screw; Wherein, the dialing mechanism is used for locking and unlocking the locking holder; in the initial state, the cross axle is inserted into the axle hole, the locking holder is locked in the launching channel, the unlocking plate lifts the locking pin, and the locking pin is in the unlocked state; when the unmanned aerial vehicle needs to be selected, the servo lead screw moves right to drive the dialing piece to dial the locking ring, the locking ring drives the cross axle to separate from the axle hole and is inserted into the thrust mechanism selection mechanism; when the selection mechanism is completed, the thrust mechanism drives the locking holder and pushes the unmanned aerial vehicle out of the launching channel, the forward movement of the locking holder makes the unlocking plate separate from the locking pin, and the locking pin is locked into the locking ring.

2. The selection lock mechanism suitable for use in a catapult of an unmanned aerial vehicle as claimed in claim 1, wherein, The dialing mechanism is fixed in the unmanned aerial vehicle launching channel.

3. The selection lock mechanism suitable for use in a catapult of an unmanned aerial vehicle as claimed in claim 1, wherein, The cross axle slides left and right in the axle hole.

4. The selection lock mechanism suitable for use in a catapult of an unmanned aerial vehicle as claimed in claim 1, wherein, The adapter is installed around the shell.

5. The selection lock mechanism suitable for use in a catapult of an unmanned aerial vehicle as claimed in claim 1, wherein, The unlocking plate is installed on the back of the installation seat by screws.

6. A method of using a selection lock mechanism suitable for a UAV catapult, according to any one of claims 1-5, characterized in that, It comprises: Insert the cross axle into the axle hole, lock the locking holder in the launching channel, lift the locking pin by the unlocking plate, and make the locking pin in the unlocked state; When the unmanned aerial vehicle needs to be selected, the servo lead screw is given a movement signal, the servo lead screw moves right to drive the dialing piece to dial the locking ring, thereby driving the cross axle to separate from the axle hole and insert into the thrust mechanism to complete the selection action; The thrust mechanism drives the locking holder and pushes the unmanned aerial vehicle out of the launching channel, the forward movement of the locking holder makes the unlocking plate separate from the locking pin, and the locking pin is locked into the locking ring to complete the locking of the shaft; When the thrust mechanism returns, the locking holder is returned, when the locking holder approaches the dialing mechanism, the unlocking plate lifts the locking pin again, the locking pin is unlocked from the locking ring, then the servo lead screw is given a movement signal, the servo lead screw moves left to drive the dialing piece to dial the locking ring, thereby driving the cross axle to separate from the thrust mechanism and insert into the axle hole to complete the locking action.

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