Vehicle-mounted launcher and method for unmanned aerial vehicle

Abstract

The invention discloses a vehicle-mounted launching rack and method for an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle launching. Comprising N sets of supporting beams, N sets of launching angle adjusting mechanisms, N sets of unmanned aerial vehicle bearing mechanisms, a frame body assembly and a wire control mechanism. The N groups of supporting beams are arranged in an array; wherein N is an integer greater than 1; a frame body assembly is arranged between every two adjacent supporting beams. The N groups of emission angle adjusting mechanisms are correspondingly arranged on each group of supporting beams respectively; the launching angle adjusting mechanism at least comprises a lifting arm with a head end and a tail end; the tail end of the lifting arm is rotationally connected to the supporting beam; the unmanned aerial vehicle bearing mechanisms are correspondingly arranged on each group of lifting arms respectively; the drive-by-wire mechanism is arranged between the adjacent unmanned aerial vehicle bearing mechanisms. The unmanned aerial vehicle is launched through manual mechanical or wireless remote control operation by means of the drive-by-wire mechanism, and the corresponding launching mode is selected based on requirements; adjustment of the launching angle is achieved through the lead screw transmission assembly, and it is ensured that the unmanned aerial vehicle can be launched according to the preset angle.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle (UAV) launch, and in particular relates to a vehicle-mounted launch rack and a method for unmanned aerial vehicle (UAV). Background Art

[0002] With the rapid development of drone technology, drones have been widely used in many fields. In order to achieve rapid deployment and flexible use of drones, the performance and functions of drone launchers, as important auxiliary equipment for drone take-off, are increasingly valued. Existing drone vehicle-mounted launchers generally have problems such as a single drone control launch working mode and an unadjustable launch angle.

[0003] Most of the existing launchers can only adopt fixed launch modes and cannot be flexibly adjusted according to mission requirements. This results in the inability of drones to fully exert their flexibility and efficiency when performing tasks, limiting their scope of application. In addition, the problem of non-adjustable launch angles limits the application of drones in complex environments. In situations where the launch angle needs to be adjusted, the existing launchers cannot meet the requirements, resulting in the drone being unable to accurately reach the target location or unable to complete the scheduled mission. This not only affects the application effect of the drone, but also increases the risk of mission failure. Summary of the invention

[0004] Purpose of the invention: In order to solve the above problems, the present invention provides a UAV vehicle-mounted launcher and method.

[0005] Technical solution: A vehicle-mounted launcher for a UAV, comprising: N groups of support beams are arranged in an array; wherein N is an integer greater than 1; and frame assemblies are arranged between adjacent support beams; N groups of emission angle adjustment mechanisms are respectively arranged on each group of support beams; the emission angle adjustment mechanism comprises at least a lifting arm having a head end and a tail end; the tail end of the lifting arm is rotatably connected to the support beam; The same number of drone carrying mechanisms as the launch angle adjustment mechanisms are respectively arranged on each set of lifting arms; The wire control mechanism is arranged between adjacent UAV carrying mechanisms; each group of wire control mechanisms is used to control the take-off of two groups of UAVs at the same time; the wire control mechanism includes the following working modes: manual mechanical mode and wireless remote control mode.

[0006] In a further embodiment, the wire control mechanism comprises: A thread connection member is disposed above the frame assembly; Two sets of first guide members are respectively and correspondingly arranged on the side walls of the tails of the two sets of lifting arms; A second guide member is provided on the frame assembly; A third guide member, disposed on the frame assembly close to the second guide member; Two sets of spring latch assemblies are respectively arranged on two sets of lifting arms; An aircraft lock catch connected to the spring latch assembly; A driving member, disposed on the frame assembly; Two groups of first control lines are symmetrically arranged; one end of the first control line is connected to the line connector and the other end bypasses the first guide and is connected to the spring latch assembly; A second control line, one end of which is connected to the line connector and the other end of which is elastically connected to the outer wall of the second guide member; A third control line, one end of which is connected to the line connector and the other end of which passes around the third guide and extends downward; A fourth control line has one end connected to the line connector and the other end bypassing the second guide member; the other end of the fourth control line is connected to the output end of the drive member.

[0007] In a further embodiment, the wire control mechanism further includes: a fourth guide member, mirroring the second guide member and disposed on the frame assembly; a movable guide connected to the other end of the fourth control line; A fifth control line has one end connected to the output end of the driving member and the other end bypasses the moving guide member and the fourth guide member in sequence and is connected to the outer wall of the moving guide member.

[0008] In a further embodiment, the wire control mechanism further includes: A wire reverse tension spring has one end connected to the second control wire and the other end connected to the outer wall of the second guide member.

[0009] In a further embodiment, the spring latch assembly comprises: A first shell and a second shell are successively on the lifting arm; A spring pin, one end of which is connected to the first control line and the other end of which sequentially passes through the first housing and extends into the second housing; A return spring is arranged in the first housing and sleeved on the spring pin.

[0010] In a further embodiment, the aircraft locking member is an aircraft locking sleeve; the aircraft locking member is used to connect a drone; Before the UAV flies, the aircraft lock member aircraft lock sleeve is located between the first shell and the second shell and is sleeved on the spring pin and is limited by the spring latch assembly.

[0011] In a further embodiment, the frame assembly comprises: At least two groups of connecting beams, vertically connected to the supporting beams; The reinforcing beam is parallel to the supporting beam and connected to the connecting beam.

[0012] In a further embodiment, the emission angle adjustment mechanism further comprises: A screw drive assembly is disposed on the support beam and below the head end of the lifting arm; A slider, drivingly connected to the screw rod rotating assembly; A lifting connection member, one end of which is rotatably connected to the slider and the other end of which is connected to the head end of the lifting arm; The locking assembly is connected to the screw transmission assembly; the locking assembly is used to position the screw transmission assembly.

[0013] In a further embodiment, the drone carrying mechanism comprises: A first adjusting block and a second adjusting block are respectively arranged at the head end and the tail end of the lifting arm; Two sets of drone fixing blocks are respectively arranged on the first adjusting block and the second adjusting block; The tail block of the UAV is arranged behind the second adjusting block; A plurality of support blocks are arranged on the lifting arm and connected to the first adjusting block or the second adjusting block.

[0014] In another technical solution, a method for using the above-mentioned vehicle-mounted launcher for a UAV is provided, comprising the following steps: Step 1, assembling the drone: when assembling the drone on each set of drone carrying mechanisms, pull the first control line adjacent to the drone carrying mechanism to release the assembly space in the spring latch assembly; place the drone in the drone carrying mechanism, and after placing the aircraft lock fastener in the assembly space, stop pulling the first control line; repeat the above operation to place N sets of drones on N sets of drone carrying mechanisms respectively; Step 2: Adjust the launch angle: Based on the launch requirements, adjust the angle of each set of lifting arms so that the launch angle of each set of drones meets the launch requirements; Step 3, control the drone to take off: select the working mode of the wire control mechanism as manual mechanical mode or wireless remote control mode; in the manual mechanical mode, manually pull the third control line, and then the third control line drives the wire connection piece and the first control line connected to the wire connection piece, and then drives the movable part in the spring latch assembly and releases the aircraft lock buckle on the spring latch assembly to complete the drone take-off; Or, in the wireless remote control mode, the control driving member drives the fourth control line to move close to the driving member, and drives the line connecting member and the first control line connected to the line connecting member to move, thereby driving the movable parts in the spring latch assembly and releasing the aircraft lock fastener on the spring latch assembly to complete the take-off of the drone.

[0015] Beneficial effects: (1) The present invention uses a wire control mechanism to realize manual mechanical or wireless remote control operation to launch the drone. Manual launch allows the operator to quickly adjust the launch angle and force of the drone according to the on-site conditions and mission requirements, thereby ensuring that the drone can take off accurately and efficiently; it can respond quickly and provide the drone with instant take-off capabilities. Wireless remote control launch realizes the automated launch of the drone, as well as the intelligent launch, improving the efficiency and accuracy of mission execution.

[0016] (2) The screw drive assembly of the present invention can achieve fine adjustment of the launch angle, ensuring that the drone can be launched at a predetermined angle. The design of the locking assembly can ensure that the screw in the screw drive assembly remains in a fixed position after the angle adjustment is completed, thereby preventing the launch angle from changing due to external force or vibration, and improving the accuracy and stability of the launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the structure of the present invention; Figure 2 is a top view of the present invention; Figure 3 It is a schematic diagram of the local structure of the present invention; Figure 4 It is a partial structural schematic diagram of another viewing angle of the present invention; Figure 5 It is a partial structural schematic diagram of another viewing angle of the present invention; Figure 6 yes Figure 4 A magnified view of the local structure; Figure 7 It is a structural schematic diagram of a spring latch assembly.

[0018] Figures 1 to 7The labels are as follows: support beam 1, frame assembly 2, connecting beam 21, reinforcing beam 22, launch angle adjustment mechanism 3, lifting arm 31, screw transmission assembly 32, mounting block 321, screw 322, rocker 323, locking block 324, locking handle 325, slider 33, lifting connector 34, drone carrying mechanism 4, first adjustment block 41, second adjustment block 42, drone fixing block 43, tail block 44, support block 45, wire control mechanism 5, wire connector 51, first guide member 52, second guide member 53, fourth guide member 54, third guide member 55, spring latch assembly 56, spring pin 561, reset spring 562, drive member 57, first control line 58, second control line 59, third control line 510, fourth control line 511, fifth control line 512, wire reverse tension spring 513, moving guide member 514, aircraft locking member 6, angle pointer 7, angle ruler 8. DETAILED DESCRIPTION

[0019] Example 1 like Figure 1 As shown, this embodiment provides a UAV vehicle-mounted launcher (hereinafter referred to as the launcher), including: N groups of support beams 1, N groups of launch angle adjustment mechanisms 3, N groups of UAV carrying mechanisms 4, a frame assembly 2 and a wire control mechanism 5.

[0020] N groups of support beams 1 are arranged in parallel, and N is an integer greater than 1, that is, the number of support beams 1 is at least two groups. This embodiment is described in detail by taking two groups as an example; in other embodiments, the value of N is set based on the number of drones launched each time, and N can be 3, 4, 5, etc.

[0021] A frame assembly 2 is provided between adjacent support beams 1. The frame assembly 2 is used to connect adjacent support beams 1 to form a stable whole.

[0022] A group of emission angle adjustment mechanisms 3 are arranged on each group of support beams 1. The emission angle adjustment mechanisms 3 at least include an adjustable angle lifting arm 31. The lifting arm 31 is provided with a head end and a tail end. The tail end of the lifting arm 31 is rotatably connected to the support beam 1, such as by using a profile hinge to achieve the rotational connection between the two.

[0023] A set of UAV carrying mechanisms 4 is arranged on each set of lifting arms 31. Before the UAV is launched, the UAV is placed in the UAV carrying mechanism 4.

[0024] A set of wire control mechanisms 5 is arranged between adjacent drone carrying mechanisms 4. Each set of wire control mechanisms 5 is used to control the take-off of two sets of drones at the same time; the wire control mechanisms 5 include the following working modes: manual mechanical mode and wireless remote control mode.

[0025] In the above technical solution, the number of support beams 1 is adjusted according to the number of drones launched each time, thereby optimizing resource use and avoiding unnecessary waste. After multiple groups of support beams 1 are formed into a whole through the frame assembly 2, the launch operation is performed synchronously to improve the overall launch efficiency. In addition, multiple groups of support beams 1 are connected into a whole through the frame assembly 2, which enhances the structural stability of the entire launch rack and reduces the risk of overall launch failure caused by failure or instability of a single support beam 1.

[0026] In addition, the number of support beams 1 is flexibly set and the frame assembly 2 is used to form a whole, so that the entire launcher can be quickly adjusted according to different mission requirements. For example, for tasks that require large-scale drone cluster combat, the number of support beams 1 and the number of launched drones can be increased; while for tasks that require high-precision reconnaissance, the number of support beams 1 can be reduced and the launch angle and height of the drone can be optimized.

[0027] By raising and lowering each set of lifting arms 31, the launch angle of the UAV is adjusted to ensure that the UAV can fly according to a predetermined trajectory and altitude after launch, thereby improving flight stability and safety.

[0028] In a further embodiment, the frame assembly 2 includes: at least two groups of connection beams 21, and reinforcement beams 22. In this example, there are two groups of connection beams 21. The two groups of connection beams 21 are vertically connected to the support beams 1. The reinforcement beams 22 are parallel to the support beams 1. The two ends of the reinforcement beams 22 are connected to the midpoints of the two groups of connection beams 21.

[0029] In the above scheme, two groups of connecting beams 21 and reinforcing beams 22 are arranged between adjacent supporting beams 1. The above structure forms a whole, which improves the stability of the launch frame, can resist various external interferences and vibrations, and ensure the stability and safety of the UAV during the launch process.

[0030] In a further embodiment, Figure 2 , Figure 4 and Figure 6 As shown, the wire control mechanism 5 includes: a wire connecting member 51, two groups of first guide members 52, a second guide member 52, a third guide member 55, two groups of spring latch assemblies 56, a driving member 57, two groups of first control wires 58, a second control wire 59, a third control wire 510, a fourth control wire 511, and an aircraft lock member 6. The first guide member 52, the second guide member 52, and the third guide member 55 are pulley assemblies.

[0031] The line connector 51 is arranged above the reinforcing beam 22. Each group of first guide members 52 is installed on the side wall of the tail of each group of lifting arms 31. The second guide member 53 is installed on the reinforcing beam 22. The third guide member 55 is installed on the side wall of the connecting beam 21 near the second guide member 53. Each group of spring latch assemblies 56 is installed on each group of lifting arms 31, and the specific position is set based on actual installation requirements, such as on the side wall of the head of the lifting arm 31, or at the top of each group of lifting arms 31. The driving member 57 is installed on the reinforcing beam 22. The driving member 57 can be an electric telescopic cylinder, a servo or a cylinder, etc. The driving member 57 is used to pull the fourth control line 511 horizontally. In this embodiment, the principle of wireless remote control technology is adopted to control the operation of the driving member 57. The aircraft lock member 6 is connected to the spring latch assembly 56.

[0032] Two groups of first control lines 58 are symmetrically arranged. One end of the first control line 58 is connected to the thread connector 51 and the other end bypasses the first guide 52 and is connected to the spring latch assembly 56. One end of the second control line 59 is connected to the thread connector 51 and the other end is elastically connected to the outer wall of the second guide 53. One end of the third control line 510 is connected to the thread connector 51 and the other end bypasses the third guide 55 and extends downward. One end of the fourth control line 511 is connected to the thread connector 51 and the other end bypasses the second guide 53. The other end of the fourth control line 511 is connected to the output end of the driving member 57.

[0033] In the above technical solution, the first control line 58, the second control line 59, the third control line 510, and the fourth control line 511 form a line control system. In the absence of external force, the first control line 58, the second control line 59, the third control line 510, and the fourth control line 511 are in a tensioned state.

[0034] The second control line 59 is elastically connected to the outer wall of the second wire guide 53. The elastic connection is achieved by setting a wire reverse tension spring 513 between the second control line 59 and the second wire guide 53. Figure 6 As shown, one end of the thread reverse tension spring 513 is connected to the second control line 59 and the other end is connected to the outer wall of the second guide member 53. The thread reverse tension spring 513 is stretched to a certain extent (but not completely stretched) to keep the second control line 59 in a tensioned state.

[0035] Therefore, under the above-mentioned wire control system, the control lines will not be entangled, so as to avoid affecting the normal launch process of the UAV. Since each wire control mechanism 5 controls the launch of two groups of UAVs, when assembling the UAV to the UAV carrying mechanism 4, only one operator needs to first pull open one of the first control lines 58, assemble the aircraft lock 6 to the spring latch assembly 56, and then assemble the aircraft lock 6 of another UAV. During this process, the above-mentioned wire control system is in a tensioned state and will not fail; there is no need for two people to operate at the same time, which reduces the allocation of personnel and improves the assembly efficiency of the UAV.

[0036] In a further embodiment, in order to reduce the pulling force required by the driving member 57 to pull the fourth control line 411, the following components are further provided in the wire control mechanism 5: a fourth guide member 54, a movable guide member 514, and a fifth control line 512. The fourth guide member 54 is a pulley assembly, and the movable guide member 514 is a movable pulley assembly.

[0037] like Figure 6 As shown, the fourth guide member 54 is a mirror image of the second guide member 53 and is disposed on the reinforcing beam 22. One side wall of the movable guide member 514 is connected to the other end of the fourth control line 511. One end of the fifth control line 512 is connected to the output end of the driving member 57, and the other end sequentially bypasses the movable guide member 514, the fourth guide member 54, and finally connects to the outer wall of the movable guide member 514.

[0038] In the above technical solution, by providing a movable pulley assembly and utilizing the labor-saving principle of the movable pulley assembly, the pulling force requirement is reduced, thereby achieving labor saving.

[0039] In a further embodiment, Figure 7 As shown, the spring latch assembly 56 includes: a first housing, a second housing, a spring pin 561, and a return spring 562. The first housing and the second housing (not shown) are mounted on the side wall of the lifting arm 31. Figure 7 As shown in the orientation in (b), the first housing is located on the right and the second housing is located on the left. A cavity is provided in each of the first housing and the second housing. One end of the spring pin 561 is connected to the first control line 58 and the other end extends through the cavity into the second housing. The spring pin 561 is slidably connected to the first housing and the second housing. The reset spring 562 is provided in the first housing and is sleeved on the spring pin 561. The elasticity of the reset spring 562 is greater than the line reverse tension spring 513.

[0040] A limit plate is provided on the spring pin 561 so that when the spring pin 561 is stretched by an external force, the return spring 562 is compressed; when there is no external force, the return spring 562 restores its original length and drives the spring pin 561 to return to its original length.

[0041] In the above technical solution, when there is no external force, Figure 7As shown in (b), the aircraft lock 6 is sleeved on the spring pin 561. The aircraft lock 6 is connected to the drone, and the spring pin assembly 56 serves to limit the position of the drone. Under the action of external force, the first control line 58 is pulled to drive the spring pin 561 to move out of the second housing, release the aircraft lock 6, and launch the drone.

[0042] In a further embodiment, Figure 3 and Figure 4 As shown, the launch angle adjustment mechanism 3 also includes: a screw transmission assembly 32, a slider 33, a lifting connection member 34, and a locking assembly. The screw transmission assembly 32 is installed on the support beam 1 and is located below the head end of the lifting arm 31. The slider 33 is in transmission connection with the screw transmission assembly 32. One end of the lifting connection member 34 is rotatably connected to the slider 33 (such as hinged) and the other end is connected to the head end of the lifting arm 31 (such as abutment or hinged). The locking assembly is connected to the screw transmission assembly; the locking assembly is used to position the screw transmission assembly.

[0043] In the above technical solution, the screw transmission assembly 32 rotates to drive the slider 33 to move, and then drives the lifting connection 34 to move, thereby realizing the lifting and lowering of the lifting arm 31, or adjusting the angle of the lifting arm 31, thereby adjusting the launch angle of the drone.

[0044] In a further embodiment, Figure 3 and Figure 5 As shown, the screw drive assembly 32 includes: two sets of mounting blocks 321, a screw 322, and a rocker 323. The two sets of mounting blocks 321 are arranged on the support beam 1. Both ends of the screw 322 are rotatably connected to the mounting blocks 321. One end of the screw 322 penetrates the mounting block 321 and extends outward. The rocker 323 is connected to one end of the screw 322 (the end of the screw 322 that penetrates the mounting block 321).

[0045] The locking assembly includes a locking block 324 and a locking handle 325. The locking block 324 is located between the rocker 323 and the mounting block 321, and the locking block 324 is fixed on the mounting block 321. The locking block 324 is sleeved on the outside of the screw rod 322. The locking handle 325 is connected to the locking block 324. Through the cooperation between the locking handle 325 and the locking block 324, the screw rod 322 is positioned and the screw rod 322 is prevented from rotating without the action of external force. The cooperation between the locking handle 325 and the locking block 324 is as follows: the locking handle 325 is a rotatable handle and a threaded column is connected below the handle, and the threaded column is threadedly connected to the locking block 324; when locking, the locking handle 325 is rotated, and the threaded column will rotate and press the screw rod 322 downward, thereby achieving the positioning of the screw rod 322. In addition, in addition to the above structure, the locking assembly can also use a locking wrench to achieve the positioning of the screw rod 322, which is a prior art and will not be described in detail here.

[0046] In the above technical solution, during the launch of the drone, if the launch angle needs to be adjusted, the crank 323 is manually rotated to drive the screw rod 322 to rotate, thereby achieving angle adjustment; after the angle adjustment is completed, the locking handle 325 is rotated to position the screw rod 322 and keep the launch angle unchanged.

[0047] By manually turning the rocker 323 and the locking handle 325, the user can easily adjust and fix the launch angle of the drone without the need for complex mechanical structures or electronic equipment, which reduces the difficulty and cost of operation. Manual operation has the characteristics of fast response. The user can quickly adjust the launch angle as needed and lock it immediately after the adjustment is completed, which improves the flexibility and efficiency of operation.

[0048] The mechanical structure of manually rotating the rocker 323 and the locking handle 325 is relatively simple and stable, and is not easily disturbed or damaged by the external environment, thereby improving the reliability and durability of the system. Compared with complex electronic equipment, the manually operated mechanical structure has a lower failure rate, reducing the risk of launch failure or accidents caused by equipment failure.

[0049] In addition, the above technical solution can adapt to different launch scenarios and conditions, such as outdoor, indoor, complex terrain, etc., and only needs manual adjustment to meet different launch requirements; it can be compatible with various types and specifications of drones, and only needs to adjust the stroke and locking force of the screw 322 according to the size and weight of the drone.

[0050] In a further embodiment, Figure 1 and Figure 2 As shown, the UAV carrying mechanism 4 includes: a first adjusting block 41 , a second adjusting block 42 , two groups of UAV fixing blocks 43 , a UAV tail stopper 44 , and a plurality of groups of supporting blocks 45 .

[0051] The first adjusting block 41 and the second adjusting block 42 are respectively mounted on the head end and the tail end of the lifting arm 31. Two sets of drone fixing blocks 43 are respectively mounted on the first adjusting block 41 and the second adjusting block 42. The drone tail stopper 44 is mounted behind the second adjusting block 42.

[0052] A plurality of support blocks 45 are mounted on the lifting arm 31 and connected to the first adjustment block 41 or the second adjustment block 42. The support blocks 45 are used to improve the stability of the entire UAV carrying mechanism 4.

[0053] In the above technical solution, before the drone is launched, the lifting arm 31 is set to an upwardly tilted state, the drone is placed in the drone fixing block 43, and the tail of the drone abuts against the drone tail block 44. The upwardly tilted drone fixing block 43 provides a stable support platform for the drone, ensuring the stability and accuracy of the drone before launching. The abutment of the drone tail block 44 further fixes the position of the drone to prevent launch failure caused by position offset during the launch process. The setting of the drone tail block 44 can also prevent the tail of the drone from swinging due to wind or other factors during the launch process, thereby avoiding collision with surrounding objects.

[0054] Placing the drone in the tilted drone fixing block 43 and fixing it with the drone tail block 44 simplifies the preparation work before launching. Just make sure that the drone is properly placed and fixed before the subsequent launch operation. The design of the tilted positioning block and the tail block 44 helps to quickly locate the drone and reduce the preparation time before launching. This can improve the launch efficiency, especially in emergency situations, and can respond and complete the mission more quickly.

[0055] In a further embodiment, Figure 7 As shown, the launcher also includes: an angle pointer 7 and an angle ruler 8. The angle pointer 7 is installed on the tail of the lifting arm 31. The angle ruler 8 is installed below the angle pointer 7.

[0056] In the above technical solution, when adjusting the angle of the lifting arm 31, the lifting arm 31 drives the angle pointer 7, and the angle of rotation of the angle pointer 7 is read by the angle ruler 8, thereby obtaining the launch angle of the UAV. In the scenario where the launch mission is for multiple UAVs to have the same launch angle, the launch angles of the multiple UAVs can be made the same by setting the readings of the multiple angle rulers 8 to be the same.

[0057] Example 2 This embodiment provides a method for using a UAV vehicle-mounted launcher as described in Embodiment 1, comprising the following steps: Step 1, assembling drones: When assembling drones on each set of drone carrying mechanisms 4, pull the first control line 58 adjacent to the drone carrying mechanism 4 to release the assembly space in the spring latch assembly 56; place the drone in the drone carrying mechanism 4, and after the aircraft locking fastener 6 is placed in the assembly space, stop pulling the first control line 58; repeat the above operation to place N sets of drones on N sets of drone carrying mechanisms 4 respectively; Step 2: Adjust the launch angle: Based on the launch requirement, adjust the angle of each group of lifting arms 31 so that the launch angle of each group of UAVs meets the launch requirement; Step 3, control the drone to take off: select the working mode of the wire control mechanism 5 as manual mechanical mode or wireless remote control mode; in the manual mechanical mode, manually pull the third control line 510, and then the third control line 510 drives the wire connection member 51 and the first control line 58 connected to the wire connection member, and then drives the movable parts in the spring latch assembly 56 and releases the aircraft lock buckle 6 on the spring latch assembly 56, so that the drone takes off; Or, in the wireless remote control mode, the control driving member drives the fourth control line 511 to move close to the driving member, and drives the line connector 51 and the first control line 58 connected to the line connector to move, thereby driving the movable parts in the spring latch assembly 56 and releasing the aircraft locking member 6 on the spring latch assembly 56 to complete the take-off of the drone.

Claims

1. A vehicle-mounted launcher for an unmanned aerial vehicle, characterized in that: include: N groups of support beams are arranged in an array; wherein N is an integer greater than 1; and frame assemblies are arranged between adjacent support beams; N groups of emission angle adjustment mechanisms are respectively arranged on each group of support beams; the emission angle adjustment mechanism comprises at least a lifting arm having a head end and a tail end; the tail end of the lifting arm is rotatably connected to the support beam; The same number of drone carrying mechanisms as the launch angle adjustment mechanisms are respectively arranged on each set of lifting arms; The wire control mechanism is arranged between adjacent UAV carrying mechanisms; each group of wire control mechanisms is used to control the take-off of two groups of UAVs at the same time; the wire control mechanism includes the following working modes: manual mechanical mode and wireless remote control mode.

2. The UAV vehicle-mounted launcher as claimed in claim 1, characterized in that: The wire control mechanism comprises: A thread connection member is disposed above the frame assembly; Two sets of first guide members are respectively and correspondingly arranged on the side walls of the tails of the two sets of lifting arms; A second guide member is provided on the frame assembly; a third guide member, disposed on the frame assembly close to the second guide member; Two sets of spring latch assemblies are respectively arranged on two sets of lifting arms; An aircraft lock catch connected to the spring latch assembly; A driving member, disposed on the frame assembly; Two groups of first control lines are symmetrically arranged; one end of the first control line is connected to the line connector and the other end bypasses the first guide and is connected to the spring latch assembly; A second control line, one end of which is connected to the line connector and the other end of which is elastically connected to the outer wall of the second guide member; A third control line, one end of which is connected to the line connector and the other end of which passes around the third guide and extends downward; A fourth control line has one end connected to the line connector and the other end bypassing the second guide member; the other end of the fourth control line is connected to the output end of the drive member.

3. The UAV vehicle-mounted launcher as claimed in claim 2, characterized in that: The wire control mechanism also includes: a fourth guide member, mirroring the second guide member and disposed on the frame assembly; a movable guide connected to the other end of the fourth control line; A fifth control line has one end connected to the output end of the driving member and the other end bypasses the moving guide member and the fourth guide member in sequence and is connected to the outer wall of the moving guide member.

4. The UAV vehicle-mounted launcher as claimed in claim 2, characterized in that: The wire control mechanism also includes: A wire reverse tension spring has one end connected to the second control wire and the other end connected to the outer wall of the second guide member.

5. The UAV vehicle-mounted launcher as claimed in claim 4, characterized in that: The spring latch assembly comprises: A first shell and a second shell are successively on the lifting arm; A spring pin, one end of which is connected to the first control line and the other end of which sequentially passes through the first housing and extends into the second housing; A return spring is arranged in the first housing and sleeved on the spring pin.

6. The UAV vehicle-mounted launcher as claimed in claim 5, characterized in that: Also includes: The aircraft lock buckle is an aircraft lock buckle sleeve; The aircraft locking fastener is used to connect the drone; Before the UAV flies, the aircraft lock member aircraft lock sleeve is located between the first shell and the second shell and is sleeved on the spring pin and is limited by the spring latch assembly.

7. The UAV vehicle-mounted launcher as claimed in claim 1, characterized in that: The frame assembly comprises: At least two groups of connecting beams, vertically connected to the supporting beams; The reinforcing beam is parallel to the supporting beam and connected to the connecting beam.

8. The UAV vehicle-mounted launcher as claimed in claim 1, characterized in that: The emission angle adjustment mechanism also includes: A screw drive assembly is disposed on the support beam and below the head end of the lifting arm; A slider, drivingly connected to the screw rod rotating assembly; A lifting connecting member, one end of which is rotatably connected to the slider and the other end of which is connected to the head end of the lifting arm; The locking assembly is connected to the screw transmission assembly; the locking assembly is used to position the screw transmission assembly.

9. The UAV vehicle-mounted launcher as claimed in claim 1, characterized in that: The UAV carrying mechanism comprises: A first adjusting block and a second adjusting block are respectively arranged at the head end and the tail end of the lifting arm; Two sets of drone fixing blocks are respectively arranged on the first adjusting block and the second adjusting block; The tail block of the UAV is arranged behind the second adjusting block; A plurality of support blocks are arranged on the lifting arm and connected to the first adjusting block or the second adjusting block.

10. A method for using a vehicle-mounted launcher for a UAV according to any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1, assembling the drone: when assembling the drone on each set of drone carrying mechanisms, pull the first control line adjacent to the drone carrying mechanism to release the assembly space in the spring latch assembly; place the drone in the drone carrying mechanism, and after placing the aircraft lock fastener in the assembly space, stop pulling the first control line; repeat the above operation to place N sets of drones on N sets of drone carrying mechanisms respectively; Step 2: Adjust the launch angle: Based on the launch requirements, adjust the angle of each set of lifting arms so that the launch angle of each set of drones meets the launch requirements; Step 3, control the drone to take off: select the working mode of the wire control mechanism as manual mechanical mode or wireless remote control mode; in the manual mechanical mode, manually pull the third control line, and then the third control line drives the wire connection piece and the first control line connected to the wire connection piece, and then drives the movable part in the spring latch assembly and releases the aircraft lock buckle on the spring latch assembly to complete the drone take-off; Or, in the wireless remote control mode, the control driving member drives the fourth control line to move close to the driving member, and drives the line connecting member and the first control line connected to the line connecting member to move, thereby driving the movable parts in the spring latch assembly and releasing the aircraft lock fastener on the spring latch assembly to complete the take-off of the drone.

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