A lightweight unmanned aerial vehicle weapon system

Abstract

The application discloses a light unmanned aerial vehicle weapon equipment, which comprises an unmanned aerial vehicle and a weapon station, wherein the unmanned aerial vehicle is provided with a square cavity-shaped suspension rack used for suspending the weapon station. The rotor yoke frame of the unmanned aerial vehicle adopts a square frame structure, and the arm adopts a cable-stayed mode, so that the height of the unmanned aerial vehicle is reduced, and the stability of the unmanned aerial vehicle during flight is enhanced. In addition, the arm, the rotor yoke frame and the upper shell are connected into an integrated structure through welding, so that the safety performance of the unmanned aerial vehicle is improved, and the unmanned aerial vehicle is simple to install, disassemble and maintain and high in efficiency. The weapon station changes the arrangement mode of the power mechanism and the photoelectric module of the driven launching cabin, and the power mechanism and the photoelectric module of the launching cabin are changed from the previous longitudinal arrangement mode into a transverse arrangement mode, so that the height of the weapon station is reduced, the stability of the weapon station during flight is improved, and the weapon station is provided with a power mechanism used for driving the rotation of the suspension rack, so that the whole weapon station can rotate in the horizontal direction, and the flexibility of the weapon station is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of weapon equipment, in particular to a light unmanned aerial vehicle weapon equipment. BACKGROUND

[0002] With the rapid development of modern military technology, unmanned weapon equipment frequently appears on modern battlefield, and weapon equipment unmanned has become a development trend.

[0003] At present, the unmanned aerial vehicle can carry a weapon station, since the weapon station is mounted on the unmanned aerial vehicle, the weapon station is easily affected by the unmanned aerial vehicle movement, body vibration and the like, resulting in the risk of instability of the unmanned aerial vehicle weapon equipment in the flight process. In addition, due to the design defects of the unmanned aerial vehicle weapon equipment, the flexibility of the weapon station is poor, thereby affecting the accuracy of the rocket projectile. SUMMARY

[0004] In order to solve the above problems existing in the prior art, the present application provides a light unmanned aerial vehicle weapon equipment, which has simple structure, light weight, good stability in flight process, and good flexibility of the weapon station, thereby making the accuracy of the rocket projectile high.

[0005] The technical scheme adopted to achieve the above-mentioned purpose of the present application is as follows:

[0006] A light unmanned aerial vehicle weapon equipment, comprising an unmanned aerial vehicle and a weapon station, the unmanned aerial vehicle comprising a fuselage, a rotor yoke, rotors and arms, the rotor yoke being a square frame, the rotors being four, the four rotors being respectively installed on four corners of the rotor yoke, the fuselage being located in the center of the rotor yoke, the arms being four, the four arms being obliquely arranged, one end of each of the four arms being connected with the four corners of the rotor yoke, the other end of each of the four arms being connected with the fuselage.

[0007] The weapon station comprises a frame, a launch cabin, a horizontal rotation mechanism, a vertical rotation mechanism and an optical-electric mechanism, the two launch cabins being symmetrically distributed on both sides of the frame, the vertical rotation mechanism and the optical-electric mechanism being distributed side by side along the length direction of the launch cabin, the horizontal rotation mechanism being located between the vertical rotation mechanism and the optical-electric mechanism, the fixed part of the horizontal rotation mechanism being carried on the bottom of the fuselage, the rotating part of the horizontal rotation mechanism being fixedly connected with the frame, the horizontal rotation mechanism being capable of driving the frame to rotate, the vertical rotation mechanism being respectively installed on the frame, the vertical rotation mechanism being respectively connected with the two launch cabins, the vertical rotation mechanism driving the two launch cabins to rotate synchronously, the optical-electric mechanism comprising an optical-electric module and an optical-electric power mechanism, the optical-electric power mechanism being installed on the frame, and the optical-electric power mechanism driving the optical-electric module to rotate.

[0008] The rotor yoke comprises four connecting rods and four motor seats, the four motor seats are distributed in a square shape, the four connecting rods are distributed on four sides of the same square, each connecting rod is located between two adjacent motor seats, and the two ends of each connecting rod are connected with the two adjacent motor seats respectively, and the rotor comprises a rotor motor and a propeller, and the motor is fixed on the corresponding motor seat.

[0009] The motor seat is annular, a plurality of through holes are uniformly distributed on the circumferential direction of the motor seat, the rotor motor is in a cylindrical shape, the propeller is installed on the upper end surface of the rotor motor, a plurality of threaded holes are uniformly distributed on the lower end surface of the rotor motor in the circumferential direction, the lower end surface of the rotor motor is located on the upper end surface of the motor seat, and the rotor motor is fixed on the motor seat by screws.

[0010] The upper end surface of the motor seat is inclined, the height of the side of the motor seat facing the fuselage is higher than the height of the side of the motor seat away from the fuselage, and the inclination angle of the upper end surface of the motor seat is the same as the inclination angle of the arm.

[0011] The arm comprises two symmetrical inclined pull rods, the two inclined pull rods are distributed in an eight-shaped manner, the ends of the two inclined pull rods close to each other are respectively connected to the upper part of the fuselage symmetrically, the ends of the two inclined pull rods far away from each other are respectively connected to the sides of the two adjacent connecting rods close to each other symmetrically, the ends of the two inclined pull rods far away from each other are symmetrically distributed on both sides of the corresponding motor seat, and the ends of the two inclined pull rods far away from each other are respectively close to the corresponding motor seat.

[0012] The frame comprises a first side support plate, a second side support plate and a top support plate, and the top parts of the first side support plate and the second side support plate are respectively connected to the top support plate symmetrically.

[0013] The horizontal rotation mechanism comprises a first motor and a first transmission shaft, the first motor is installed on the top of the top support plate, the first transmission shaft penetrates the top support plate and the stator of the first motor in sequence, the first transmission shaft is rotatably connected with the top support plate, the first transmission shaft is fixedly connected with the stator of the first motor, and the upper end of the first transmission shaft is installed on the bottom of the fuselage.

[0014] The vertical rotation mechanism comprises a second motor and a second transmission shaft, the second transmission shaft is perpendicular to the length direction of the launching cartridge, the second motor is installed on one side of the first side support plate, one side of the second transmission shaft penetrates the first side support plate and the rotating shaft of the second motor in sequence, the second transmission shaft is fixedly connected with the rotating shaft of the second motor, the second transmission shaft is in clearance fit with the first side support plate, the other side of the second transmission shaft movably penetrates one side of the second side support plate, and the two ends of the second transmission shaft are fixedly connected with the inner side of the launching cartridge shell.

[0015] The photoelectric power mechanism includes a third motor, a first pin, and a second pin. The third motor is mounted on the other side of the first side support plate. The first pin and the second pin are symmetrically arranged on both sides of the photoelectric module. The inner ends of the first pin and the second pin are respectively connected to the photoelectric module. The outer end of the first pin passes through the rotating shaft of the third motor and is fixedly connected to the rotating shaft of the third motor. The outer side of the second pin moves through the second side support plate.

[0016] Compared with the prior art, the beneficial effects and advantages of the present invention are as follows:

[0017] 1. The UAV of the present invention is equipped with a square cavity-shaped suspension frame for suspending a weapon station. The weapon station is highly integrated with the UAV in terms of structure, which can effectively utilize the suspended weapon station to maintain the stability of the entire UAV during flight and operation.

[0018] 2. The rotor yoke of the UAV of the present invention adopts a square frame structure, and the arms adopt a diagonal pull method, which reduces the height of the UAV and enhances the stability of the UAV during flight.

[0019] 3. The drone of the present invention is lightweight, has strong endurance, and long flight time, which can meet the current work needs of the drone industry.

[0020] 4. The arms, rotor yoke, and upper shell of this invention are all made of lightweight aluminum, which not only reduces the weight of the UAV, but also avoids using screw-fixed joints at the connection points between the rotor yoke and the arms and the rotor yoke and upper shell. Instead, they are welded together to form an integrated structure, which not only improves the safety performance of the UAV, but also makes installation, disassembly and maintenance simple and efficient.

[0021] 5. The weapon station of this invention is equipped with a mounting platform, which facilitates the suspension of the weapon station on the UAV. Furthermore, the suspension can be secured using bolts, increasing the stability of the suspension.

[0022] 6. The weapon station of the present invention changes the arrangement of the power mechanism and optoelectronic module driving the launch chamber. The power mechanism and optoelectronic module of the launch chamber are changed from the previous longitudinal arrangement to a transverse arrangement, which reduces the height of the weapon station and improves the stability of the weapon station when it is loaded and in flight.

[0023] 7. The weapon station of the present invention is equipped with a power mechanism that drives the mounting platform to rotate horizontally, so that the entire weapon station can rotate horizontally, increasing the flexibility of the weapon station and thus improving the accuracy of rocket launch. Attached Figure Description

[0024] Figure 1 This is a structural diagram of a lightweight unmanned aerial vehicle (UAV) weapon system.

[0025] Figure 2 for Figure 1 The main view.

[0026] Figure 3 This is a schematic diagram of the structure of a drone.

[0027] Figure 4 for Figure 3 The main view.

[0028] Figure 5 for Figure 4 Sectional view along line AA.

[0029] Figure 6 for Figure 5 A magnified view of part I.

[0030] Figure 7 for Figure 3 Top view.

[0031] Figure 8 for Figure 3 A bottom view.

[0032] Figure 9 This is a structural diagram of a weapons station.

[0033] Figure 10 for Figure 9 The main view.

[0034] Figure 11 for Figure 9 Sectional view along line AA.

[0035] Figure 12 for Figure 9 Sectional view along the BB direction.

[0036] Figure 13 for Figure 9 EE sectional view

[0037] Figure 14 for Figure 9 Top view.

[0038] Figure 15 for Figure 9 The right view.

[0039] Among them, 1-rotor motor, 2-propeller, 3-connecting rod, 4-motor mount, 5-reinforcing clip, 6-diagonal tie rod, 7-upper shell, 8-lower shell, 9-battery cavity, 10-landing strut, 11-connecting sleeve, 12-mounting platform, 13-connecting frame, 14-mounting hole, 15-power supply battery, 16-launching magazine, 17-first side support plate, 18-second side support plate, 19-top support plate, 20-lower support plate, 21-bottom support. Plate, 22-First motor, 25-First motor mount, 24-First drive shaft, 25-First encoder, 26-Connecting ring, 27-Upper suspension plate, 28-Intermediate support sleeve, 29-Lower suspension plate, 30-Second motor, 31-Second drive shaft, 32-Second motor mount, 33-Second encoder, 34-Photoelectric module, 35-Third motor, 36-Third encoder, 37-First pin, 38-Protective cover, 39-Second pin. Detailed Implementation

[0040] The present invention will now be described in detail with reference to the accompanying drawings.

[0041] The structure of the lightweight unmanned aerial vehicle weapon system provided in this embodiment is as follows: Figures 1-2 As shown, the weapon system has a symmetrical structure, and the drone is mounted on a drone weapon station.

[0042] like Figure 3 , Figure 4 , Figure 7 and Figure 8 As shown, the UAV has a symmetrical structure and includes a rotor, rotor yoke, fuselage, arms, landing support, power supply battery 15, and mounting platform 12.

[0043] like Figures 7-8 As shown, the rotor yoke is a near-square frame, comprising four connecting rods 3 and four motor mounts 4. Both the connecting rods 3 and motor mounts 4 are made of lightweight aluminum. The four motor mounts 4 are arranged in a square, with the four connecting rods 3 distributed along the four sides of the same square. Each connecting rod 3 is located between two adjacent motor mounts 4, and both ends of each connecting rod 3 are welded to the corresponding two adjacent motor mounts 4. The connecting rod 3 has a U-shaped cross-section with its opening facing downwards. Reinforcing clips 5 are symmetrically positioned on both sides of the bottom of the connecting rod 3. The reinforcing clips 5 are U-shaped, with their sides respectively clamping the bottom of the connecting rod 3 at corresponding positions. The middle part of the reinforcing clip is pressed against the bottom of the diagonal tie rod at the corresponding position. Making the connecting rods hollow internally reduces the weight of the rotor yoke, thereby further reducing the weight of the UAV and facilitating stable flight. Additionally, the U-shaped cavity of the connecting rod 3 facilitates the routing of motor connection cables, simplifying the installation and fixing of the motor connection cables.

[0044] The motor mount 4 is annular, and has a series of through holes evenly distributed along its circumference. The upper surface of the motor mount 4 is inclined, and the height of the side of the motor mount 4 facing the center of the rotor yoke is higher than the height of the side of the motor mount 4 facing away from the center of the rotor yoke. The rotor includes a rotor motor 1 and a propeller 2. The rotor motor 1 is nearly cylindrical, and the propeller 2 is mounted on the upper surface of the rotor motor 1. The lower surface of the rotor motor 1 has four threaded holes evenly distributed along its circumference. The lower surface of the rotor motor 1 is located on the upper surface of the motor mount 4, and the rotor motor 1 is fixed to the motor mount 4 with screws.

[0045] The fuselage is located in the center of the rotor yoke. The fuselage consists of an upper shell 7 and a lower shell 8, with the upper shell 7 made of lightweight aluminum. Both the upper shell 7 and the lower shell 8 have cylindrical external contours, and their side walls are fastened together. The lower shell 8 contains cavities for installing electrical components, such as circuit boards.

[0046] The machine arm has four sections, each including two symmetrically distributed diagonal braces 6. The tilt angle of the diagonal braces 6 is the same as the tilt angle of the upper surface of the motor base 4, and the two diagonal braces 6 are arranged in a V-shape. The diagonal braces 6 are made of lightweight aluminum. The ends of the two diagonal braces 6 that are closer together are symmetrically welded to the outer wall of the upper housing 7, and the ends of the two diagonal braces 6 that are farther apart are symmetrically welded to the sides of the two adjacent connecting rods 3 that are close to each other. The ends of the two diagonal braces 6 that are farther apart are symmetrically distributed on both sides of the corresponding motor base 4, and the ends of the two diagonal braces 6 that are farther apart are close to the corresponding motor base 4.

[0047] The cross-section of the diagonal brace 6 is U-shaped, with the opening facing downwards. A reinforcing clip is located at the bottom center of the diagonal brace 6. The reinforcing clip 5 is also U-shaped, with its two sides respectively clamping the bottom of the diagonal brace 6, and its center pressing against the bottom of the diagonal brace 6. Designing the diagonal brace 6 as hollow internally reduces the weight of the arm, thereby further reducing the weight of the drone and facilitating stable flight. Additionally, the U-shaped cavity of the diagonal brace 6 facilitates the routing of motor connection cables, simplifying their installation and securing.

[0048] like Figure 5 As shown, the mounting platform 12 is a square cavity. A connecting frame 13, also square, is located at the top of the mounting platform 12. The inner wall of the connecting frame is fitted to the top of the side wall of the mounting platform 12. A first through hole for the mounting platform to pass through is opened at the bottom of the upper housing 7, and a second through hole for the mounting platform to pass through is opened at the bottom of the lower housing 8. The mounting platform 12 passes through the first through hole 3 and the second through hole in sequence. The connecting frame 13 is fitted to the top surface of the upper housing 7 and is fixedly connected to the top of the upper housing 7 by screws. The bottom of the lower housing 8 is fastened to the bottom of the mounting platform 12.

[0049] like Figure 6As shown, the mounting platform 12 has an opening at the top, through which the power supply battery 15 passes. The edge of the power supply battery 15 is fitted to the connecting frame 13, and the power supply battery 15 is fastened to the mounting platform 12. The mounting platform 12 has a mounting hole 14 at the bottom, which can be used to suspend various weapon stations.

[0050] There are four landing support components, including a landing strut 10 and a connecting sleeve 11. Both the connecting sleeve 11 and the landing strut 10 are hollow, which reduces the weight of the drone. The connecting sleeve 11 is conical, with external threads on the outer wall of its large end and internal threads on its small end. The inner wall of the motor mount 4 has internal threads, and the large end of the connecting sleeve 11 is threaded to the motor mount 4. The upper end of the landing strut 10 has external threads, and the landing strut 10 is threaded to the small end of the connecting sleeve 11. When the drone lands, the landing strut 10 can be easily inserted into the insertion hole of the landing platform, which is beneficial to the stable landing of the drone.

[0051] like Figure 9 , Figure 10 , Figure 14 and Figure 15 As shown, the weapon station includes a frame, a missile launcher 16, an optoelectronic mechanism, a suspension frame, a horizontal rotation mechanism, and a vertical rotation mechanism.

[0052] like Figures 12-13 As shown, the frame includes a first side support plate 17, a second side support plate 18, a top support plate 19, a lower support plate 20, a bottom support plate 21, a front cover plate, and a rear cover plate. The two side edges of the top support plate 19 are connected to the tops of the first side support plate 17 and the second side support plate 18, respectively. The two side edges of the bottom support plate 21 are connected to the bottoms of the first side support plate 17 and the second side support plate 18, respectively. The rear cover plate is fixed to the rear ends of the first side support plate 17 and the second side support plate 18, respectively. The front cover plate is located between the first side support plate 17 and the second side support plate 18, and is fixedly connected to the bottom support plate 21 and the top support plate 19, respectively. The first side support plate 17, the second side support plate 18, the top support plate 19, the bottom support plate 21, the front cover plate, and the rear cover plate constitute a sealed space. The top support plate 19, the lower support plate 20 and the bottom support plate 21 are parallel to each other. The lower support plate 20 is located between the top support plate 19 and the bottom support plate 21. The two sides of the lower support plate 20 are connected to the first side support plate 17 and the second side support plate 18, respectively.

[0053] The missile launch bay 16 includes an outer shell and two missile tubes, which are installed inside the outer shell and have their length parallel to the front-to-back direction.

[0054] like Figure 12As shown, the horizontal rotation mechanism includes a first motor 22, a first motor mount 23, a first drive shaft 24, and a first encoder 25. The first motor mount 23 (the portion above the top support plate is not shown) is fixed to the top support plate 19. The rotor of the first motor 22 is mounted on the first motor mount 23. The first motor mount 23 is a metal plate that reinforces the top support plate 19. The first drive shaft 24 passes sequentially through the central hole of the first motor mount 23, the top support plate 19, and the stator of the first motor 22. The diameter of the first drive shaft 24 is smaller than the diameter of the central hole of the first motor mount 23. The first drive shaft 24 is connected to the top support plate 19 via bearings, and the first drive shaft 24 and the stator of the first motor 22 are fixedly connected. The first drive shaft 24 is thicker at the top and thinner at the bottom. A connecting ring 26 is provided at the upper end of the first drive shaft 24. The inner wall of the connecting ring 26 is fitted against the top of the outer wall of the first drive shaft 24, forming a T-shaped structure with the connecting ring 26. The first encoder 25 is sleeved on the lower end of the first drive shaft 246 and is located within the enclosed space. The first encoder 25 is similar to a bearing structure, with its inner ring fixedly connected to the first drive shaft 24 and its outer ring fixedly connected to the top support plate 19.

[0055] The suspension frame has a symmetrical structure and includes an upper suspension plate 27, a lower suspension plate 29, and an intermediate support sleeve 28. Both the upper and lower suspension plates 27 and 29 are disc-shaped. The upper suspension plate 27 has multiple threaded holes evenly distributed along its circumference. The upper suspension plate 27 is fixedly connected to the upper end face of the intermediate support sleeve 28. The lower suspension plate 29 is located inside the intermediate support sleeve 28, close to its lower end face, and is fixedly connected to the inner wall of the intermediate support sleeve 28. A connecting ring 26 is located below the lower suspension plate 29, with its upper part inside the intermediate support sleeve 28. The bottom surface of the lower suspension plate 29 is in contact with the connecting ring 26, and the lower suspension plate 29 and the connecting ring 26 are fixed together by screws.

[0056] like Figure 13 As shown, the vertical rotation mechanism includes a second motor 30, a second drive shaft 31, a second motor mount 32, and a second encoder 33. The second motor mount 32 is U-shaped, with its opening facing the second side support plate 18. The top of the second motor mount 32 is attached to the bottom surface of the top support plate 19, and the top of the second motor mount 32 is fixedly connected to the top support plate 19 by screws. The bottom of the second motor mount 32 is attached to the top surface of the lower support plate 20, and the bottom of the second motor mount 32 is fixedly connected to the lower support plate 20 by screws. The vertical portion in the middle of the second motor mount 32 is attached to the inner wall of one side of the first side support plate 17, and the second motor mount 32 is fixedly connected to the first side support plate 17 by screws. A first mounting hole for mounting the second motor 30 is provided on one side of the first side support plate 17. The second motor 30 passes through the first mounting hole and is fixed to the outer wall of the second motor mount 32.

[0057] The second drive shaft 31 is perpendicular to the length of the missile tube inside the launch bay 16. One side of the second drive shaft 31 passes through the rotating shafts of the second motor base 32 and the second motor 30 in sequence, and the second drive shaft 31 is fixedly connected to the rotating shaft of the second motor 30. The second drive shaft 31 and the second motor base 32 are clearance-fitted. The other side of the second drive shaft 31 passes through one side of the second side support plate 18, and the second drive shaft 31 is connected to the second side support plate 18 through a bearing. Both ends of the second drive shaft 31 are fixedly connected to the inner side of the outer shell of the launch bay 16. When the second motor 30 is working, the second motor 30 drives the second drive shaft 31 to rotate, and the second drive shaft 31 drives the two launch bays 16 to rotate, so that the launch bays 16 can launch rockets 360 degrees in the vertical direction. The second encoder 33 can measure the rotation angle of the launch bays 16 in real time.

[0058] like Figure 11 As shown, the photoelectric mechanism includes a photoelectric module 34 and a photoelectric power mechanism. The photoelectric module 34 is located between the first side support plate 17 and the second side support plate 18, and is positioned directly in front of the enclosed space. The photoelectric power mechanism includes a third motor 35, a third motor mount, a third encoder 36, a first pin 37, and a second pin. The third motor mount is plate-shaped and fits against the inner wall of the other side of the first side support plate 17. The third motor mount is fixedly connected to the first side support plate 19 by screws. A second mounting hole for mounting the third motor 35 is provided on the other side of the first side support plate 19. The third motor 35 passes through the second mounting hole and is fixed to the outer wall of the third motor mount.

[0059] The first pin 37 and the second pin 39 are symmetrically arranged on both sides of the photoelectric module 34. The inner ends of the first pin 37 and the second pin 39 are respectively connected to the photoelectric module 34. The outer end of the first pin 37 passes through the shaft of the third motor mount and the third motor 35 in sequence. The first pin 37 is clearance-fitted with the third motor mount, and the outer end of the first pin 37 is fixedly connected to the shaft of the third motor 35. The outer end of the second pin 39 passes through the second side support plate 18. The second pin 39 is connected to the second side support plate 18 through a bearing. The third encoder 36 is sleeved on the outer end of the second pin 39 and is located outside the second side support plate 18. When the third motor 35 is working, the third motor 35 drives the first pin 37 to rotate, and the first pin 37 drives the photoelectric module 34 to rotate, so that the photoelectric module 34 can rotate 360 ​​degrees in the vertical direction. The third encoder 36 can measure the rotation angle of the photoelectric module 34 in real time.

[0060] The first side support plate 17 and the second side support plate 18 are symmetrically provided with protective covers 38. The second motor 30 and the third motor 35 are located in the space enclosed by one of the protective covers 38 and the first side support plate 17. The second encoder 33 and the third encoder 36 are located in the space enclosed by the other protective cover 38 and the second side support plate 18, thereby protecting the electrical components, motors and encoders.

[0061] The upper suspension plate 27 is attached to the bottom of the mounting platform 12 and is fixedly connected to the mounting platform 12 by six screws. Through the cooperation of the suspension plate and the mounting platform 12, the weapon station is mounted on the UAV, and rockets are precisely launched by controlling the UAV and the weapon station.

Claims

1. A lightweight unmanned aerial vehicle (UAV) weapon system, characterized in that: The system includes a drone and a weapon station. The drone includes a fuselage, a rotor yoke, rotors, and arms. The rotor yoke is a roughly square frame. There are four rotors, which are respectively installed at the four corners of the rotor yoke. The fuselage is located in the center of the rotor yoke. There are four arms, which are tilted. One end of each arm is connected to one of the four corners of the rotor yoke, and the other end of each arm is connected to the fuselage. The weapon station includes a frame, a missile launcher, a horizontal rotation mechanism, a vertical rotation mechanism, and an optoelectronic mechanism. The two missile launchers are symmetrically distributed on both sides of the frame. The vertical rotation mechanism and the optoelectronic mechanism are arranged side by side along the length of the missile tubes inside the missile launchers. The horizontal rotation mechanism is located between the vertical rotation mechanism and the optoelectronic mechanism. The fixed part of the horizontal rotation mechanism is mounted on the bottom of the fuselage, and the rotating part of the horizontal rotation mechanism is fixedly connected to the frame. The horizontal rotation mechanism can drive the frame to rotate. The vertical rotation mechanisms are respectively installed on the frame and are respectively connected to the two missile launchers. The vertical rotation mechanisms drive the two missile launchers to rotate synchronously. The optoelectronic mechanism includes an optoelectronic module and an optoelectronic power mechanism. The optoelectronic power mechanism is installed on the frame and drives the optoelectronic module to rotate.

2. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 1, characterized in that: The rotor yoke includes four connecting rods and four motor mounts. The four motor mounts are arranged in a square, and the four connecting rods are distributed on the four sides of the same square. Each connecting rod is located between two adjacent motor mounts, and the two ends of each connecting rod are connected to the two adjacent motor mounts respectively. The rotor includes a rotor motor and a propeller, and the motor is fixed on the corresponding motor mount.

3. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 2, characterized in that: The motor base is ring-shaped and has multiple through holes evenly distributed along the circumference. The rotor motor is cylindrical and the propeller is mounted on the upper end face of the rotor motor. The lower end face of the rotor motor has multiple threaded holes evenly distributed along the circumference. The lower end face of the rotor motor is located on the upper end face of the motor base, and the rotor motor is fixed to the motor base by screws.

4. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 3, characterized in that: The upper surface of the motor base is inclined, and the height of the side of the motor base facing the machine body is higher than the height of the side of the motor base facing away from the machine body. The inclination angle of the upper surface of the motor base is the same as the inclination angle of the machine arm.

5. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 1, characterized in that: The arm includes two symmetrically distributed diagonal braces arranged in a figure-eight pattern. The ends of the two diagonal braces that are closer together are symmetrically connected to the upper part of the arm body, and the ends of the two diagonal braces that are farther apart are symmetrically connected to the sides of two adjacent connecting rods that are close to each other. The ends of the two diagonal braces that are farther apart are symmetrically distributed on both sides of the corresponding motor base, and the ends of the two diagonal braces that are farther apart are close to the corresponding motor base.

6. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 1, characterized in that: The frame includes a first side support plate, a second side support plate, and a top support plate, with the tops of the first side support plate and the second side support plate symmetrically connected to the top support plate, respectively.

7. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 1, characterized in that: The horizontal rotation mechanism includes a first motor and a first drive shaft. The first motor is mounted on the top of the top support plate. The first drive shaft passes through the top support plate and the stator of the first motor in sequence. The first drive shaft is rotatably connected to the top support plate and fixedly connected to the stator of the first motor. The upper end of the first drive shaft is mounted on the bottom of the machine body.

8. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 1, characterized in that: The vertical rotation mechanism includes a second motor and a second drive shaft. The second drive shaft is perpendicular to the length direction of the missile tube inside the launch chamber. The second motor is mounted on one side of the first side support plate. One side of the second drive shaft passes through the first side support plate and the rotating shaft of the second motor in sequence. The second drive shaft is fixedly connected to the rotating shaft of the second motor. The second drive shaft is clearance-fitted with the first support side plate. The other side of the second drive shaft movably passes through one side of the second side support plate. Both ends of the second drive shaft are fixedly connected to the inner side of the launch chamber shell.

9. The lightweight unmanned aerial vehicle (UAV) weapon system according to claim 1, characterized in that: The photoelectric power mechanism includes a third motor, a first pin, and a second pin. The third motor is mounted on the other side of the first side support plate. The first pin and the second pin are symmetrically arranged on both sides of the photoelectric module. The inner ends of the first pin and the second pin are respectively connected to the photoelectric module. The outer end of the first pin passes through the rotating shaft of the third motor and is fixedly connected to the rotating shaft of the third motor. The outer side of the second pin moves through the second side support plate.

Images