Single-soldier launching system of folding quad-rotor unmanned aerial vehicle

Abstract

The utility model discloses a folding quad-rotor unmanned aerial vehicle individual soldier launching system, which comprises four shells (1), a base (2), an aircraft fixing seat (7) and a lock mechanism (8), the number of the shells (1) is four, the centers of the bottoms of the four shells (1) are rotatably connected with the four vertex angles of the base (2) respectively, the opening angle of the shells (1) relative to the base (2) is 0-90 degrees, the tops of the four shells (1) are locked through the lock mechanism (8), and the aircraft fixing seat (7) is connected with the aircraft fixing seat (7) through the lock mechanism (8). The aircraft fixing seat (7) is fixed to the center of the upper end of the base (2) and located in the space formed by the four shells (1), and the unmanned aerial vehicle (9) is installed on the aircraft fixing seat (7).

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicle launch, and in particular relates to a folding four-rotor unmanned aerial vehicle individual launch system. Background Art

[0002] In recent years, with the rapid development of drone technology, drone launch technology has also received attention and concern from everyone. However, there are many types of existing multi-rotor drone launch systems, most of which are powered elastic launch, which has a loud noise during the launch process, a heavy device, and is not easy to carry. Therefore, in response to the above needs, the utility model discloses a non-powered individual launch system that integrates carrying and launching. Utility Model Content

[0003] The utility model aims to solve the problems of the prior art and provides a foldable quad-rotor unmanned aerial vehicle individual launching system.

[0004] In order to solve the technical problem, the technical solution of the utility model is: a folding quad-rotor UAV individual launching system, comprising a shell, a base, an aircraft fixing seat and a locking mechanism, wherein there are four shells, and the bottom centers of the four shells are rotatably connected to the four top corners of the base respectively, and the opening angle of the shell relative to the base is 0 to 90°. The tops of the four shells are locked by a locking mechanism, and the aircraft fixing seat is fixed to the center of the upper end of the base and is in the space formed by the four shells, and the UAV is installed on the aircraft fixing seat.

[0005] Preferably, the shell includes a carbon tube, a baffle, a connecting ear, a motor blade clamp, a connecting rib and an upper connecting seat. There are two baffles, which are vertically connected. A carbon tube is arranged at the intersection of the two baffles. The top of the carbon tube is connected to the upper connecting seat. The upper connecting seats of the four shells are locked by a locking mechanism. The bottom of the carbon tube is rotatably connected to the top angle of the base. Connecting ribs are respectively arranged on the upper and lower sides of the baffle. The connecting ribs are connected to the carbon tube through the connecting ears. A motor blade clamp is arranged at the root of the shell, and the rotor arm motor and blades of the drone are clamped on the motor blade clamp.

[0006] Preferably, the carbon tube is a circular or square carbon tube.

[0007] Preferably, the base includes a lower base plate, side plates, an upper base plate, automatic folding tube clamps, support plate nuts and a first aluminum column. There are four automatic folding tube clamps, and the four top corners of the lower base plate and the upper base plate are respectively connected by automatic folding tube clamps. The rotatable ends of the automatic folding tube clamps are connected to the bottom of the carbon tube. A first aluminum column is arranged between the lower base plate and the upper base plate to increase rigidity. There are four side plates, and the side plates are respectively installed around the lower base plate and the upper base plate. The aircraft fixing seat is fixed to the center position of the upper end surface of the upper base plate by support plate nuts.

[0008] Preferably, the locking mechanism includes a servo, a second aluminum column, a servo rocker arm, a locking shaft and a servo pull rod. The locking mechanism is installed at the bottom of the upper connecting seat of any one of the shells. The servo is connected to the bottom of the upper connecting seat through the second aluminum column. The servo is connected to the servo rocker arm. The servo rocker arm is hinged to the servo pull rod. The servo pull rod is connected to the locking shaft. Lock holes are provided at the overlapping parts of the other three upper connecting seats. The servo is connected to an external remote control. The servo drives the servo rocker arm and the servo pull rod to control the locking shaft to move up and down in the locking holes of the other three upper connecting seats, thereby controlling the opening and closing of each shell.

[0009] Preferably, the automatic folding tube clamp has a torsion spring, which can make the shell open at an angle of 0 to 90 degrees. The two sides of the automatic folding tube clamp are respectively connected to the lower base plate and the upper base plate, and the middle rotatable end is connected to the bottom of the carbon tube. A guide support bar is installed at the bottom of the lower base plate.

[0010] Preferably, two adjacent shells are connected via a movable latch, and the movable latch is a ball pin.

[0011] Preferably, a cover is provided on the top of the four shells, and the cover is connected to each shell via a movable latch.

[0012] Preferably, two adjacent shells are also provided with shoulder straps, which are mounted on upper and lower connecting ears of the shells.

[0013] Preferably, the four shells open downward in a petal-like shape when unfolded, the UAV is installed on an aircraft fixing seat, and the rotor arm motor and blades of the UAV are clamped on the motor blade clamping plate. When stored, the four shells close upward to form a barrel-like structure with a rectangular or circular cross-section.

[0014] Compared with the prior art, the advantages of the utility model are:

[0015] (1) The utility model discloses a folding quad-rotor UAV single-soldier launching system. The UAV is placed in a space composed of four shells. The four shells are opened in a petal shape when unfolded and in a barrel-shaped structure when stored. The unfolding and storage are relatively convenient. The tops of the four shells are fixed by a locking mechanism. The locking mechanism is externally connected to a remote control for convenient control. The overall structure of the utility model is small in size, light in weight, and simple to deploy. It is convenient to place and carry the UAV. It does not require any propellant or additional special disassembly and assembly tools, saving time and effort.

[0016] (2) The base of the utility model is provided with a guide support bar for fixed connection with the launch platform. The launch system of the utility model can be launched by a single soldier or carried on a launch platform (vehicle-mounted, ground-mounted launch platform) for multiple launches;

[0017] (3) When the shell of the utility model is released, it automatically unfolds under the action of the torsion spring, gravity, and the thrust of the rotor arm of the drone, without any noise, and without restrictions on space and environment. The outer shell is made of fiberglass board, and the frame structure uses carbon tubes and aluminum alloy machined parts. It is light in weight, strong and durable, and has low processing cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 , a schematic diagram of the external structure of a foldable quad-rotor UAV individual launch system of the utility model;

[0019] Figure 2 , a schematic diagram of the internal structure of a foldable quad-rotor UAV individual launch system of the utility model;

[0020] Figure 3 , a schematic diagram of a foldable four-rotor UAV individual launching system of the utility model when launching a UAV.

[0021] Description of reference numerals:

[0022] 1. Shell, 2. Base, 3. Strap, 4. Cover, 5. Active latch, 6. Guide support bar, 7. Aircraft fixing seat, 8. Locking mechanism, 9. UAV;

[0023] 11. carbon tube, 12. baffle, 13. connecting ear, 14. motor blade clamp, 15. connecting rib, 16. upper connecting seat;

[0024] 21. Lower base plate, 22. Side plate, 23. Upper base plate, 24. Automatic folding pipe clamp, 25. Support plate nut, 26. Aluminum column;

[0025] 81. Servo, 82. Aluminum column, 83. Servo rocker arm, 84. Lock shaft, 85. Servo pull rod. DETAILED DESCRIPTION

[0026] The following describes the specific implementation of the utility model in conjunction with embodiments:

[0027] It should be noted that the structures, proportions, sizes, etc. shown in this specification are only used to match the contents disclosed in the specification so that people familiar with this technology can understand and read them, and are not used to limit the conditions under which the present invention can be implemented. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed in the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0028] Example 1

[0029] like Figures 1 to 3As shown, the utility model discloses a foldable quad-rotor UAV individual launching system, comprising a shell 1, a base 2, an aircraft fixing seat 7 and a locking mechanism 8, wherein the shells 1 are four, and the bottom centers of the four shells 1 are rotatably connected to the four top corners of the base 2 respectively, and the opening angle of the shells 1 relative to the base 2 is 0-90°, and the tops of the four shells 1 are locked by the locking mechanism 8, the aircraft fixing seat 7 is fixed to the center of the upper end of the base 2 and is in the space formed by the four shells 1, and the UAV 9 is installed on the aircraft fixing seat 7.

[0030] Example 2

[0031] like Figure 2 As shown, preferably, the shell 1 includes a carbon tube 11, a baffle 12, a connecting ear 13, a motor blade clamp 14, a connecting rib 15 and an upper connecting seat 16, there are two baffles 12, the two baffles 12 are vertically connected, a carbon tube 11 is arranged at the intersection of the two baffles 12, the top of the carbon tube 11 is connected to the upper connecting seat 16, the upper connecting seats 16 of the four shells 1 are locked by a locking mechanism 8, the bottom of the carbon tube 11 is rotatably connected to the top angle of the base 2, the upper and lower sides of the baffle 12 are respectively provided with connecting ribs 15, the connecting ribs 15 are connected to the carbon tube 11 through the connecting ears 13, a motor blade clamp 14 is arranged at the root of the shell 1, and the rotor arm motor and blades of the drone 9 are clamped on the motor blade clamp 14.

[0032] Preferably, the carbon tube 11 is a circular or square carbon tube, the shell 1 is made of glass fiber board, and the frame structure uses carbon tubes and aluminum alloy machined parts.

[0033] like Figure 2 As shown, preferably, two adjacent shells 1 are connected via a movable latch 5, and the movable latch 5 is a ball pin.

[0034] like Figure 2 As shown, preferably, a cover 4 is further provided on the top of the four shells 1 , and the cover 4 is connected to each shell 1 via a movable latch 5 .

[0035] like Figure 2 As shown, preferably, two adjacent shells 1 are further provided with shoulder straps 3 , and the shoulder straps 3 are installed on the upper and lower connecting ears 13 of the shells 1 .

[0036] like Figure 3 As shown, preferably, the four shells 1 open downward in a petal-like shape when unfolded, the UAV 9 is installed on the aircraft fixing seat 7, and the rotor arm motor and blades of the UAV 9 are clamped on the motor blade clamping plate 14. When stored, the four shells 1 are closed upward into a barrel-like structure with a rectangular or circular cross-section.

[0037] The shell 1 is composed of two vertical baffles 12, and a round or square carbon tube 11 is provided at the intersection of the two baffles 12. Two connecting ribs 15 and an upper connecting seat 16 are provided on the carbon tube 11 to strengthen the rigidity of the shell 1. The connecting rib 15 and the upper connecting seat 16 are clamped and connected to the carbon tube 11 through connecting ears 13, and are connected to the two vertical baffles 12 to form a rigid shell 1.

[0038] Example 3

[0039] like Figure 2 As shown, preferably, the base 2 includes a lower base plate 21, a side plate 22, an upper base plate 23, an automatic folding tube clamp 24, a support plate nut 25 and a first aluminum column 26. There are four automatic folding tube clamps 24. The four top corners of the lower base plate 21 and the upper base plate 23 are respectively connected by the automatic folding tube clamps 24. The rotatable end of the automatic folding tube clamp 24 is connected to the bottom of the carbon tube 11. A first aluminum column 26 is arranged between the lower base plate 21 and the upper base plate 23 to increase rigidity. There are four side plates 22. The side plates 22 are respectively installed around the lower base plate 21 and the upper base plate 23. The aircraft fixing seat 7 is fixed to the center position of the upper end surface of the upper base plate 23 by the support plate nut 25.

[0040] like Figure 2 As shown, preferably, the automatic folding tube clamp 24 has a torsion spring, which can make the shell 1 open at an angle of 0 to 90 degrees. The two sides of the automatic folding tube clamp 24 are respectively connected to the lower base plate 21 and the upper base plate 23, and the middle rotatable end is connected to the bottom of the carbon tube 11. The bottom of the lower base plate 21 is installed with a guide support bar 6.

[0041] The base 2 is formed by a lower base plate 21 and an upper base plate 23 connected at four top corners by four automatic folding pipe clamps 24. Four first aluminum columns 26 are also installed between the upper and lower base plates to increase rigidity. Four side panels 22 are installed around the upper base plate 23 and the lower base plate 21. Four guide support bars 6 are installed at the bottom of the lower base plate 21 for fixed connection with the launch platform. The aircraft fixing seat 7 is fixedly installed by three support plate nuts 25 in the middle above the upper base plate 23. The aircraft fixing seat 7 is used to fix the drone.

[0042] Example 4

[0043] like Figure 2As shown, preferably, the locking mechanism 8 includes a servo 81, a second aluminum column 82, a servo rocker arm 83, a locking shaft 84 and a servo pull rod 85. The locking mechanism 8 is installed at the bottom of the upper connecting seat 16 of any one of the shells 1. The servo 81 is connected to the bottom of the upper connecting seat 16 through the second aluminum column 82. The servo 81 is connected to the servo rocker arm 83. The servo rocker arm 83 is hinged to the servo pull rod 85. The servo pull rod 85 is connected to the locking shaft 84. Lock holes are provided at the overlapping portions of the other three upper connecting seats 16. The servo 81 is externally connected to a remote control. The servo 81 drives the servo rocker arm 83 and the servo pull rod 85 to control the locking shaft 84 to move up and down in the locking holes of the other three upper connecting seats 16, thereby controlling the opening and closing of each shell 1.

[0044] The working principle of the utility model is as follows:

[0045] like Figures 1 to 3 As shown, the utility model discloses a foldable quad-rotor UAV individual launch system, the quad-rotor UAV can be loaded inside the launch system, the launch system is in the shape of a rectangular box, and is surrounded by a movable thin-walled shell 1, each shell 1 can be opened about 90 degrees, with a shoulder strap 3 on the outside, and a guide support bar 6 is installed under the bottom of the base 2. It can be launched by a single soldier, or it can be carried on a platform (vehicle-mounted, ground launch platform) for multiple launches.

[0046] The utility model cooperates with the unmanned aerial vehicle 9. When a single soldier needs to carry the unmanned aerial vehicle 9, the movable latches 5 between all the shells 1 are first unplugged, the lid 4 is removed, the locking mechanism 8 is driven by a remote controller, the four shells 1 are opened, the unmanned aerial vehicle 9 is folded and inserted into the aircraft fixing seat 7 on the upper bottom plate 23, the four shells 1 are manually closed in sequence, the rotor arm motor and the blades of the unmanned aerial vehicle are just stuck in the motor blade clamping plate 14, the locking shaft 84 on the locking mechanism 8 is manually reset, and finally the movable latches 5 between the four shells are inserted in sequence, and the unmanned aerial vehicle 9 can be carried and transported. When the unmanned aerial vehicle 9 needs to be released, the movable latches 5 between the lid 4 and the four shells 1 are first unplugged, and the locking mechanism 8 of the remote controller is unlocked, and the four shells 1 can be automatically unfolded and released, and the unmanned aerial vehicle reaches the take-off state.

[0047] The utility model discloses a foldable quad-rotor UAV individual launching system, wherein the UAV is placed in a space composed of four shells, which are opened in a petal shape when unfolded and in a barrel-shaped structure when stored, so that the unfolding and storage are relatively convenient. The tops of the four shells are fixed by a locking mechanism, and the locking mechanism is externally connected to a remote controller for convenient control. The overall structure of the utility model is small in size, light in weight, and simple to deploy, so that the UAV can be conveniently placed and carried, and no propellant or additional special disassembly and assembly tools are required, thus saving time and effort.

[0048] The base of the utility model is provided with a guide support bar for fixedly connecting with the launch platform. The launch system of the utility model can be launched by a single soldier or carried on a launch platform (vehicle-mounted, ground-mounted launch platform) for multiple launches.

[0049] When the shell of the utility model is released, the shell is automatically unfolded under the action of the torsion spring, gravity and the thrust of the rotor arm of the drone, without noise, and without restrictions on space and environmental requirements. The outer shell is made of fiberglass board, and the frame structure uses carbon tubes and aluminum alloy machined parts. It is light in weight, strong and durable, and has low processing cost.

[0050] The preferred embodiments of the present invention are described in detail above, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of ordinary technicians in this field without departing from the purpose of the present invention.

[0051] Many other changes and modifications can be made without departing from the concept and scope of the utility model. It should be understood that the utility model is not limited to a specific embodiment, and the scope of the utility model is defined by the appended claims.

Claims

1. A folding quad-rotor UAV individual launch system, characterized by: The invention comprises a shell (1), a base (2), an aircraft fixing seat (7) and a locking mechanism (8), wherein the shells (1) are four in number, the bottom centers of the four shells (1) are rotatably connected to the four top corners of the base (2) respectively, the opening angle of the shells (1) relative to the base (2) is 0 to 90 degrees, the tops of the four shells (1) are locked by the locking mechanism (8), the aircraft fixing seat (7) is fixed to the center of the upper end of the base (2) and is located in the space formed by the four shells (1), and the unmanned aerial vehicle (9) is mounted on the aircraft fixing seat (7).

2. A folding quad-rotor UAV individual launch system according to claim 1, characterized in that: The shell (1) comprises a carbon tube (11), a baffle (12), a connecting ear (13), a motor blade clamp (14), a connecting rib (15) and an upper connecting seat (16); the baffle (12) is two, the two baffles (12) are vertically connected, a carbon tube (11) is arranged at the intersection of the two baffles (12), the top of the carbon tube (11) is connected to the upper connecting seat (16), the upper connecting seats (16) of the four shells (1) are locked by a locking mechanism (8), the bottom of the carbon tube (11) is rotatably connected to the top angle of the base (2), the upper side and the lower side of the baffle (12) are respectively provided with connecting ribs (15), the connecting ribs (15) are connected to the carbon tube (11) through the connecting ear (13), the base of the shell (1) is provided with a motor blade clamp (14), and the rotor arm motor and blades of the unmanned aerial vehicle (9) are clamped on the motor blade clamp (14).

3. A folding quad-rotor UAV individual launch system according to claim 2, characterized in that: The carbon tube (11) is a circular or square carbon tube.

4. A folding quad-rotor UAV individual launch system according to claim 2, characterized in that: The base (2) comprises a lower base plate (21), a side plate (22), an upper base plate (23), an automatic folding tube clamp (24), a support plate nut (25) and a first aluminum column (26). There are four automatic folding tube clamps (24). Four top corners of the lower base plate (21) and the upper base plate (23) are connected by the automatic folding tube clamps (24). The rotatable end of the automatic folding tube clamp (24) is connected to the bottom of the carbon tube (11). A first aluminum column (26) is arranged between the lower base plate (21) and the upper base plate (23) to increase rigidity. There are four side plates (22). Side plates (22) are respectively installed around the lower base plate (21) and the upper base plate (23). The aircraft fixing seat (7) is fixed to the center position of the upper end surface of the upper base plate (23) by the support plate nut (25).

5. The foldable quad-rotor UAV individual launch system according to claim 2, characterized in that: The locking mechanism (8) comprises a steering gear (81), a second aluminum column (82), a steering gear rocker arm (83), a locking shaft (84) and a steering gear pull rod (85). The locking mechanism (88) is mounted on the bottom of an upper connecting seat (16) of any housing (1). The steering gear (81) is connected to the bottom of the upper connecting seat (16) via the second aluminum column (82). The steering gear (81) is connected to the steering gear rocker arm (83). The steering gear rocker arm (83) is hinged to the steering gear pull rod (85). The steering gear pull rod (85) is connected to the locking shaft (84). Lock holes are provided at the overlapping portions of the other three upper connecting seats (16). The steering gear (81) is externally connected to a remote controller. The steering gear (81) drives the steering gear rocker arm (83) and the steering gear pull rod (85) to control the locking shaft (84) to move up and down in the locking holes of the other three upper connecting seats (16), thereby controlling the opening and closing of each housing (1).

6. A folding quad-rotor UAV individual launch system according to claim 4, characterized in that: The automatic folding tube clamp (24) is provided with a torsion spring, which enables the shell (1) to open at an angle of 0 to 90 degrees. The two sides of the automatic folding tube clamp (24) are respectively connected to the lower bottom plate (21) and the upper bottom plate (23), and the middle rotatable end is connected to the bottom of the carbon tube (11). The bottom of the lower bottom plate (21) is provided with a guide support bar (6).

7. The foldable quad-rotor UAV individual launch system according to claim 1, characterized in that: Two adjacent shells (1) are connected via a movable latch (5), and the movable latch (5) is a ball pin.

8. The foldable quad-rotor UAV individual launch system according to claim 1, characterized in that: A cover (4) is also provided on the top of the four shells (1), and the cover (4) is connected to each shell (1) via a movable latch (5).

9. The foldable quad-rotor UAV individual launch system according to claim 2, characterized in that: Two adjacent shells (1) are also provided with shoulder straps (3), which are mounted on upper and lower connecting ears (13) of the shells (1).

10. The foldable quad-rotor UAV individual launch system according to claim 2, characterized in that: When the four shells (1) are unfolded, they open downwards in a petal-like shape. The drone (9) is mounted on an aircraft fixing seat (7). The rotor arm motor and blades of the drone (9) are clamped on a motor blade clamping plate (14). When stored, the four shells (1) are closed upwards into a barrel-like structure with a rectangular or circular cross-section.

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