Multi-rotor unmanned aerial vehicle assembling and debugging teaching aid and use method thereof

Abstract

The invention discloses a multi-rotor unmanned aerial vehicle assembling and debugging teaching aid and a use method thereof, the multi-rotor unmanned aerial vehicle assembling and debugging teaching aid comprises a teaching aid assembly, the teaching aid assembly comprises two side plates and an upper plate and a lower plate which are arranged between the two side plates, adjusting screw rods are rotatably arranged in the middles of the side plates, and the two ends of the upper plate are in threaded connection with the adjusting screw rods on the two side plates respectively; the two ends of the lower plate are installed at the bottoms of the two side plates correspondingly, and clamping pieces are arranged on the inner side of the upper plate and the inner side of the lower plate correspondingly. The teaching aid assembly is arranged, the fuselage of the unmanned aerial vehicle is clamped in the teaching aid assembly, the teaching aid assembly and the unmanned aerial vehicle are integrally hoisted through the suspension rope, then the unmanned aerial vehicle is started for debugging, the unmanned aerial vehicle can be prevented from falling to damage the fuselage even if the unmanned aerial vehicle stops running due to problems, and the teaching aid assembly is convenient to disassemble and assemble and high in stability; the method is convenient to use in unmanned aerial vehicle debugging.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicle debugging, in particular to a multi-rotor unmanned aerial vehicle assembly and debugging teaching aid and a use method thereof. Background Art

[0002] Unmanned aerial vehicle, referred to as "UAV", is an unmanned aircraft controlled by radio remote control equipment and self-contained program control devices, or operated completely or intermittently autonomously by an onboard computer. UAVs can be divided into military and civilian use according to their application areas.

[0003] Before a drone is tested for flight, the installation strength and stability need to be debugged before it can be officially put into use. During the debugging process, the drone is directly tested at low altitude to check whether the drone is working normally during the flight. If there is a problem with the drone during flight and it falls out of control, the body will be further damaged. Therefore, the present invention proposes a multi-rotor drone assembly and debugging teaching aid and a method of using the same to solve the above problems. Summary of the invention

[0004] The purpose of the present invention is to provide a multi-rotor UAV assembly and debugging teaching aid and a method of using the same, so as to solve the problem proposed in the above background technology that during the debugging process, the UAV is directly subjected to a low-altitude test flight to check whether the UAV is operating normally during the flight. If there is a problem with the UAV during the flight and it falls out of control, the body of the UAV will be further damaged.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a multi-rotor drone assembly and debugging teaching aid, comprising a teaching aid assembly, comprising two side panels and an upper panel and a lower panel arranged between the two side panels, wherein an adjusting screw is rotatably arranged in the middle of the side panels, and the two ends of the upper panel are respectively threadedly connected with the adjusting screws on the two side panels, and the two ends of the lower panel are respectively installed at the bottom of the two side panels, and the inner sides of the upper panel and the lower panel are both provided with clamping members; The clamping member comprises a suction cup, and two suction cups are symmetrically arranged between the upper plate and the lower plate; The unmanned aerial vehicle component comprises a fuselage and wings arranged at the four corners of the fuselage, wherein the fuselage is arranged between the suction cups of two clamping members.

[0006] As a preferred solution of the present invention, the clamping member further comprises an outer sleeve, an inner sleeve and a spring, the middle parts of the upper plate and the lower plate are both embedded with an outer sleeve, one end of the inner sleeve is inserted into the outer sleeve, the other end of the inner sleeve is connected to the suction cup, the spring is arranged in the outer sleeve and located at the top of the inner sleeve, one end of the spring is connected to the outer sleeve, and the other end of the spring is connected to the inner sleeve.

[0007] As a preferred solution of the present invention, through holes are provided on both sides of the outer sleeve, one end of the inner sleeve is connected to the interior of the outer sleeve, and the other end of the sleeve is connected to the interior of the suction cup.

[0008] As a preferred solution of the present invention, the outer wall of the inner sleeve is in contact with the inner wall of the outer sleeve, and an annular structure is provided at one end of the inner sleeve located inside the outer sleeve, the outer diameter of the annular structure is the same as the outer diameter of the inner sleeve, and the inner diameter of the annular structure is smaller than the inner diameter of the inner sleeve.

[0009] As a preferred solution of the present invention, square grooves are provided on the inner sides of the two side panels, the adjusting screw passes through the side panels and is located in the square grooves, a knob is provided on the top end of the adjusting screw, and the bottom end of the adjusting screw is rotatably connected to the lower plate.

[0010] As a preferred solution of the present invention, the two ends of the upper plate are inserted into the square grooves of the side plate, the adjusting screw passes through the upper plate and is threadedly connected to it, a bracket is also provided on the top of the upper plate, and a hanging rope is connected to the middle of the bracket.

[0011] As a preferred solution of the present invention, the fuselage is arranged between the two suction cups, mounting rings are arranged at the four corners of the fuselage, motors are arranged inside the mounting rings of the fuselage, and the output end of the motor is connected to the wing.

[0012] As a preferred solution of the present invention, a tensioning bolt is provided on one side of the mounting ring, and the tensioning bolt passes through the mounting ring and is threadedly connected thereto.

[0013] As a preferred solution of the present invention, the four corners of the bottom of the fuselage are also provided with support foot mounting seats.

[0014] A method for using a multi-rotor drone assembly and debugging teaching aid comprises the following steps: Step (A), assemble the drone, connect the four sets of wings to the output ends of the motors, install the four sets of motors in the mounting rings at the four corners of the fuselage, and then level the four sets of wings; Step (B), by rotating the tension bolt on the mounting ring, the end of the tension bolt contacts the outside of the motor, thereby fixing the motor; Step (C), debug the drone, place the drone body between the two suction cups, turn the knob on the side panel to rotate the adjustment screw, and since the adjustment screw is threadedly connected to the upper plate, the upper plate can move up and down along the adjustment screw, so that the upper plate and the lower plate can move closer to or farther away from each other; Step (D), when the upper plate and the lower plate are close to each other, the fuselage is clamped between the two suction cups. When the upper plate and the lower plate continue to approach each other, the suction cup is squeezed and moves and abuts against the plate body. When the suction cup moves, it pushes the inner sleeve to move, so that the inner sleeve is received in the outer sleeve and pushes the spring to contract. The through holes on both sides of the outer sleeve are closed by the inner sleeve. At this time, the inside of the suction cup is in a closed state. When the upper plate and the lower plate continue to approach each other, the suction cup is squeezed and deformed to discharge the air and adsorbed on the fuselage to fix it; Step (E), lifting the teaching aid assembly and the drone assembly by the suspension rope, then starting the drone for flight debugging, and removing the drone assembly after the debugging is completed; Step (F), when removing the drone component, it is necessary to turn the knob on the side panel again to move the upper plate and the lower plate away from each other. The spring in the outer sleeve stretches to push out the inner sleeve, so that the inner sleeve no longer closes the through holes on both sides of the outer sleeve, allowing air to enter the inner sleeve and the suction cup through the through holes. At this time, the suction cup no longer adheres to the fuselage, and the upper plate and the lower plate continue to move away from each other, so that the suction cup is separated from the fuselage, and the drone component is removed for use.

[0015] Compared with the prior art, the present invention has the following beneficial effects: The present invention is provided with a teaching aid assembly, by clamping the fuselage of the drone in the teaching aid assembly, then hoisting the teaching aid assembly and the drone as a whole through a hanging rope, and then starting the drone for debugging. Even if the drone stops operating due to problems, the drone can be prevented from falling and damaging the fuselage. Moreover, the teaching aid assembly is easy to disassemble and assemble, has strong stability, and is convenient to use in drone debugging. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention; Figure 2 It is a schematic diagram of the three-dimensional bottom-up structure of the present invention; Figure 3 It is a schematic diagram of the cross-sectional structure of the upper plate when the spring of the present invention is in an extended state; Figure 4 For the present invention Figure 3 A schematic diagram of the enlarged structure at A in the middle; Figure 5 It is a schematic diagram of the cross-sectional structure of the upper plate when the spring of the present invention is in a contracted state; Figure 6 For the present invention Figure 5 A schematic diagram of the enlarged structure at B in the middle; Figure 7 It is a schematic diagram of the cross-sectional structure of the mounting ring of the present invention.

[0017] In the figure: 1, teaching aid assembly; 101, side plate; 101a, square groove; 102, upper plate; 103, lower plate; 104, adjusting screw; 104a, knob; 105, clamping member; 105a, suction cup; 105b, outer sleeve; 105c, inner sleeve; 105d, spring; 105e, through hole; 106, bracket; 107, hanging rope; 2. UAV components; 201. fuselage; 201a. mounting ring; 202. wing; 203. motor; 204. tensioning bolt; 205. support foot mounting base. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] See also Figure 1-Figure 7 A multi-rotor drone assembly and debugging teaching aid includes a teaching aid component 1, including two side panels 101 and an upper panel 102 and a lower panel 103 arranged between the two side panels 101, an adjusting screw 104 is rotatably arranged in the middle of the side panels 101, two ends of the upper panel 102 are respectively threadedly connected with the adjusting screws 104 on the two side panels 101, two ends of the lower panel 103 are respectively installed at the bottom of the two side panels 101, and a clamping member 105 is arranged on the inner side of the upper panel 102 and the lower panel 103; The clamping member 105 includes a suction cup 105a, and two suction cups 105a are symmetrically arranged between the upper plate 102 and the lower plate 103; The drone assembly 2 includes a fuselage 201 and wings 202 arranged at four corners of the fuselage 201 . The fuselage 201 is arranged between the suction cups 105 a of the two clamping members 105 .

[0020] In this embodiment, the clamping member 105 further includes an outer sleeve 105b, an inner sleeve 105c and a spring 105d. The outer sleeve 105b is embedded in the middle of the upper plate 102 and the lower plate 103. One end of the inner sleeve 105c is inserted into the outer sleeve 105b, and the other end of the inner sleeve 105c is connected to the suction cup 105a. The spring 105d is arranged in the outer sleeve 105b and located at the top of the inner sleeve 105c. One end of the spring 105d is connected to the outer sleeve 105b, and the other end of the spring 105d is connected to the inner sleeve 105c. Wherein, through holes 105e are provided on both sides of the outer sleeve 105b, one end of the inner sleeve 105c is connected to the inside of the outer sleeve 105b, and the other end of the sleeve is connected to the inside of the suction cup 105a; It should be noted that when the spring 105d is fully extended, the top end of the inner sleeve 105c is located below the through hole 105e of the outer sleeve 105b, and air can enter the outer sleeve 105b and the inner sleeve 105c through the through hole 105e. When the inner sleeve 105c is received in the outer sleeve 105b, the spring 105d contracts, and the outer wall of the inner sleeve 105c covers the through holes 105e on both sides of the outer sleeve 105b. At this time, the outer sleeve 105b and the inner sleeve 105c are in a closed state. The outer wall of the inner sleeve 105c fits with the inner wall of the outer sleeve 105b, so that the outer wall of the inner sleeve 105c can be tightly attached to the through holes 105e on both sides of the outer sleeve 105b to close it. An annular structure is provided at one end of the inner sleeve 105c located inside the outer sleeve 105b. The outer diameter of the annular structure is the same as the outer diameter of the inner sleeve 105c, and the inner diameter of the annular structure is smaller than the inner diameter of the inner sleeve 105c, thereby increasing the contact area between the spring 105d and the end of the inner sleeve 105c, so as to facilitate the connection between the spring 105d and the inner sleeve 105c.

[0021] In this embodiment, a square groove 101a is provided on the inner side of each of the two side plates 101, and an adjusting screw 104 passes through the side plates 101 and is located in the square groove 101a. A knob 104a is provided on the top of the adjusting screw 104, and the bottom end of the adjusting screw 104 is rotatably connected to the lower plate 103; Among them, the two ends of the upper plate 102 are inserted into the square groove 101a of the side plate 101, and the adjusting screw 104 passes through the upper plate 102 and is threadedly connected thereto. Specifically, both sides of the upper plate 102 are provided with threaded holes that match the threads of the adjusting screw 104, and the adjusting screw 104 is screwed into the threaded holes of the upper plate 102 to form a threaded connection therewith. A bracket 106 is also provided on the top of the upper plate 102, and a hanging rope 107 is connected to the middle of the bracket 106. The hanging rope 107 is used to hang the teaching aid component 1 and the drone component 2; It should be noted that both ends of the upper plate 102 and the lower plate 103 are provided with block-shaped protrusions, which cooperate with the square groove 101a of the side plate 101 so that both ends of the upper plate 102 and the lower plate 103 can be inserted into the square groove 101a of the side plate 101.

[0022] In this embodiment, the fuselage 201 is disposed between the two suction cups 105a, and mounting rings 201a are disposed at the four corners of the fuselage 201. Motors 203 are disposed in the mounting rings 201a of the fuselage 201, and the output end of the motor 203 is connected to the wing 202; A tension bolt 204 is provided on one side of the mounting ring 201a, and the tension bolt 204 penetrates the mounting ring 201a and is threadedly connected thereto. Specifically, a threaded hole matching the thread of the tension bolt 204 is provided on one side of the mounting ring 201a, and the tension bolt 204 is screwed into the threaded hole of the mounting ring 201a to form a threaded connection therewith. The four corners of the bottom of the fuselage 201 are also provided with support foot mounting seats 205; It should be noted that after the motor 203 is installed in the mounting ring 201 a , the wings 202 at the four corners of the fuselage 201 need to be leveled, and then the motor 203 is fixed by rotating the tension bolts 204 .

[0023] The debugging process of the drone of the present invention is as follows: when debugging the drone, firstly debug without propellers, then debug with propellers; The main contents of propellerless debugging include: connecting all lines, turning on the power, performing the first power-on test, checking whether the flight controller, ESC, motor and receiver are powered normally, and checking whether there is any short circuit or open circuit; Check the remote controller, perform frequency binding and related settings, and confirm that the signals of each channel sent by the remote controller can be accurately received and transmitted to the flight controller; Connect the flight controller to the computer and use the debugging software to debug the flight controller, such as firmware burning, ESC calibration, accelerometer calibration, etc. Turn on the power, unlock the flight controller with the remote controller, push the throttle to check whether the direction of the motor 203 is correct; The main contents of the propeller debugging include: installing the propeller and correctly installing the propeller according to the direction of the motor 203; Flight test: check whether the aircraft is normal through flight status.

[0024] The method for using the multi-rotor unmanned aerial vehicle assembly and debugging teaching aid of the present invention comprises the following steps: Step (A), assembling the drone, connecting the four sets of wings 202 to the output ends of the motors 203, and then installing the four sets of motors 203 in the mounting rings 201a at the four corners of the fuselage 201, and then leveling the four sets of wings 202; Step (B), by rotating the tension bolt 204 on the mounting ring 201a, the end of the tension bolt 204 abuts against the outside of the motor 203, thereby fixing the motor 203; Step (C), debugging the drone, placing the fuselage 201 between the two suction cups 105a, and rotating the knob 104a on the side panel 101 to rotate the adjusting screw 104. Since the adjusting screw 104 is threadedly connected to the upper panel 102, the upper panel 102 can move up and down along the adjusting screw 104, so that the upper panel 102 and the lower panel 103 can move closer to or farther away from each other; Step (D), when the upper plate 102 and the lower plate 103 are close to each other, the fuselage 201 is clamped between the two suction cups 105a, and when the upper plate 102 and the lower plate 103 continue to approach each other, the suction cup 105a is squeezed and moves and abuts against the plate body, and when the suction cup 105a moves, it pushes the inner sleeve 105c to move, so that the inner sleeve 105c is received in the outer sleeve 105b and pushes the spring 105d to contract, and the through holes 105e on both sides of the outer sleeve 105b are closed by the inner sleeve 105c. At this time, the interior of the suction cup 105a is in a closed state, and the upper plate 102 and the lower plate 103 continue to approach each other, and the suction cup 105a is squeezed and deformed to discharge the air and adsorbed on the fuselage 201 to fix it; Step (E), lifting the teaching aid component 1 and the drone component 2 by the suspension rope 107, and then starting the drone to perform flight debugging, and then removing the drone component 2 after the debugging is completed; Step (F), when removing the drone component 2, it is necessary to rotate the knob 104a on the side panel 101 again to move the upper panel 102 and the lower panel 103 away from each other, and the spring 105d in the outer sleeve 105b stretches to push out the inner sleeve 105c, so that the inner sleeve 105c no longer closes the through holes 105e on both sides of the outer sleeve 105b, allowing air to enter the inner sleeve 105c and the suction cup 105a through the through holes 105e. At this time, the suction cup 105a no longer adheres to the fuselage 201, and the upper panel 102 and the lower panel 103 continue to move away from each other, so that the suction cup 105a is separated from the fuselage 201, and the drone component 2 is removed and used.

[0025] In summary, by clamping the drone's fuselage in the teaching aid assembly, then lifting the teaching aid assembly and the drone as a whole with a hanging rope, and then starting the drone for debugging, even if the drone has a problem and stops operating, the drone can be prevented from falling and damaging the fuselage.

[0026] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

Claims

1. A multi-rotor drone assembly and debugging teaching aid, characterized in that: include, A teaching aid assembly (1), comprising two side panels (101) and an upper panel (102) and a lower panel (103) arranged between the two side panels (101); an adjusting screw (104) is rotatably arranged in the middle of the side panels (101); two ends of the upper panel (102) are respectively threadedly connected to the adjusting screws (104) on the two side panels (101); two ends of the lower panel (103) are respectively installed at the bottom of the two side panels (101); and clamping members (105) are arranged on the inner sides of the upper panel (102) and the lower panel (103); The clamping member (105) comprises a suction cup (105a), and the two suction cups (105a) are symmetrically arranged between the upper plate (102) and the lower plate (103); The drone assembly (2) comprises a fuselage (201) and wings (202) arranged at the four corners of the fuselage (201); the fuselage (201) is arranged between the suction cups (105a) of two clamping members (105).

2. The multi-rotor drone assembly and debugging teaching aid according to claim 1, characterized in that: The clamping member (105) further comprises an outer sleeve (105b), an inner sleeve (105c) and a spring (105d); the outer sleeve (105b) is embedded in the middle of the upper plate (102) and the lower plate (103); one end of the inner sleeve (105c) is inserted into the outer sleeve (105b); the other end of the inner sleeve (105c) is connected to the suction cup (105a); the spring (105d) is arranged in the outer sleeve (105b) and located at the top of the inner sleeve (105c); one end of the spring (105d) is connected to the outer sleeve (105b); and the other end of the spring (105d) is connected to the inner sleeve (105c).

3. The multi-rotor drone assembly and debugging teaching aid according to claim 2, characterized in that: Through holes (105e) are provided on both sides of the outer sleeve (105b); one end of the inner sleeve (105c) is connected to the interior of the outer sleeve (105b); and the other end of the sleeve is connected to the interior of the suction cup (105a).

4. The multi-rotor drone assembly and debugging teaching aid according to claim 3, characterized in that: The outer wall of the inner sleeve (105c) fits with the inner wall of the outer sleeve (105b); an annular structure is provided at one end of the inner sleeve (105c) located inside the outer sleeve (105b); the outer diameter of the annular structure is the same as the outer diameter of the inner sleeve (105c), and the inner diameter of the annular structure is smaller than the inner diameter of the inner sleeve (105c).

5. The multi-rotor drone assembly and debugging teaching aid according to claim 1 or 4, characterized in that: A square groove (101a) is provided on the inner side of the two side plates (101); the adjusting screw (104) passes through the side plates (101) and is located in the square groove (101a); a knob (104a) is provided at the top end of the adjusting screw (104); and the bottom end of the adjusting screw (104) is rotatably connected to the lower plate (103).

6. The multi-rotor drone assembly and debugging teaching aid according to claim 5, characterized in that: The two ends of the upper plate (102) are inserted into the square groove (101a) of the side plate (101), the adjusting screw (104) passes through the upper plate (102) and is threadedly connected thereto, and a bracket (106) is also provided on the top of the upper plate (102), and a hanging rope (107) is connected to the middle of the bracket (106).

7. The multi-rotor drone assembly and debugging teaching aid according to claim 1 or 6, characterized in that: The fuselage (201) is arranged between the two suction cups (105a), and mounting rings (201a) are arranged at the four corners of the fuselage (201). Motors (203) are arranged inside the mounting rings (201a) of the fuselage (201), and the output end of the motor (203) is connected to the wing (202).

8. The multi-rotor drone assembly and debugging teaching aid according to claim 7, characterized in that: A tensioning bolt (204) is provided on one side of the mounting ring (201a); the tensioning bolt (204) passes through the mounting ring (201a) and is threadedly connected thereto.

9. The multi-rotor drone assembly and debugging teaching aid according to claim 8, characterized in that: The four corners of the bottom of the fuselage (201) are also provided with support foot mounting seats (205).

10. A method for using the multi-rotor drone assembly and debugging teaching aid according to any one of claims 1 to 9, characterized in that: The following steps are involved: Step (A), assembling the drone, connecting the four sets of wings (202) to the output ends of the motors (203), then installing the four sets of motors (203) in the mounting rings (201a) at the four corners of the fuselage (201), and then leveling the four sets of wings (202); Step (B), by rotating the tensioning bolt (204) on the mounting ring (201a), the end of the tensioning bolt (204) is brought into contact with the outside of the motor (203), thereby fixing the motor (203); Step (C), debugging the drone, placing the fuselage (201) between the two suction cups (105a), and rotating the knob (104a) on the side panel (101) to rotate the adjusting screw (104). Since the adjusting screw (104) is threadedly connected to the upper panel (102), the upper panel (102) can move up and down along the adjusting screw (104), so that the upper panel (102) and the lower panel (103) can move closer to or farther away from each other; Step (D), when the upper plate (102) and the lower plate (103) are brought closer to each other, the body (201) is clamped between the two suction cups (105a), and when the upper plate (102) and the lower plate (103) continue to approach each other, the suction cup (105a) is squeezed and moves and abuts against the plate body, and when the suction cup (105a) moves, it pushes the inner sleeve (105c) to move, so that the inner sleeve (105c) is received in the outer sleeve (105b) and pushes the spring (105d) to contract, and the through holes (105e) on both sides of the outer sleeve (105b) are closed through the inner sleeve (105c). At this time, the inside of the suction cup (105a) is in a closed state, and the upper plate (102) and the lower plate (103) continue to approach each other, and the suction cup (105a) is squeezed and deformed to discharge air and adsorbed on the body (201) to fix it; Step (E), lifting the teaching aid component (1) and the drone component (2) by means of the suspension rope (107), then starting the drone to perform flight debugging, and removing the drone component (2) after the debugging is completed; In step (F), when removing the drone component (2), it is necessary to rotate the knob (104a) on the side plate (101) again to move the upper plate (102) and the lower plate (103) away from each other, and the spring (105d) in the outer sleeve (105b) stretches to push out the inner sleeve (105c), so that the inner sleeve (105c) no longer closes the through holes (105e) on both sides of the outer sleeve (105b), allowing air to enter the inner sleeve (105c) and the suction cup (105a) through the through holes (105e). At this time, the suction cup (105a) no longer adsorbs the fuselage (201), and the upper plate (102) and the lower plate (103) continue to move away from each other, so that the suction cup (105a) is separated from the fuselage (201), and the drone component (2) is removed and used.

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