Unmanned aerial vehicle flight control IMU second-order damping device

Abstract

The utility model discloses an unmanned aerial vehicle flight control IMU second-order damping device, and relates to the technical field of unmanned aerial vehicle damping, the unmanned aerial vehicle flight control IMU second-order damping device comprises a housing, the top end of the housing is clamped and connected with a cover plate; a condensation pipe is fixedly installed on the bottom face of the inner wall of the shell. A second circuit board is arranged on the upper surface of the condensation pipe; a balancing weight is arranged on the upper surface of the second circuit board; a damping assembly is arranged on the balancing weight; the upper surface of the balancing weight is fixedly connected with a first circuit board; the first circuit board is electrically connected with the second circuit board through a flexible flat cable, and a plurality of elastic pieces are fixedly arranged on the upper end face of the condensation pipe. The interior of the elastic piece is communicated with the interior of the condensation pipe; by arranging an elastic piece, a first damper, a second damper and a third damper, when the unmanned aerial vehicle vibrates, resistance is generated to movement of a balancing weight through the elastic piece, the first damper, the second damper and the third damper; therefore, vibration is reduced, and the damping effect of the device is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle (UAV) shock absorption, in particular to an IMU second-order shock absorption device for an unmanned aerial vehicle (UAV) flight control. Background Art

[0002] UAV flight control is the abbreviation of UAV flight control system. It is the core system for the entire flight process of UAV, including take-off, air flight, mission execution and return recovery. IMU, or inertial measurement unit, consists of three single-axis accelerometers and three single-axis gyroscopes, which are used to measure and track the attitude, position and motion state of objects.

[0003] A novel flight control constant temperature shock absorption structure disclosed in Chinese patent CN218411207U includes a support frame, which is the main support and installation structure of the flight control. The support frame is respectively installed with a counterweight copper block, a gyroscope sensor PCB board and a flight control main board. The flight control main board is located at the bottom of the gyroscope sensor PCB board, and the counterweight copper block is located at the top of the gyroscope sensor PCB board. By setting a heating resistor and a weight-reducing foam, the gyroscope sensor PCB board and the counterweight copper block can be directly heated under low temperature conditions. The foam is stretched by gravity to supplement the toughness of the foam and improve the shock absorption ability of the gyroscope sensor PCB board.

[0004] However, the above-mentioned flight control constant temperature shock-absorbing structure has the following problems when in use: the above-mentioned structure only achieves shock absorption by sticking and connecting weight-reducing foam between the support frame and the counterweight copper block, resulting in a low shock absorption effect and failing to achieve a good shock absorption effect on the entire motherboard.

[0005] In order to solve the above problems, the utility model proposes a second-order shock absorption device for an unmanned aerial vehicle flight control IMU. Utility Model Content

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a second-order shock absorption device of an unmanned aerial vehicle flight control IMU, comprising a shell, the top of which is snap-connected with a cover plate; a condenser is fixedly installed on the bottom surface of the inner wall of the shell; a second circuit board is arranged on the upper surface of the condenser; a counterweight is arranged on the upper surface of the second circuit board; a shock absorption assembly is arranged on the counterweight; a first circuit board is fixedly connected to the upper surface of the counterweight; the first circuit board is electrically connected to the second circuit board through a flexible flat cable;

[0007] A plurality of elastic parts are fixedly provided on the upper end surface of the condenser; the interior of the elastic parts is communicated with the interior of the condenser; the counterweight block and the second circuit board are both plugged into and matched with the elastic parts; one end of the condenser is connected to a hydraulic cylinder via a connecting pipe; exhaust holes are provided on both sides of the outer wall of the outer shell; filter plates are fixedly installed inside the exhaust holes; a cooling component is provided on the inner bottom surface of the outer shell at a position corresponding to the exhaust hole on the left side; the hydraulic cylinder is drivingly connected to the cooling component.

[0008] Preferably, the elastic member includes an elastic ball and connecting tubes fixedly connected to the upper and lower sides of the elastic ball; the lower connecting tubes are connected to the interior of the condenser tube; and the top ends of the upper connecting tubes are sealed with sealing plates.

[0009] Preferably, a through hole is provided on the upper end surface of the second circuit board at a position corresponding to the elastic member; the lower connecting pipe is correspondingly inserted into the through hole on the second circuit board;

[0010] The upper end surface of the counterweight block is provided with a through hole at the position corresponding to the elastic member; the upper connecting pipe is correspondingly inserted into the through hole on the counterweight block; the lower end surface of the counterweight block is provided with a groove at the position corresponding to the elastic member; and the elastic ball is correspondingly arranged inside the groove.

[0011] Preferably, the shock absorbing assembly includes a first damper, a second damper and a third damper, the first damper is fixedly mounted on the left surface of the counterweight; the other end of the first damper is fixedly connected to the inner wall of the outer shell; two second dampers are provided; the two second dampers are respectively fixedly connected to the front and rear surfaces of the counterweight; the other ends of the second dampers are both fixedly connected to the inner wall of the outer shell; the third damper is fixedly mounted on the inner bottom surface of the outer shell; an avoidance hole is opened at the position corresponding to the third damper on the second circuit board; the other end of the third damper passes through the avoidance hole and is fixedly connected to the bottom surface of the counterweight.

[0012] Preferably, the cooling component includes a fixed plate; the fixed plate is fixedly installed on the inner bottom surface of the shell at a position corresponding to the left exhaust hole; a connecting shaft is rotatably installed on the top of the fixed plate; a fan blade is fixedly installed on one end of the connecting shaft; the fan blade corresponds to the exhaust hole; a gear is fixedly installed on the other end of the connecting shaft; and a driving component for driving the gear to rotate is arranged inside the hydraulic cylinder.

[0013] Preferably, the driving assembly includes a piston plate; the piston plate is slidably installed inside the hydraulic cylinder; a sliding rod is fixedly connected to the side of the piston plate away from the connecting pipe; a rack is fixedly installed on the other end of the sliding rod; the gear and the rack are meshingly connected; the sliding rod is slidably connected to the hydraulic cylinder; a spring is fixedly connected to the piston plate; the other end of the spring is fixedly connected to the inner wall of the hydraulic cylinder; the spring is sleeved on the outside of the sliding rod.

[0014] Beneficial Effects

[0015] Compared with the prior art, the beneficial effects of the utility model are:

[0016] (1) The second-order shock absorption device of the UAV flight control IMU is provided with an elastic member, a first damper, a second damper and a third damper. When the UAV vibrates, the elastic member, the first damper, the second damper and the third damper generate resistance to the movement of the counterweight block, thereby reducing the vibration and improving the shock absorption effect of the device.

[0017] (2) The second-order shock absorption device of the UAV flight control IMU moves the coolant into the hydraulic cylinder through the movement of the counterweight block, so that the piston plate moves back and forth in the hydraulic cylinder, so that the gas in the fan blade rotation acceleration device circulates, thereby reducing the temperature of the first circuit board and the second circuit board, and extending the service life of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The utility model is further described below in conjunction with the accompanying drawings and embodiments:

[0019] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0020] Figure 2 This is a schematic diagram of the internal structure of the utility model;

[0021] Figure 3 For this utility model Figure 2 A magnified schematic diagram of the middle part;

[0022] Figure 4 This is a schematic diagram of the explosion of a local component of the utility model;

[0023] Figure 5 This is a schematic diagram of the structure of the hydraulic cylinder of the utility model.

[0024] Figure numerals: 1. outer shell; 2. filter plate; 3. cover plate; 4. first damper; 5. first circuit board; 6. counterweight; 7. second damper; 8. sealing plate; 9. elastic member; 10. flexible flat cable; 11. second circuit board; 12. condenser; 13. hydraulic cylinder; 14. rack; 15. gear; 16. exhaust hole; 17. fixing plate; 18. fan blade; 19. third damper; 20. mounting hole; 21. groove; 22. piston plate; 23. spring; 24. slide rod. DETAILED DESCRIPTION

[0025] This section will describe in detail the specific embodiments of the utility model. The preferred embodiments of the utility model are shown in the accompanying drawings. The purpose of the accompanying drawings is to supplement the description of the text part of the specification with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the utility model, but it cannot be understood as a limitation on the protection scope of the utility model.

[0026] See also Figure 1-5 The utility model provides a technical solution: a second-order shock absorption device for an unmanned aerial vehicle flight control IMU, comprising a housing 1, the housing 1 being fixedly connected to the unmanned aerial vehicle. A cover plate 3 is snap-connected to the top of the housing 1. A condenser 12 is fixedly installed on the bottom surface of the inner wall of the housing 1. A second circuit board 11 is disposed on the upper surface of the condenser 12. A counterweight 6 is disposed on the upper surface of the second circuit board 11.

[0027] The counterweight block 6 is provided with a shock absorbing assembly.

[0028] The shock absorbing assembly includes a first damper 4, a second damper 7 and a third damper 19. The first damper 4 is fixedly mounted on the left surface of the counterweight 6. The other end of the first damper 4 is fixedly connected to the inner wall of the outer shell 1. Two second dampers 7 are provided. The two second dampers 7 are respectively fixedly connected to the front and rear surfaces of the counterweight 6. The other ends of the second dampers 7 are both fixedly connected to the inner wall of the outer shell 1. The third damper 19 is fixedly mounted on the inner bottom surface of the outer shell 1. An avoidance hole is provided on the second circuit board 11 at a position corresponding to the third damper 19. The other end of the third damper 19 passes through the avoidance hole and is fixedly connected to the bottom surface of the counterweight 6.

[0029] The first circuit board 5 is fixedly connected to the upper surface of the counterweight 6. The first circuit board 5 is electrically connected to the second circuit board 11 through a flexible flat cable 10.

[0030] A plurality of elastic members 9 are fixedly disposed on the upper end surface of the condensing tube 12 . The interior of the elastic member 9 is communicated with the interior of the condensing tube 12 .

[0031] It should be noted that condensate is provided in the elastic member 9 and the condenser tube 12 to cool the first circuit board 5 and the second circuit board 11. The elastic member 9 includes an elastic ball and connecting tubes fixed to the upper and lower sides of the elastic ball. The lower connecting tubes are connected to the inside of the condenser tube 12. The top of the upper connecting tube is sealed with a sealing plate 8.

[0032] The counterweight block 6 and the second circuit board 11 are both plug-fitted with the elastic member 9 .

[0033] Specifically, a through hole is provided on the upper end surface of the second circuit board 11 at a position corresponding to the elastic member 9 . The lower connecting pipe is correspondingly inserted into the through hole on the second circuit board 11 .

[0034] The upper end surface of the counterweight block 6 is provided with a through hole at a position corresponding to the elastic member 9. The upper connecting pipe is correspondingly inserted into the through hole of the counterweight block 6. The lower end surface of the counterweight block 6 is provided with a groove 21 at a position corresponding to the elastic member 9. The elastic ball is correspondingly arranged inside the groove 21.

[0035] One end of the condenser pipe 12 is connected to the hydraulic cylinder 13 through a connecting pipe. Exhaust holes 16 are provided on both sides of the outer wall of the housing 1. The filter plates 2 are fixedly installed inside the exhaust holes 16.

[0036] A cooling component is provided on the inner bottom surface of the housing 1 at a position corresponding to the left exhaust hole 16 .

[0037] The cooling assembly includes a fixing plate 17. The fixing plate 17 is fixedly mounted on the inner bottom surface of the housing 1 at a position corresponding to the left exhaust hole 16. A connecting shaft is rotatably mounted on the top of the fixing plate 17. A fan blade 18 is fixedly mounted on one end of the connecting shaft. The fan blade 18 corresponds to the exhaust hole 16. A gear 15 is fixedly mounted on the other end of the connecting shaft. A driving assembly for driving the gear 15 to rotate is arranged inside the hydraulic cylinder 13.

[0038] The driving assembly includes a piston plate 22. The piston plate 22 is slidably mounted inside the hydraulic cylinder 13. A slide bar 24 is fixedly mounted on the side of the piston plate 22 away from the connecting pipe. A rack 14 is fixedly mounted on the other end of the slide bar 24. The gear 15 is meshedly connected with the rack 14. The slide bar 24 is slidably connected to the hydraulic cylinder 13. A spring 23 is fixedly mounted on the piston plate 22; the other end of the spring 23 is fixedly connected to the inner wall of the hydraulic cylinder 13; and the spring 23 is sleeved on the outside of the slide bar 24.

[0039] Working principle:

[0040] When the drone vibrates due to external interference, the force applied to the counterweight 6 will change. When the counterweight 6 is displaced downward due to the vibration, the elastic ball on the elastic member 9 will be compressed, and the elastic member 9 will apply an upward thrust to the counterweight 6; and the third damper 19 will also generate upward resistance; thereby helping to reduce the downward displacement of the counterweight 6 and achieve a shock absorbing effect.

[0041] At the same time, the compression of the elastic member 9 causes the elastic member 9 and the coolant in the condenser 12 to move into the hydraulic cylinder 13, so that the piston plate 22 compresses the spring 23. At this time, the spring 23 has the force to restore the piston plate 22 to its original state. The piston plate 22 causes the slide bar 24 to move out of the hydraulic cylinder 13, and the slide bar 24 causes the rack 14 to move. The rack 14 and the gear 15 engage to cause the fan blades 18 to rotate, so as to accelerate the gas circulation in the device, reduce the temperature of the first circuit board 5 and the second circuit board 11, and thereby extend the service life of the device.

[0042] When the compression of the elastic ball in the elastic member 9 reaches the maximum value, the counterweight 6 will stop moving downward under the action of thrust and resistance; at this time, the elastic member 9 returns to its original state and generates an upward thrust, pushing the counterweight 6 to move upward; since the resistance generated by the damper is always opposite to the direction of movement of the object, when the counterweight 6 moves upward, the third damper 19 generates a downward resistance to prevent the counterweight 6 from moving upward, thereby achieving a shock absorbing effect.

[0043] By providing the first damper 4 and the second damper 7, when the drone vibrates due to external interference, the counterweight 6 is prevented from excessively shaking left and right or forward and backward, thereby protecting the circuit board from damage.

[0044] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge scope of ordinary technicians in the technical field without departing from the purpose of the present invention.

Claims

1. A second-order shock absorption device for an unmanned aerial vehicle flight control IMU, comprising a housing (1), the top end of the housing (1) being snap-connected with a cover plate (3); characterized in that: A condenser (12) is fixedly mounted on the bottom surface of the inner wall of the housing (1); a second circuit board (11) is arranged on the upper surface of the condenser (12); a counterweight (6) is arranged on the upper surface of the second circuit board (11); a shock absorbing assembly is arranged on the counterweight (6); a first circuit board (5) is fixedly connected to the upper surface of the counterweight (6); the first circuit board (5) is electrically connected to the second circuit board (11) via a flexible flat cable (10); A plurality of elastic members (9) are fixedly arranged on the upper end surface of the condenser tube (12); the interior of the elastic member (9) is in communication with the interior of the condenser tube (12); the counterweight (6) and the second circuit board (11) are both plug-fitted with the elastic member (9); one end of the condenser tube (12) is connected to a hydraulic cylinder (13) via a connecting pipe; exhaust holes (16) are provided on both sides of the outer wall of the housing (1); filter plates (2) are fixedly installed inside the exhaust holes (16); a cooling component is provided on the inner bottom surface of the housing (1) at a position corresponding to the exhaust hole (16) on the left side; and the hydraulic cylinder (13) is drivingly connected to the cooling component.

2. The UAV flight control IMU second-order shock absorption device according to claim 1 is characterized by: The elastic member (9) comprises an elastic ball and connecting tubes fixedly connected to the upper and lower sides of the elastic ball; the lower connecting tubes are connected to the interior of the condenser tube (12); and the top ends of the upper connecting tubes are sealed with sealing plates (8).

3. The UAV flight control IMU second-order shock absorption device according to claim 1 is characterized by: A through hole is provided on the upper end surface of the second circuit board (11) at a position corresponding to the elastic member (9); the lower connecting pipe is correspondingly inserted into the through hole on the second circuit board (11); A through hole is provided on the upper end surface of the counterweight block (6) at a position corresponding to the elastic member (9); the upper connecting pipe is correspondingly inserted into the through hole on the counterweight block (6); a groove (21) is provided on the lower end surface of the counterweight block (6) at a position corresponding to the elastic member (9); and the elastic ball is correspondingly arranged in the groove (21).

4. The UAV flight control IMU second-order shock absorption device according to claim 1, characterized in that: The shock absorbing assembly comprises a first damper (4), a second damper (7) and a third damper (19), wherein the first damper (4) is fixedly mounted on the left surface of the counterweight (6); the other end of the first damper (4) is fixedly connected to the inner wall of the housing (1); two second dampers (7) are provided; the two second dampers (7) are respectively fixedly connected to the front and rear surfaces of the counterweight (6); the other ends of the second dampers (7) are both fixedly connected to the inner wall of the housing (1); the third damper (19) is fixedly mounted on the inner bottom surface of the housing (1); a avoidance hole is provided at a position corresponding to the third damper (19) on the second circuit board (11); the other end of the third damper (19) passes through the avoidance hole and is fixedly connected to the bottom surface of the counterweight (6).

5. The UAV flight control IMU second-order shock absorption device according to claim 1, characterized in that: The cooling component comprises a fixing plate (17); the fixing plate (17) is fixedly mounted on the inner bottom surface of the housing (1) at a position corresponding to the left exhaust hole (16); a connecting shaft is rotatably mounted on the top end of the fixing plate (17); a fan blade (18) is fixedly mounted on one end of the connecting shaft; the fan blade (18) corresponds to the exhaust hole (16); a gear (15) is fixedly mounted on the other end of the connecting shaft; and a driving component for driving the gear (15) to rotate is arranged inside the hydraulic cylinder (13).

6. The UAV flight control IMU second-order shock absorption device according to claim 5, characterized in that: The driving assembly comprises a piston plate (22); the piston plate (22) is slidably mounted inside the hydraulic cylinder (13); a sliding rod (24) is fixedly connected to the side of the piston plate (22) away from the connecting pipe; a rack (14) is fixedly mounted on the other end of the sliding rod (24); the gear (15) is meshingly connected to the rack (14); the sliding rod (24) is slidably connected to the hydraulic cylinder (13); a spring (23) is fixedly connected to the piston plate (22); the other end of the spring (23) is fixedly connected to the inner wall of the hydraulic cylinder (13); and the spring (23) is sleeved on the outside of the sliding rod (24).

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