Lightweight controllable battery putting device of ornithopter and ornithopter

Abstract

The invention provides a lightweight controllable battery putting device of an ornithopter and the ornithopter, and relates to the technical field of ornithopters. The top of the throwing frame is connected with an ornithopter body, a steering engine is installed on the lower portion of the throwing frame, a throwing control shaft and a battery baffle rotating shaft are rotatably installed at the bottom of the throwing frame, a plurality of arc-shaped check blocks are installed on the throwing control shaft and have different radians, and elastic check rings are installed on the portions, located on the two sides of the arc-shaped check blocks, of the throwing control shaft. An output shaft of the steering engine is connected with one end of a steering engine rocker arm, a throwing control shaft is connected with one end of a throwing control shaft rocker arm, and the other end of the steering engine rocker arm and the other end of the throwing control shaft rocker arm are rotationally connected with two ends of a connecting rod; the battery baffle rotating shaft is rotationally connected with one end of the battery baffle, the other end of the battery baffle is matched with the arc-shaped check block, and the battery is placed on the battery baffle. The ornithopter is simple in structure and light in weight, battery putting is achieved, useless loads of the ornithopter are reduced, and the cruising ability of the ornithopter is improved.

Description

Technical Field

[0001] This invention relates to the field of ornithopter technology, and in particular to a lightweight and controllable battery delivery device for ornithopters and an ornithopter. Background Technology

[0002] Currently, ornithopters have a great need to improve their range. The drawback of traditional electric drive solutions is that the battery power is constantly consumed during flight, but the total mass of the battery remains unchanged. Therefore, the battery will gradually become a useless load during use, reducing the ornithopter's range. Summary of the Invention

[0003] This invention provides a lightweight and controllable battery deployment device for ornithopter and an ornithopter itself. Existing technologies have the problem that batteries gradually become useless loads during use, reducing the ornithopter's range.

[0004] To address the aforementioned problems, the present invention provides the following technical solution:

[0005] On one hand, a lightweight and controllable battery delivery device for an ornithopter includes a delivery frame, the top of which is connected to the fuselage of the ornithopter. A servo motor is installed at the lower part of the delivery frame. A delivery control shaft and a battery baffle shaft are rotatably installed at the bottom of the delivery frame. Multiple arc-shaped blocks with different curvatures are installed on the delivery control shaft. Elastic retaining rings are installed on both sides of the arc-shaped blocks on the delivery control shaft.

[0006] The output shaft of the servo motor is connected to one end of the servo motor rocker arm, the release control shaft is connected to one end of the release control shaft rocker arm, and the other end of the servo motor rocker arm and the other end of the release control shaft rocker arm are rotatably connected to the two ends of the connecting rod.

[0007] The battery baffle is rotatably connected to one end of the battery baffle by a rotating shaft, and the other end of the battery baffle cooperates with the arc-shaped block, with the battery placed on the battery baffle.

[0008] Optionally, the launch rack includes two thick main boards, with a thin main board arranged between the two thick main boards. Side plates are connected to the sides of the thick main boards and the sides of the thin main boards. A thick main board connector is detachably installed on the top of the thick main boards, and a thin main board connector is detachably installed on the top of the thin main boards. The thick main board connector and the thin main board connector are connected to the fuselage of the flapping-wing aircraft.

[0009] Optionally, a servo mounting slot is provided on the side of one of the thick motherboards, a servo is installed in the servo mounting slot, and the servo is detachably connected to the side of the thick motherboard.

[0010] Optionally, shaft mounting holes are provided on both sides of the bottom of the thick main board and the thin main board respectively. A dispensing control shaft is rotatably installed in the shaft mounting hole on one side of the thick main board and the thin main board, and a battery baffle shaft is rotatably installed in the shaft mounting hole on the other side of the thick main board and the thin main board.

[0011] Optionally, a battery separator is arranged between the thick main board and the thin main board, and the battery separator is arranged between two adjacent thin main boards, with side plates connected to both ends of the battery separator.

[0012] Optionally, the top of the thick motherboard and the thin motherboard is provided with a chassis placement slot, and through holes are provided on both sides of the top of the thick motherboard and the thin motherboard located in the chassis placement slot;

[0013] The thick motherboard connector and the thin motherboard connector are provided with body buckle grooves, and threaded holes are provided on both sides of the body buckle grooves on the thick motherboard connector and the thin motherboard connector. The thick motherboard connector and the thin motherboard connector are provided with motherboard grooves.

[0014] The through hole and the threaded hole are positioned correspondingly, and screws are installed in the through hole and the threaded hole.

[0015] Optionally, the curvature of the plurality of arc-shaped stops is set in a gradient, with the arc-shaped stops closer to the middle of the delivery control axis having a larger curvature and the arc-shaped stops farther away from the middle of the delivery control axis having a smaller curvature.

[0016] Optionally, the end of the battery baffle near the arc-shaped block has an arc-shaped structure.

[0017] Optionally, a parachute compartment is installed on the side of the launch rack, and a parachute is placed inside the parachute compartment, the parachute being connected to a battery.

[0018] On the other hand, there is an ornithopter, which includes the aforementioned lightweight and controllable battery delivery device.

[0019] The above technical solution has at least the following advantages compared with the existing technology:

[0020] The above-described solution, in this embodiment, features a lightweight and controllable battery delivery device for ornithopter aircraft. The device utilizes a servo-controlled four-bar linkage to separate the arc-shaped stop from the battery baffle, enabling battery delivery. This reduces the aircraft's unused load, improves its endurance, and enhances the overall flight performance. The design of arc-shaped stops with varying curvatures ensures orderly battery delivery with high controllability. Furthermore, controlling the rotation angle of the servo's output shaft allows for precise battery delivery with high reliability. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the lightweight and controllable battery delivery device for flapping-wing aircraft according to the present invention;

[0023] Figure 2 This is a schematic diagram of the lightweight and controllable battery delivery device for flapping-wing aircraft with a parachute compartment according to the present invention.

[0024] Figure 3 This is a schematic diagram of the lightweight and controllable battery delivery device for flapping-wing aircraft of the present invention, which includes a battery.

[0025] Figure 4 This is a schematic diagram of the battery baffle and arc-shaped block in the closed state of the lightweight controllable battery delivery device for flapping-wing aircraft according to the present invention.

[0026] Figure 5 This is a schematic diagram of the battery baffle and arc-shaped block in the open state of the lightweight controllable battery delivery device for flapping-wing aircraft according to the present invention.

[0027] Figure 6 This is a schematic diagram of the deployment control shaft of the lightweight controllable battery deployment device for flapping-wing aircraft of the present invention;

[0028] Figure 7 This is a schematic diagram of the battery baffle of the lightweight and controllable battery delivery device for flapping-wing aircraft of the present invention.

[0029] The annotations in the attached figures are explained as follows:

[0030] 1. Side panel; 2. Battery baffle; 3. Battery separator; 4. Thin mainboard; 5. Ornithopter fuselage; 6. Thin mainboard connector; 7. Thick mainboard connector; 8. Servo mainboard; 9. Arc-shaped stop block; 10. Shaft mounting hole; 11. Fuselage mounting slot; 12. Fuselage latching slot; 13. Mainboard slot; 14. Parachute compartment; 15. Deployment control shaft; 16. Thick mainboard; 17. Servo; 18. Deployment control shaft rocker arm; 19. Linkage rod; 20. Servo rocker arm; 21. Fastening nut; 22. Battery baffle pivot; 23. Screw; 25. Battery; 26. Elastic retaining ring; 27. Servo mounting slot; 28. Parachute compartment connector; 29. ​​Baffle through hole; 30. Retaining ring groove; 31. Arc-shaped structure. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the described embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0032] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms “first,” “second,” and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Similarly, the terms “an,” “a,” or “the,” and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms “comprising,” “including,” or “including,” and similar terms mean that the element or object preceding the word encompasses the element or object listed following the word and its equivalents, without excluding other elements or objects. The terms “connected,” “linked,” or “connected,” and similar terms are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect.

[0033] It should be noted that the terms "up", "down", "left", "right", "front", and "back" used in this invention are only used to indicate relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0034] The following text has been replaced item by item strictly according to the attached diagram (the replaced parts are shown in bold):

[0035] Example 1

[0036] like Figure 1As shown, this embodiment provides a lightweight and controllable battery deployment device for an ornithopter, including a deployment frame. The top of the deployment frame is connected to the ornithopter fuselage 5. A servo motor 17 is installed at the lower part of the deployment frame. A deployment control shaft 15 and a battery baffle pivot 22 are rotatably mounted at the bottom of the deployment frame. Multiple arc-shaped blocks 9 are mounted on the deployment control shaft 15, and the multiple arc-shaped blocks 9 have different curvatures. Elastic retaining rings 26 are installed on both sides of the deployment control shaft 15 located at the arc-shaped blocks 9. Specifically, when the deployment control shaft 15 is located at the arc-shaped blocks 9, elastic retaining rings 26 are installed on both sides of the arc-shaped blocks 9. The arc-shaped stop block 9 has retaining ring grooves 30 on both sides, and elastic retaining rings 26 are installed on the retaining ring grooves 30; the output shaft of the servo motor 17 is connected to one end of the servo motor rocker arm 20, the release control shaft 15 is connected to one end of the release control shaft rocker arm 18, and the other end of the servo motor rocker arm 20 and the other end of the release control shaft rocker arm 18 are rotatably connected to the two ends of the connecting rod 19; the battery baffle shaft 22 is rotatably connected to one end of the battery baffle 2, and the other end of the battery baffle 2 cooperates with the arc-shaped stop block 9, and the battery 25 is placed on the battery baffle 2. In the initial state, the arc-shaped stop 9 and the battery baffle 2 are closed (equivalent to the arc-shaped stop 9 locking the battery baffle 2), and the battery 25 is placed on the battery baffle 2. During the flight of the ornithopter, when the battery 25 no longer supplies power, the control servo 17 is activated, and the output shaft of the servo 17 rotates. This rotation drives the release control shaft rocker arm 18 to rotate via the connecting rod 19. The rotation of the release control shaft rocker arm 18 drives the release control shaft 15 to rotate, and the rotation of the release control shaft 15 drives the arc-shaped stop 9 to rotate. The arc-shaped stop 9 separates from the battery baffle 2. Under the gravity of the battery 25 and the battery baffle 2, the battery baffle 2 rotates downward, and the battery 25 falls. The multiple arc-shaped stops 9 have different curvatures, which can realize the orderly release of multiple batteries 25 by controlling the rotation angle of the output shaft of the servo 17.

[0037] Specifically, the launch frame includes two thick main boards 16, with a thin main board 4 arranged between them. Side plates 1 are connected to the sides of the thick main boards 16 and the thin main boards 4. Specifically, the thick main boards 16 and the side plates 1 are snap-fitted together to form a stable fixed structure before being fixedly connected. A thick main board connector 7 is detachably installed on the top of the thick main boards 16, and a thin main board connector 6 is detachably installed on the top of the thin main boards 4. The thick main board connector 7 and the thin main board connector 6 are connected to the fuselage 5 of the flapping-wing aircraft. A battery separator 3 is arranged between the thick main boards 16 and the thin main boards 4, and a battery separator 3 is arranged between two adjacent thin main boards 4. The two ends of the battery separator 3 are respectively connected to the side plates 1. Specifically, the battery separator 3 has protruding portions at both ends, which are fitted into the side fixing plates to ensure the stability of the entire launch frame structure. The top of the thick motherboard 16 and the thin motherboard 4 is provided with a body placement groove 11, and through holes are provided on both sides of the top of the thick motherboard 16 and the thin motherboard 4 located in the body placement groove 11; the thick motherboard connector 7 and the thin motherboard connector 6 are provided with a body buckle groove 12, and threaded holes are provided on both sides of the body buckle groove 12 on the thick motherboard connector 7 and the thin motherboard connector 6; the thick motherboard connector 7 and the thin motherboard connector 6 are provided with a motherboard groove 13; the positions of the through holes and the threaded holes correspond, and screws 23 are installed in the through holes and the threaded holes.

[0038] More specifically, a servo mounting slot 27 is provided on the side of one of the thick motherboards 16, a servo 17 is installed in the servo mounting slot 27, and the servo 17 is detachably connected to the side of the thick motherboard 16.

[0039] Specifically, shaft mounting holes 10 are provided on both sides of the bottom of the thick main board 16 and the thin main board 4. A dispensing control shaft 15 is rotatably installed in the shaft mounting hole 10 on one side of the thick main board 16 and the thin main board 4, and a battery baffle shaft 22 is rotatably installed in the shaft mounting hole 10 on the other side of the thick main board 16 and the thin main board 4.

[0040] Specifically, the curvature of the multiple arc-shaped blocks 9 is set in a gradient, with the arc-shaped blocks 9 closer to the middle of the dispensing control shaft 15 having a larger curvature and the arc-shaped blocks 9 farther from the middle of the dispensing control shaft 15 having a smaller curvature. The end of the battery baffle 2 near the arc-shaped blocks 9 is an arc-shaped structure 31, and the end of the battery baffle 2 away from the arc-shaped blocks 9 is provided with a baffle through hole 29, which is sleeved on the battery baffle rotating shaft 22; specifically, there are retaining ring grooves 30 on both sides of the battery baffle 2 on the battery baffle rotating shaft 22, and elastic retaining rings 26 are installed in the retaining ring grooves 30. Each time a battery is dispensed, the rotation angle of the blocks is driven by the servo motor 17 and can be precisely adjusted. Since the curvature of the blocks is different, the rotation angle required to disengage is also different. The blocks with smaller curvature disengage first, and the blocks with larger curvature disengage later, thereby achieving orderly dispensing of each battery 25. When a battery 25 is depleted, the delivery device can automatically release the battery 25 to reduce the burden on the aircraft.

[0041] like Figure 2 As shown, a parachute compartment 14 is installed on the side of the deployment rack, and a parachute is placed inside the parachute compartment 14. The parachute is connected to a battery 25. During the deployment and descent, the parachute opens, and the battery 25 descends slowly. Specifically, one end of a parachute compartment connector 28 is connected to the top of the parachute compartment 14, and the other end of the parachute compartment connector 28 is installed on the fuselage 5 of the flapping-wing aircraft. More specifically, the parachute compartment 14 is engaged with the thick mainboard 16 and the thin mainboard 4. The parachute compartment 14 has parachute mounting cavities, the number of which matches the number of batteries 25. Each parachute mounting cavity is large enough to accommodate a parachute matching one battery 25, ensuring that the deployed battery 25 can land smoothly on the ground.

[0042] The working process of the lightweight and controllable battery delivery device for ornithopter aircraft in this embodiment is as follows:

[0043] like Figure 5 As shown, in the initial state, with the battery compartment closed, the arc-shaped stop 9 and one end of the battery baffle 2 are engaged, and the battery baffle 2 is blocked by the arc-shaped stop 9, so the battery baffle 2 cannot be rotated downwards to open.

[0044] like Figure 6 As shown, when the battery 25 is not in use, the servo motor 17 is activated, controlling the rotation of the deployment control shaft 15. The arc-shaped block 9 disengages from the arc-shaped structure 31 end of the battery baffle 2, and the battery baffle 2 rotates downward to open. The battery 25 will fall due to gravity, and at the same time, the parachute connected to the battery 25 will be released from the parachute compartment 14, so that the battery 25 can be deployed.

[0045] Example 2

[0046] This embodiment provides an ornithopter, which includes the lightweight and controllable battery deployment device of Embodiment 1. By deploying unused batteries 25, the ornithopter reduces its load and improves its range.

[0047] This embodiment provides an ornithopter, which includes the lightweight and controllable battery deployment device of Embodiment 1. By deploying unused batteries 25, the ornithopter reduces its load and improves its range. The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto; the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A lightweight, controllable battery deployment device for an ornithopter, characterized in that, The device includes a launch rack, the top of which is connected to the fuselage of the flapping wing aircraft. A servo motor is installed at the bottom of the launch rack. A launch control shaft and a battery baffle shaft are rotatably installed at the bottom of the launch rack. Multiple arc-shaped blocks with different curvatures are installed on the launch control shaft. Elastic retaining rings are installed on both sides of the arc-shaped blocks. The output shaft of the servo motor is connected to one end of the servo motor rocker arm, the release control shaft is connected to one end of the release control shaft rocker arm, and the other end of the servo motor rocker arm and the other end of the release control shaft rocker arm are rotatably connected to the two ends of the connecting rod. The battery baffle is rotatably connected to one end of the battery baffle by a rotating shaft, and the other end of the battery baffle cooperates with the arc-shaped block, with the battery placed on the battery baffle.

2. The lightweight and controllable battery deployment device for flapping-wing aircraft according to claim 1, characterized in that, The delivery rack includes two thick main boards, with a thin main board arranged between the two thick main boards, and side plates connected to the sides of the thick main boards and the thin main boards. A thick motherboard connector is detachably installed on the top of the thick motherboard, and a thin motherboard connector is detachably installed on the top of the thin motherboard. The thick motherboard connector and the thin motherboard connector are connected to the fuselage of the flapping-wing aircraft.

3. The lightweight and controllable battery deployment device for flapping-wing aircraft according to claim 2, characterized in that, A servo mounting slot is provided on the side of one of the thick motherboards, a servo is installed in the servo mounting slot, and the servo is detachably connected to the side of the thick motherboard.

4. The lightweight and controllable battery deployment device for flapping-wing aircraft according to claim 2, characterized in that, Shaft mounting holes are provided on both sides of the bottom of the thick main board and the thin main board. A dispensing control shaft is rotatably installed in the shaft mounting hole on one side of the thick main board and the thin main board, and a battery baffle shaft is rotatably installed in the shaft mounting hole on the other side of the thick main board and the thin main board.

5. The lightweight controllable battery deployment device for flapping-wing aircraft according to claim 2, characterized in that, A battery separator is arranged between the thick main board and the thin main board, and the battery separator is arranged between two adjacent thin main boards. The two ends of the battery separator are respectively connected to side plates.

6. The lightweight controllable battery deployment device for flapping-wing aircraft according to claim 2, characterized in that, The top of the thick motherboard and the thin motherboard is provided with a body placement slot, and through holes are provided on both sides of the top of the thick motherboard and the thin motherboard located in the body placement slot; The thick motherboard connector and the thin motherboard connector are provided with body buckle grooves, and threaded holes are provided on both sides of the body buckle grooves on the thick motherboard connector and the thin motherboard connector. The thick motherboard connector and the thin motherboard connector are provided with motherboard grooves. The through hole and the threaded hole are positioned correspondingly, and screws are installed in the through hole and the threaded hole.

7. The lightweight and controllable battery delivery device for flapping-wing aircraft according to claim 1, characterized in that, The arcs of the multiple arc-shaped stops are arranged in a gradient, with the arcs closer to the center of the delivery control axis having a larger arc and the arcs farther away from the center of the delivery control axis having a smaller arc.

8. The lightweight controllable battery deployment device for flapping-wing aircraft according to claim 1, characterized in that, The end of the battery baffle near the arc-shaped block has an arc-shaped structure.

9. The lightweight and controllable battery deployment device for flapping-wing aircraft according to claim 1, characterized in that, A parachute compartment is installed on the side of the launch rack, and a parachute is placed inside the parachute compartment. The parachute is connected to a battery.

10. A flapping-wing aircraft, characterized in that, The flapping-wing aircraft includes the lightweight and controllable battery delivery device for flapping-wing aircraft as described in any one of claims 1-9.

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