CN217554180U - Bionic flapping wing aircraft capable of amphibious autonomous take-off and landing in waterway - Google Patents
Bionic flapping wing aircraft capable of amphibious autonomous take-off and landing in waterway Download PDFInfo
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- CN217554180U CN217554180U CN202123400637.4U CN202123400637U CN217554180U CN 217554180 U CN217554180 U CN 217554180U CN 202123400637 U CN202123400637 U CN 202123400637U CN 217554180 U CN217554180 U CN 217554180U
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Abstract
The utility model discloses a bionical flapping wing aircraft that can amphibious independently take off and land in water route, including frame and the fin fixed station that articulates at the frame afterbody, be equipped with No. three steering engines on the fin fixed station, the output shaft fin of No. three steering engines, the frame afterbody is equipped with No. two steering engines, the output shaft of No. two steering engines is equipped with the connecting rod No. one, be equipped with the connecting rod No. two on the fin fixed station, the tip of a connecting rod and No. two connecting rods all articulates with No. three connecting rods, be equipped with the flapping wing in the frame and control the flapping wing fan-operated steering engine No. one, still be equipped with in the frame for a steering engine, no. two steering engines, no. three steering engines provide the battery case of electric quantity, frame head and afterbody all are equipped with the culvert way screw, the frame bottom is equipped with the flotation pontoon. The utility model adopts the mixed layout of the rotor wings and the flapping wings, and does not need manual gliding takeoff or bouncing takeoff under the action of the ducted propeller, thereby realizing free take-off and landing and being more convenient and practical; install the flotation pontoon additional, can satisfy the autonomic take off and land of surface of water and land simultaneously.
Description
Technical Field
The utility model relates to an aircraft field especially relates to a but bionical flapping wing aircraft of amphibious autonomic take off and land in water route.
Background
The unmanned aerial vehicle is mainly divided into a rotor wing, a fixed wing and a flapping wing. The bionic flapping wing type aircraft is an aircraft with a new principle, a new concept and a new technology which are highly integrated, and compared with the aircraft with a rotor wing and a fixed wing, the bionic flapping wing type aircraft has the characteristics of compact structure, good maneuverability, high flying efficiency and the like. The method has wide application scenes in both military activities and human natural activities, and plays a relatively important role. The flying device has the characteristics of small volume and high flying efficiency, so that the flying device is suitable for shuttling flight and even stopping in complex environments such as urban building groups, dense forests and the like; the method has the characteristics of strong concealment and small mechanical noise, and is particularly suitable for exploration of human and nature and research and protection of scarce birds; the high bionic, large lifting force and long endurance make it possess wide development prospect.
Firstly, most flapping wing aircrafts on the market at present adopt a hand-throwing type take-off and landing method, cannot take off and land autonomously, and have high danger coefficient and great challenge to take-off sites; secondly, in order to solve the problem of hand-thrown take-off and landing, other special means are adopted for part of flapping wing aircrafts, so that either the basic principle of bionics is destroyed, or the added take-off and landing device is too complex; finally, birds can take off and land freely on the water surface, but no flapping wing type aircraft capable of taking off and land autonomously on the water surface and performing overwater operation exists at present.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art's not enough, provide a simple structure light, can independently take off and land, can carry out the bionical flapping wing aircraft of operation on water.
The purpose of the utility model is realized through the following technical scheme:
the utility model provides a but bionical flapping wing aircraft of amphibious autonomic take-off and landing in water route, including the frame and articulate the fin fixed station at the frame afterbody, the fin fixed station can rotate from top to bottom in vertical direction, be equipped with No. three steering engines on the fin fixed station, the output shaft fin of No. three steering engines, the fin can rotate at the horizontal direction, the frame afterbody is equipped with No. two steering engines, the output shaft of No. two steering engines is on a parallel with the frame and is perpendicular to the output shaft of No. three steering engines, the output shaft of No. two steering engines is equipped with the connecting rod No. one, be equipped with the connecting rod No. two on the fin fixed station, the tip of connecting rod No. one and No. two connecting rods all articulates with No. three connecting rods, be equipped with flapping wing and the steering engine of control flapping wing fanning in the frame, still be equipped with in the frame for a steering engine, no. two steering engines, the battery case that No. three steering engines provided the electric quantity, frame head and afterbody all are equipped with the duct screw, the frame bottom is equipped with the flotation pontoon.
Preferably, the head of the frame is provided with a photoelectric pod.
Preferably, the output shaft of a steering wheel is equipped with the gear No. one, is equipped with two intermeshing's No. two gears in the frame, gear and one of them No. two gear engagement, the eccentric flapping wing connecting rod that is equipped with on No. two gears, the flapping wing includes skeleton, no. two skeletons, no. three skeletons, and the one end of skeleton is articulated with the one end of flapping wing connecting rod, and the other end of skeleton is articulated with No. three skeletons, and the one end of No. two skeletons is articulated with the other end of flapping wing connecting rod, and the other end and No. three skeleton of No. two skeletons are connected, and skeleton still is articulated with the frame No. one.
Preferably, two buoys are symmetrically arranged at the bottom of the frame.
The utility model has the advantages that:
(1) Under the effect of duct screw, do not need manual gliding to take off or the spring takes off, realized independently taking off and land, convenient and practical more has improved flapping wing air vehicle's application scope.
(2) Install the flotation pontoon additional, can satisfy the autonomic take off and land of surface of water and land simultaneously, filled flapping wing type aircraft in the existing market and landed and the practice blank of taking off on water, it is highly bionical to birds further to accomplish, can float for a long time at the surface of water, carries out the surface of water operation, has improved the application scope of aircraft once more.
(3) The hybrid layout of rotor and flapping wings is adopted, the rotor provides ascending power to achieve the purpose of vertical take-off and landing, the flapping wings provide advancing power for the aircraft, the hybrid layout enables the flapping wing aircraft to integrate three flight attitudes of vertical take-off and landing, advancing and hovering, the functions are various, and the operating capability of the aircraft is improved.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the flapping wing configuration;
in the figure, 1-a steering engine, 2-a steering engine, 3-a steering engine, 4-a rack, 5-a battery box, 6-a tail wing, 7-a connecting rod, 8-a connecting rod, 9-a connecting rod, 10-a tail wing fixing platform, 11-a ducted propeller, 12-flapping wings, 13-a photoelectric pod, 14-a buoy, 15-a gear, 16-a gear, 17-a flapping wing connecting rod, 18-a framework, 19-a framework and 20-a framework.
Detailed Description
The technical solutions of the present invention will be described clearly and completely below with reference to embodiments, and it should be understood that the described embodiments are only some embodiments of the present invention, but not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1-2, the present invention provides a technical solution:
the utility model provides a but bionical flapping wing aircraft of amphibious autonomic take off and land in water route, includes frame 4 and articulates the fin fixed station 10 at 4 afterbody in frame, fin fixed station 10 can rotate from top to bottom in vertical direction, and the rotational degree of freedom is 120 degrees, is equipped with No. three steering wheel 3 on the fin fixed station 10, and No. three steering wheel 3's output shaft fin 6, fin 6 can rotate at the horizontal direction, and the rotational degree of freedom is 60 degrees.
No. two steering wheel 2 are arranged at the tail part of the rack 4, the output shaft of the No. two steering wheel 2 is parallel to the rack 4 and is perpendicular to the output shaft of the No. three steering wheel 3, the output shaft of the No. two steering wheel 2 is provided with a connecting rod 7, the tail wing fixing platform 10 is provided with a connecting rod 9, and the end parts of the connecting rod 7 and the connecting rod 9 are hinged to a connecting rod 8. The output shaft of the third steering engine 3 rotates, the first connecting rod 7 rotates, the second connecting rod 9 is driven by the third connecting rod 8, and the empennage fixing platform 10 can rotate up and down along the hinged position due to the fact that the second connecting rod 9 is fixedly connected with the empennage fixing platform 10.
A flapping wing 12 and a first steering engine 1 for controlling the flapping wing 12 to move are arranged on the rack 4, a battery box 5 for supplying electricity to the first steering engine 1, a second steering engine 2 and a third steering engine 3 is also arranged on the rack 4, ducted propellers 11 are arranged at the head and the tail of the rack 4, and a buoy 14 is arranged at the bottom of the rack 4.
Furthermore, the head of the frame 4 is provided with a photoelectric pod 13 for aircraft reconnaissance.
Furthermore, the output shaft of the first steering engine 1 is provided with a first gear 15, the frame 4 is provided with two gears 16 which are meshed with each other, the first gear 15 is meshed with one of the second gear 16, the second gear 16 is eccentrically provided with a hinged flapping wing connecting rod 17, the flapping wing 12 comprises a first framework 18, a second framework 19 and a third framework 20, one end of the first framework 18 is hinged to one end of the flapping wing connecting rod 17, the other end of the first framework 18 is hinged to the third framework 20, one end of the second framework 19 is hinged to the other end of the flapping wing connecting rod 17, the other end of the second framework 19 is connected to the third framework 20, and the first framework 18 is further hinged to the frame 4. Two second gears 16 of the two flapping wings are meshed with each other, one second gear 16 is meshed with the first gear 15, and the first gear 15 rotates to drive the two second gears 16 to rotate towards opposite directions, so that the two flapping wings can simultaneously move upwards or downwards.
Furthermore, two buoys 14 are symmetrically arranged at the bottom of the frame 4, and the two buoys are symmetrically arranged to be beneficial to stable landing of the aircraft and stopping on the water surface.
The aircraft highly imitates birds in appearance and function, and the aircraft body is made of all-carbon fiber composite material, so that the aircraft has the characteristics of light weight, high structural strength, corrosion resistance and the like; the wings use polyester film or cloth art, and the wings are used for supporting the development of a tiny, light and efficient take-off and landing device.
The foregoing is illustrative of the preferred embodiments of the present invention, and it is to be understood that the invention is not limited to the precise forms disclosed herein, and that various other combinations, modifications, and environments may be resorted to, falling within the scope of the invention as defined by the appended claims. But that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention, which is to be limited only by the claims appended hereto.
Claims (4)
1. A bionic flapping wing aircraft capable of being amphibious and taking off and landing independently is characterized in that: comprises a machine frame (4) and an empennage fixing platform (10) hinged at the tail part of the machine frame (4), the empennage fixing platform (10) can rotate up and down in the vertical direction, a third steering engine (3) is arranged on the empennage fixing platform (10), the output shaft of the third steering engine (3) is connected with an empennage (6), the empennage (6) can rotate in the horizontal direction,
the tail part of the rack (4) is provided with a second steering engine (2), the output shaft of the second steering engine (2) is parallel to the rack (4) and is vertical to the output shaft of the third steering engine (3), the output shaft of the second steering engine (2) is provided with a first connecting rod (7), the tail wing fixing platform (10) is provided with a second connecting rod (9), the end parts of the first connecting rod (7) and the second connecting rod (9) are hinged with a third connecting rod (8),
be equipped with flapping wing (12) and control flapping wing (12) fan-moving steering wheel (1) No. one on frame (4), still be equipped with battery case (5) that provide the electric quantity for steering wheel (1), steering wheel (2) No. two, steering wheel (3) No. three on frame (4), frame (4) head and afterbody all are equipped with duct screw (11), and frame (4) bottom is equipped with flotation pontoon (14).
2. The bionic flapping wing aircraft capable of amphibious autonomous take-off and landing according to claim 1, wherein: the head of the frame (4) is provided with a photoelectric pod (13).
3. The bionic flapping wing aircraft capable of amphibious autonomous take-off and landing according to claim 1, wherein the bionic flapping wing aircraft comprises: the output shaft of a steering wheel (1) is equipped with gear (15) No. one, is equipped with two intermeshing No. two gears (16) on frame (4), gear (15) meshes with one of them No. two gears (16), and the off-centre is equipped with articulated flapping wing connecting rod (17) on No. two gears (16), flapping wing (12) are including skeleton (18), no. two skeleton (19), no. three skeleton (20), and the one end of skeleton (18) is articulated with the one end of flapping wing connecting rod (17), and the other end of skeleton (18) is articulated with No. three skeleton (20), and the one end of No. two skeleton (19) is articulated with the other end of flapping wing connecting rod (17), and the other end of No. two skeleton (19) is connected with No. three skeleton (20), and skeleton (18) still articulates with frame (4).
4. The bionic flapping wing aircraft capable of amphibious autonomous take-off and landing according to claim 1, wherein the bionic flapping wing aircraft comprises: two buoys (14) are symmetrically arranged at the bottom of the frame (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123400637.4U CN217554180U (en) | 2021-12-30 | 2021-12-30 | Bionic flapping wing aircraft capable of amphibious autonomous take-off and landing in waterway |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123400637.4U CN217554180U (en) | 2021-12-30 | 2021-12-30 | Bionic flapping wing aircraft capable of amphibious autonomous take-off and landing in waterway |
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| Publication Number | Publication Date |
|---|---|
| CN217554180U true CN217554180U (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202123400637.4U Active CN217554180U (en) | 2021-12-30 | 2021-12-30 | Bionic flapping wing aircraft capable of amphibious autonomous take-off and landing in waterway |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117602070A (en) * | 2023-12-04 | 2024-02-27 | 武汉科技大学 | Flapping wing aircraft power system and flapping wing aircraft thereof |
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2021
- 2021-12-30 CN CN202123400637.4U patent/CN217554180U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117602070A (en) * | 2023-12-04 | 2024-02-27 | 武汉科技大学 | Flapping wing aircraft power system and flapping wing aircraft thereof |
| CN117602070B (en) * | 2023-12-04 | 2024-05-14 | 武汉科技大学 | Flapping wing aircraft power system and flapping wing aircraft thereof |
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