Aircraft imitating fan-closing of swan wings
By designing an aircraft that imitates swan wings and using electric cylinders to push the flapping wings, the existing flapping wings cannot take off due to the large weight of the power mechanism, and achieve efficient flight performance and long battery life.
Patent Information
- Application Number
- CN202421870642.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-02
- Publication Date
- 2025-06-27
- Estimated Expiration
- 2034-08-02
AI Technical Summary
The existing flapping wing aircraft lacks practical flapping products due to the large power mechanism, which leads to the problem of inability to take off due to the lack of power mechanism.
An aircraft that imitates swan wing flapping is designed, using an electric cylinder to push the flapping wings, and the opening and closing movement of the upper and lower wings is realized through the coordination of the central axis and the push-pull shaft.
The lift of the flapping wing lift is much greater than the total weight of the flapping wing itself, extending the battery life, reducing energy consumption, and improving flight safety.
Smart Images
Figure CN223031280U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of flapping-wing aircraft, and particularly relates to an aircraft imitating the flapping and closing of a swan's wings. Background Art
[0002] A flapping-wing aircraft refers to a heavier-than-air aircraft whose wings can flap up and down like those of birds and insects, also known as an oscillating-wing aircraft. The flapping wings generate not only lift but also forward thrust.
[0003] Currently, the categories and status of civilian low-altitude aircraft in the market include:
[0004] I. Existing categories of low-altitude aircraft:
[0005] 1. Wing suit aircraft, which are divided into unpowered and powered types. The flight pattern of such aircraft is that the flight altitude becomes lower and lower. The pilot cannot independently increase the flight altitude, which is dangerous and monotonous, and is only for entertainment without practicality.
[0006] 2. Personal aircraft, where the pilot flies by stepping on a jet mechanism. Although it can fly independently, the center of gravity of the overall structure is too high, making it easy to roll over in the air, which is very dangerous, and the flight range is too short, without practicality.
[0007] 3. Electric unmanned aircraft, which have a wide range of uses but are not flapping-wing aircraft.
[0008] II. Current status of existing flapping-wing aircraft:
[0009] Currently, there is no practical flapping-wing aircraft in the field of low-altitude aircraft. The main reasons are as follows:
[0010] 1. The weight of the engine itself is too large.
[0011] Whether it is a gas engine or an electric motor, the weight of these power machinery itself is too large, exceeding the lift that the flapping wings can provide.
[0012] 2. The flapping frequency of the flapping wings of the flapping-wing aircraft is not very high during flight.
[0013] However, the rotational speed of the power output of a gas engine or an electric motor is very high. In order to match the flapping frequency of the flapping wings with the rotational speed of the power output, it is necessary to reduce the rotational speed of the power output machinery. Therefore, a speed reduction mechanism must be configured for the power output machinery. The weight of this speed reduction mechanism is not less than that of the power output machinery. The total weight of the power output machinery and the speed reduction mechanism is much greater than the lift that the flapping wings can provide. So far, there has been no practical product for flapping-wing aircraft.
[0014] In view of this, the inventor of this application has designed an aircraft imitating the flapping and closing of a swan's wings in order to overcome the above technical problems. Content of the Utility Model
[0015] The technical problem to be solved by the present utility model is to overcome the defects in the prior art that the power mechanism of the flapping-wing aircraft is heavy and cannot take off, and to provide an aircraft that imitates the flapping and closing of a swan's wings.
[0016] The present utility model solves the above technical problem through the following technical solutions:
[0017] An aircraft that imitates the flapping and closing of a swan's wings, characterized in that the aircraft includes:
[0018] A frame mechanism and a fuselage frame, and the fuselage frame is installed on the frame mechanism;
[0019] At least two groups of wing assemblies, and the wing assemblies are respectively symmetrically installed on both sides of the fuselage frame;
[0020] At least four electric cylinders, with every two electric cylinders as a group, which are respectively symmetrically installed between both sides of the wing assembly and the fuselage frame, and are used to push the flapping and closing angle of the corresponding wing assembly;
[0021] Each group of the wing assemblies includes an upper wing and a lower wing, and the upper wing and the lower wing are rotationally connected through a central axis, so that the upper wing and the lower wing open and close around the central axis.
[0022] According to an embodiment of the present utility model, the upper wing is rotationally connected to the fuselage frame.
[0023] According to an embodiment of the present utility model, a core plate is provided at the connection between each lower wing and the central axis, and the core plate is rigidly connected to the lower wing.
[0024] According to an embodiment of the present utility model, a first mounting hole and a second mounting hole are provided on the core plate, the central axis is installed in the first mounting hole, and a push-pull shaft rod is installed in the second mounting hole;
[0025] Each electric cylinder is connected to the push-pull shaft rod, and by pushing the push-pull shaft rod to rotate, the upper wing and the lower wing are opened and closed.
[0026] According to an embodiment of the present utility model, each electric cylinder is connected to the core plate through two clamping plates, one end of the clamping plate is rotationally connected to the push-pull shaft rod, the other end of the clamping plate is connected to the internal steel rod of the corresponding electric cylinder through a clamping plate shaft, and the two clamping plates are located on both sides of the clamping plate shaft.
[0027] According to an embodiment of the present utility model, the central axis and the push-pull shaft rod are eccentrically arranged, and after the push-pull shaft rod is stressed, it rotates around the central axis.
[0028] According to an embodiment of the present utility model, a third mounting hole is further provided on the core board, and a blocking shaft rod is installed in the third mounting hole. When the lower wing is opened to a horizontal posture, the blocking shaft rod touches and blocks the housing of the central shaft.
[0029] According to an embodiment of the present utility model, a cylinder shaft is installed at the tail of each cylinder, and the cylinder shaft is rotationally connected to the fuselage frame.
[0030] According to an embodiment of the present utility model, two symmetrically arranged cylinders are arranged side by side on the corresponding cylinder shafts and the push-pull shaft rods, and the cylinder shafts and the push-pull shaft rods are parallel to each other.
[0031] According to an embodiment of the present utility model, the movement trajectories of the push-pull shaft rod and the central shaft are swinging up and down, left and right.
[0032] The positive and progressive effects of the present utility model are as follows:
[0033] The aircraft of the present utility model imitating the flapping of a swan's wings uses cylinders to drive the flapping wings. The lift force generated by the flapping wings is much greater than the total weight of the flapping wing aircraft itself. The flapping wing aircraft has a long endurance time, low energy consumption, and needs to be remotely controlled to fly. It belongs to a low-altitude, slow-speed, large-load aircraft and is relatively safe. BRIEF DESCRIPTION OF THE DRAWINGS
[0034] The above-mentioned and other features, properties and advantages of the present utility model will become more obvious through the following description in conjunction with the drawings and embodiments. In the drawings, the same reference numerals always represent the same features, where:
[0035] Figure 1 is the front view of the aircraft of the present utility model imitating the flapping of a swan's wings.
[0036] Figure 2 is Figure 1 the enlarged view of part A in
[0037] Figure 3 is the top view of the aircraft of the present utility model imitating the flapping of a swan's wings.
[0038] Figure 4 is Figure 3 the enlarged view of part B in
[0039] Figure 5 is the side view of the aircraft of the present utility model imitating the flapping of a swan's wings.
[0040] Figure 6 is the schematic diagram of the swinging of the upper wing and the lower wing in the aircraft of the present utility model imitating the flapping of a swan's wings.
[0041] Figure 7In the aircraft imitating the flapping of a swan's wings according to the present utility model, it is a schematic structural diagram of an electric cylinder.
[0042]
Reference Signs
[0043] Frame mechanism 10
[0044] Fuselage frame 20
[0045] Electric cylinder 30
[0046] Upper wing 40
[0047] Lower wing 50
[0048] Central axis 60
[0049] Backing shaft 41
[0050] Tail fin 100
[0051] Shaft 110
[0052] Core plate 70
[0053] First mounting hole 71
[0054] Second mounting hole 72
[0055] Third mounting hole 73
[0056] Blocking shaft rod 74
[0057] Push-pull shaft rod 80
[0058] A clamping plate 31
[0059] Clamping plate shaft 32
[0060] Inner cylinder rod 33
[0061] Fish-eye hole 34
[0062] Electric cylinder shaft 35 Detailed implementation manners
[0063] To make the above objects, features, and advantages of the present utility model more obvious and understandable, the following detailed description of the specific implementation manners of the present utility model will be given with reference to the accompanying drawings.
[0064] Now, embodiments of the present utility model will be described in detail with reference to the drawings. Now, preferred embodiments of the present utility model will be described in detail, and examples thereof are shown in the drawings. Whenever possible, the same reference signs will be used throughout the drawings to represent the same or similar parts.
[0065] In addition, although the terms used in the present utility model are selected from well-known and commonly used terms, some of the terms mentioned in the description of the present utility model may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of the present description.
[0066] In addition, it is required to understand the present utility model not only through the actual terms used, but also through the meanings implied by each term.
[0067] As Figures 1 to 7 shown, the present utility model discloses an aircraft imitating the flapping and closing of a swan's wings, which includes: a frame mechanism 10, a fuselage frame 20, at least two groups of wing assemblies, and at least four electric cylinders 30. The fuselage frame 20 is installed on the frame mechanism 10. The wing assemblies are respectively symmetrically installed on both sides of the fuselage frame 20. Every two electric cylinders 30 form a group and are respectively symmetrically installed between both sides of the wing assembly and the fuselage frame 20 for pushing the flapping and closing angle of the corresponding wing assembly.
[0068] Each group of the wing assemblies includes an upper wing 40 and a lower wing 50. The upper wing 40 and the lower wing 50 are rotationally connected by a central shaft 60, so that the upper wing 40 and the lower wing 50 open and close around the central shaft 60 to perform a flapping and closing action. The upper wing 40 is rotationally connected to the fuselage frame 20 through a backing shaft 41.
[0069] The aircraft further includes a tail fin 100. The tail fin 100 is rotationally installed at the tail of the fuselage frame 20, for example, rotationally connected to the fuselage frame 20 through a shaft 110 to realize the operation of lifting up and down.
[0070] In this embodiment, the aircraft can be an ornithopter. Two or more electric cylinders 30 are used and divided into left and right groups to respectively push the left and right flapping wings. For example, the aircraft currently uses four electric cylinders 30, and there are 2 electric cylinders in each of the left and right groups. The two electric cylinders 30 are respectively arranged at both ends of the central shaft 60 to increase the thrust. Two groups are respectively independently configured with PLC servo electric control devices, which can accurately control the flapping and closing angles of the wings on both sides and make full use of the lifting force of the airflow. By using multiple electric cylinders 30 here, the thrust can be greatly increased while the mechanical weight of itself increases very little, and the effective load of the ornithopter can be increased a lot.
[0071] Further preferably, the left and right wing assemblies of the aircraft can be respectively independently controlled by the electric cylinders 30, that is, the wing assemblies on both sides can respectively flap and close or stop independently, which is convenient for the ornithopter to change direction.
[0072] Preferably, a core plate 70 is provided at the connection between each lower wing 50 and the central shaft 60, and the core plate 70 is rigidly connected to the lower wing 50.
[0073] Further, a first mounting hole 71 and a second mounting hole 72 (such as a round hole with a diameter of 30 mm) are provided on the core plate 70. The central shaft 60 is installed in the first mounting hole 71, and a push-pull shaft rod 80 is installed in the second mounting hole 72. Each electric cylinder 30 is connected to the push-pull shaft rod 80. By pushing the push-pull shaft rod 80 to rotate, the upper wing 40 and the lower wing 50 are opened and closed.
[0074] Each electric cylinder 30 is connected to the core plate 70 through two clamping plates 31. One end of the clamping plate 31 is rotatably connected to the push-pull shaft rod 80, and the other end of the clamping plate 31 is connected to the inner cylinder rod 33 of the corresponding electric cylinder 30 through a clamping plate shaft 32. The two clamping plates 31 are located on both sides of the clamping plate shaft 32.
[0075] For example, the length of the clamping plate 31 is 385 mm, and two holes with a diameter of 30 mm are provided. One hole installs the clamping plate shaft 32, and the other hole installs the push-pull shaft rod 80.
[0076] The push-pull shaft rod 80 is installed in the 30-mm diameter hole of the clamping plate 31 and also installed in the fisheye hole 34 (provided at the top of the cylinder rod, such as a round hole with a diameter of 30 mm) of the inner cylinder rod of the electric cylinder 30. The clamping plate 31 is rigidly connected to the inner cylinder rod of the electric cylinder 30. The cylinder rod in the electric cylinder 30 can extend and retract to make a reciprocating motion.
[0077] Here, the push-pull shaft rod 80 connects the inner cylinder rod 33, the clamping plate 31, the clamping plate shaft 32, the core plate 70, and the lower wing 50 together.
[0078] Preferably, the central shaft 60 and the push-pull shaft rod 80 are eccentrically arranged. When the push-pull shaft rod 80 is stressed, it rotates around the central shaft 60. After the push-pull shaft rod 80 is subjected to a tensile force, it drives the lower wing 50 to rotate around the 30-mm diameter central shaft 60 through the clamping plate 31, the clamping plate shaft 32, and the core plate 70.
[0079] During flight, the movement trajectory of the push-pull shaft rod 80 is to swing up, down, left, and right. Therefore, the connection between the cylinder rod of the electric cylinder and the push-pull shaft rod 80 is a rotatable movable connection. The connection between the bottom single-ear hole 36 of the electric cylinder 30 and the fuselage frame 20 is also a rotatable movable connection.
[0080] Therefore, during flight, the posture of the electric cylinder 30 is also in a posture of swinging up, down, left, and right. Due to the light weight of the electric cylinder 30 itself, it is suitable for swinging installation. The trajectory of the central shaft 60 that drives the upper and lower wings to fan and close is also to swing up, down, left, and right. Since the central shaft 60 is the center of gravity of the upper and lower wings, the swinging installation of the electric cylinder 30 can obtain the highest efficiency of thrust output.
[0081] In addition, a third mounting hole 73 is also provided on the core board 70, and a blocking shaft rod 74 is installed in the third mounting hole 73. When the lower wing 50 is fanned out to the horizontal posture, the blocking shaft rod 74 touches and is blocked by the housing of the central shaft 60, preventing the lower wing from fanning out too far.
[0082] An electric cylinder shaft 35 is installed at the tail of each electric cylinder 30, and is rotationally connected to the fuselage frame 20 through the electric cylinder shaft 35. Two symmetrically arranged electric cylinders 30 are arranged side by side on the corresponding electric cylinder shafts 35 and push-pull shaft rods 80, and the electric cylinder shafts 35 and push-pull shaft rods 80 are parallel to each other.
[0083] The movement trajectories of the push-pull shaft rod 80 and the central shaft 60 are swinging up and down, left and right. In this way, when flying, while increasing the thrust of the upper and lower wing frames, the flight stability and rigidity of the upper and lower wing frames are increased.
[0084] For example, in this application, the length of one side of the wing of the aircraft is set to 2465 mm, and the width is set to 1142 mm. The area of one side of the wing is about 2.8 square meters, and the total area of the two wings is about 5.6 square meters. The electric cylinders are installed in the front and back of the central axis of the wing frame, which can prevent the wing frame from being twisted and deformed during flight.
[0085] In this application, the aircraft adopts 4 electric cylinders, a battery, an electronic controller, and the fuselage structure of a flapping wing aircraft (i.e., the aircraft), with a total weight of about 500 kg. The total area of the flapping wings is 5.6 square meters, and the weight borne per square meter of the flapping wings is about 89.3 kg, that is, the weight borne per square centimeter of the flapping wings is about 8.93 g.
[0086] Each of the configured electric cylinders has a round-trip thrust of 534 kg, and the total round-trip thrust of the four electric cylinders is 2136 kg in total. The lift provided by the flapping wings is 38.2 g per square centimeter. The lift generated by the electric cylinders driving the flapping wings is much greater than the total weight of the flapping wing aircraft.
[0087] Of course, the above dimensions and load of the aircraft are only for illustrative purposes and are not intended as a limitation. The aircraft can be designed and selected according to actual needs.
[0088] According to the above description, the aircraft of the present utility model that imitates the wing flapping of a swan uses electric cylinders to drive the flapping wings, and has high energy utilization efficiency. When gliding with the wings spread, it does not consume electricity. The lift generated by the electric cylinders driving the flapping wings is much greater than the total weight of the flapping wing aircraft itself. The electric cylinders are light in weight and large in output power, and can output power intermittently and consume electricity intermittently. This application utilizes these two characteristics of the electric cylinders, which can greatly extend the endurance time and endurance mileage of the flapping wing aircraft.
[0089] In summary, the aircraft of the present utility model that imitates the flapping of a swan's wings uses an electric cylinder to drive the flapping wings. The lift force generated by the flapping wings is much greater than the total weight of the flapping-wing aircraft itself. The flapping-wing aircraft has a long endurance time and low energy consumption. It needs to be remotely controlled to fly. It belongs to a low-altitude, slow-speed, large-load aircraft and is relatively safe.
[0090] For those skilled in the art, the above invention disclosure is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still fall within the spirit and scope of the exemplary embodiments of this application.
[0091] At the same time, specific terms are used in this application to describe the embodiments of this application. Such as "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.
[0092] Although the specific implementation manners of the present utility model have been described above, those skilled in the art should understand that these are only examples. The protection scope of the present utility model is defined by the appended claims. Those skilled in the art can make various changes or modifications to these implementation manners without departing from the principle and essence of the present utility model, but these changes and modifications all fall within the protection scope of the present utility model.
Claims
1. A flying machine imitating the flapping of swan wings, characterized in that: The aircraft comprises: A frame mechanism and a fuselage frame, wherein the fuselage frame is mounted on the frame mechanism; At least two sets of wing assemblies, the wing assemblies are symmetrically mounted on both sides of the fuselage frame; At least four electric cylinders, each two of which form a group, are symmetrically installed on both sides of the wing assembly and between the fuselage frame, and are used to push the corresponding wing assembly to a fanning angle; Each group of wing assemblies includes an upper wing and a lower wing, and the upper wing and the lower wing are rotatably connected via a central axis so that the upper wing and the lower wing open and close around the central axis.
2. The flying machine imitating the flapping of swan wings as claimed in claim 1, characterized in that: The upper wing is rotatably connected to the fuselage frame.
3. The flying machine imitating the flapping of swan wings as claimed in claim 1, characterized in that: A core plate is provided at the connection between each lower wing and the central shaft, and the core plate is rigidly connected to the lower wing.
4. The flying machine imitating the flapping of swan wings as claimed in claim 3, characterized in that: The core plate is provided with a first mounting hole and a second mounting hole, the central shaft is mounted in the first mounting hole, and a push-pull shaft rod is mounted in the second mounting hole; Each of the electric cylinders is connected to the push-pull shaft rod, and the upper wing and the lower wing are opened and closed by pushing the push-pull shaft rod to rotate.
5. The flying machine imitating the flapping of swan wings as claimed in claim 4, characterized in that: Each of the electric cylinders is connected to the core plate via two clamps, one end of the clamp is rotatably connected to the push-pull shaft, and the other end of the clamp is connected to the internal steel rod of the corresponding electric cylinder via a clamp shaft, and the two clamps are located on both sides of the clamp shaft.
6. The flying machine imitating the flapping of swan wings as claimed in claim 4, characterized in that: The central axis and the push-pull shaft are eccentrically arranged, and the push-pull shaft rotates around the central axis after being subjected to force.
7. The flying machine imitating the flapping of swan wings as claimed in claim 6, characterized in that: A third mounting hole is also provided on the core plate, and a blocking shaft is installed in the third mounting hole. When the lower wing is flapped to a horizontal posture, the blocking shaft contacts and blocks the shell of the central shaft.
8. The flying machine imitating the flapping of swan wings as claimed in claim 4, characterized in that: An electric cylinder shaft is installed at the tail of each electric cylinder, and is rotatably connected to the fuselage frame through the electric cylinder shaft.
9. The flying machine imitating the flapping of swan wings as claimed in claim 8, characterized in that: The two symmetrically arranged electric cylinders are mounted side by side on the corresponding electric cylinder shafts and the push-pull shaft rods, and the electric cylinder shafts and the push-pull shaft rods are parallel to each other.
10. The flying machine imitating the flapping of swan wings as claimed in claim 9, characterized in that: The movement tracks of the push-pull shaft and the central axis are swinging up, down, left and right.