CN112498677A - Flapping wing-like device capable of simultaneously generating thrust and lift - Google Patents
Flapping wing-like device capable of simultaneously generating thrust and lift Download PDFInfo
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- CN112498677A CN112498677A CN202011346902.2A CN202011346902A CN112498677A CN 112498677 A CN112498677 A CN 112498677A CN 202011346902 A CN202011346902 A CN 202011346902A CN 112498677 A CN112498677 A CN 112498677A
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- main shaft
- assembly
- support frame
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention discloses a flapping wing device capable of generating thrust and lift simultaneously, which comprises: the aircraft comprises an aircraft body, a supporting component, two rotary wing components, a driving component, a brake component, a pulling component, a control component and a lifting component, wherein the two rotary wing components are respectively and symmetrically arranged at two sides of the aircraft body, each rotary wing component comprises a revolution main shaft, a rotary arm, a rotation main shaft and a rotary wing part, through the linkage fit among the revolution main shaft, the rotating arm, the rotation main shaft, the rotor part and the driving component, thereby leading the revolution main shaft in the rotary wing component to drive the rotating arm and the rotation main shaft to revolve, and leading the rotation main shaft to rotate, thereby leading the continuously rotating wing panel to generate upward lifting force, leading the arrangement of the pulling assembly to provide forward pulling force or pushing force for the flapping wing device, thereby provide forward ascending thrust and lift for this type of flapping wing device takes off and land for this type of flapping wing device can realize the technical effect of short distance take off and land.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a flapping wing device capable of generating thrust and lift simultaneously.
Background
The flapping rotor aircraft is an aircraft manufactured by simulating bird flight, and lift force and pulling force are generated by using flapping wing surfaces like wings of flying birds, at present, although a great number of experts and scholars conduct a great deal of research and experiments on the flight mode of the flapping rotor aircraft at home and abroad, because the lift force generated by the existing flapping rotor aircraft can be offset in the process of rotor up-going and down-going operation, the development of the flapping rotor aircraft still has a great number of technical difficulties, and therefore, the existing flapping rotor aircraft has poor stability and low safety and poor flexibility and cannot freely change the flight direction of the aircraft.
Therefore, it is an urgent need to solve the problem of the art to provide a flapping wing device with reasonable design, compact structure, easy operation, convenient control, high efficiency, energy saving, capability of generating large lift force, realizing short-distance take-off and landing, and simultaneously generating thrust and lift force.
Disclosure of Invention
The invention aims to solve at least one of the technical problems in the prior art to a certain extent, and provides the flapping wing device which has the advantages of reasonable design, compact structure, easy operation, convenient control, high efficiency and energy conservation, can generate larger lift force, realizes short-distance take-off and landing, and simultaneously generates thrust force and lift force.
In order to achieve the purpose, the invention adopts the following technical scheme:
a flapping-wing like apparatus for producing both thrust and lift, comprising:
a body;
the supporting component comprises two groups of supporting frames, the two groups of supporting frames are respectively and symmetrically arranged on two sides of the machine body and extend outwards along the machine body, and one end of each supporting frame is fixedly connected with the machine body;
the two rotor wing assemblies are respectively and correspondingly arranged on two sides of the fuselage and are respectively connected with the other ends of the corresponding support frames;
the driving assembly is arranged on the rotary wing assembly, is in transmission connection with the rotary wing assembly and is used for driving the rotary wing assembly to rotate;
the brake assembly is arranged on the rotor wing assembly, is connected with the rotor wing assembly and is used for controlling the rotor wing assembly to be in a fixed state;
the pulling assembly is arranged at the head of the machine body and is connected with the machine body through a connecting piece;
the control assembly is arranged in the machine body, is electrically connected with the driving assembly, the brake assembly and the pulling assembly and is used for controlling the driving assembly, the brake assembly and the pulling assembly;
the lifting assembly comprises a landing gear and a sliding wheel, the landing gear is a three-point landing gear, the lifting frame is arranged on the bottom end face of the machine body, one end of the landing gear is hinged to the machine body, the other end of the landing gear is provided with the sliding wheel, and the sliding wheel is rotatably connected with the landing gear through a connecting piece.
According to the technical scheme, compared with the prior art, the flapping wing device capable of simultaneously generating the thrust and the lift is provided, the rotating wing assemblies are symmetrically arranged on the two sides of the body respectively, so that the flapping wing device can generate stable lift in the takeoff process, meanwhile, the flapping wing device can also take off forwards while taking off upwards by utilizing the pulling assembly arranged at the head of the body, namely, the flapping wing device can simultaneously generate the pulling force or the thrust, so that the flapping wing device can simultaneously generate the thrust and the pulling force in the takeoff process, and the short-distance takeoff and landing are realized. The flapping wing device capable of simultaneously generating the thrust and the pulling force has the advantages of compact structure, smaller overall size, lighter overall weight and capability of generating larger lift force and thrust in the flying process, so that the beneficial effects of high efficiency and energy conservation in the flying process of the device are achieved.
Furthermore, every group the support frame all includes preceding support frame and back support frame, preceding support frame with back support frame is followed the fuselage axial is evenly arranged, just preceding support frame with back support frame is located respectively and is close to the fuselage head with fuselage afterbody department, preceding support frame axis with back support frame axis parallel arrangement, every the both ends of rotor subassembly pass respectively corresponding preceding support frame with back support frame, and with preceding support frame with back support frame connects.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can effectively guarantee this type of flapping wing device overall structure's stability to guarantee that the rotor wing subassembly provides lasting stable lift for the device.
Furthermore, each rotary wing assembly comprises a revolution main shaft, a rotary arm, a rotation main shaft and a rotary wing part; two ends of the revolution main shaft respectively penetrate through the front support frame and the rear support frame and are rotatably connected with the front support frame and the rear support frame, and the axis of the revolution main shaft is arranged in parallel with the axis of the machine body; the rotating arm is arranged on the revolution main shaft and is close to the end part of the revolution main shaft, and one end of the rotating arm is vertical to and fixedly connected with the revolution main shaft; the rotation main shaft is arranged at the other end of the rotating arm, is perpendicular to and fixedly connected with the other end of the rotating arm, and is arranged in parallel with the revolution main shaft; the rotor part is arranged on the rotation main shaft and is connected with the rotation main shaft.
Adopt the beneficial effect that above-mentioned technical scheme produced to be, can guarantee that this rotor assembly can carry out effectual rotation to produce stable ascending lift at the rotation in-process.
Furthermore, the rotating arm comprises a front rotating arm and a rear rotating arm, the front rotating arm and the rear rotating arm are respectively and symmetrically arranged at two ends of the rotation main shaft and the revolution main shaft, the number of the front rotating arm, the number of the rear rotating arm and the number of the rotation main shafts are the same and are all a plurality, and the number of the rotating wing parts corresponding to the rotation main shafts is a plurality.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can guarantee that the rotor wing subassembly continuously produces lift at rotatory in-process, makes the structure of this type of flapping wing device compacter simultaneously, and stability is stronger.
Furthermore, the rotor wing subassembly still includes the rotor wing frame, the rotor wing frame is located on the rotation main shaft and with rotation main shaft fixed connection, the rotor wing frame is located the correspondence the rotor wing portion is outside, is used for the protection the rotor wing portion avoids the great impact force of air current.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can effectively protect the rotor portion and avoid the air current to strike to the life of extension rotor portion, and then improve the security of this aircraft operation in-process.
Further, the rotor section includes center pin, bearing, rolling disc and fin, the perpendicular and fixed connection of one end of center pin is in on the rotation main shaft, the bearing rotates to be connected on the center pin, rolling disc fixed connection be in on the circumference lateral wall of bearing, the one end of fin is located on the periphery of rolling disc, and with rolling disc fixed connection, the fin is last airfoil and all is curved biconvex symmetrical wing type with lower airfoil, just the leading edge of fin is thicker, and the trailing edge is thinner.
Furthermore, the number of the vanes is multiple, the vanes are uniformly arranged on the same circumferential surface, and the directions of the leading edges of the vanes are the same.
Further, the airfoil is one of a NACA0012 airfoil or a NACA0016 airfoil.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can realize that the fin of rotor portion continuously produces ascending lift at the in-process that rotates.
Furthermore, each rotor part comprises two coaxially arranged rotating disks, wherein the two rotating disks are provided with fins, and the direction of the front edge of each fin on the rotating disk on the upper layer is opposite to that of the front edge of each fin on the rotating disk on the lower layer.
The beneficial effect who adopts above-mentioned technical scheme to produce is, not only makes the structure of this type of flapping wing device mesopter wing subassembly compacter, still makes this type of flapping wing device can receive bigger lift under the rotation effect of double-deck fin, and simultaneously, leading edge opposite direction's setting makes the fin can offset because the fin rotates and act on the epaxial torsion of center at the rotation in-process in the double-deck fin.
Furthermore, the driving assembly comprises a first driving motor, a driving wheel, a driven wheel and a second driving motor, the first driving motor is fixedly connected to the front support frame or the rear support frame through a connecting piece, the output end of the first driving motor is in transmission connection with the driving wheel, the driven wheel is arranged at one end of the revolution main shaft and is concentrically arranged with and fixedly connected to the revolution main shaft, the driving wheel is meshed with the driven wheel, the second driving motor is fixed at one end of the rotation main shaft through a connecting piece, and the output shaft of the second driving motor is in transmission connection with the rotation main shaft.
The flapping rotor wing device has the advantages that the first driving motor is used for driving the revolution spindle to revolve, and the second driving motor is used for driving the rotation spindle to rotate, so that the rotation of the rotation spindle can be realized while the revolution spindle drives the rotating arm and the rotation spindle to revolve; and, utilize the transmission relation of being connected of second driving motor and rotation main shaft, make the rotation main shaft in the device in the operation process that moves downwards, drive the rotation main shaft by the second driving motor and make the rotor subassembly rotating surface of locating on the rotation main shaft keep parallel with the horizontal plane all the time, thereby make the fin continuously provide vertical ascending great lift for the aircraft in high-speed rotatory in-process, simultaneously, in the revolution of rotation main shaft is ascending in-process, second driving motor drive rotor subassembly makes rotor subassembly rotating surface keep the vertical state with the rocking arm axis all the time, thereby make rotor subassembly ascending in-process not produce resistance or produce less resistance, vertical ascending lift that the car produced in the rotor subassembly descending in-process can not offset has been ensured, and then provide great lift for the aircraft, and has energy-conserving efficient beneficial effect.
Furthermore, the brake assembly comprises a brake braking part and a photoelectric detection switch, the brake braking part and the photoelectric detection switch are both arranged on the front support frame or the rear support frame and are fixedly connected with the front support frame or the rear support frame, and the brake braking part and the photoelectric detection switch are both electrically connected with the control assembly; the revolution main shaft is provided with a positioning hole, the positioning hole is arranged corresponding to the brake braking piece and the photoelectric detection switch, the photoelectric detection switch is used for detecting the rotating surfaces of the rotating disc and the wing pieces, when the photoelectric detection switch detects that the rotating surfaces of the rotating disc and the wing pieces are in a horizontal state, the photoelectric detection switch sends a detection signal to the control assembly, and the control assembly controls the brake braking piece to act on the positioning hole; the brake braking part comprises a brake motor, a brake rod, a fixing rod, a compression spring and a driving rod, the brake motor is fixed on the front support frame or the rear support frame, a brake wheel is arranged at the output end of the brake motor, and one end of the brake rod is fixedly connected to the circumferential side wall of the brake wheel; one end of the fixed rod is vertically fixed on the front support frame or the rear support frame, the other end of the fixed rod extends outwards, one end of the compression spring is fixedly connected to the middle of the fixed rod, the other end of the compression spring is fixedly connected with one end of the driving rod, the other end of the driving rod is opposite to the positioning hole, and the other end of the brake rod is fixed to the middle of the driving rod; the control assembly is electrically connected with the brake motor and is used for controlling the brake motor.
The technical proposal has the advantages that in the flying process of the flapping-wing device, if emergency situations such as failure and the like need forced landing or energy-saving flying, the revolution main shaft can stop revolution by using the brake and the photoelectric detection switch, and the rotating surface of one of the rotor parts is kept in a horizontal state, thereby ensuring that the rotor part can provide stable lifting force for the flying aircraft, improving the buffer performance of the rotor part, when the rotating disc of the rotary wing part on the autorotation main shaft and the rotating surface of the wing part are in a horizontal state, the photoelectric detection switch sends a signal of detecting that the rotating disc and the rotating surface are in the horizontal state to the control assembly, the control assembly controls the brake motor to enable the brake wheel and the brake rod to rotate, so as to drive the compression spring to stretch and retract, and then the driving rod is embedded into a positioning hole on the revolution main shaft, so that the revolution main shaft stops rotating, and the brake of the flapping wing device is realized.
Furthermore, the pulling assembly comprises a propeller and a third driving motor, the propeller is arranged at the head of the machine body and is rotatably connected with the machine body through a connecting piece, the third driving motor is fixed at the head of the machine body through the connecting piece, and an output shaft of the third driving motor is in transmission connection with the propeller; the control assembly is electrically connected with the third driving motor and used for controlling the opening and closing of the third driving motor.
The technical scheme has the beneficial effects that forward pulling force or pushing force can be provided for keeping the flapping wing device flying, so that great power is provided for forward flying of the flying aircraft.
The aircraft further comprises two wings and an empennage, wherein the two wings are symmetrically arranged on two side walls of the fuselage and fixedly connected with the fuselage, and the wings are positioned above or below the rotor assembly; the tail wing comprises a vertical tail wing and a horizontal tail wing, the vertical tail wing and the horizontal tail wing are both arranged at the tail part of the body and are fixedly connected with the body, the vertical tail wing is used for adjusting the pitching angle of the body, and the horizontal tail wing is used for adjusting the direction of the head part of the body; the control assembly is electrically connected with the vertical tail and the horizontal tail and is used for controlling the vertical tail and the horizontal tail.
The beneficial effect that adopts above-mentioned technical scheme to produce is, can adjust the every single move angle and the left and right sides rotation direction of this type of flapping wing device flight in-process, and then improves the flexibility of this type of flapping wing device.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below.
FIG. 1 is a rear view of a flapping wing apparatus for generating thrust and lift simultaneously in accordance with the present invention;
FIG. 2 is a left side view of a flapping wing apparatus for generating thrust and lift simultaneously in accordance with the present invention;
FIG. 3 is a top view of a flapping wing device capable of generating thrust and lift simultaneously according to the present invention;
FIG. 4 is a schematic structural diagram of a rotor assembly of an flapping wing apparatus for generating thrust and lift simultaneously according to the present invention;
FIG. 5 is an enlarged view of a portion of FIG. 4 at A;
FIG. 6 is a schematic structural diagram of a rotor portion of an flapping wing device capable of generating thrust and lift simultaneously.
Wherein: 1-fuselage, 2-support frame, 21-front support frame, 22-rear support frame, 3-rotor assembly, 31-revolution spindle, 32-rotor arm, 321-front rotor arm, 322-rear rotor arm, 33-rotation spindle, 34-rotor part, 341-center shaft, 342-bearing, 343-rotating disk, 344-wing, 35-rotor frame, 4-drive assembly, 41-first drive motor, 42-driving wheel, 43-driven wheel, 44-second drive motor, 5-brake, 51-brake motor, 52-brake lever, 53-fixed lever, 54-compression spring, 55-drive lever, 6-pulling assembly, 61-propeller, 62-third drive motor, 7-landing gear assembly, 71-landing gear, 72-sliding wheel, 8-wing, 9-tail, 91-vertical tail and 92-horizontal tail.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
The invention discloses a flapping wing device capable of generating thrust and lift simultaneously, which comprises:
a body 1;
the supporting component comprises two groups of supporting frames 2, the two groups of supporting frames 2 are respectively and symmetrically arranged on two sides of the machine body 1 and extend outwards along the machine body 1, and one end of each supporting frame 2 is fixedly connected with the machine body 1;
the number of the rotor wing assemblies 3 is two, the two rotor wing assemblies 3 are respectively and correspondingly arranged on two sides of the fuselage 1, and the two rotor wing assemblies 3 are respectively connected with the other ends of the corresponding support frames;
the driving assembly 4 is arranged on the rotor wing assembly 3, is in transmission connection with the rotor wing assembly 3 and is used for driving the rotor wing assembly 3 to rotate;
the brake assembly is arranged on the rotor wing assembly 3, is connected with the rotor wing assembly 3 and is used for controlling the rotor wing assembly 3 to be in a fixed state;
the pulling assembly 6 is arranged at the head of the machine body 1, and the pulling assembly 6 is connected with the machine body 1 through a connecting piece;
the control assembly is arranged in the machine body 1, is electrically connected with the driving assembly 4, the brake assembly and the pulling assembly 6 and is used for controlling the driving assembly 4, the brake assembly and the pulling assembly 6;
the landing assembly 7, the landing assembly 7 includes undercarriage 71 and movable pulley 72, and undercarriage 71 is three point type undercarriage 71, and undercarriage 71 locates on the bottom face of fuselage 1, and one end of undercarriage 71 is articulated with fuselage 1, and the other end is equipped with movable pulley 72, and movable pulley 72 passes through the connecting piece and is connected with undercarriage 71 rotation.
According to an alternative embodiment of the invention, each group of support frames 2 comprises a front support frame 21 and a rear support frame 22, the front support frame 21 and the rear support frame 22 are uniformly arranged along the axial direction of the fuselage 1, the front support frame 21 and the rear support frame 22 are respectively arranged at the positions close to the head part of the fuselage 1 and the tail part of the fuselage 1, the axes of the front support frame 21 and the rear support frame 22 are arranged in parallel, and two ends of each rotor assembly 3 respectively penetrate through the corresponding front support frame 21 and the corresponding rear support frame 22 and are connected with the front support frame 21 and the rear support frame 22; therefore, the stability of the overall structure of the flapping wing device can be effectively ensured, and the rotating wing component is ensured to provide continuous and stable lift force for the flapping wing device.
According to an alternative embodiment of the present invention, each rotor assembly 3 includes a revolution spindle 31, a rotation arm 32, a rotation spindle 33, and a rotor portion 34; two ends of the revolution main shaft 31 respectively penetrate through the front support frame 21 and the rear support frame 22 and are rotationally connected with the front support frame 21 and the rear support frame 22, and the axis of the revolution main shaft 31 is arranged in parallel with the axis of the machine body 1; the rotating arm 32 is arranged on the revolution main shaft 31 and close to the end part of the revolution main shaft 31, and one end of the rotating arm 32 is vertical to and fixedly connected with the revolution main shaft 31; the rotation main shaft 33 is arranged at the other end of the rotating arm 32, the rotation main shaft 33 is perpendicular to and fixedly connected with the other end of the rotating arm 32, and the rotation main shaft 33 and the revolution main shaft 31 are arranged in parallel; the rotor part 34 is arranged on the rotation main shaft 33 and connected with the rotation main shaft 33; thereby can guarantee that this rotor wing subassembly can carry out effectual rotation to produce at the rotation in-process and stabilize ascending lift.
According to an alternative embodiment of the present invention, the rotating arm 32 includes a front rotating arm 321 and a rear rotating arm 322, the front rotating arm 321 and the rear rotating arm 322 are respectively symmetrically disposed at two ends of the rotation main shaft 33 and the revolution main shaft 31, the number of the front rotating arm 321, the number of the rear rotating arm 322 and the number of the rotation main shafts 33 are the same and are all plural, and the number of the rotor parts 34 disposed corresponding to the rotation main shafts 33 is plural; thereby can guarantee that the rotor wing subassembly continuously produces lift at the rotatory in-process, make the structure of this type of flapping wing device compacter simultaneously, and stability is stronger.
According to an alternative embodiment of the present invention, the rotor assembly 3 further includes a rotor frame 35, the rotor frame 35 is disposed on the rotation main shaft 33 and fixedly connected to the rotation main shaft 33, and the rotor frame 35 is located outside the corresponding rotor portion 34 and is used for protecting the rotor portion 34 from a large impact force of an airflow, so that the rotor portion can be effectively protected from the impact of the airflow, the service life of the rotor portion is prolonged, and the safety of the aircraft during operation is further improved.
According to an alternative embodiment of the present invention, the rotor portion 34 includes a central shaft 341, a bearing 342, a rotating disc 343 and a wing 344, one end of the central shaft 341 is vertically and fixedly connected to the rotation main shaft 33, the bearing 342 is rotatably connected to the central shaft 341, the rotating disc 343 is fixedly connected to a circumferential sidewall of the bearing 342, one end of the wing 344 is disposed on a circumferential surface of the rotating disc 343 and is fixedly connected to the rotating disc 343, the wing 344 is a double convex symmetrical wing type in which an upper wing surface and a lower wing surface are both arc-shaped, and a leading edge of the wing 344 is thicker and a trailing edge thereof is thinner; specifically, each rotor wing part 34 includes three vanes 344, and the three vanes 344 are uniformly arranged on the same circumferential surface, and the directions of the leading edges of the three vanes 344 are the same; specifically, the airfoil 344 is a NACA0016 airfoil, so that the airfoil of the rotor can effectively generate upward lift continuously during the rotation process.
According to an alternative embodiment of the present invention, each rotor 34 includes two coaxially disposed rotating disks 343, three vanes 344 are disposed on each of the two rotating disks 343, and the direction of the leading edge of the vane 344 on the upper rotating disk 343 is opposite to the direction of the leading edge of the vane 344 on the lower rotating disk 343, so that not only the structure of the rotor assembly in the flapping wing device is more compact, but also the flapping wing device can receive a larger lift force under the rotation action of the double-layer vanes, and meanwhile, the arrangement of the opposite leading edge directions in the double-layer vanes enables the vanes to counteract the torsion force acting on the central shaft due to the rotation of the vanes during the rotation process.
According to an alternative embodiment of the present invention, the driving assembly 4 includes a first driving motor 41, a driving wheel 42, a driven wheel 43 and a second driving motor 44, the first driving motor 41 is fixedly connected to the front support frame 21 or the rear support frame 22 through a connecting member, an output end of the first driving motor 41 is in transmission connection with the driving wheel 42, the driven wheel 43 is arranged at one end of the revolution spindle 31 and is concentrically arranged and fixedly connected with the revolution spindle 31, the driving wheel 42 is meshed with the driven wheel 43, the second driving motor 44 is fixed at one end of the rotation spindle 33 through a connecting member, and an output shaft of the second driving motor 44 is in transmission connection with the rotation spindle 33; the flapping rotor wing device has the advantages that the first driving motor is used for driving the revolution spindle to revolve, and the second driving motor is used for driving the rotation spindle to rotate, so that the revolution spindle in the flapping rotor wing device can drive the rotating arm and the rotation spindle to revolve, and the rotation spindle can rotate; and, utilize the transmission relation of being connected of second driving motor and rotation main shaft, make the rotation main shaft in the device in the operation process that moves downwards, drive the rotation main shaft by the second driving motor and make the rotor subassembly rotating surface of locating on the rotation main shaft keep parallel with the horizontal plane all the time, thereby make the fin continuously provide vertical ascending great lift for the aircraft in high-speed rotatory in-process, simultaneously, in the revolution of rotation main shaft is ascending in-process, second driving motor drive rotor subassembly makes rotor subassembly rotating surface keep the vertical state with the rocking arm axis all the time, thereby make rotor subassembly ascending in-process not produce resistance or produce less resistance, vertical ascending lift that the car produced in the rotor subassembly descending in-process can not offset has been ensured, and then provide great lift for the aircraft, and has energy-conserving efficient beneficial effect.
According to an alternative embodiment of the invention, the brake assembly comprises a brake braking part 5 and a photoelectric detection switch, the brake braking part 5 and the photoelectric detection switch are both arranged on the front support frame 21 or the rear support frame 22 and are fixedly connected with the front support frame 21 or the rear support frame 22, and the brake braking part 5 and the photoelectric detection switch are both electrically connected with the control assembly; a positioning hole is formed in the revolution spindle 31, the positioning hole is arranged corresponding to the brake braking member 5 and the photoelectric detection switch, the photoelectric detection switch is used for detecting the rotating surfaces of the rotating disc 343 and the fins 344, when the photoelectric detection switch detects that the rotating surfaces of the rotating disc 343 and the fins 344 are in a horizontal state, the photoelectric detection switch sends a detection signal to the control assembly, and the control assembly controls the brake braking member 5 to act on the positioning hole; the brake braking part 5 comprises a brake motor 51, a brake lever 52, a fixing rod 53, a compression spring 54 and a driving rod 55, the brake motor 51 is fixed on the front support frame 21 or the rear support frame 22, a brake wheel is arranged at the output end of the brake motor 51, and one end of the brake lever 52 is fixedly connected to the circumferential side wall of the brake wheel; one end of the fixed rod 53 is vertically fixed on the front support frame 21 or the rear support frame 22, the other end extends outwards, one end of the compression spring 54 is fixedly connected to the middle part of the fixed rod 53, the other end of the compression spring is fixedly connected with one end of the driving rod 55, the other end of the driving rod 55 is arranged opposite to the positioning hole, and the other end of the brake rod 52 is fixed on the middle part of the driving rod 55; the control component is electrically connected with the brake motor 51 and used for controlling the brake motor 51; thereby make this kind of flapping wing device at the flight in-process, if emergency such as break down needs compel to land or when needing energy-conserving flight, usable brake braking piece and photoelectric detection switch make revolution main shaft stop the revolution, and keep the rotating surface of one of them rotor wing portion in the horizontality, thereby guarantee that rotor wing portion can provide stable lift for the aircraft in flight, improve rotor wing portion's shock-absorbing capacity, when the rotating disc of rotor wing portion on the rotation main shaft and the rotating surface of fin are in the horizontality, photoelectric detection switch sends the signal that detects to be in the horizontality for control assembly, control assembly control brake motor makes brake wheel and brake lever rotate, thereby drive compression spring is flexible, and then make the actuating lever imbed in the locating hole on the revolution main shaft, make the revolution main shaft stop rotating, thereby realize the brake braking to this kind of flapping wing device
According to an alternative embodiment of the invention, the pulling assembly 6 comprises a propeller 61 and a third driving motor 62, the propeller 61 is arranged at the head of the machine body 1 and is rotatably connected with the machine body 1 through a connecting piece, the third driving motor 62 is fixed at the head of the machine body 1 through a connecting piece, and an output shaft of the third driving motor 62 is in transmission connection with the propeller 61; the control component is electrically connected with the third driving motor 62 and is used for controlling the on-off of the third driving motor 62; therefore, forward pulling force or pushing force can be provided for keeping the flapping wing device flying, and then larger power is provided for the flying aircraft to fly forwards.
According to an optional embodiment of the invention, the aircraft further comprises two wings 8 and a tail wing 9, wherein the two wings 8 are symmetrically arranged on two side walls of the fuselage 1 and fixedly connected with the fuselage 1, and the wings 8 are positioned above or below the rotor assembly 3; the tail wing 9 comprises a vertical tail wing 91 and a horizontal tail wing 92, the vertical tail wing 91 and the horizontal tail wing 92 are both arranged at the tail part of the fuselage 1 and are fixedly connected with the fuselage 1, the vertical tail wing 91 is used for adjusting the pitching angle of the fuselage 1, and the horizontal tail wing 92 is used for adjusting the direction of the head part of the fuselage 1; the control assembly is electrically connected with the vertical tail 91 and the horizontal tail 92 and is used for controlling the vertical tail 91 and the horizontal tail 92; therefore, the pitching angle and the left-right rotation direction of the flapping-wing device in the flying process can be effectively adjusted, and the flexibility of the flapping-wing device is improved.
According to the flapping wing device capable of simultaneously generating the thrust and the lift, the rotor wing assemblies are respectively and symmetrically arranged on the two sides of the body, so that the flapping wing device can generate stable lift in the takeoff process, meanwhile, the flapping wing device can also take off forwards while taking off upwards by utilizing the pulling assembly arranged on the head of the body, namely, the flapping wing device can simultaneously generate the pulling force or the thrust, and therefore the flapping wing device can simultaneously generate the thrust and the pulling force in the takeoff process, and the short-distance takeoff and landing are realized. The flapping wing device capable of simultaneously generating the thrust and the pulling force has the advantages of compact structure, smaller overall size, lighter overall weight and capability of generating larger lift force and thrust in the flying process, so that the beneficial effects of high efficiency and energy conservation in the flying process of the device are achieved.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A flapping-wing like apparatus for producing both thrust and lift, comprising:
a fuselage (1);
the supporting assembly comprises two groups of supporting frames (2), the two groups of supporting frames (2) are respectively and symmetrically arranged on two sides of the machine body (1) and extend outwards along the machine body (1), and one end of each supporting frame (2) is fixedly connected with the machine body (1);
the number of the rotary wing assemblies (3) is two, the two rotary wing assemblies (3) are respectively and correspondingly arranged on two sides of the fuselage (1), and the two rotary wing assemblies (3) are respectively connected with the other ends of the corresponding support frames;
the driving assembly (4) is arranged on the rotary wing assembly (3), is in transmission connection with the rotary wing assembly (3) and is used for driving the rotary wing assembly (3) to rotate;
the brake assembly is arranged on the rotary wing assembly (3), is connected with the rotary wing assembly (3) and is used for controlling the rotary wing assembly (3) to be in a fixed state;
the pulling assembly (6) is arranged at the head of the machine body (1), and is connected with the machine body (1) through a connecting piece;
the control assembly is arranged inside the machine body (1), is electrically connected with the driving assembly (4), the brake assembly and the pulling assembly (6) and is used for controlling the driving assembly (4), the brake assembly and the pulling assembly (6);
landing assembly (7), landing assembly (7) include undercarriage (71) and movable pulley (72), undercarriage (71) are three-point undercarriage (71), undercarriage (71) are located on the bottom face of fuselage (1), just one end of undercarriage (71) with fuselage (1) is articulated, and the other end is equipped with movable pulley (72), movable pulley (72) pass through the connecting piece with undercarriage (71) rotate and are connected.
2. The flapping wing device of claim 1, wherein each group of said support frames (2) comprises a front support frame (21) and a rear support frame (22), said front support frame (21) and said rear support frame (22) are arranged axially and uniformly along said fuselage (1), said front support frame (21) and said rear support frame (22) are respectively disposed near the head of said fuselage (1) and the tail of said fuselage (1), the axis of said front support frame (21) and the axis of said rear support frame (22) are arranged in parallel, and both ends of each said rotor assembly (3) respectively pass through the corresponding front support frame (21) and said rear support frame (22) and are connected with said front support frame (21) and said rear support frame (22).
3. The flapping wing device of claim 2, wherein each said rotor assembly (3) comprises a revolution axis (31), a rotation arm (32), a rotation axis (33), and a rotor section (34); two ends of the revolution main shaft (31) respectively penetrate through the front support frame (21) and the rear support frame (22) and are rotatably connected with the front support frame (21) and the rear support frame (22), and the axis of the revolution main shaft (31) is arranged in parallel with the axis of the machine body (1); the rotating arm (32) is arranged on the revolution main shaft (31) and is close to the end part of the revolution main shaft (31), and one end of the rotating arm (32) is vertical to and fixedly connected with the revolution main shaft (31); the rotation main shaft (33) is arranged at the other end of the rotating arm (32), the rotation main shaft (33) is perpendicular to and fixedly connected with the other end of the rotating arm (32), and the rotation main shaft (33) and the revolution main shaft (31) are arranged in parallel; the rotor part (34) is arranged on the rotation main shaft (33) and connected with the rotation main shaft (33).
4. The flapping wing device of claim 3, wherein the rotating arm (32) comprises a front rotating arm (321) and a rear rotating arm (322), the front rotating arm (321) and the rear rotating arm (322) are respectively and symmetrically arranged at two ends of the rotation main shaft (33) and the revolution main shaft (31), the number of the front rotating arm (321), the number of the rear rotating arm (322) and the number of the rotation main shaft (33) are the same and are all multiple, and the number of the rotor parts (34) corresponding to the rotation main shaft (33) is multiple.
5. The flapping wing device capable of generating thrust and lift simultaneously according to claim 4, wherein said rotor assembly (3) further comprises a rotor frame (35), said rotor frame (35) is disposed on the corresponding rotation main shaft (33) and fixedly connected with the rotation main shaft (33), said rotor frame (35) is disposed outside said rotor portion (34) for protecting said rotor portion (34) from a large impact force of the airflow.
6. The flapping wing device according to any one of claims 3-5, wherein the rotor part (34) comprises a central shaft (341), a bearing (342), a rotating disc (343), and vanes (344), one end of the central shaft (341) is vertically and fixedly connected to the rotation main shaft (33), the bearing (342) is rotatably connected to the central shaft (341), the rotating disc (343) is fixedly connected to the circumferential sidewall of the bearing (342), one end of each vane (344) is arranged on the circumferential surface of the rotating disc (343) and is fixedly connected to the rotating disc (343), the vanes (344) are double convex symmetrical wing type with the upper wing surface and the lower wing surface being arc-shaped, and the leading edge of each vane (344) is thicker and the trailing edge thereof is thinner.
7. The flapping wing device of claim 2 wherein the lift force is generated by a combination of a thrust force and a lift force, the driving component (4) comprises a first driving motor (41), a driving wheel (42), a driven wheel (43) and a second driving motor (44), the first driving motor (41) is fixedly connected to the front support frame (21) or the rear support frame (22) through a connecting piece, the output end of the first driving motor (41) is in transmission connection with the driving wheel (42), the driven wheel (43) is arranged at one end of the revolution main shaft (31), and is concentrically arranged and fixedly connected with the revolution main shaft (31), the driving wheel (42) is meshed with the driven wheel (43), the second driving motor (44) is fixed at one end of the rotation main shaft (33) through a connecting piece, and the output shaft of the second driving motor (44) is in transmission connection with the rotation main shaft (33).
8. The flapping wing device capable of generating thrust and lift simultaneously according to claim 6, wherein the brake assembly comprises a brake braking component (5) and a photoelectric detection switch, the brake braking component (5) and the photoelectric detection switch are both arranged on the front support frame (21) or the rear support frame (22) and fixedly connected with the front support frame (21) or the rear support frame (22), and the brake braking component (5) and the photoelectric detection switch are both electrically connected with the control assembly; a positioning hole is formed in the revolution spindle (31), the positioning hole is arranged corresponding to the brake braking piece (5) and the photoelectric detection switch, the photoelectric detection switch is used for detecting the rotating surfaces of the rotating disc (343) and the fins (344), when the photoelectric detection switch detects that the rotating surfaces of the rotating disc (343) and the fins (344) are in a horizontal state, the photoelectric detection switch sends a detection signal to the control assembly, and the control assembly controls the brake braking piece (5) to act on the positioning hole; the brake braking part (5) comprises a braking motor (51), a braking rod (52), a fixing rod (53), a compression spring (54) and a driving rod (55), the braking motor (51) is fixed on the front supporting frame (21) or the rear supporting frame (22), a braking wheel is arranged at the output end of the braking motor (51), and one end of the braking rod (52) is fixedly connected to the circumferential side wall of the braking wheel; one end of the fixing rod (53) is vertically fixed on the front support frame (21) or the rear support frame (22), the other end of the fixing rod extends outwards, one end of the compression spring (54) is fixedly connected to the middle of the fixing rod (53), the other end of the compression spring is fixedly connected with one end of the driving rod (55), the other end of the driving rod (55) is arranged opposite to the positioning hole, and the other end of the brake rod (52) is fixed in the middle of the driving rod (55); the control assembly is electrically connected with the brake motor (51) and used for controlling the brake motor (51).
9. The flapping wing device capable of generating thrust and lift simultaneously according to claim 1, wherein the pulling assembly (6) comprises a propeller (61) and a third driving motor (62), the propeller (61) is arranged at the head of the fuselage (1) and is rotatably connected with the fuselage (1) through a connecting piece, the third driving motor (62) is fixed at the head of the fuselage (1) through a connecting piece, and an output shaft of the third driving motor (62) is in transmission connection with the propeller (61); the control assembly is electrically connected with the third driving motor (62) and is used for controlling the opening and closing of the third driving motor (62).
10. The flapping wing device capable of generating thrust and lift simultaneously according to any one of claims 1-5 and 7-9, further comprising two wings (8) and a tail wing (9), wherein the two wings (8) are symmetrically arranged on two side walls of the fuselage (1) and fixedly connected with the fuselage (1), and the wings (8) are arranged above or below the rotor assembly (3); the tail wing (9) comprises a vertical tail wing (91) and a horizontal tail wing (92), the vertical tail wing (91) and the horizontal tail wing (92) are both arranged at the tail part of the machine body (1) and are fixedly connected with the machine body (1), the vertical tail wing (91) is used for adjusting the pitching angle of the machine body (1), and the horizontal tail wing (92) is used for adjusting the direction of the head part of the machine body (1); the control assembly is electrically connected with the vertical tail (91) and the horizontal tail (92) and is used for controlling the vertical tail (91) and the horizontal tail (92).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346902.2A CN112498677A (en) | 2020-11-26 | 2020-11-26 | Flapping wing-like device capable of simultaneously generating thrust and lift |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346902.2A CN112498677A (en) | 2020-11-26 | 2020-11-26 | Flapping wing-like device capable of simultaneously generating thrust and lift |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112498677A true CN112498677A (en) | 2021-03-16 |
Family
ID=74966178
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011346902.2A Withdrawn CN112498677A (en) | 2020-11-26 | 2020-11-26 | Flapping wing-like device capable of simultaneously generating thrust and lift |
Country Status (1)
| Country | Link |
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| CN (1) | CN112498677A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022110942A1 (en) * | 2020-11-26 | 2022-06-02 | 佛山市神风航空科技有限公司 | Apparatus and method for converting reciprocating motion into continuous rotation and application |
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| US20030096553A1 (en) * | 2001-11-16 | 2003-05-22 | Seung-Woo Kim | Power-driven ornithopter |
| CN1629038A (en) * | 2004-10-02 | 2005-06-22 | 高晓燕 | Aircraft with flapping wings |
| CN104443384A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Rotary wing blade type flapping wing air vehicle |
| CN104494828A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Panel type flapping wing lifting device with electromagnetic brake |
| CN107963211A (en) * | 2017-12-06 | 2018-04-27 | 佛山市神风航空科技有限公司 | A kind of fixed wing aircraft with flapping wing |
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2020
- 2020-11-26 CN CN202011346902.2A patent/CN112498677A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030096553A1 (en) * | 2001-11-16 | 2003-05-22 | Seung-Woo Kim | Power-driven ornithopter |
| CN1629038A (en) * | 2004-10-02 | 2005-06-22 | 高晓燕 | Aircraft with flapping wings |
| CN104443384A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Rotary wing blade type flapping wing air vehicle |
| CN104494828A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Panel type flapping wing lifting device with electromagnetic brake |
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| WO2022110942A1 (en) * | 2020-11-26 | 2022-06-02 | 佛山市神风航空科技有限公司 | Apparatus and method for converting reciprocating motion into continuous rotation and application |
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Application publication date: 20210316 |