CN112429197A - Flat flapping wing low-altitude aircraft - Google Patents
Flat flapping wing low-altitude aircraft Download PDFInfo
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- CN112429197A CN112429197A CN202011341900.4A CN202011341900A CN112429197A CN 112429197 A CN112429197 A CN 112429197A CN 202011341900 A CN202011341900 A CN 202011341900A CN 112429197 A CN112429197 A CN 112429197A
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- 230000005540 biological transmission Effects 0.000 claims description 31
- 230000001360 synchronised effect Effects 0.000 claims description 2
- 230000033001 locomotion Effects 0.000 abstract description 8
- 230000005484 gravity Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to the technical field of aircrafts, in particular to a flat flapping wing low-altitude aircraft, which comprises a rack, wherein the front end of the rack is provided with a nose, the tail end of the rack is provided with a propelling device, a first flying unit, a second flying unit and a third flying unit are sequentially arranged between the nose and the propelling device, the second flying unit is arranged at the central position between the first flying unit and the third flying unit and is arranged at the gravity center position of the rack, a control circuit is arranged on the rack, the first flying unit, the second flying unit and the third flying unit are respectively controlled by the control circuit, and the first flying unit and the third flying unit synchronously lift and vertically stagger with the second flying unit. By adopting the structure, the lift force is generated to realize the take-off of the aircraft under the matching action of the first flying unit, the second flying unit and the third flying unit, and the forward movement is realized under the action of the propelling device.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a flat flapping wing low-altitude aircraft.
Background
The lift device of an aircraft is an aerodynamic-based device, and can be divided into a fixed wing and a rotor wing according to the structure, and the fixed wing aircraft generally has a fuselage and symmetrically arranged fixed wings, and is powered by a propeller to obtain larger flight speed and maneuverability. The flying principle of the airplane is that relative speed exists between the fixed wing and air, and the air and all surfaces of the fixed wing interact to generate lift force so as to enable the airplane to obtain flying capability. Fixed wing aircraft have the disadvantages of being unable to hover in the air, requiring taxiing takeoff or landing on a runway and support for airport facility construction. A rotary-wing aircraft such as helicopter features that it can take off without runway and hover in sky, and its power system is composed of engine and rotary wings. The defects of the method are that the cruising speed is low, the load capacity is not high, the efficiency is low, but the dependence on ground facilities is little.
The autorotation gyroplane is an aircraft combining two modes of a fixed wing and a rotor wing, and the main structure of the autorotation gyroplane comprises the rotor wing, a wheel type undercarriage and a propeller, wherein the propeller drives the autorotation gyroplane to slide on a runway, air and rotor blades interact in the sliding process, the air can push the rotor blades to rotate, the rotor blades rotate and generate acting force in the relative sliding direction, and when the rotating speed of the rotor blades is high enough, the acting force makes the aircraft lift off to realize flight. Its advantages are low requirement to take-off runway, long running distance, and limited application range. Accordingly, the prior art is yet to be improved and developed.
Disclosure of Invention
Aiming at the problems, the invention provides a flat flapping wing low-altitude aircraft, which effectively solves the defects of the prior art.
In order to achieve the purpose, the technical scheme applied by the invention is as follows:
the utility model provides a flat flapping wing low-altitude aircraft, which comprises a frame, the frame front end is equipped with the aircraft nose, the frame tail end is equipped with advancing device, be equipped with first flight unit between aircraft nose and the advancing device in proper order, second flight unit and third flight unit, the second flight unit is located the central point between first flight unit and the third flight unit and is put, and locate the focus position of frame, be equipped with control circuit in the frame, first flight unit, second flight unit and third flight unit are respectively through control circuit control, first flight unit and the synchronous lift action of third flight unit, and with the crisscross lift action of second flight unit from top to bottom.
According to the scheme, the first flying unit comprises a first short flat flapping wing, a first transmission rod, a first sleeve, a first support, a first fixing rod, a first crank rotating wheel and a first driving motor, wherein the first sleeve is fixed on the rack through the first support, the first short flat flapping wing is fixed at the upper end of the first transmission rod, the lower end of the first transmission rod penetrates through the first sleeve and is hinged to the first fixing rod, the first fixing rod is fixed on the first crank rotating wheel, the first driving motor drives the first crank rotating wheel to rotate, and a circuit of the first driving motor is connected to a control circuit.
According to the scheme, the second flying unit comprises a long flat flapping wing, a second transmission rod, a second sleeve, a second support, a second fixing rod, a second crank rotating wheel and a second driving motor, the second sleeve is fixed on the rack through the second support, the long flat flapping wing is fixed at the upper end of the second transmission rod, the lower end of the second transmission rod penetrates through the second sleeve and is hinged to the second fixing rod, the second fixing rod is fixed on the second crank rotating wheel, the second driving motor drives the second crank rotating wheel to rotate, and the second driving motor is connected to the control circuit in a circuit mode.
According to the scheme, the third flying unit comprises a second short flat flapping wing, a third transmission rod, a third sleeve, a third support, a third fixing rod, a third crank rotating wheel and a third driving motor, the third sleeve is fixed on the rack through the third support, the second short flat flapping wing is fixed at the upper end of the third transmission rod, the lower end of the third transmission rod penetrates through the third sleeve and is hinged to the third fixing rod, the third fixing rod is fixed on the third crank rotating wheel, the third driving motor drives the third crank rotating wheel to rotate, and a third driving motor circuit is connected to the control circuit.
According to the scheme, the short flat flapping wing I of the first flight unit, the long flat flapping wing of the second flight unit and the short flat flapping wing II of the third flight unit have the same structure, the upper side plane of the short flat flapping wing I of the first flight unit is a spoiler wing surface, and the lower side plane of the short flat flapping wing I of the second flight unit is a fanning wing surface; the spoiler airfoil is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil protrudes upwards relative to the rotating plane of the flat flapping wing, and the longitudinal projection planes of the spoiler airfoil and the fan-moving airfoil are in an asymmetric structure.
According to the scheme, the front side edges of the turbulence wing surface and the fanning wing surface are mutually closed to form a front wing edge, and the rear side edges of the turbulence wing surface and the fanning wing surface are mutually closed to form a rear wing tail; the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil is located is close to the front wing edge.
According to the scheme, an attack angle C exists between the fanning wing surface and the plane of the flat flapping wing, and the value range of C is-2-6 degrees.
According to the scheme, the propulsion device comprises a driving motor IV and the tail wing, and the driving motor IV drives the tail wing to rotate.
According to the scheme, the bottom of the rack is provided with the wheel type undercarriage.
The invention has the beneficial effects that:
the invention adopts the structure arrangement, the control circuit respectively controls the first flying unit, the second flying unit and the third flying unit to act, and controls the first flying unit and the third flying unit to synchronously lift and control the second flying unit, the first flying unit and the third flying unit to vertically stagger and lift, that is, when the first flying unit and the third flying unit act downwards, the second flying unit acts upwards, when the first flying unit and the third flying unit act upwards, the second flying unit acts downwards, and under the cooperation effect among the first flying unit, the second flying unit and the third flying unit, lift force is generated to realize the take-off of the aircraft, and the forward movement is realized under the effect of the propelling device.
Drawings
FIG. 1 is a top view of the overall structure of the present invention;
FIG. 2 is a side view of the overall structure of the present invention;
fig. 3 is a cross-sectional view of a flat flapping wing of the present invention.
In the figure: 1. a frame; 2. driving a motor IV; 3. a tail wing; 4. a machine head; 5. short and flat flapping wings I; 6. long flat flapping wings; 7. a second short and flat flapping wing; 8. a control circuit; 9. a wheeled landing gear; 20. a spoiler airfoil; 21. a fanning airfoil; 22. a leading fin edge; 23. the rear wing tail; 51. a first transmission rod; 52. a first sleeve; 53. a first bracket; 54. fixing a rod I; 55. a crank rotating wheel I; 56. driving a motor I; 61. a second transmission rod; 62. a second sleeve; 63. a second bracket; 64. a second fixing rod; 65. a crank rotating wheel II; 66. a second driving motor; 71. a third transmission rod; 72. a sleeve III; 73. a third bracket; 74. fixing a rod III; 75. a crank rotating wheel III; 76. driving a motor III;
Detailed Description
The technical solution of the present invention is described below with reference to the accompanying drawings and examples.
As shown in figure 1, the flat flapping wing low-altitude aircraft comprises a frame 1, wherein a nose 4 is arranged at the front end of the frame 1, a propelling device is arranged at the tail end of the frame 1, a first flying unit, a second flying unit and a third flying unit are sequentially arranged between the nose 4 and the propelling device, the second flying unit is arranged at the central position between the first flying unit and the third flying unit and is arranged at the gravity center position of the frame 1, a control circuit 8 is arranged on the frame 1, the first flying unit, the second flying unit and the third flying unit are respectively controlled by the control circuit 8, and the first flying unit and the third flying unit synchronously lift and lift alternately up and down with the second flying unit. The above constitutes the basic structure of the present invention.
The invention adopts the structure arrangement, the control circuit 8 respectively controls the first flying unit, the second flying unit and the third flying unit to act, and controls the first flying unit and the third flying unit to synchronously lift and control the second flying unit, the first flying unit and the third flying unit to vertically stagger and lift, that is, when the first flying unit and the third flying unit act downwards, the second flying unit acts upwards, when the first flying unit and the third flying unit act upwards, the second flying unit acts downwards, and under the cooperation effect among the first flying unit, the second flying unit and the third flying unit, the lifting force is generated to realize the take-off of the aircraft, and the forward movement is realized under the effect of the propelling device.
As shown in fig. 2, the first flying unit includes a short flat flap 5, a transmission rod 51, a sleeve 52, a bracket 53, a fixing rod 54, a crank wheel 55 and a driving motor 56, the sleeve 52 is fixed on the frame 1 through the bracket 53, the short flat flap 5 is fixed on the upper end of the transmission rod 51, the lower end of the transmission rod 51 is hinged on the fixing rod 54 through the sleeve 52, the fixing rod 54 is fixed on the crank wheel 55, the driving motor 56 drives the crank wheel 55 to rotate, and the driving motor 56 is electrically connected to the control circuit 8. With the adoption of the structure, the driving motor I56 is controlled by the control circuit 8 to drive the crank rotating wheel I55 to rotate, so that the driving rod I51 is pulled up and down, and the short flat flapping wing I5 is pulled vertically and up and down due to the fact that the driving rod I51 is positioned in the sleeve I52.
In this embodiment, the second flying unit includes a long flat flapping wing 6, a second transmission rod 61, a second sleeve 62, a second bracket 63, a second fixing rod 64, a second crank wheel 65 and a second driving motor 66, the second sleeve 62 is fixed on the frame 1 through the second bracket 63, the long flat flapping wing 6 is fixed at the upper end of the second transmission rod 61, the lower end of the second transmission rod 61 penetrates through the second sleeve 62 to be hinged to the second fixing rod 64, the second fixing rod 64 is fixed on the second crank wheel 65, the second driving motor 66 drives the second crank wheel 65 to rotate, and the second driving motor 66 is electrically connected to the control circuit 8. By adopting the structure, the driving motor II 66 is controlled by the control circuit 8 to drive the crank rotating wheel II 65 to rotate, so that the driving rod II 61 is pulled up and down, and the long flat flapping wing 6 is pulled up and down vertically due to the fact that the driving rod II 61 is positioned in the sleeve II 62.
In this embodiment, the third flying unit includes a short flat flap 7, a third transmission rod 71, a third sleeve 72, a third bracket 73, a third fixed rod 74, a third crank wheel 75 and a third driving motor 76, the third sleeve 72 is fixed to the frame 1 through the third bracket 73, the short flat flap 7 is fixed to the upper end of the third transmission rod 71, the lower end of the third transmission rod 71 passes through the third sleeve 72 and is hinged to the third fixed rod 74, the third fixed rod 74 is fixed to the third crank wheel 75, the third driving motor 76 drives the third crank wheel 75 to rotate, and the third driving motor 76 is electrically connected to the control circuit 8. By adopting the structure, the driving motor III 76 is controlled by the control circuit 8 to drive the crank rotating wheel III 75 to rotate, so that the driving rod III 71 is pulled up and down, and the short and flat flapping wing II 7 is pulled vertically and vertically under the positioning of the sleeve III 72 by the driving rod III 71.
As shown in fig. 3, the first short flat flapping wing 5 of the first flight unit, the second long flat flapping wing 6 of the second flight unit, and the second short flat flapping wing 7 of the third flight unit have the same structure, and the upper plane is a spoiler wing surface 20 and the lower plane is a fanning wing surface 21; the spoiler airfoil 20 is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil 20 is upward convex relative to a rotating plane of the flat flapping wing, and the spoiler airfoil 20 and the fanning airfoil 21 are in an asymmetric structure in the longitudinal projection plane. By adopting the structure, the driving component drives the transmission rod 9 to vertically reciprocate in the sleeve 11, when the upper layer flat flapping wing 6 rises, the spoiler wing surface 20 interacts with the air above, the air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler wing surface 20, and the pressure difference pushes the flat flapping wing to move forwards; when the flat flapping wing descends, the fanning wing surface 21 interacts with the air below, the flat flapping wing combines with the descending motion to enable the fanning wing surface 21 to form a vector attack angle C, and the vector attack angle C enables a vertical upward acting force to be generated between the fanning wing surface 21 and the air; and the speed of the flying device is faster and faster along with the up-and-down reciprocating motion, and when the flying device reaches a certain speed, the flying device generates lift force to enable the flying device to obtain the lift force to achieve the flying purpose.
In the present embodiment, the front side edges of the spoiler airfoil 20 and the fanning airfoil 21 are closed to form a front wing edge 22, and the rear side edges of the spoiler airfoil 20 and the fanning airfoil 21 are closed to form a rear wing tail 23; the spanwise meridian H at which the maximum camber point of the leading airfoil surface 20 is located is proximate the leading fin edge 22. By adopting the structure, the front wing edge 22 is a curved surface so as to respectively continue the front side edges of the spoiler wing surface 20 and the fanning wing surface 21, the existence of the front wing edge 22 can improve the structural strength of the wing-type flat flapping wing, and the front wing edge 22 is positioned at the front side of the rotation direction of the flat flapping wing, so that the curved front wing edge 22 can reduce the air resistance when the flat flapping wing rotates, and improve the power conversion efficiency of the driving device. In the figure, the X direction is the chord length direction of the airfoil structure, and in the figure, the Z direction is the spanwise direction of the airfoil structure. The contour line of the cross section of the spoiler airfoil 20 along the X direction is in a curve shape relative to the rotating plane of the flat flapping wing, the highest point of the contour line forms a span meridian H along the Z direction, and the span meridian H is positioned on the front curved surface of the spoiler airfoil 20 and is close to the front wing edge 22, so that the spoiler airfoil 20 is in a front-back asymmetric structure. When the flat flapping wings ascend, the spoiler wing surfaces 20 interact with air above, pressure difference is generated between the air and the front side and the rear side of the span longitude line H of the spoiler wing surfaces 20, the pressure difference pushes the flat flapping wings to move forwards, and the two flat flapping wings act in the same direction to rotate unidirectionally by taking the rotating bearing as the center.
In the embodiment, an attack angle C exists between the fanning wing surface 21 and the rotation plane of the flat flapping wing, and the value range of C is-2 to 6 degrees. The flat flapping wing has an angle of attack C on the rotating bearing, which is calculated as the flapping wing surface 21 relative to the plane of rotation of the flat flapping wing. After the flat flapping wing is started, the flat flapping wing reciprocates up and down, the spoiler wing surface 20 moves upwards, air flows through the spoiler wing surface 20 to generate pressure difference on the front side and the rear side of the span longitude line H, the pressure difference forms a forward driving force for the flat flapping wing to enable the flat flapping wing to rotate, at the moment, the front wing edge 22 generates differential speed relative to the air to form resistance for the flat flapping wing, and the driving force overcomes the resistance to drive the flat flapping wing to rotate; the flapping wing surface 21 moves downwards, when the rotating speed of the flat flapping wing is very low, the attack angle C enables the acting force of air relative to the flapping wing surface 21 to be basically vertical to the rotating plane of the flat flapping wing, and the resistance of the lower layer of air to the forward rotating motion of the flat flapping wing is very small, so that the flat flapping wing can obtain higher rotating speed after reciprocating up and down for a period of time. When the rotation speed of the flat flapping wing is high, the fanning wing surface 21 moves downwards and forwards, the vector angle of the vector motion formed by the superposition of the two relative to the rotation plane of the flat flapping wing is larger than the attack angle C, namely the lift force generated by the fanning wing surface 21 is larger as the rotation speed of the flat flapping wing is faster, and the rotation speed of the flat flapping wing can be improved by controlling the up-and-down movement frequency of the flat flapping wing, so that the lift force generated by the flat flapping wing is changed.
In this embodiment, the propulsion device includes a driving motor 2 and a tail wing 3, and the driving motor 2 drives the tail wing 3 to rotate. By adopting the structure, the tail wing 3 is driven to rotate by the driving motor 2, so that the thrust for the aircraft is realized.
In this embodiment, the undercarriage 1 is provided with a wheeled undercarriage 9 at the bottom. By adopting the structure, the aircraft can conveniently slide.
While the embodiments of the present invention have been described, the present invention is not limited to the above-mentioned embodiments, which are only illustrative and not restrictive, and those skilled in the art can make various modifications without departing from the spirit and scope of the present invention as defined by the appended claims.
Claims (9)
1. A flat flapping wing low-altitude aircraft comprises a frame (1), and is characterized in that: frame (1) front end is equipped with aircraft nose (4), frame (1) tail end is equipped with advancing device, be equipped with first flight unit, second flight unit and third flight unit between aircraft nose (4) and the advancing device in proper order, the central point that first flight unit and third flight unit between is located to the second flight unit just locates the barycentric position of frame (1), be equipped with control circuit (8) on frame (1), first flight unit, second flight unit and third flight unit are respectively through control circuit (8) control, first flight unit and the synchronous lift action of third flight unit to crisscross lift action from top to bottom with second flight unit.
2. A flat-flapping wing low-altitude aircraft according to claim 1, wherein: the first flying unit comprises a first short flat flapping wing (5), a first transmission rod (51), a first sleeve (52), a first support (53), a first fixing rod (54), a first crank rotating wheel (55) and a first driving motor (56), wherein the first sleeve (52) is fixed on the rack (1) through the first support (53), the first short flat flapping wing (5) is fixed at the upper end of the first transmission rod (51), the lower end of the first transmission rod (51) penetrates through the first sleeve (52) to be hinged to the first fixing rod (54), the first fixing rod (54) is fixed on the first crank rotating wheel (55), the first driving motor (56) drives the first crank rotating wheel (55) to rotate, and the first driving motor (56) is connected to the control circuit (8) in a circuit mode.
3. A flat-flapping wing low-altitude aircraft according to claim 1, wherein: the second flying unit comprises a long flat flapping wing (6), a second transmission rod (61), a second sleeve (62), a second bracket (63), a second fixing rod (64), a second crank rotating wheel (65) and a second driving motor (66), wherein the second sleeve (62) is fixed on the rack (1) through the second bracket (63), the long flat flapping wing (6) is fixed at the upper end of the second transmission rod (61), the lower end of the second transmission rod (61) penetrates through the second sleeve (62) to be hinged to the second fixing rod (64), the second fixing rod (64) is fixed on the second crank rotating wheel (65), the second driving motor (66) drives the second crank rotating wheel (65) to rotate, and the second driving motor (66) is in circuit connection with the control circuit (8).
4. A flat-flapping wing low-altitude aircraft according to claim 1, wherein: the third flight unit comprises a short flat flapping wing II (7), a transmission rod III (71), a sleeve III (72), a support III (73), a fixing rod III (74), a crank rotating wheel III (75) and a driving motor III (76), wherein the sleeve III (72) is fixed on the rack (1) through the support III (73), the short flat flapping wing II (7) is fixed at the upper end of the transmission rod III (71), the lower end of the transmission rod III (71) penetrates through the sleeve III (72) to be hinged to the fixing rod III (74), the fixing rod III (74) is fixed on the crank rotating wheel III (75), the driving motor III (76) drives the crank rotating wheel III (75) to rotate, and the driving motor III (76) is in circuit connection with the control circuit (8).
5. A flat-flapping wing low-altitude aircraft according to claim 1, wherein: the short flat flapping wing I (5) of the first flight unit, the long flat flapping wing (6) of the second flight unit and the short flat flapping wing II (7) of the third flight unit have the same structure, the upper plane of the short flat flapping wing I is a spoiler wing surface (20), and the lower plane of the short flat flapping wing I is a fanning wing surface (21); the spoiler airfoil (20) is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil (20) is upwards raised relative to a rotating plane of the flat flapping wing, and the spoiler airfoil (20) and the fan-moving airfoil (21) are in an asymmetric structure in the longitudinal projection plane.
6. The flat-flapping low-altitude aircraft according to claim 5, wherein: the front side edges of the spoiler airfoil (20) and the fanning airfoil (21) are mutually closed to form a front wing edge (22), and the rear side edges of the spoiler airfoil (20) and the fanning airfoil (21) are mutually closed to form a rear wing tail (23); the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil (20) is located is close to the front wing edge (22).
7. The flat-flapping low-altitude aircraft according to claim 5, wherein: an attack angle C exists between the fanning wing surface (21) and the plane of the flat flapping wing, and the value range of C is-2-6 degrees.
8. A flat-flapping wing low-altitude aircraft according to claim 1, wherein: the propulsion device comprises a driving motor IV (2) and a tail wing (3), and the driving motor IV (2) drives the tail wing (3) to rotate.
9. A flat-flapping wing low-altitude aircraft according to claim 1, wherein: the bottom of the frame (1) is provided with a wheel type undercarriage (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011341900.4A CN112429197A (en) | 2020-11-26 | 2020-11-26 | Flat flapping wing low-altitude aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011341900.4A CN112429197A (en) | 2020-11-26 | 2020-11-26 | Flat flapping wing low-altitude aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112429197A true CN112429197A (en) | 2021-03-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011341900.4A Withdrawn CN112429197A (en) | 2020-11-26 | 2020-11-26 | Flat flapping wing low-altitude aircraft |
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| Country | Link |
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| CN (1) | CN112429197A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6089501A (en) * | 1998-06-22 | 2000-07-18 | Frost; Stanley A. | Tandem-rotor gyroplane |
| US20140034774A1 (en) * | 2011-09-12 | 2014-02-06 | Eurocopter | Fast, long-range aircraft |
| CN105775117A (en) * | 2016-04-19 | 2016-07-20 | 倪德玉 | Helicopter taking off and landing vertically and flying horizontally and application thereof |
| CN207029551U (en) * | 2017-03-13 | 2018-02-23 | 北京天宇新超航空科技有限公司 | A kind of combined type tilt rotor helicopter |
| CN108995804A (en) * | 2018-08-01 | 2018-12-14 | 北京理工大学 | The bionic Aircraft for flutterring rotor and the conversion of flapping flight mode is realized based on the deformation wing |
| CN111776206A (en) * | 2020-07-31 | 2020-10-16 | 江富余 | Three-rotor helicopter with unequal chord lengths |
-
2020
- 2020-11-26 CN CN202011341900.4A patent/CN112429197A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6089501A (en) * | 1998-06-22 | 2000-07-18 | Frost; Stanley A. | Tandem-rotor gyroplane |
| US20140034774A1 (en) * | 2011-09-12 | 2014-02-06 | Eurocopter | Fast, long-range aircraft |
| CN105775117A (en) * | 2016-04-19 | 2016-07-20 | 倪德玉 | Helicopter taking off and landing vertically and flying horizontally and application thereof |
| CN207029551U (en) * | 2017-03-13 | 2018-02-23 | 北京天宇新超航空科技有限公司 | A kind of combined type tilt rotor helicopter |
| CN108995804A (en) * | 2018-08-01 | 2018-12-14 | 北京理工大学 | The bionic Aircraft for flutterring rotor and the conversion of flapping flight mode is realized based on the deformation wing |
| CN111776206A (en) * | 2020-07-31 | 2020-10-16 | 江富余 | Three-rotor helicopter with unequal chord lengths |
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Application publication date: 20210302 |