CN112455701A - Aircraft convenient to control flight gesture - Google Patents
Aircraft convenient to control flight gesture Download PDFInfo
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- CN112455701A CN112455701A CN202011346740.2A CN202011346740A CN112455701A CN 112455701 A CN112455701 A CN 112455701A CN 202011346740 A CN202011346740 A CN 202011346740A CN 112455701 A CN112455701 A CN 112455701A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 59
- 238000005096 rolling process Methods 0.000 claims 6
- 108010066057 cabin-1 Proteins 0.000 description 9
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects 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
- 238000010276 construction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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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
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or 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
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
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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
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Toys (AREA)
Abstract
The invention relates to the technical field of aircrafts, in particular to an aircraft convenient for controlling flight attitudes, which comprises a cabin, wherein the tail part of the cabin is provided with a propelling device used for controlling the aircraft to move forwards, the bottom of the cabin is provided with a landing gear, the cabin is internally provided with a power device and a control circuit board, the power device is in circuit connection with the control circuit board, the top of the cabin is provided with a flight device and a flight attitude adjusting device, the flight device and the flight attitude adjusting device are respectively driven by the power device, the flight device comprises a sleeve I, a transmission rod I, a rotating bearing I and first rotor wings I symmetrically fixed on two sides of the rotating bearing I, the sleeve I is fixed on the top of the cabin, the upper end of the transmission rod I is fixed on the rotating bearing I, the lower end of the transmission rod passes through the sleeve, the flight attitude adjusting device comprises a first control device and a second control device which are symmetrically arranged on two sides of the flight device.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft convenient for controlling flight attitude.
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 an aircraft convenient for controlling flight attitude, 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:
an aircraft convenient for controlling flight attitudes comprises a cabin, wherein the tail part of the cabin is provided with a propelling device used for controlling the aircraft to move forwards, the bottom of the cabin is provided with a landing gear, the cabin is internally provided with a power device and a control circuit board, the power device is in circuit connection with the control circuit board, the top of the cabin is provided with a flight device and a flight attitude adjusting device, the flight device and the flight attitude adjusting device are respectively driven by the power device, the flight device comprises a sleeve I, a transmission rod I, a rotating bearing I and rotor wings I symmetrically fixed on two sides of the rotating bearing I, the sleeve I is fixed on the top of the cabin, the upper end of the transmission rod I is fixed on the rotating, and the power device is connected with a power device in the cabin, the power device drives the first transmission rod to vertically reciprocate in the first sleeve, and the flight attitude adjusting device comprises a first control device and a second control device which are symmetrically arranged at two sides of the flight device.
According to the scheme, the first control device comprises a second sleeve, a second transmission rod, a second rotating bearing and second rotors symmetrically fixed on two sides of the second rotating bearing, the second sleeve is fixed at the top of the cabin, the upper end of the second transmission rod is fixed on the second rotating bearing, the lower end of the second transmission rod penetrates through the second sleeve and is connected to a power device in the cabin, and the power device drives the second transmission rod to vertically reciprocate in the second sleeve.
According to the scheme, the second control device comprises a third sleeve, a third transmission rod, a third rotating bearing and third rotors symmetrically fixed on two sides of the third rotating bearing, the third sleeve is fixed at the top of the engine room, the upper end of the third transmission rod is fixed on the third rotating bearing, the lower end of the third transmission rod penetrates through the third sleeve and is connected to a power device in the engine room, and the power device drives the third transmission rod to vertically reciprocate in the third sleeve.
According to the scheme, the power device comprises a first driving assembly used for driving the flying device, a second driving assembly used for driving the first control device and a third driving assembly used for driving the second control device, and the first driving assembly, the second driving assembly and the third driving assembly are respectively in circuit connection with the control circuit board.
According to the scheme, the first driving assembly comprises a first connecting rod, a first crank rotating wheel, a first transmission belt and a first driving motor, the upper end of the first connecting rod is hinged to a first transmission rod of the flying device, the lower end of the first connecting rod is fixed to the first crank rotating wheel, and the first driving motor drives the first crank rotating wheel to rotate through the first transmission belt.
According to the scheme, the second driving assembly comprises a second connecting rod, a second crank rotating wheel, a second driving belt and a second driving motor, the upper end of the second connecting rod is hinged to a second transmission rod of the first control device, the lower end of the second connecting rod is fixed to the second crank rotating wheel, and the second driving motor drives the second crank rotating wheel to rotate through the second driving belt.
According to the scheme, the third driving assembly comprises a third connecting rod, a third crank rotating wheel, a third driving belt and a third driving motor, the upper end of the third connecting rod is hinged to a third transmission rod of the second control device, the lower end of the third connecting rod is fixed to the third crank rotating wheel, and the third driving motor drives the third crank rotating wheel to rotate through the third driving belt.
According to the scheme, the first rotor wing, the second rotor wing and the third rotor wing of the second control device of the flight device have the same structure, the upper side plane of the first rotor wing is a turbulent wing surface, and the lower side plane of the first rotor wing 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 a rotating plane of the rotor, and the spoiler airfoil and the fanning airfoil are in an asymmetric structure in the longitudinal projection plane.
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 rotating plane of the rotor wing, and the value range of C is-2-6 degrees.
The invention has the beneficial effects that:
the invention adopts the structure arrangement, the power device is controlled by the control circuit board to drive the flight device to work, so as to drive the first rotary bearing and the first rotary wings on the two sides of the first rotary bearing to vertically reciprocate, so that the first rotary wings rotate around the first rotary bearing in a circumferential direction, the rotating speed of the first rotary wings is faster and faster along with the vertical motion, when a certain rotating speed is reached, the lift force can be generated, and therefore, the effect of vertical take-off of the aircraft is achieved, and the power device is controlled by the control circuit board to drive the flight attitude adjusting device, so as to adjust the flight attitude of the aircraft.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
figure 2 is a cross-sectional view of a rotor of the present invention.
In the figure: 1. a nacelle; 2. a landing gear; 3. a control circuit board; 4. a propulsion device; 6. a first rotor wing; 7. a first connecting rod; 8. rotating the first bearing; 9. a first transmission rod; 10. a crank rotating wheel I; 11. a first sleeve; 12. a first transmission belt; 13. driving a motor I; 14. rotating a second bearing; 15. a second rotor wing; 16. a second transmission rod; 17. a second sleeve; 18. a second connecting rod; 19. a crank rotating wheel II; 20. a second transmission belt; 21. a second driving motor; 22. rotating a bearing III; 23. a third rotor wing; 24. a third transmission rod; 25. a sleeve III; 26. a third connecting rod; 27. a crank rotating wheel III; 28. a third transmission belt; 29. driving a motor III; 30. a spoiler airfoil; 31. a fanning airfoil; 32. a leading fin edge; 33. the rear wing tail.
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 aircraft convenient for controlling flight attitudes comprises a cabin 1, a propelling device 4 used for controlling the aircraft to move forwards is arranged at the tail of the cabin 1, an undercarriage 2 is arranged at the bottom of the cabin 1, a power device and a control circuit board 3 are arranged in the cabin 1, the power device is in circuit connection with the control circuit board 3, a flight device and a flight attitude adjusting device are arranged at the top of the cabin 1, the flight device and the flight attitude adjusting device are respectively driven by the power device, the flight device comprises a sleeve I11, a transmission rod I9, a rotating bearing I8 and rotor blades I6 symmetrically fixed at two sides of the rotating bearing I8, the sleeve I11 is fixed at the top of the cabin 1, the upper end of the transmission rod I9 is fixed on the rotating bearing I8, the lower end of the transmission rod I9 penetrates through the sleeve I11 and is connected with the power device in the cabin 1, the power device drives, the flight attitude adjusting device comprises a first control device and a second control device which are symmetrically arranged on two sides of the flight device. The above constitutes the basic structure of the present invention.
The invention adopts the structure, the power device is controlled by the control circuit board 3 to drive the flight device to work, the power device drives the transmission rod I9 to vertically reciprocate in the sleeve I11, so as to drive the rotary bearing I8 and the rotary wings I6 at two sides of the rotary bearing I8 to vertically reciprocate, the rotary wings I6 circumferentially rotate around the rotary bearing I8, the rotating speed of the rotary wings is faster and faster along with the vertical motion, when reaching a certain rotating speed, the lifting force can be generated, so that the vertical take-off effect of the aircraft is achieved, and the flight attitude adjusting device is controlled by the control circuit board to drive the flight attitude adjusting device by the power device, so that the adjustment of the flight attitude of the aircraft is achieved.
The first control device and the second control device have the same configuration.
In the embodiment, the first control device comprises a second sleeve 17, a second transmission rod 16, a second rotary bearing 14 and a second rotary wing 15 symmetrically fixed on two sides of the second rotary bearing 15, the second sleeve 17 is fixed on the top of the nacelle 1, the upper end of the second transmission rod 16 is fixed on the second rotary bearing 15, the lower end of the second transmission rod 16 penetrates through the second sleeve 17 and is connected to a power device in the nacelle 1, and the power device drives the second transmission rod 16 to vertically reciprocate in the second sleeve 17; the second control device comprises a sleeve III 25, a transmission rod III 24, a rotating bearing III 22 and a rotor wing III 23 symmetrically fixed on two sides of the rotating bearing III 22, the sleeve III 25 is fixed on the top of the cabin 1, the upper end of the transmission rod III 24 is fixed on the rotating bearing III 22, the lower end of the transmission rod III 24 penetrates through the sleeve III 25 and is connected with a power device in the cabin 1, and the power device drives the transmission rod III 24 to vertically reciprocate in the sleeve III 25. By adopting the structure, when the first control device works and the second control device stops, the aircraft can rotate towards the direction of the second control device, otherwise, when the first control device stops and the second control device works, the aircraft can rotate towards the direction of the first control device, or when the rotation speed of the second rotor 15 of the first control device is higher than that of the third rotor 23 of the second control device, the aircraft can rotate towards the direction of the second control device, otherwise, when the rotation speed of the second rotor 15 of the first control device is lower than that of the third rotor 23 of the second control device, the aircraft can rotate towards the direction of the first control device.
It should be noted that the working principle of the first control device and the second control device is the same as that of the flying device, except that the overall structure of the first control device and the second control device is smaller than that of the flying device, and the first control device and the second control device are symmetrically arranged below two sides of the flying device.
In this embodiment, the power device includes a first driving assembly for driving the flying device, a second driving assembly for driving the first control device, and a third driving assembly for driving the second control device, and the first driving assembly, the second driving assembly, and the third driving assembly are respectively connected to the control circuit board 3 through circuits. By adopting the structure, the control circuit board 3 controls different driving components to control the flight device, the first control device and the second control device to work, and further the flight and the flight attitude of the aircraft are controlled.
In this embodiment, the first driving assembly includes a first connecting rod 7, a first crank rotating wheel 10, a first transmission belt 12 and a first driving motor 13, the upper end of the first connecting rod 7 is hinged to a first transmission rod 9 of the flying device, the lower end of the first connecting rod 7 is fixed to the first crank rotating wheel 10, and the first driving motor 13 drives the first crank rotating wheel 10 to rotate through the first transmission belt 12. By adopting the structure, the purpose that the first driving component drives the transmission rod I9 to vertically reciprocate in the sleeve I11 is achieved.
In this embodiment, the second driving assembly includes a second connecting rod 18, a second crank rotating wheel 19, a second driving belt 20 and a second driving motor 21, the upper end of the second connecting rod 18 is hinged to the second transmission rod 16 of the first control device, the lower end of the second connecting rod 18 is fixed to the second crank rotating wheel 19, and the second driving motor 21 drives the second crank rotating wheel 19 to rotate through the second driving belt 20. By adopting the structure, the purpose that the second driving component drives the second transmission rod 16 to vertically reciprocate in the second sleeve 17 is achieved.
In this embodiment, the third driving assembly includes a third connecting rod 26, a third crank wheel 27, a third driving belt 28 and a third driving motor 29, the upper end of the third connecting rod 26 is hinged to the third transmission rod 24 of the second control device, the lower end of the third connecting rod 26 is fixed to the third crank wheel 27, and the third driving motor 29 drives the third crank wheel 27 to rotate through the third driving belt 28. By adopting the structure, the purpose that the third driving component drives the transmission rod III 24 to vertically reciprocate in the sleeve III 25 is achieved.
As shown in fig. 2, the first rotor wing 6 of the flying device, the second rotor wing 15 of the first control device, and the third rotor wing 23 of the second control device have the same structure, and the upper plane thereof is a spoiler wing 30 and the lower plane thereof is a fanning wing 31; the spoiler airfoil 30 is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil 30 protrudes upwards relative to the rotating plane of the rotor, and the spoiler airfoil 30 and the fanning airfoil 31 are in an asymmetric structure in the longitudinal projection plane. By adopting the structure, the first driving assembly drives the transmission rod I9 to vertically reciprocate in the sleeve I11, when the rotor I6 ascends, the spoiler airfoil 30 interacts with air above, the air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler airfoil 30, and the pressure difference pushes the rotor I6 to move forwards, so that the rotor I6 rotates unidirectionally by taking the rotating bearing I8 as a center; when the rotor wing I6 descends, the spoiler surface 31 interacts with the air below, the rotational motion of the rotor wing I6 is combined with the downward motion to enable the spoiler surface 31 to form a vector attack angle C, and the vector attack angle C enables a vertical upward acting force to be generated between the spoiler surface 31 and the air; the first rotor wing 6 converts the up-and-down reciprocating motion into the self rotary motion, the rotating speed of the first rotor wing is faster and faster along with the up-and-down reciprocating motion, and when the first rotor wing reaches a certain rotating speed, the lift force is generated 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 30 and the fanning airfoil 31 are closed to form a front wing edge 32, and the rear side edges of the spoiler airfoil 30 and the fanning airfoil 31 are closed to form a rear wing tail 33; the spanwise meridian H at which the maximum camber point of the leading airfoil surface 30 is located is proximate the leading fin edge 32. By adopting the structure, the front wing edge 32 is a curved surface so as to respectively continue the front side edges of the spoiler airfoil 30 and the spoiler airfoil 31, the structural strength of the wing-shaped rotor wing can be improved due to the front wing edge 32, the front wing edge 32 is positioned at the front side of the rotation direction of the rotor wing, the air resistance borne by the curved surface front wing edge 32 during the rotation of the rotor wing can be reduced, and the power conversion efficiency of the driving device is improved. 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 30 along the X direction is in a curve shape relative to the rotating plane of the rotor 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 30 and is close to the front wing edge 32, so that the spoiler airfoil 30 is in a front-back asymmetric structure. When the rotor wings ascend, the spoiler wing surfaces 30 interact with air above, pressure difference is generated between the front side and the rear side of the wingspan longitude line H of the spoiler wing surfaces 30 by the air, the rotor wings are pushed to move forwards by the pressure difference, and the two rotor wings act in the same direction and rotate unidirectionally by taking the rotating bearing as the center.
In the present embodiment, an attack angle C exists between the flapping wing surface 31 and the rotation plane of the rotor, and the value range of C is-2 ° to 6 °. The rotor has an angle of attack C on the rotary bearing, which is calculated with the spoiler surface 31 relative to the plane of rotation of the rotor. After the rotor wing is started, the spoiler wing surfaces 30 move upwards in a reciprocating mode, air flows through the spoiler wing surfaces 30 to generate pressure difference on the front side and the rear side of the wingspan meridian H, the pressure difference forms forward driving force on the rotor wing to enable the rotor wing to rotate, at the moment, the front wing edge 32 generates differential speed relative to the air to form resistance on the rotor wing, and the driving force overcomes the resistance to drive the rotor wing to rotate; the spoiler airfoil 31 moves downwards, when the rotating speed of the rotor wing is very low, the attack angle C enables air to be basically vertical to the rotating plane of the rotor wing relative to the acting force of the spoiler airfoil 31, and then the lower layer of air causes very little resistance to the forward rotating motion of the rotor wing, so that the rotor wing can obtain higher rotating speed after reciprocating up and down for a period of time. When the rotor speed is higher, the spoiler airfoil 31 both has downward motion and also has forward motion, and the vector angle of the vector motion formed by the superposition of the two relative to the rotor rotation plane is greater than the attack angle C, i.e. the faster the rotation speed of the rotor, the greater the lift force generated by the spoiler airfoil 31, and the rotation speed of the rotor can be improved by controlling the up-and-down motion frequency of the rotor, so that the lift force generated by the rotor can be changed.
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 (10)
1. An aircraft convenient to control flight attitude, includes cabin (1), cabin (1) afterbody is equipped with advancing device (4) that are used for controlling the aircraft to move ahead, cabin (1) bottom is equipped with undercarriage (2), its characterized in that:
be equipped with power device and control circuit board (3) in cabin (1), power device and control circuit board (3) circuit connection, cabin (1) top is equipped with flight device and flight gesture adjusting device, flight device and flight gesture adjusting device are respectively through the power device drive, flight device includes sleeve (11), transfer line (9), rolling bearing (8) and symmetry are fixed in rotor (6) of rolling bearing (8) both sides, sleeve (11) are fixed in cabin (1) top, transfer line (9) upper end is fixed in rolling bearing (8), sleeve (11) are passed to transfer line (9) lower extreme to be connected in the power device in cabin (1), reciprocating motion about vertical is done in sleeve (11) to power device drive transfer line (9), the flight attitude adjusting device comprises a first control device and a second control device which are symmetrically arranged on two sides of the flight device.
2. An aircraft for facilitating control of attitude in accordance with claim 1, wherein: first controlling means includes sleeve two (17), transfer line two (16), rolling bearing two (14) and the symmetry is fixed in two (15) rotors of rolling bearing two (15) both sides, sleeve two (17) are fixed in cabin (1) top, transfer line two (16) upper end is fixed in rolling bearing two (15), transfer line two (16) lower extreme passes sleeve two (17) to be connected in the power device in cabin (1), power device drive transfer line two (16) do perpendicular up-and-down reciprocating motion in sleeve two (17).
3. An aircraft for facilitating control of attitude in accordance with claim 1, wherein: the second control device comprises a sleeve III (25), a transmission rod III (24), a rotating bearing III (22) and three rotors (23) symmetrically fixed on two sides of the rotating bearing III (22), the sleeve III (25) is fixed at the top of the cabin (1), the upper end of the transmission rod III (24) is fixed on the rotating bearing III (22), the lower end of the transmission rod III (24) penetrates through the sleeve III (25) and is connected to a power device in the cabin (1), and the power device drives the transmission rod III (24) to vertically reciprocate in the sleeve III (25).
4. An aircraft for facilitating control of attitude in accordance with any one of claims 1 to 3, wherein: the power device comprises a first driving assembly used for driving the flying device, a second driving assembly used for driving the first control device and a third driving assembly used for driving the second control device, and the first driving assembly, the second driving assembly and the third driving assembly are respectively in circuit connection with the control circuit board (3).
5. An aircraft for facilitating control of attitude in accordance with claim 4, wherein: the first driving assembly comprises a first connecting rod (7), a first crank rotating wheel (10), a first transmission belt (12) and a first driving motor (13), the upper end of the first connecting rod (7) is hinged to a first transmission rod (9) of the flying device, the lower end of the first connecting rod (7) is fixed to the first crank rotating wheel (10), and the first driving motor (13) drives the first crank rotating wheel (10) to rotate through the first transmission belt (12).
6. An aircraft for facilitating control of attitude in accordance with claim 4, wherein: the second driving assembly comprises a second connecting rod (18), a second crank rotating wheel (19), a second transmission belt (20) and a second driving motor (21), the upper end of the second connecting rod (18) is hinged to a second transmission rod (16) of the first control device, the lower end of the second connecting rod (18) is fixed to the second crank rotating wheel (19), and the second driving motor (21) drives the second crank rotating wheel (19) to rotate through the second transmission belt (20).
7. An aircraft for facilitating control of attitude in accordance with claim 4, wherein: the third driving assembly comprises a third connecting rod (26), a third crank rotating wheel (27), a third transmission belt (28) and a third driving motor (29), the upper end of the third connecting rod (26) is hinged to a third transmission rod (24) of the second control device, the lower end of the third connecting rod (26) is fixed to the third crank rotating wheel (27), and the third driving motor (29) drives the third crank rotating wheel (27) to rotate through the third transmission belt (28).
8. An aircraft for facilitating control of attitude in accordance with claim 1, wherein: the first rotor wing (6) of the flight device, the second rotor wing (15) of the first control device and the third rotor wing (23) of the second control device are identical in structure, the upper side plane of the flight device is a turbulent wing surface (30), and the lower side plane of the flight device is a fanning wing surface (31); the vortex wing surface (30) is connected by anterior curved surface and rear portion smooth surface and constitutes, and the anterior curved surface of vortex wing surface (30) is upwards protruding for the rotation plane of rotor, vortex wing surface (30) and fan move wing surface (31) and be asymmetric structure at fore-and-aft projection plane.
9. An aircraft for facilitating control of attitude in accordance with claim 8, wherein: the front side edges of the spoiler airfoil (30) and the fanning airfoil (31) are mutually closed to form a front wing edge (32), and the rear side edges of the spoiler airfoil (30) and the fanning airfoil (31) are mutually closed to form a rear wing tail (33); the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil (30) is located is close to the front wing edge (32).
10. An aircraft for facilitating control of attitude in accordance with claim 8, wherein: an attack angle C exists between the fanning wing surface (31) and a rotating plane of the rotor wing, and the value range of C is-2-6 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346740.2A CN112455701A (en) | 2020-11-26 | 2020-11-26 | Aircraft convenient to control flight gesture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346740.2A CN112455701A (en) | 2020-11-26 | 2020-11-26 | Aircraft convenient to control flight gesture |
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| Publication Number | Publication Date |
|---|---|
| CN112455701A true CN112455701A (en) | 2021-03-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011346740.2A Withdrawn CN112455701A (en) | 2020-11-26 | 2020-11-26 | Aircraft convenient to control flight gesture |
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| CN (1) | CN112455701A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203094441U (en) * | 2013-01-16 | 2013-07-31 | 广州大学 | Improved four-rotor aircraft |
| CN105539839A (en) * | 2015-12-30 | 2016-05-04 | 北京航空航天大学 | Miniature mechanical sliding rail type controllable flapping rotor craft |
| CN205554576U (en) * | 2016-04-28 | 2016-09-07 | 曾宪东 | Multiaxis screw and rotor combination flight lift arrangement |
| CN106741896A (en) * | 2016-12-30 | 2017-05-31 | 武汉华伍航空科技有限公司 | A kind of quadrotor |
| 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 |
| CN110104175A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | A kind of coaxial reversed pair is flutterred rotor mechanism |
-
2020
- 2020-11-26 CN CN202011346740.2A patent/CN112455701A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203094441U (en) * | 2013-01-16 | 2013-07-31 | 广州大学 | Improved four-rotor aircraft |
| CN105539839A (en) * | 2015-12-30 | 2016-05-04 | 北京航空航天大学 | Miniature mechanical sliding rail type controllable flapping rotor craft |
| CN205554576U (en) * | 2016-04-28 | 2016-09-07 | 曾宪东 | Multiaxis screw and rotor combination flight lift arrangement |
| CN106741896A (en) * | 2016-12-30 | 2017-05-31 | 武汉华伍航空科技有限公司 | A kind of quadrotor |
| 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 |
| CN110104175A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | A kind of coaxial reversed pair is flutterred rotor mechanism |
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Application publication date: 20210309 |