WO2022111537A1 - 一种上行竖直运转下行水平运转的扑旋翼装置 - Google Patents
一种上行竖直运转下行水平运转的扑旋翼装置 Download PDFInfo
- Publication number
- WO2022111537A1 WO2022111537A1 PCT/CN2021/132860 CN2021132860W WO2022111537A1 WO 2022111537 A1 WO2022111537 A1 WO 2022111537A1 CN 2021132860 W CN2021132860 W CN 2021132860W WO 2022111537 A1 WO2022111537 A1 WO 2022111537A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotor
- main shaft
- rotation
- fixed
- revolution
- Prior art date
Links
- 230000001174 ascending effect Effects 0.000 title abstract description 4
- 238000000034 method Methods 0.000 claims abstract description 27
- 230000008569 process Effects 0.000 claims abstract description 24
- 230000007246 mechanism Effects 0.000 claims description 44
- 230000005540 biological transmission Effects 0.000 claims description 33
- 238000009434 installation Methods 0.000 claims description 11
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
-
- 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
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
- B64D31/06—Initiating means actuated automatically
Definitions
- the invention relates to the technical field of airfoils, in particular to a flapping rotor device that runs vertically upwards and runs downwards horizontally.
- the flapping-rotor is a new type of aircraft that imitates the flight of birds. It has the advantages of vertical lift-off and aerial hovering of the rotorcraft and helicopter.
- the flapping-rotor device in the prior art will cancel out part of the lift in the process of performing the upward and downward movements, resulting in the lower efficiency of the flapping-rotor aircraft rising.
- the rotor When the rotor is going up or down, it always keeps rotating, which causes the rotating surface of the rotor to rotate 360 degrees, which not only makes the lift provided by the flapper device unstable, but also causes the rotating surface of the rotor to cause self-loss during the 360-degree rotation. lift, thus further reducing the efficiency of the flapper's ascent.
- the present invention aims to solve one of the above-mentioned technical problems in the prior art at least to a certain extent.
- the present invention provides a flapping rotor device that runs vertically upwards and downwards horizontally, which not only improves lift, but also improves the stability of lift generation.
- a flapping rotor device that runs vertically upward and runs horizontally downward, is symmetrically arranged on both sides of the fuselage, and includes:
- the revolving main shaft is arranged on both sides of the fuselage through the flapping rotor bracket, and is rotatably connected to the flapping rotor bracket through a bearing, and the axial centerline of the revolving main shaft is connected to the axial direction of the fuselage.
- the center lines are parallel, and at the same time, the front and rear ends of the revolution main shaft are respectively vertically fixed with a front arm and a rear arm, and the front arm and the rear arm are symmetrically arranged on both sides of the revolution main shaft;
- the revolution motor is fixed on the flapper bracket, and is electrically connected with the controller, and is connected with the revolution main shaft through the revolution transmission gear set at the same time;
- the rotation main shafts are respectively arranged on both sides of the revolving main shaft and are parallel to the revolving main shafts, while the two ends of the rotation main shafts on each side of the revolving main shaft are respectively connected to the front arm and the front arm through bearings.
- the servo motor is fixed on the flapping rotor bracket, and is electrically connected with the controller, and is in a one-to-one correspondence with the rotation spindle drive connection;
- the rotor devices are fixed on the rotation main shafts on both sides of the revolving main shaft in a one-to-one correspondence, and the rotor device includes a rotor, and the rotating surfaces of the rotor wings on both sides of the revolving main shaft are vertical;
- the rotor includes a center A shaft, a turntable and a plurality of rotating airfoils, the center of the turntable is provided with a central hole, the central shaft passes through the central hole and is rotatably connected to the turntable through a bearing, and the rotating airfoil is symmetrical biconvex airfoil;
- one of the servo motors controls one of the self-revolution main shafts correspondingly.
- the rotation plane of the rotor on one side of the revolving main shaft is driven to be always horizontal, and the rotation plane of the rotor on the other side is always vertical;
- the revolving motor drives the revolving main shaft to drive the front arm,
- one of the servo motors controls one of the rotation main shafts, and correspondingly drives the rotation plane of the rotor on one side of the revolving main shaft to convert to always. Being vertical, the plane of rotation of the rotor on the other side is converted to always be horizontal.
- the invention provides a flapping rotor device that runs vertically upwards and runs horizontally downwards. Under the control of a controller, a revolution motor drives a revolution main shaft to revolve to drive a front arm, a rear arm, an autorotation main shaft and a rotor device to go up and down. , since the rotating surfaces of the rotors on both sides of the revolving main shaft of the present invention are vertical, mutual resistance and mutual disturbance can be avoided between the rotors on both sides, the stability of the lift force generation is improved, and the rotating surfaces of the rotors on both sides of the revolving main shaft can be avoided.
- the rotor surface is always kept vertical, and in the process of going up with the revolution main axis, the rotor surface is converted to always remain horizontal by the servo motor.
- the rotor surface is always kept horizontal, and in the process of going up with the main axis of revolution, the rotor surface is converted to be always vertical by the servo motor, so that the main axis of revolution of the present invention drives the rotor in the process of going up and going down.
- the rotating surface of the rotor on one side of the revolving main shaft is always kept horizontal, so that the lift of the present invention is significantly improved, and the stability of generating lift is obviously enhanced.
- the leading edge of the symmetrical double-convex airfoil is convex arc-shaped
- the trailing edge is a flat airfoil structure
- the upper and lower airfoil surfaces are both arc-shaped, so that when the airflow passes through the symmetrical double-convex airfoil
- it can ensure that the speed towards the leading edge is always generated, and combined with the flapping speed of the flapping rotor, according to the fluid mechanics, it can ensure that the continuous upward lift can be generated.
- the roots of the plurality of rotating airfoils are uniformly fixed on the turntable along the circumferential direction, and form an inclination angle of 0 degrees with the rotation, while the leading edges of the plurality of rotating airfoils rotate in the same direction around the axis .
- the inclination angle between the rotary airfoil and the turntable in the rotor of the present invention is 0 degrees, and the leading edges of the plurality of rotary airfoils rotate in the same direction around the axis, during the rotation of the main shaft, regardless of the frontal direction of the rotor Up or back up, as long as the rotating surface of the rotor is in a horizontal state, the maximum upward lift can be generated, and when the rotating surface of the rotor is inclined, a partial upward lift can also be generated, thus making the lift provided by the present invention larger.
- the rotor device further includes an installation frame, the shaft end of the central shaft is fixed on the inner wall of the installation frame, and the outer wall of the installation frame is fixed on the main axis of rotation. Protection of the rotor.
- the mounting frame has a hexahedral structure, and two pairs of opposite faces have panels, and the other pair of faces is hollow;
- a pair of two opposite panels are fixed to the main axis of rotation, and the other pair of opposite two panels are fixed to both ends of the central axis in a one-to-one correspondence.
- the mounting frame is set as two pairs of opposite faces with panels, and the other pair of faces is a hollow hexahedral structure, so that the rotor can not only be fixed on the main axis of rotation by the mounting frame, but also can be used to fix the central axis.
- the support surface is provided, and at the same time, the air flow is provided through the direction of the hollow surface, so that the turntable of the rotor can rotate around the central axis under the driving of the air flow, so as to realize the effect of keeping the rotation of the rotor.
- the installation frame has a "U"-shaped structure, comprising two first panels arranged oppositely and a second panel connecting the two first panels, wherein the two first panels arranged oppositely are fixed On the main axis of rotation, one shaft end of the central shaft is fixed on the second panel.
- the installation frame is set to have two oppositely arranged first panels and a second panel connecting the two first panels, so that not only can the oppositely arranged first panels be fixedly connected to the rotation main shaft, so that the rotor can be arranged in the
- the central axis is fixed on the main axis of rotation and through the second panel, and the turntable that drives the rotor to rotate relative to the central axis can provide airflow through the directions of other surfaces, so the strength of the airflow driving the turntable can be improved, and the cost can be reduced.
- the pulling force device includes a pulling force airfoil and an angle of attack adjusting mechanism
- the pulling force airfoil is penetrated on the front turning arm, and is rotatably connected with the front turning arm through a bearing, so
- the angle-of-attack adjusting mechanism is installed on the revolving main shaft and the front turning arm, and the angle-of-attack adjusting mechanism is electrically connected with the controller to drive the tension airfoil to tilt around the front turning arm to generate
- the pulling airfoil has the same structure as the rotating airfoil, and its leading edge faces the head end of the fuselage.
- a pulling airfoil is rotatably connected to the front turning arm, and the structure of the pulling airfoil is the same as that of the rotating airfoil, and the leading edge of the pulling airfoil faces the head end of the fuselage.
- the angle of attack of the pulling airfoil can be adjusted under the driving, so that the pulling force of the fuselage to sail forward can be provided and changed by the pulling airfoil, and at the same time, the ascent can be assisted, so that the efficiency of the ascent can be improved and the maneuverability is flexible.
- the angle of attack adjustment mechanism includes a first angle of attack adjustment mechanism and a second angle of attack adjustment structure; and the first angle of attack adjustment mechanism includes a first adjustment sleeve, a first angle of attack adjustment motor, and a bevel gear set , the second drive shaft, the cylindrical gear and the second sleeve;
- the first adjusting sleeve is arranged on the front turning arm, one end is fixed with the side end of the tension airfoil, and the other end has gear teeth;
- the second sleeve is fixed on the front rotating arm through a connecting rod, and is rotatably connected to the rotating arm through a bearing, and the second transmission shaft passes through the second sleeve and is connected to the rotating arm through the bearing.
- the inner wall of the second sleeve is rotatably connected;
- the first angle of attack adjusting motor is fixed on the revolving main shaft, and its output shaft is connected to one end of the second transmission shaft through the bevel gear set, while the other end of the second transmission shaft is connected to the cylindrical gear. connected, the cylindrical gear meshes with the gear teeth on the first adjusting sleeve;
- the first angle-of-attack adjusting motor is electrically connected to the controller, and drives the first adjusting sleeve to rotate around the front through the bevel gear set, the second transmission shaft and the cylindrical gear in sequence
- the arm tilts to drive the pulling airfoil to tilt to generate the angle of attack.
- the present invention provides the driving force through the first angle-of-attack adjusting motor, and transmits the power torque to the first adjusting sleeve fixed in the tension airfoil through the transmission between the bevel gear set, the second transmission shaft and the cylindrical gear, Therefore, the present invention achieves the purpose of driving the tilting of the pulling airfoil by driving the first adjusting sleeve to tilt, has a compact structure, and realizes the effect of changing the angle of attack of the pulling airfoil.
- the second angle of attack adjusting mechanism includes a second angle of attack adjusting motor, a swing follower cam mechanism and a second adjusting sleeve;
- the second adjusting sleeve is passed through the front turning arm, and is rotatably connected to the front turning arm through a bearing, and one end face of the second adjusting sleeve is fixed on the side end of the tension airfoil ;
- the second angle of attack adjusting motor is fixed on the revolving main shaft and is connected to the controller, and its output shaft is fixed with the cam in the swing follower cam mechanism.
- the swing follower cam mechanism One end of the swing rod is fixed to the outer wall of the second adjusting sleeve, and the other end is slidably connected with the outer edge of the cam in the swing follower cam mechanism.
- the controller of the controller controls the operation of the second angle-of-attack adjusting motor, thereby driving the cam in the cam mechanism of the swing follower to rotate, thereby driving the swing rod in the cam mechanism of the swing follower to swing. , so that the pulling airfoil and the second adjusting sleeve can be controlled to rotate a certain inclination angle relative to the front turning arm, so as to control the attack angle of the pulling airfoil, so that the pulling force can be changed.
- one rotation main shaft is rotatably connected between the front rotation arm and the rear rotation arm on each side of the revolving main shaft, and a plurality of all rotation main shafts are fixed on each side of the revolving main shaft.
- the rotor device is rotatably connected between the front rotation arm and the rear rotation arm on each side of the revolving main shaft, and a plurality of all rotation main shafts are fixed on each side of the revolving main shaft.
- the present invention can further improve the lifting efficiency of the present invention by arranging a plurality of rotor devices on the main axis of rotation on each side.
- a plurality of the rotation main shafts are rotatably connected between the front rotation arm and the rear rotation arm on each side of the revolving main shaft, and one or more of the rotor devices are fixed on each of the rotation main shafts .
- a plurality of rotation main shafts are rotatably connected between the front and rear rotation arms on each side of the revolving main shaft, so that one or more rotor devices are fixed on each rotation main shaft, which can further improve the lifting efficiency of the present invention.
- the present invention discloses and provides a flapping rotor device that runs vertically upwards and runs downwards horizontally, which can achieve the following technical effects:
- the invention provides a flapping rotor device that runs vertically upwards and runs horizontally downwards. Under the control of a controller, a revolution motor drives a revolution main shaft to revolve to drive a front arm, a rear arm, an autorotation main shaft and a rotor device to go up and down. , since the rotating surfaces of the rotors on both sides of the revolving main shaft of the present invention are vertical, mutual resistance and mutual disturbance can be avoided between the rotors on both sides, the stability of the lift force generation is improved, and the rotating surfaces of the rotors on both sides of the revolving main shaft can be avoided.
- the rotor surface is always kept vertical, and in the process of going up with the revolution main axis, the rotor surface is converted to always remain horizontal by the servo motor.
- the rotor surface is always kept horizontal, and in the process of going up with the main axis of revolution, the rotor surface is converted to be always vertical by the servo motor, so that the main axis of revolution of the present invention drives the rotor in the process of going up and going down.
- the rotating surface of the rotor on one side of the revolving main shaft is always kept horizontal, so that the lift of the present invention is significantly improved, and the stability of generating lift is obviously enhanced.
- Fig. 1 is a schematic diagram of the structure of a flapping rotor device of the present invention that runs vertically upwards and runs downwards horizontally;
- Figure 2 is a schematic diagram of the working state of the rotor on one side of the revolving main shaft in a flapping rotor device of the present invention that runs vertically up and down horizontally with the main shaft of revolution up and down;
- Figure 3 is a schematic structural diagram of a rotor device in a flapping rotor device that runs vertically upward and horizontally downward according to the present invention
- Figure 4 is a schematic structural diagram of a first angle of attack adjusting mechanism of a flapping rotor device that operates vertically upward and downward horizontally according to the present invention
- FIG. 5 is a schematic structural diagram of a second angle of attack adjusting mechanism of a flapping rotor device that operates vertically upward and downward horizontally according to the present invention.
- first and second are only used for descriptive purposes, and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, a feature defined as “first” or “second” may expressly or implicitly include one or more of that feature.
- “plurality” means two or more, unless otherwise expressly and specifically defined.
- the terms “installed”, “connected”, “connected”, “fixed” and other terms should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection , or integrated; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of the two elements or the interaction relationship between the two elements.
- installed may be a fixed connection or a detachable connection , or integrated; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of the two elements or the interaction relationship between the two elements.
- a first feature "on” or “under” a second feature may include the first and second features in direct contact, or may include the first and second features Not directly but through additional features between them.
- the first feature being “above”, “over” and “above” the second feature includes the first feature being directly above and obliquely above the second feature, or simply means that the first feature is level higher than the second feature.
- the first feature is “below”, “below” and “below” the second feature includes the first feature is directly below and diagonally below the second feature, or simply means that the first feature has a lower level than the second feature.
- the embodiment of the present invention discloses a flapping rotor device that runs vertically upward and runs horizontally downward, which is symmetrically arranged on both sides of the fuselage, including:
- the revolving main shaft 21 is arranged on both sides of the fuselage through the flapping rotor bracket 11, and is rotatably connected with the flapping rotor bracket 11 through the bearing, and the axial centerline of the revolving main shaft 21 is parallel to the axial centerline of the fuselage, and the revolving main shaft 21 is parallel to the axial centerline of the fuselage.
- the front and rear ends of the swivel are respectively vertically fixed with the front turning arm 211 and the rear turning arm 212, and the front turning arm 211 and the rear turning arm 212 are symmetrically arranged on both sides of the revolution main shaft 21;
- the revolution motor 22 is fixed on the flapper bracket 11, and is electrically connected with the controller, and at the same time, is connected with the revolution main shaft 21 through the revolution transmission gear set 24;
- the rotation main shafts 23 are respectively arranged on both sides of the revolution main shaft 21, and are parallel to the revolution main shaft 21. At the same time, the two ends of the rotation main shafts 23 on each side of the revolution main shaft 21 are respectively connected to the front rotation arm 211 and the rear rotation arm 212 through bearings.
- the servo motor 6 is fixed on the flapper bracket 11, and is electrically connected with the controller, and is connected with the rotation main shaft 23 in a one-to-one correspondence at the same time;
- the rotor device 3 is fixed on the rotation main shaft 23 on both sides of the revolving main shaft 21 in a one-to-one correspondence, and the rotor device 3 includes a rotor 32, and the rotating surfaces of the rotor 32 on both sides of the revolving main shaft 21 are vertical;
- a plurality of rotating airfoils 323, the center of the turntable 322 is provided with a center hole, the central shaft 321 passes through the center hole and is rotatably connected to the turntable 322 through a bearing, and the rotating airfoil 323 is a symmetrical biconvex wing;
- the revolution motor 22 drives the revolution main shaft 21 to drive the front rotating arm 211, the rear rotating arm 212, the self-rotating main shaft 23 and the rotor device 3 to go up, a servo motor 6 correspondingly controls a self-rotating main shaft 23, correspondingly drives the rotor on one side of the revolution main shaft 21.
- the rotation plane of 32 is always horizontal, and the rotation plane of the rotor 32 on the other side is always vertical;
- the revolution motor 22 drives the revolution main shaft 21 to drive the front rotating arm 211, the rear rotating arm 212, the rotation main shaft 23 and the process of the rotor device 3 going down Among them, one servo motor 6 controls one rotation main shaft 23 correspondingly, and correspondingly drives the rotation plane of the rotor 32 on one side of the revolution main shaft 21 to be always vertical, and the rotation plane of the rotor 32 on the other side is converted to always be horizontal.
- the leading edge of the symmetrical double-convex airfoil is in a convex arc shape
- the trailing edge is a flat airfoil structure
- both the upper airfoil surface and the lower airfoil surface are arcuate.
- the roots of the plurality of rotating airfoils 323 are uniformly fixed on the turntable 322 along the circumferential direction, and form an inclination angle of 0 degrees with the turntable 322, and the leading edges of the plurality of rotating airfoils 323 rotate in the same direction around the axis .
- the rotor device 3 further includes an installation frame 31 .
- the mounting frame 31 has a hexahedral structure, and two pairs of opposite faces have panels, and the other pair of faces is hollow;
- a pair of opposite two panels are fixed with the rotation main shaft 23, and the other pair of opposite two panels are fixed to both ends of the central shaft 321 in one-to-one correspondence.
- the installation frame 31 has a "U"-shaped structure, including two oppositely arranged first panels and a second panel connecting the two first panels, wherein the two oppositely arranged first panels are fixed on the On the rotation main shaft 32, one shaft end of the central shaft 321 is fixed on the second panel.
- the tension device 4 includes a tension airfoil 41 and an angle of attack adjusting mechanism 42.
- the tension airfoil 41 is worn on the front turning arm 211 and rotates with the front turning arm 211 through a bearing.
- the angle of attack adjustment mechanism 42 is installed on the revolution main shaft 21 and the front rotating arm 211
- the angle of attack adjustment mechanism 42 is electrically connected with the controller, and drives the pulling force airfoil 41 to tilt around the front rotating arm 211 to generate the angle of attack, and at the same time
- the pulling airfoil 41 has the same structure as the rotating airfoil 323, and its leading edge faces the head end of the fuselage.
- the angle of attack adjustment mechanism 42 includes a first angle of attack adjustment mechanism and a second angle of attack adjustment structure; and the first angle of attack adjustment mechanism includes a first adjustment sleeve 411, a first angle of attack adjustment motor 421, bevel gear set 422, first transmission shaft 424, spur gear 425 and second sleeve 426;
- the first adjusting sleeve 411 is passed through the front turning arm 211, one end is fixed with the side end of the tension airfoil 41, and the other end has gear teeth;
- the second sleeve 426 is fixed on the front rotating arm 211 through the connecting rod, and is rotatably connected to the rotating arm 211 through the bearing, and the first transmission shaft 424 passes through the second sleeve 426 and is connected to the second sleeve 426 through the bearing.
- the inner wall is connected by rotation;
- the first angle of attack adjusting motor 421 is fixed on the revolving main shaft 21, and its output shaft is connected to one end of the first transmission shaft 424 through the bevel gear set 422, and the other end of the first transmission shaft 424 is connected to the cylindrical gear 425, which is connected to the cylindrical gear 425.
- the gear teeth on the first adjusting sleeve 411 are engaged;
- the first angle of attack adjusting motor 421 is electrically connected to the controller, and drives the first adjusting sleeve 411 to tilt around the front arm 211 through the bevel gear set 422, the second transmission shaft 424 and the cylindrical gear 425 in turn, so as to drive the tension wings
- the Type 41 is tilted to generate an angle of attack.
- the second angle of attack adjusting mechanism includes a second angle of attack adjusting motor 401, a swing follower cam mechanism 402 and a second adjusting sleeve 403;
- the second adjusting sleeve 403 is threaded on the front rotating arm 211, and is rotatably connected to the front rotating arm 211 through a bearing, and one end surface of the second adjusting sleeve 403 is fixed on the side end of the tension airfoil 41;
- the second angle of attack adjusting motor 401 is fixed on the revolving main shaft 21 and connected to the controller, and its output shaft is fixed with the cam in the swing follower cam mechanism 402 , and at the same time, the swing rod in the swing follower cam mechanism 402 is fixed.
- One end is fixed to the outer wall of the second adjusting sleeve 403 , and the other end is slidably connected with the outer edge of the cam in the swing follower cam mechanism 402 .
- a rotation main shaft 23 is rotatably connected between the front rotation arm 211 and the rear rotation arm 212 on each side of the revolution main shaft 21 , and a plurality of rotor devices 3 are fixed on the rotation main shaft 23 on each side of the revolution main shaft 21 . .
- a plurality of rotation main shafts 23 are rotatably connected between the front rotation arm 211 and the rear rotation arm 212 on each side of the revolution main shaft 21 , and one or more rotor devices 3 are fixed on each rotation main shaft 23 .
- Embodiment 1 of the present invention discloses symmetrically arranged on both sides of the fuselage, including:
- the revolving main shaft 21 is arranged on both sides of the fuselage through the flapping rotor bracket 11, and is rotatably connected with the flapping rotor bracket 11 through the bearing, and the axial centerline of the revolving main shaft 21 is parallel to the axial centerline of the fuselage, and the revolving main shaft 21 is parallel to the axial centerline of the fuselage.
- the front and rear ends of the swivel are respectively vertically fixed with the front turning arm 211 and the rear turning arm 212, and the front turning arm 211 and the rear turning arm 212 are symmetrically arranged on both sides of the revolution main shaft 21;
- the revolution motor 22 is fixed on the flapper bracket 11, and is electrically connected with the controller, and at the same time, is connected with the revolution main shaft 21 through the revolution transmission gear set 24;
- the rotation main shafts 23 are respectively arranged on both sides of the revolution main shaft 21, and are parallel to the revolution main shaft 21. At the same time, the two ends of the rotation main shafts 23 on each side of the revolution main shaft 21 are respectively connected to the front rotation arm 211 and the rear rotation arm 212 through bearings.
- the servo motor 6 is fixed on the flapper bracket 11, and is electrically connected with the controller, and is connected with the rotation main shaft 23 in a one-to-one correspondence at the same time;
- the rotor devices 3 are fixed on the rotation main shafts 23 on both sides of the revolving main shaft 21 in a one-to-one correspondence, and the rotor device 3 includes a mounting frame 31 and a rotor 32.
- the outer wall of the mounting frame 31 is fixed on the rotation main shaft 23.
- the rotating surface of 32 is vertical; the rotor 3 includes a central shaft 321, a turntable 322 and a plurality of rotating airfoils 323, the center of the turntable 322 is provided with a central hole, the central shaft 321 passes through the central hole and is rotatably connected with the turntable 322 through a bearing, and the center
- the shaft end of the shaft 321 is fixed on the inner wall of the mounting frame 31, and the rotating airfoil 323 is a symmetrical biconvex airfoil (the model of the symmetrical biconvex airfoil conforms to the general standard for aircraft design, which is NACA0012 or NACA0016), and the symmetrical biconvex airfoil
- the leading edge of the airfoil is convex arc
- the trailing edge is a flat airfoil structure
- the upper airfoil surface and the lower airfoil surface are arc-shaped
- the roots of the plurality of rotating airfoils 323 are uniform
- the revolution motor 22 drives the revolution main shaft 21 to drive the front rotating arm 211, the rear rotating arm 212, the rotation main shaft 23, the mounting frame 31 and the rotor 32 in the process of moving upward, one servo motor 6 correspondingly controls one self rotating main shaft 23, and correspondingly drives the revolution main shaft 21 to one.
- the rotation plane of the rotor 32 on one side is always horizontal, and the rotation plane of the rotor 32 on the other side is always vertical;
- a servo motor 6 correspondingly controls an autorotation main shaft 23, and correspondingly drives the rotation plane of the rotor 32 on one side of the revolution main shaft 21 to be converted to always be vertical, and the rotation plane of the rotor 32 on the other side is converted into always level;
- the mounting frame 31 has a hexahedral structure, and two pairs of opposite faces have panels, and the other pair of faces is hollow; the two opposite panels of a pair are both fixed to the rotation spindle 23, and the other pair of opposite panels are in one-to-one correspondence Both ends of the central shaft 321 are fixed, so that the rotor 31 can be protected by the mounting frame 31 of the hexahedron structure, and the service life of the rotor 32 can be improved.
- the present invention provides a flapping rotor device that runs vertically upward and runs horizontally downward.
- the revolution motor 22 drives the revolution main shaft 21 to orbit through the revolution transmission gear set 24, thereby driving the front rotating arm 211 and the rear rotating arm.
- the rotation main shaft 23, the mounting frame 31 and the rotor 32 go up and down, because the rotating surfaces of the rotors 32 on both sides of the revolution main shaft 21 of the present invention are vertical, so that mutual resistance and mutual disturbance can be avoided between the rotors 32 on both sides.
- At least the rotor 32 on one side of the revolving main shaft 21 can provide lift, so that the present invention can continuously generate lift and further improve the At the same time, because the rotor 32 on one side of the revolving main shaft 21 of the present invention keeps the surface of the rotor 32 vertical in the process of going up with the revolving main shaft 21, and the servo motor 6 is used in the process of going up with the revolving main shaft 21.
- the surface of its rotor 32 is converted to always remain horizontal, and at the same time, the rotor 32 on the other side of the main axis of revolution 21 of the present invention keeps its surface of the rotor 32 horizontal in the process of going up with the main axis of revolution 21, and with the main axis of revolution 21 In the process of ascending, the rotor 32 is converted to be always vertical by the servo motor 6, so that the revolution main shaft 21 of the present invention drives the rotor 32 to keep the rotation of the rotor 32 on one side of the revolution main shaft 21 in the process of going up and down.
- the surface is horizontal, thus making the lift of the present invention significantly improved, as well as the stability of generating lift.
- the mounting frame 31 is a "U"-shaped structure, comprising two oppositely arranged first panels and a second panel connecting the two first panels, wherein the two oppositely arranged first panels are fixed.
- the main axis of rotation 32 On the main axis of rotation 32, one shaft end of the central shaft 321 is fixed on the second panel.
- the mounting frame 31 is set to have two oppositely arranged first panels and a second panel connecting the two first panels, so that not only can the oppositely arranged first panels be fixedly connected to the rotation main shaft 23 to make the rotor 32 is arranged on the main axis of rotation 23, and the central axis is fixed through the second panel, and the turntable 322 of the rotor 32 can be rotated relative to the central axis by providing airflow in the direction of other surfaces, so the intensity of the airflow that drives the turntable 322 to rotate can be improved, and at the same time Reduced costs.
- the pulling force device 4 includes a pulling force airfoil 41 and an angle of attack adjusting mechanism 42.
- the pulling force airfoil 41 is worn on the front turning arm 211 and is connected to the front turning arm 211 through a bearing.
- the angle of attack adjusting mechanism 42 is installed on the revolving main shaft 21 and the front rotating arm 211, the angle of attack adjusting mechanism 42 is electrically connected with the controller, and the pulling force airfoil 41 is driven to tilt around the front rotating arm 211 to generate the angle of attack, and at the same time , the pulling airfoil 41 has the same structure as the rotating airfoil 323, and its leading edge faces the head end of the fuselage;
- the angle of attack adjustment mechanism 42 is a first angle of attack adjustment mechanism, and the first angle of attack adjustment mechanism includes a first adjustment sleeve 411, a first angle of attack adjustment motor 421, a bevel gear set 422, a first transmission shaft 424, a cylinder gear 425 and second sleeve 426;
- the first adjusting sleeve 411 is passed through the front turning arm 211, one end is fixed with the side end of the tension airfoil 41, and the other end has gear teeth;
- the second sleeve 426 is fixed on the front rotating arm 211 through the connecting rod, and is rotatably connected to the rotating arm 211 through the bearing, and the first transmission shaft 424 passes through the second sleeve 426 and is connected to the second sleeve 426 through the bearing.
- the inner wall is connected by rotation;
- the first angle of attack adjusting motor 421 is fixed on the revolving main shaft 21, and its output shaft is connected to one end of the first transmission shaft 424 through the bevel gear set 422, and the other end of the first transmission shaft 424 is connected to the cylindrical gear 425, which is connected to the cylindrical gear 425.
- the gear teeth on the first adjusting sleeve 411 are engaged;
- the first angle of attack adjusting motor 421 is electrically connected to the controller, and drives the first adjusting sleeve 411 to tilt around the front arm 211 through the bevel gear set 422, the second transmission shaft 424 and the cylindrical gear 425 in turn, so as to drive the tension wings
- the Type 41 is tilted to generate an angle of attack.
- the pulling airfoil 41 is rotatably connected to the front rotating arm 211, and the structure of the pulling airfoil 41 and the rotating airfoil 323 is the same, and the leading edge of the pulling airfoil 41 is directed to the head end of the fuselage, so the Driven by the first angle of attack adjusting motor 421, the driving force of the first angle of attack adjusting motor 421 is transmitted to the first adjusting sleeve 411 through the bevel gear set 422, the second transmission shaft 424 and the cylindrical gear 425, so as to pass the first adjusting sleeve 411.
- An adjusting sleeve 411 can drive the pulling airfoil 41 to tilt, so the angle of attack of the pulling airfoil 41 can be adjusted, so that the pulling force of the fuselage traveling forward can be provided and changed through the pulling airfoil 41, and at the same time, it can assist the rise, so that the Improve the efficiency of ascent.
- the second angle of attack adjusting mechanism includes a second angle of attack adjusting motor 401, a swing follower cam mechanism 402 and a second adjusting sleeve 403;
- the second adjusting sleeve 403 is threaded on the front rotating arm 211, and is rotatably connected to the front rotating arm 211 through a bearing, and one end surface of the second adjusting sleeve 403 is fixed on the side end of the tension airfoil 41;
- the second angle of attack adjusting motor 401 is fixed on the revolving main shaft 21 and connected to the controller, and its output shaft is fixed with the cam in the swing follower cam mechanism 402 , and at the same time, the swing rod in the swing follower cam mechanism 402 is fixed.
- One end is fixed to the outer wall of the second adjusting sleeve 403 , and the other end is slidably connected with the outer edge of the cam in the swing follower cam mechanism 402 .
- a rotation main shaft 23 is rotatably connected between the front rotation arm 211 and the rear rotation arm 212 on each side of the revolution main shaft 21 , and a plurality of rotor devices are fixed on the rotation main shaft 23 on each side of the revolution main shaft 21 3.
- the lifting efficiency of the present invention can be further improved
- a plurality of rotation main shafts 23 are rotatably connected between the front rotation arm 211 and the rear rotation arm 212 on each side of the revolution main shaft 21 , and one or more rotor devices 3 are fixed on each rotation main shaft 23 .
- a plurality of autorotation main shafts 23 are rotatably connected between the front rotary arm 211 and the rear rotary arm 212 on each side of the revolution main shaft 21, so that one or more rotor devices 3 are fixed on each autorotation main shaft 23, which can further improve the The present invention increases efficiency.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
本发明公开了一种上行竖直运转下行水平运转的扑旋翼装置，伺服电机和公转电机均与控制器电性连接，且公转电机驱动公转主轴带动前转臂、后转臂、自转主轴和旋翼装置上行的过程中，伺服电机分别控制两个自转主轴，驱使公转主轴一侧的旋翼的旋转平面始终处于水平，另一侧的旋翼的旋转平面始终处于竖直；公转电机驱动公转主轴带动前转臂、后转臂、自转主轴和旋翼装置下行的过程中，伺服电机分别控制两个自转主轴，对应驱使公转主轴一侧的旋翼的旋转平面转换为始终处于竖直，另一侧的旋翼的旋转平面转换为始终处于水平。本发明公开了一种上行竖直运转下行水平运转的扑旋翼装置，不仅提高了升力，而且提高了升力产生的稳定性。
Description
本发明涉及机翼技术领域，更具体的说是涉及一种上行竖直运转下行水平运转的扑旋翼装置。
扑旋翼飞行器是一种模仿鸟类飞行的新型飞行器，它兼备旋翼飞行器以及直升机具有的垂直升空、空中悬停等优点，而扑旋翼飞行器工作的核心装置就是设置在机身两侧的扑旋翼装置，但是现有技术中的扑旋翼装置在执行上行和下行动作的过程会相互抵消部分升力，导致扑旋翼飞行器上升的效率较低，同时现有技术中的扑旋翼装置中的旋翼不管在扑旋翼上行还是下行的过程中，始终保持自转，导致旋翼的旋转面做360度旋转，因此不仅使得扑旋翼装置提供的升力不稳定，而且使得旋翼的旋转面在360度自转的过程中导致自损升力，因此会进一步降低扑旋翼飞行器上升的效率。
本发明旨在至少在一定程度上解决现有技术中的上述技术问题之一。
有鉴于此，本发明提供了一种上行竖直运转下行水平运转的扑旋翼装置，不仅提高了升力，而且提高了升力产生的稳定性。
为了实现上述目的，本发明采用如下技术方案：
一种上行竖直运转下行水平运转的扑旋翼装置，对称设置在机身的两侧，包括：
扑旋翼支架、公转主轴、公转电机、公转传动齿轮组、自转主轴、伺服电机、旋翼装置和控制器；
所述公转主轴通过所述扑旋翼支架设置在所述机身的两侧，并通过轴承与所述扑旋翼支架转动连接，且所述公转主轴的轴向中心线与所述机身的轴向中心线平行，同时所述公转主轴的首尾两端分别对应垂直固定有前转臂和后转臂，且所述前转臂和所述后转臂均对称设置在所述公转主轴的两侧；
所述公转电机固定在所述扑旋翼支架上，并与所述控制器电性连接，同时通过所述公转传动齿轮组与所述公转主轴传动连接；
所述自转主轴分别设置在所述公转主轴的两侧，并平行所述所述公转主轴，同时所述公转主轴每侧的所述自转主轴的两端分别通过轴承转动连接所述前转臂和所述后转臂；
所述伺服电机固定在所述扑旋翼支架上，并与所述控制器电性连接，同时一一对应与所述自转主轴传动连接；
所述旋翼装置一一对应固定在所述公转主轴两侧的所述自转主轴上，且所述旋翼装置包括旋翼，所述公转主轴两侧的所述旋翼的旋转面垂直；所述旋翼包括中心轴、转盘和多个转动翼型，所述转盘的中心开设有中心孔，所述中心轴穿过所述中心孔并通过轴承与所述转盘转动连接，同时所述转动翼型为对称双凸翼型；
所述公转电机驱动所述公转主轴带动所述前转臂、所述后转臂、所述自转主轴和所述旋翼装置上行的过程中，一个所述伺服电机对应控制一个所述自转主轴，对应驱使所述公转主轴一侧的所述旋翼的旋转平面始终处于水平，另一侧的所述旋翼的旋转平面始终处于竖直 ；所述公转电机驱动所述公转主轴带动所述前转臂、所述后转臂、所述自转主轴、所述旋翼装置下行的过程中，一个所述伺服电机对应控制一个所述自转主轴，对应驱使所述公转主轴一侧的所述旋翼的旋转平面转换为始终处于竖直，另一侧的所述旋翼的旋转平面转换为始终处于水平。
本发明提供了一种上行竖直运转下行水平运转的扑旋翼装置，在控制器的控制下，通过公转电机驱动公转主轴公转，带动前转臂、后转臂、自转主轴和旋翼装置上行和下行，由于本发明公转主轴两侧的旋翼的旋转面垂直，从而可以避免两侧旋翼之间相互产生阻力以及避免相互扰动，提高了升力产生的稳定性，并且可以避免公转主轴两侧旋翼的旋转面均竖直，因此至少可以通过公转主轴一侧的旋翼提供升力，从而本发明可以持续产生升力，进一步提高本发明升力产生的效率；同时由于本发明公转主轴一侧的旋翼在随公转主轴上行的过程中使其旋翼面始终保持竖直，而随公转主轴上行的过程中通过伺服电机使其旋翼面转换为始终保持水平，并且与此同时，本发明公转主轴另一侧的旋翼在随公转主轴上行的过程中使其旋翼面始终保持水平，而随公转主轴上行的过程中通过伺服电机使其旋翼面转换为始终保持竖直，从而使得本发明的公转主轴带动旋翼在上行和下行的过程中，始终保持公转主轴一侧旋翼的旋转面为水平，因此使得本发明的升力提高显著，以及明显增强了产生升力的稳定性。
优选的，所述对称双凸翼型的前缘呈凸起弧形，后缘为扁平状的翼型结构，上翼面和下翼面均呈弧形，从而当气流经过对称双凸翼型时，可以保证始终产生朝向前缘方向的速度，并结合扑旋翼拍打的速度，根据流体力学，从而保证可以产生持续向上的升力。
优选的，多个所述转动翼型的根部沿圆周方向均匀固定在所述转盘上，并与所述转形成0度倾角，同时多个所述转动翼型的前缘绕轴旋转的方向相同。
由于本发明中的旋翼中的转动翼型与转盘之间的倾角为0度，以及多个转动翼型的前缘绕轴旋转的方向相同，因此在主轴转动的过程中，不管旋翼的正面朝上还是背面朝上，只要旋翼的旋转面处于水平状态，均可以产生向上的最大升力，并且当旋翼的旋转面倾斜时，还可以产生部分向上的升力，因此使得本发明提供的升力较大。
优选的，所述旋翼装置还包括安装框，所述中心轴的轴端固定在所述安装框的内壁，同时所述安装框的外壁固定在所述自转主轴上，本发明通过安装框可以提供对旋翼的保护。
优选的，所述安装框为六面体结构，且其中两对相对的面具有面板，另外一对面为中空；
其中，一对相对的两个面板均与所述自转主轴固定，另一对相对的两个面板一一对应固定所述中心轴的两端。
本发明通过将安装框设置为两对相对的面具有面板，另外一对面为中空的六面体结构，从而不仅可以通过安装框固定自转主轴，来将旋翼设置在自转主轴上，而且可以为固定中心轴提供支撑面，同时，通过中空面的方向提供气流，使得旋翼的转盘可以在气流的驱动下绕中心轴转动，实现旋翼保持转动的效果。
优选的，所述安装框为“U”字形结构，包括两个相对设置的第一面板和连接两个所述第一面板的第二面板，其中，两个相对设置的所述第一面板固定在所述自转主轴上，所述中心轴的一个轴端固定在所述第二面板上。
本发明将安装框设置为具有两个向对设置的第一面板以及一个连接两个第一面板的第二面板，从而不仅可以通过将相对设置的第一面板固定连接自转主轴，使得旋翼设置在自转主轴上，以及通过第二面板固定中心轴，而且可以通过其他面的方向提供气流驱动旋翼的转盘相对中心轴转动，因此可以提高驱动转盘转动的气流的强度，同时降低了成本。
优选的，还包括拉力装置，所述拉力装置包括拉力翼型和迎角调节机构，所述拉力翼型穿设在所述前转臂上，并通过轴承与所述前转臂转动连接，所述迎角调节机构安装在所述公转主轴和所述前转臂上，所述迎角调节机构与所述控制器电性连接，驱动所述拉力翼型绕所述前转臂倾转而产生迎角，同时，所述拉力翼型与所述转动翼型的结构相同，且其前缘朝向所述机身的首端。
本发明通过在前转臂上转动连接有拉力翼型，并且使得拉力翼型与转动翼型的结构相同，以及使拉力翼型的前缘朝向机身的首端，因此在迎角调节机构的驱动下可以调节拉力翼型的迎角，从而可以通过拉力翼型提供以及改变机身向前航行的拉力，同时可以辅助上升，从而可以提高上升的效率，并且机动灵活。
优选的，所述迎角调节机构包括第一迎角调节机构和第二迎角调节结构；且所述第一迎角调节机构包括第一调节套筒、第一迎角调节电机、锥齿轮组、第二传动轴、圆柱齿轮和第二套筒；
所述第一调节套筒穿设在所述前转臂上，且一端与所述拉力翼型的侧端固定，另一端具有轮齿；
所述第二套筒通过连接杆固定在所述前转臂上，同时通过轴承与所述转臂转动连接，且所述第二传动轴穿过所述第二套筒，并通过轴承与所述第二套筒的内壁转动连接；
所述第一迎角调节电机固定在所述公转主轴上，其输出轴通过所述锥齿轮组连接所述第二传动轴的一端，同时所述第二传动轴的另一端与所述圆柱齿轮连接，所述圆柱齿轮与所述第一调节套筒上的轮齿啮合；
所述第一迎角调节电机与所述控制器电性连接，并依次通过所述锥齿轮组、所述第二传动轴和所述圆柱齿轮驱动所述第一调节套筒绕所述前转臂倾转，以带动所述拉力翼型倾转而产生迎角。
本发明通过第一迎角调节电机提供驱动力，并通过锥齿轮组、第二传动轴以及圆柱齿轮之间的传动，将动力扭矩传递到固定在拉力翼型中的第一调节套筒上，从而本发明通过驱动第一调节套筒倾转的方式实现驱动拉力翼型倾转的目的，结构紧凑，并实现了改变拉力翼型迎角的作用。
优选的，所述第二迎角调节机构包括第二迎角调剂电机、摆动从动件凸轮机构和第二调节套筒；
所述第二调节套筒穿设在所述前转臂上，同时通过轴承与所述前转臂转动连接，且所述第二调节套筒的一个端面固定在所述拉力翼型的侧端；
所述第二迎角调剂电机固定在公转主轴上，并与所述控制器连接，且其输出轴与所述摆动从动件凸轮机构中的凸轮固定，同时，所述摆动从动件凸轮机构中的摆杆的一端固定所述第二调节套筒的外壁，另一端与所述摆动从动件凸轮机构中凸轮的外缘滑动连接。
本发明在所述控制器的控制器，控制所述第二迎角调剂电机工作，从而驱动所述摆动从动件凸轮机构中的凸轮转动，进而驱动摆动从动件凸轮机构中的摆杆摆动，因此可以控制拉力翼型和第二调节套筒相对前转臂转动一定的倾角，从而控制拉力翼型的迎角，以便可以改变拉力。
优选的，所述公转主轴每侧的所述前转臂和所述后转臂之间转动连接有一个所述自转主轴，且所述公转主轴每侧的所述自转主轴上固定有多个所述旋翼装置。
本发明通过在每侧的自转主轴上设置多个旋翼装置，从而可以进一步提高本发明上升的效率。
优选的，所述公转主轴每侧的所述前转臂和所述后转臂之间转动连接有多个所述自转主轴，且每个所述自转主轴上固定一个或多个所述旋翼装置。
本发明通过在公转主轴每侧的前转臂和后转臂之间转动连接有多个自转主轴，从而在每个自转主轴上固定一个或多个旋翼装置，可以进一步提高本发明上升的效率。
经由上述的技术方案可知，与现有技术相比，本发明公开提供了一种上行竖直运转下行水平运转的扑旋翼装置，可以实现以下技术效果：
本发明提供了一种上行竖直运转下行水平运转的扑旋翼装置，在控制器的控制下，通过公转电机驱动公转主轴公转，带动前转臂、后转臂、自转主轴和旋翼装置上行和下行，由于本发明公转主轴两侧的旋翼的旋转面垂直，从而可以避免两侧旋翼之间相互产生阻力以及避免相互扰动，提高了升力产生的稳定性，并且可以避免公转主轴两侧旋翼的旋转面均竖直，因此至少可以通过公转主轴一侧的旋翼提供升力，从而本发明可以持续产生升力，进一步提高本发明升力产生的效率；同时由于本发明公转主轴一侧的旋翼在随公转主轴上行的过程中使其旋翼面始终保持竖直，而随公转主轴上行的过程中通过伺服电机使其旋翼面转换为始终保持水平，并且与此同时，本发明公转主轴另一侧的旋翼在随公转主轴上行的过程中使其旋翼面始终保持水平，而随公转主轴上行的过程中通过伺服电机使其旋翼面转换为始终保持竖直，从而使得本发明的公转主轴带动旋翼在上行和下行的过程中，始终保持公转主轴一侧旋翼的旋转面为水平，因此使得本发明的升力提高显著，以及明显增强了产生升力的稳定性。
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据提供的附图获得其他的附图。
图1 附图为本发明一种上行竖直运转下行水平运转的扑旋翼装置的结构原理图；
图2 附图为本发明一种上行竖直运转下行水平运转的扑旋翼装置中公转主轴一侧的旋翼随公转主轴上行和下行过程中的工作状态示意图；
图3 附图为本发明一种上行竖直运转下行水平运转的扑旋翼装置中的旋翼装置的结构示意图；
图4 附图为本发明一种上行竖直运转下行水平运转的扑旋翼装置的第一迎角调节机构的结构示意图；
图5 附图为本发明一种上行竖直运转下行水平运转的扑旋翼装置的第二迎角调节机构的结构示意图。
其中，11为扑旋翼支架；21为公转主轴；22为公转电机；24为公转传动齿轮组；23为自转主轴；6为伺服电机；3为旋翼装置；211为前转臂；212为后转臂；31为安装框；32为旋翼；323为转动翼型；321为中心轴；322为转盘；4为拉力装置；41为拉力翼型；42为迎角调节机构；411为第一调节套筒；421为第一迎角调节电机；422为锥齿轮组；424为第二传动轴；425为圆柱齿轮；426为第二套筒；401为第二迎角调剂电机；402为摆动从动件凸轮机构；403为第二调节套筒。
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
在本发明的描述中，需要理解的是，术语“上”、“下”、“前”、“后”、“左”、“右”、 “竖直”、“水平”、“顶”、“底”“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。
此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括一个或者更多个该特征。在本发明的描述中，“多个”的含义是两个或两个以上，除非另有明确具体的限定。
在本发明中，除非另有明确的规定和限定，术语“安装”、“相连”、“连接”、“固定”等术语应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或成一体；可以是机械连接，也可以是电连接；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
在本发明中，除非另有明确的规定和限定，第一特征在第二特征之“上”或之“下”可以包括第一和第二特征直接接触，也可以包括第一和第二特征不是直接接触而是通过它们之间的另外的特征接触。而且，第一特征在第二特征“之上”、“上方”和“上面”包括第一特征在第二特征正上方和斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”包括第一特征在第二特征正下方和斜下方，或仅仅表示第一特征水平高度小于第二特征。
本发明实施例公开了一种上行竖直运转下行水平运转的扑旋翼装置，对称设置在机身的两侧，包括：
扑旋翼支架11、公转主轴21、公转电机22、公转传动齿轮组24、自转主轴23、伺服电机6、旋翼装置3和控制器；
公转主轴21通过扑旋翼支架11设置在机身的两侧，并通过轴承与扑旋翼支架11转动连接，且公转主轴21的轴向中心线与机身的轴向中心线平行，同时公转主轴21的首尾两端分别对应垂直固定有前转臂211和后转臂212，且前转臂211和后转臂212均对称设置在公转主轴21的两侧；
公转电机22固定在扑旋翼支架11上，并与控制器电性连接，同时通过公转传动齿轮组24与公转主轴21传动连接；
自转主轴23分别设置在公转主轴21的两侧，并平行公转主轴21，同时公转主轴21每侧的自转主轴23的两端分别通过轴承转动连接前转臂211和后转臂212；
伺服电机6固定在扑旋翼支架11上，并与控制器电性连接，同时一一对应与自转主轴23传动连接；
旋翼装置3一一对应固定在公转主轴21两侧的自转主轴23上，且旋翼装置3包括旋翼32，公转主轴21两侧的旋翼32的旋转面垂直；旋翼32包括中心轴321、转盘322和多个转动翼型323，转盘322的中心开设有中心孔，中心轴321穿过中心孔并通过轴承与转盘322转动连接，同时转动翼型323为对称双凸翼；
公转电机22驱动公转主轴21带动前转臂211、后转臂212、自转主轴23和旋翼装置3上行的过程中，一个伺服电机6对应控制一个自转主轴23，对应驱使公转主轴21一侧的旋翼32的旋转平面始终处于水平，另一侧的旋翼32的旋转平面始终处于竖直 ；公转电机22驱动公转主轴21带动前转臂211、后转臂212、自转主轴23和旋翼装置3下行的过程中，一个伺服电机6对应控制一个自转主轴23，对应驱使公转主轴21一侧的旋翼32的旋转平面转换为始终处于竖直，另一侧的旋翼32的旋转平面转换为始终处于水平。
为了进一步优化上述技术方案，对称双凸翼型的前缘呈凸起弧形，后缘为扁平状的翼型结构，上翼面和下翼面均呈弧形。
为了进一步优化上述技术方案，多个转动翼型323的根部沿圆周方向均匀固定在转盘322上，并与转盘322形成0度倾角，同时多个转动翼型323的前缘绕轴旋转的方向相同。
为了进一步优化上述技术方案，旋翼装置3还包括安装框31，中心轴321的轴端固定在安装框31的内壁，同时安装框31的外壁固定在自转主轴23上。
为了进一步优化上述技术方案，安装框31为六面体结构，且其中两对相对的面具有面板，另外一对面为中空；
其中，一对相对的两个面板均与自转主轴23固定，另一对相对的两个面板一一对应固定中心轴321的两端。
为了进一步优化上述技术方案，安装框31为“U”字形结构，包括两个相对设置的第一面板和连接两个第一面板的第二面板，其中，两个相对设置的第一面板固定在自转主轴32上，中心轴321的一个轴端固定在第二面板上。
为了进一步优化上述技术方案，还包括拉力装置4，拉力装置4包括拉力翼型41和迎角调节机构42，拉力翼型41穿设在前转臂211上，并通过轴承与前转臂211转动连接，迎角调节机构42安装在公转主轴21和前转臂211上，迎角调节机构42与控制器电性连接，驱动拉力翼型41绕前转臂211倾转而产生迎角，同时，拉力翼型41与转动翼型323的结构相同，且其前缘朝向机身的首端。
为了进一步优化上述技术方案，迎角调节机构42包括第一迎角调节机构和第二迎角调节结构；且第一迎角调节机构包括第一调节套筒411、第一迎角调节电机421、锥齿轮组422、第一传动轴424、圆柱齿轮425和第二套筒426；
第一调节套筒411穿设在前转臂211上，且一端与拉力翼型41的侧端固定，另一端具有轮齿；
第二套筒426通过连接杆固定在前转臂211上，同时通过轴承与转臂211转动连接，且第一传动轴424穿过第二套筒426，并通过轴承与第二套筒426的内壁转动连接；
第一迎角调节电机421固定在公转主轴21上，其输出轴通过锥齿轮组422连接第一传动轴424的一端，同时第一传动轴424的另一端与圆柱齿轮425连接，圆柱齿轮425与第一调节套筒411上的轮齿啮合；
第一迎角调节电机421与控制器电性连接，并依次通过锥齿轮组422、第二传动轴424和圆柱齿轮425驱动第一调节套筒411绕前转臂211倾转，以带动拉力翼型41倾转而产生迎角。
为了进一步优化上述技术方案，第二迎角调节机构包括第二迎角调剂电机401、摆动从动件凸轮机构402和第二调节套筒403；
第二调节套403筒穿设在前转臂211上，同时通过轴承与前转臂211转动连接，且第二调节套筒403的一个端面固定在拉力翼型41的侧端；
第二迎角调剂电机401固定在公转主轴21上，并与控制器连接，且其输出轴与摆动从动件凸轮机构402中的凸轮固定，同时，摆动从动件凸轮机构402中的摆杆的一端固定第二调节套筒403的外壁，另一端与摆动从动件凸轮机构402中凸轮的外缘滑动连接。
为了进一步优化上述技术方案，公转主轴21每侧的前转臂211和后转臂212之间转动连接有一个自转主轴23，且公转主轴21每侧的自转主轴23上固定有多个旋翼装置3。
为了进一步优化上述技术方案，公转主轴21每侧的前转臂211和后转臂212之间转动连接有多个自转主轴23，且每个自转主轴23上固定一个或多个旋翼装置3。
实施例1：
本发明实施例1公开了对称设置在机身的两侧，包括：
扑旋翼支架11、公转主轴21、公转电机22、公转传动齿轮组24、自转主轴23、伺服电机6、旋翼装置3和控制器；
公转主轴21通过扑旋翼支架11设置在机身的两侧，并通过轴承与扑旋翼支架11转动连接，且公转主轴21的轴向中心线与机身的轴向中心线平行，同时公转主轴21的首尾两端分别对应垂直固定有前转臂211和后转臂212，且前转臂211和后转臂212均对称设置在公转主轴21的两侧；
公转电机22固定在扑旋翼支架11上，并与控制器电性连接，同时通过公转传动齿轮组24与公转主轴21传动连接；
自转主轴23分别设置在公转主轴21的两侧，并平行公转主轴21，同时公转主轴21每侧的自转主轴23的两端分别通过轴承转动连接前转臂211和后转臂212；
伺服电机6固定在扑旋翼支架11上，并与控制器电性连接，同时一一对应与自转主轴23传动连接；
旋翼装置3一一对应固定在公转主轴21两侧的自转主轴23上，且旋翼装置3包括安装框31和旋翼32，安装框31的外壁固定在自转主轴23上，公转主轴21两侧的旋翼32的旋转面垂直；旋翼3包括中心轴321、转盘322和多个转动翼型323，转盘322的中心开设有中心孔，中心轴321穿过中心孔并通过轴承与转盘322转动连接，且中心轴321的轴端固定在安装框31的内壁，同时转动翼型323为对称双凸翼型（其中对称双凸翼型的型号符合飞机设计通用标准，为NACA0012或NACA0016），对称双凸翼型的前缘呈凸起弧形，后缘为扁平状的翼型结构，上翼面和下翼面均呈弧形，且多个转动翼型323的根部沿圆周方向均匀固定在转盘322上，并与转盘322形成0度倾角，同时多个转动翼型323的前缘绕轴旋转的方向相同；
公转电机22驱动公转主轴21带动前转臂211、后转臂212、自转主轴23、安装框31和旋翼32上行的过程中，一个伺服电机6对应控制一个自转主轴23，对应驱使公转主轴21一侧的旋翼32的旋转平面始终处于水平，另一侧的旋翼32的旋转平面始终处于竖直 ；公转电机22驱动公转主轴21带动前转臂211、后转臂212、自转主轴23、安装框31和旋翼32下行的过程中，一个伺服电机6对应控制一个自转主轴23，对应驱使公转主轴21一侧的旋翼32的旋转平面转换为始终处于竖直，另一侧的旋翼32的旋转平面转换为始终处于水平；
其中，安装框31为六面体结构，且其中两对相对的面具有面板，另外一对面为中空； 一对相对的两个面板均与自转主轴23固定，另一对相对的两个面板一一对应固定中心轴321的两端，从而可以通过六面体结构的安装框31对旋翼31进行保护，提高旋翼32的使用寿命。
本发明提供了一种上行竖直运转下行水平运转的扑旋翼装置，在控制器的控制下，公转电机22通过公转传动齿轮组24驱动公转主轴21公转，从而带动前转臂211、后转臂212、自转主轴23、安装框31和旋翼32上行和下行，由于本发明公转主轴21两侧的旋翼32的旋转面垂直，从而可以避免两侧旋翼32之间相互产生阻力以及避免相互扰动，提高了升力产生的稳定性，并且可以避免公转主轴21两侧旋翼32的旋转面均竖直，因此至少可以通过公转主轴21一侧的旋翼32提供升力，从而本发明可以持续产生升力，进一步提高本发明升力产生的效率；同时由于本发明公转主轴21一侧的旋翼32在随公转主轴21上行的过程中使其旋翼32面始终保持竖直，而随公转主轴21上行的过程中通过伺服电机6使其旋翼32面转换为始终保持水平，并且与此同时，本发明公转主轴21另一侧的旋翼32在随公转主轴21上行的过程中使其旋翼32面始终保持水平，而随公转主轴21上行的过程中通过伺服电机6使其旋翼32面转换为始终保持竖直，从而使得本发明的公转主轴21带动旋翼32在上行和下行的过程中，始终保持公转主轴21一侧旋翼32的旋转面为水平，因此使得本发明的升力提高显著，以及明显增强了产生升力的稳定性。
实施例2
与实施例1不同的是:安装框31为“U”字形结构，包括两个相对设置的第一面板和连接两个第一面板的第二面板，其中，两个相对设置的第一面板固定在自转主轴32上，中心轴321的一个轴端固定在第二面板上。
本发明将安装框31设置为具有两个向对设置的第一面板以及一个连接两个第一面板的第二面板，从而不仅可以通过将相对设置的第一面板固定连接自转主轴23，使得旋翼32设置在自转主轴23上，以及通过第二面板固定中心轴，而且可以通过其他面的方向提供气流驱动旋翼32的转盘322相对中心轴转动，因此可以提高驱动转盘322转动的气流的强度，同时降低了成本。
实施例3
在实施例1的基础上，还包括拉力装置4，拉力装置4包括拉力翼型41和迎角调节机构42，拉力翼型41穿设在前转臂211上，并通过轴承与前转臂211转动连接，迎角调节机构42安装在公转主轴21和前转臂211上，迎角调节机构42与控制器电性连接，驱动拉力翼型41绕前转臂211倾转而产生迎角，同时，拉力翼型41与转动翼型323的结构相同，且其前缘朝向机身的首端；
其中，迎角调节机构42为第一迎角调节机构，且第一迎角调节机构包括第一调节套筒411、第一迎角调节电机421、锥齿轮组422、第一传动轴424、圆柱齿轮425和第二套筒426；
第一调节套筒411穿设在前转臂211上，且一端与拉力翼型41的侧端固定，另一端具有轮齿；
第二套筒426通过连接杆固定在前转臂211上，同时通过轴承与转臂211转动连接，且第一传动轴424穿过第二套筒426，并通过轴承与第二套筒426的内壁转动连接；
第一迎角调节电机421固定在公转主轴21上，其输出轴通过锥齿轮组422连接第一传动轴424的一端，同时第一传动轴424的另一端与圆柱齿轮425连接，圆柱齿轮425与第一调节套筒411上的轮齿啮合；
第一迎角调节电机421与控制器电性连接，并依次通过锥齿轮组422、第二传动轴424和圆柱齿轮425驱动第一调节套筒411绕前转臂211倾转，以带动拉力翼型41倾转而产生迎角。
本发明通过在前转臂211上转动连接有拉力翼型41，并且使得拉力翼型41与转动翼型323的结构相同，以及使拉力翼型41的前缘朝向机身的首端，因此在第一迎角调节电机421的驱动下，通过锥齿轮组422、第二传动轴424和圆柱齿轮425将第一迎角调节电机421的驱动力传递至第一调节套筒411上，从而通过第一调节套筒411可以带动拉力翼型41倾转，因此可以调节拉力翼型41的迎角，从而可以通过拉力翼型41提供以及改变机身向前航行的拉力，同时可以辅助上升，从而可以提高上升的效率。
实施例4
与实施例3不同的是：第二迎角调节机构包括第二迎角调剂电机401、摆动从动件凸轮机构402和第二调节套筒403；
第二调节套403筒穿设在前转臂211上，同时通过轴承与前转臂211转动连接，且第二调节套筒403的一个端面固定在拉力翼型41的侧端；
第二迎角调剂电机401固定在公转主轴21上，并与控制器连接，且其输出轴与摆动从动件凸轮机构402中的凸轮固定，同时，摆动从动件凸轮机构402中的摆杆的一端固定第二调节套筒403的外壁，另一端与摆动从动件凸轮机构402中凸轮的外缘滑动连接。
实施例5：
在实施例3的基础上，公转主轴21每侧的前转臂211和后转臂212之间转动连接有一个自转主轴23，且公转主轴21每侧的自转主轴23上固定有多个旋翼装置3。
本发明通过在每侧的自转主轴23上设置多个旋翼装置3，从而可以进一步提高本发明上升的效率
实施例6：
在实施例4的基础上，公转主轴21每侧的前转臂211和后转臂212之间转动连接有多个自转主轴23，且每个自转主轴23上固定一个或多个旋翼装置3。
本发明通过在公转主轴21每侧的前转臂211和后转臂212之间转动连接有多个自转主轴23，从而在每个自转主轴23上固定一个或多个旋翼装置3，可以进一步提高本发明上升的效率。
本说明书中各个实施例采用递进的方式描述，每个实施例重点说明的都是与其他实施例的不同之处，各个实施例之间相同相似部分互相参见即可。对于实施例公开的装置而言，由于其与实施例公开的方法相对应，所以描述的比较简单，相关之处参见方法部分说明即可。
对所公开的实施例的上述说明，使本领域专业技术人员能够实现或使用本发明。对这些实施例的多种修改对本领域的专业技术人员来说将是显而易见的，本文中所定义的一般原理可以在不脱离本发明的精神或范围的情况下，在其它实施例中实现。因此，本发明将不会被限制于本文所示的这些实施例，而是要符合与本文所公开的原理和新颖特点相一致的最宽的范围。
Claims (10)
- 一种上行竖直运转下行水平运转的扑旋翼装置，对称设置在机身的两侧，其特征在于，包括：扑旋翼支架（11）、公转主轴（21）、公转电机（22）、公转传动齿轮组（24）、自转主轴（23）、伺服电机（6）、旋翼装置（3）和控制器；同时所述公转主轴（21）的首尾两端分别对应垂直固定有前转臂（211）和后转臂（212），且所述前转臂（211）和所述后转臂（212）均对称设置在所述公转主轴（21）的两侧；所述公转电机（22）固定在所述扑旋翼支架（11）上，并与所述控制器电性连接，同时通过所述公转传动齿轮组（24）与所述公转主轴（21）传动连接；所述自转主轴（23）分别设置在所述公转主轴（21）的两侧，并平行所述所述公转主轴（21），同时所述公转主轴（21）每侧的所述自转主轴（23）的两端分别通过轴承转动连接所述前转臂（211）和所述后转臂（212）；所述伺服电机（6）固定在所述扑旋翼支架（11）上，并与所述控制器电性连接，同时一一对应与所述自转主轴（23）传动连接；所述旋翼装置（3）一一对应固定在所述公转主轴（21）两侧的所述自转主轴（23）上，且所述旋翼装置（3）包括旋翼（32），所述公转主轴（21）两侧的所述旋翼（32）的旋转面垂直；所述旋翼（32）包括中心轴（321）、转盘（322）和多个转动翼型（323），所述转盘（322）的中心开设有中心孔，所述中心轴（321）穿过所述中心孔并通过轴承与所述转盘（322）转动连接，同时所述转动翼型（323）为对称双凸翼型；所述公转电机（22）驱动所述公转主轴（21）带动所述前转臂（211）、所述后转臂（212）、所述自转主轴（23）和所述旋翼装置（3）上行的过程中，一个所述伺服电机（6）对应控制一个所述自转主轴（23），对应驱使所述公转主轴（21）一侧的所述旋翼（32）的旋转平面始终处于水平，另一侧的所述旋翼（32）的旋转平面始终处于竖直 ；所述公转电机（22）驱动所述公转主轴（21）带动所述前转臂（211）、所述后转臂（212）、所述自转主轴（23）和旋翼装置（3）下行的过程中，一个所述伺服电机（6）对应控制一个所述自转主轴（23），对应驱使所述公转主轴（21）一侧的所述旋翼（32）的旋转平面转换为始终处于竖直，另一侧的所述旋翼（32）的旋转平面转换为始终处于水平。
- 根据权利要求1所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述对称双凸翼型的前缘呈凸起弧形，后缘为扁平状的翼型结构，上翼面和下翼面均呈弧形。
- 根据权利要求2所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，多个所述转动翼型（323）的根部沿圆周方向均匀固定在所述转盘（322）上，并与所述转盘（322）形成0度倾角，同时多个所述转动翼型（323）的前缘绕轴旋转的方向相同。
- 根据权利要求3所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述旋翼装置（3）还包括安装框（31），所述中心轴（321）的轴端固定在所述安装框（31）的内壁，同时所述安装框（31）的外壁固定在所述自转主轴（23）上。
- 根据权利要求4所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述安装框（31）为六面体结构，且其中两对相对的面具有面板，另外一对面为中空；其中，一对相对的两个面板均与所述自转主轴（23）固定，另一对相对的两个面板一一对应固定所述中心轴（321）的两端。
- 根据权利要求4所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述安装框（31）为“U”字形结构，包括两个相对设置的第一面板和连接两个所述第一面板的第二面板，其中，两个相对设置的所述第一面板固定在所述自转主轴（32）上，所述中心轴（321）的一个轴端固定在所述第二面板上。
- 根据权利要求1-6任一项所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，还包括拉力装置（4），所述拉力装置（4）包括拉力翼型（41）和迎角调节机构（42），所述拉力翼型（41）穿设在所述前转臂（211）上，并通过轴承与所述前转臂（211）转动连接，所述迎角调节机构（42）安装在所述公转主轴（21）和所述前转臂（211）上，所述迎角调节机构（42）与所述控制器电性连接，驱动所述拉力翼型（41）绕所述前转臂（211）倾转而产生迎角，同时，所述拉力翼型（41）与所述转动翼型（323）的结构相同，且其前缘朝向所述机身的首端。
- 根据权利要求7所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述迎角调节机构（42）包括第一迎角调节机构和第二迎角调节结构；且所述第一迎角调节机构包括第一调节套筒（411）、第一迎角调节电机（421）、锥齿轮组（422）、第二传动轴（424）、圆柱齿轮（425）和第二套筒（426）；所述第一调节套筒（411）穿设在所述前转臂（211）上，且一端与所述拉力翼型（41）的侧端固定，另一端具有轮齿；所述第二套筒（426）通过连接杆固定在所述前转臂（211）上，同时通过轴承与所述转臂（211）转动连接，且所述第二传动轴（424）穿过所述第二套筒（426），并通过轴承与所述第二套筒（426）的内壁转动连接；所述第一迎角调节电机（421）固定在所述公转主轴（21）上，其输出轴通过所述锥齿轮组（422）连接所述第二传动轴（424）的一端，同时所述第二传动轴（424）的另一端与所述圆柱齿轮（425）连接，所述圆柱齿轮（425）与所述第一调节套筒（411）上的轮齿啮合；所述第一迎角调节电机（421）与所述控制器电性连接，并依次通过所述锥齿轮组（422）、所述第二传动轴（424）和所述圆柱齿轮（425）驱动所述第一调节套筒（411）绕所述前转臂（211）倾转，以带动所述拉力翼型（41）倾转而产生迎角。
- 根据权利要求8所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述公转主轴（21）每侧的所述前转臂（211）和所述后转臂（212）之间转动连接有一个所述自转主轴（23），且所述公转主轴（21）每侧的所述自转主轴（23）上固定有多个所述旋翼装置（3）。
- 根据权利要求8所述的一种上行竖直运转下行水平运转的扑旋翼装置，其特征在于，所述公转主轴（21）每侧的所述前转臂（211）和所述后转臂（212）之间转动连接有多个所述自转主轴（23），且每个所述自转主轴（23）上固定一个或多个所述旋翼装置（3）。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US17/774,746 US20240158077A1 (en) | 2020-11-26 | 2021-11-24 | Flapping rotor device with uplink vertical rotation and downlink horizontal rotation |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342108.0 | 2020-11-26 | ||
| CN202011342108.0A CN112550696A (zh) | 2020-11-26 | 2020-11-26 | 一种上行竖直运转下行水平运转的扑旋翼装置 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2022111537A1 true WO2022111537A1 (zh) | 2022-06-02 |
Family
ID=75044995
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CN2021/132860 WO2022111537A1 (zh) | 2020-11-26 | 2021-11-24 | 一种上行竖直运转下行水平运转的扑旋翼装置 |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20240158077A1 (zh) |
| CN (1) | CN112550696A (zh) |
| WO (1) | WO2022111537A1 (zh) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550696A (zh) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | 一种上行竖直运转下行水平运转的扑旋翼装置 |
| CN114714343B (zh) * | 2022-05-24 | 2024-02-27 | 江苏科技大学 | 一种单电机控制公转与自转的机械手 |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009023417A (ja) * | 2007-07-18 | 2009-02-05 | Takanori Tsuchiya | 平行回転翼を利用した流体機械 |
| CN103552687A (zh) * | 2013-11-11 | 2014-02-05 | 北京航空航天大学 | 一种新式扑旋翼构型及相应的微小型扑旋翼装置 |
| CN104802983A (zh) * | 2015-05-12 | 2015-07-29 | 佛山市神风航空科技有限公司 | 一种旋转动面翼升力生成装置 |
| CN107284656A (zh) * | 2017-07-12 | 2017-10-24 | 重庆国飞通用航空设备制造有限公司 | 共轴双桨同向旋翼机构及其飞行器 |
| CN112429210A (zh) * | 2020-11-26 | 2021-03-02 | 佛山市神风航空科技有限公司 | 扑旋机 |
| CN112441229A (zh) * | 2020-11-26 | 2021-03-05 | 广东国士健科技发展有限公司 | 一种上行轴翼垂直运转下行水平运转的扑旋翼装置 |
| CN112441227A (zh) * | 2020-11-26 | 2021-03-05 | 广东国士健科技发展有限公司 | 一种类扑旋翼飞行器 |
| CN112550696A (zh) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | 一种上行竖直运转下行水平运转的扑旋翼装置 |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1629038A (zh) * | 2004-10-02 | 2005-06-22 | 高晓燕 | 新型扑翼飞行器 |
| CN102582832B (zh) * | 2012-03-07 | 2014-11-26 | 安徽工业大学 | 一种类扑翼飞行器 |
| JP2016118157A (ja) * | 2014-12-22 | 2016-06-30 | 小泉 裕功 | 外部絶縁体式宇宙船の構造 |
| CN204623825U (zh) * | 2015-05-08 | 2015-09-09 | 佛山市神风航空科技有限公司 | 一种机械传动滚筒翼升力生成装置 |
| CN108791820A (zh) * | 2018-05-08 | 2018-11-13 | 兰州空间技术物理研究所 | 一种用于副翼的扁平舵机机构 |
-
2020
- 2020-11-26 CN CN202011342108.0A patent/CN112550696A/zh not_active Withdrawn
-
2021
- 2021-11-24 WO PCT/CN2021/132860 patent/WO2022111537A1/zh active Application Filing
- 2021-11-24 US US17/774,746 patent/US20240158077A1/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009023417A (ja) * | 2007-07-18 | 2009-02-05 | Takanori Tsuchiya | 平行回転翼を利用した流体機械 |
| CN103552687A (zh) * | 2013-11-11 | 2014-02-05 | 北京航空航天大学 | 一种新式扑旋翼构型及相应的微小型扑旋翼装置 |
| CN104802983A (zh) * | 2015-05-12 | 2015-07-29 | 佛山市神风航空科技有限公司 | 一种旋转动面翼升力生成装置 |
| CN107284656A (zh) * | 2017-07-12 | 2017-10-24 | 重庆国飞通用航空设备制造有限公司 | 共轴双桨同向旋翼机构及其飞行器 |
| CN112429210A (zh) * | 2020-11-26 | 2021-03-02 | 佛山市神风航空科技有限公司 | 扑旋机 |
| CN112441229A (zh) * | 2020-11-26 | 2021-03-05 | 广东国士健科技发展有限公司 | 一种上行轴翼垂直运转下行水平运转的扑旋翼装置 |
| CN112441227A (zh) * | 2020-11-26 | 2021-03-05 | 广东国士健科技发展有限公司 | 一种类扑旋翼飞行器 |
| CN112550696A (zh) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | 一种上行竖直运转下行水平运转的扑旋翼装置 |
Also Published As
| Publication number | Publication date |
|---|---|
| US20240158077A1 (en) | 2024-05-16 |
| CN112550696A (zh) | 2021-03-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2022111537A1 (zh) | 一种上行竖直运转下行水平运转的扑旋翼装置 | |
| CN109515704B (zh) | 基于摆线桨技术的涵道卷流旋翼飞行器 | |
| CN106494617A (zh) | 一种可垂直起降扑翼飞行器及其飞行控制方法 | |
| CN105292465B (zh) | 一种直升机的刚性旋翼系统 | |
| CN108163193A (zh) | 一种主动主旋翼垂直起降飞行器 | |
| CN202828092U (zh) | 自主旋翼无尾桨直升飞机 | |
| CN211033009U (zh) | 一种小型共轴双旋翼无人机 | |
| US6837457B2 (en) | Aircraft rotor and aircraft | |
| CN210310858U (zh) | 一种变转速驱动的旋翼 | |
| CN112124582A (zh) | 一种四扑翼飞行器及其控制方法 | |
| CN207956057U (zh) | 一种主动主旋翼垂直起降飞行器 | |
| CN112441229A (zh) | 一种上行轴翼垂直运转下行水平运转的扑旋翼装置 | |
| JP5023330B2 (ja) | 回転翼機構、該回転翼機構を用いた発電装置、並びに移動装置 | |
| CN110356546B (zh) | 电控变距单旋翼无尾桨电动无人直升机 | |
| CN112441227A (zh) | 一种类扑旋翼飞行器 | |
| CN212980530U (zh) | 扑翼飞行器 | |
| CN112407276A (zh) | 一种上行半转下行水平运转的扑旋翼装置 | |
| CN112429228A (zh) | 一种多扑旋翼航空器 | |
| CN112644701A (zh) | 一种横列式双旋翼无人机 | |
| CN112319793A (zh) | 一种翼片能够调节迎角的扑翼飞行器 | |
| CN112693605A (zh) | 一种扑翼飞行器 | |
| CN112319794A (zh) | 一种能够调节迎角的四翼扑翼飞行器 | |
| CN215475702U (zh) | 一种旋翼机尾翼结构 | |
| CN111348184B (zh) | 一种扑翼结构及飞行器 | |
| CN111434583A (zh) | 一种垂直起降无人机及其控制方法 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WWE | Wipo information: entry into national phase |
Ref document number: 17774746 Country of ref document: US |
|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 21897037 Country of ref document: EP Kind code of ref document: A1 |
|
| NENP | Non-entry into the national phase |
Ref country code: DE |
|
| 122 | Ep: pct application non-entry in european phase |
Ref document number: 21897037 Country of ref document: EP Kind code of ref document: A1 |