CN215922543U - Electric take-off and landing composite wing aircraft - Google Patents

Abstract

The utility model discloses an electric take-off and landing composite wing aircraft, which adopts the technical scheme that the electric take-off and landing composite wing aircraft comprises an aircraft body and wings arranged on the aircraft body, wherein a connecting subframe is arranged on the wings, a thrust rotor wing used for providing thrust is also arranged on the wings, a nacelle is arranged at the end part of the connecting subframe, a propeller control device and a lift rotor wing connected with the propeller control device are arranged on the nacelle, the propeller control device comprises a driving mechanism, a propeller control propelling mechanism, a speed reduction mechanism and a fixed propeller mechanism, the driving mechanism is used for controlling the rotation or the stalling of the lift rotor wing, the propeller control propelling mechanism is used for controlling the speed reduction mechanism to carry out the speed reduction control on the lift rotor wing, and the propeller control propelling mechanism is also used for controlling the fixed propeller mechanism to position or release the positioning of the driving mechanism. The electric take-off and landing composite wing aircraft has the effect of reducing the flight resistance during cruising flight and improves the overall cruising performance.

Description

Electric take-off and landing composite wing aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to an electric take-off and landing composite wing aircraft.

Background

The composite wing aircraft is an aircraft combining a fixed wing aircraft and a rotor aircraft, the fixed wing aircraft has the characteristics of high flying speed, high flying height, long flying time and the like, and the rotor aircraft has the characteristics of vertical take-off and landing, hovering, flexibility and the like. The composite wing aircraft combines various characteristics of a fixed wing aircraft and a rotor aircraft together, so that the composite wing has more sufficient flight performance and is also the main direction in the field of aircraft research and development at present.

The existing fixed wing aircraft needs to run and take off, but the flight speed is high, the rotor aircraft can vertically take off and land at any place, but the flight speed is low during cruising flight, the composite wing aircraft combines the two aircrafts, the problem that the fixed wing aircraft needs to run and take off on a runway is solved, and the problem that the flight speed of the rotor aircraft is low is solved.

SUMMERY OF THE UTILITY MODEL

Aiming at the defects in the prior art, the utility model aims to provide an electric take-off and landing composite wing aircraft which has the effects of reducing the flight resistance during cruising flight and improving the overall cruising performance.

In order to achieve the purpose, the utility model provides the following technical scheme:

an electric take-off and landing composite wing aircraft comprises an aircraft body and wings arranged on the aircraft body, wherein a connecting subframe is arranged on the wings, a thrust rotor wing used for providing thrust is further arranged on the wings, the connecting subframe is arranged along the advancing direction of the aircraft body and perpendicular to the wings, a nacelle is arranged at the end part of the connecting subframe, a propeller control device and a lift rotor wing connected with the propeller control device are arranged on the nacelle, the propeller control device comprises a driving mechanism, a propeller control propelling mechanism, a speed reduction mechanism and a fixed propeller mechanism, the driving mechanism is used for controlling the rotation or the stalling of the lift rotor wing, the propeller control propelling mechanism is used for controlling the speed reduction mechanism to carry out speed reduction control on the lift rotor wing, the propeller control propelling mechanism is further used for controlling the fixed propeller mechanism to position or position release of the driving mechanism, and when the fixed propeller mechanism positions the driving mechanism, actuating mechanism stall to make the lift rotor stall, when the lift rotor stall, the lift rotor with the wing is parallel, it is right that fixed pitch mechanism when actuating mechanism removes the location, actuating mechanism control the lift rotor rotates.

As a further improvement of the utility model, the driving mechanism comprises a driving motor and a transmission shaft, the driving motor is arranged on the nacelle, the transmission shaft is coaxially and fixedly connected with an output shaft of the driving motor, one end of the transmission shaft, which is far away from the driving motor, is coaxially and fixedly connected with the lift rotor, the transmission shaft is hollow inside, and the paddle control propulsion mechanism is arranged in the transmission shaft.

As a further improvement of the utility model, the paddle control propelling mechanism comprises a propelling motor, a propelling screw rod, a guide slide rod and a propelling piece, wherein the propelling screw rod is coaxially and fixedly connected with the propelling motor, the propelling screw rod and the guide slide rod are respectively arranged in a penetrating manner along the axial direction of the propelling piece, the propelling piece is coaxially arranged with the transmission shaft, and a plurality of propelling lugs are arranged on the outer wall of the propelling piece in an array manner;

the speed reducing mechanism comprises a driving speed reducing wheel, a friction speed reducing wheel, an inner support and an outer support, the outer support is arranged on the nacelle, the inner support is arranged in the transmission shaft, a plurality of abdicating grooves are formed in the inner support along the direction perpendicular to the axis of the transmission shaft, the abdicating grooves are circumferentially arrayed along the axial direction of the transmission shaft, the driving speed reducing wheel is connected with the abdicating grooves in a sliding manner, wheel grooves for the driving speed reducing wheel to extend out are formed in the transmission shaft, and a plurality of friction speed reducing wheels are circumferentially arrayed on the outer support;

propelling motor drive impels the lead screw and rotates the drive impel the piece to remove, control when impel lug on the piece and the initiative reducing gear is contradicted, promote the initiative reducing gear stretches out from the race, drive when the transmission shaft rotates the initiative reducing gear rotates in step, the initiative reducing gear rotates with the transmission shaft when rotating respectively with a plurality of the friction reducing gear rotates the friction, the friction reducing gear provides the speed reduction resistance of lift rotor with the initiative reducing gear during friction.

As a further improvement of the utility model, a reset elastic part is also arranged in the abdicating groove, the reset elastic part is arranged along the direction vertical to the axis of the transmission shaft, one end of the reset elastic part is connected with the wheel groove, the other end of the reset elastic part is connected with the driving deceleration wheel, when the propelling part pushes the driving deceleration wheel to extend out of the wheel groove, the reset elastic part is deformed by the force accumulation of external force, and provides elastic force for driving the driving deceleration wheel to reset.

As a further improvement of the utility model, a boosting elastic piece is arranged between the outer bracket and the friction speed reducing wheel.

As a further improvement of the present invention, the fixed-pitch mechanism includes a fixed-pitch propulsion member, a fixed-pitch pin, a position-control elastic member, and a return elastic member, wherein a straight hole is formed on the transmission shaft, the fixed-pitch propulsion member and the return elastic member are both disposed in the straight hole, the return elastic member is sleeved outside the fixed-pitch propulsion member, one end of the return elastic member is connected to the straight hole, the other end of the return elastic member is connected to the fixed-pitch propulsion member, a pin slot is formed at one end of the fixed-pitch propulsion member facing the outer wall of the transmission shaft, the position-control elastic member and the fixed-pitch pin are both disposed in the pin slot, one end of the position-control elastic member is connected to the pin slot, the other end of the position-control elastic member is connected to the fixed-pitch pin, when the fixed-pitch pin is not subjected to an external force, a portion of the fixed-pitch pin extends out of the pin slot, the outer bracket is provided with a slot for inserting the fixed-pitch pin, the propulsion motor controls the propulsion member to move until the fixed-pitch propulsion member collides with one end of the fixed-pitch propulsion member far from the fixed-pitch pin, and pushes the fixed-pitch propulsion member to move along the straight hole in the axial direction, and controlling the fixed paddle pin to be inserted into the slot when the fixed paddle pin rotates to correspond to the slot.

As a further improvement of the utility model, a cabin cavity is formed in the connecting auxiliary frame, a position retreating mechanism is arranged in the cabin cavity, a moving groove communicated with the cabin cavity is formed in the connecting auxiliary frame along the axis direction, the position retreating mechanism is connected with the nacelle, and the position retreating mechanism is used for controlling the nacelle to slide along the moving groove.

As a further improvement of the utility model, the retreating mechanism comprises a retreating motor and a retreating lead screw, the retreating lead screw is coaxially and fixedly connected with the retreating motor, the retreating lead screw is in threaded connection with the nacelle, and the end part of the connecting subframe is provided with a sealing cover for sealing the nacelle cavity.

The utility model has the beneficial effects that: through setting up accuse oar device control lift rotor on the nacelle, realize providing the lifting force through the rotation of drive lift rotor when needs provide the vertical lift power, when needs are patrolled and navigated, through controlling advancing mechanism control deceleration mechanism and carrying out deceleration control, realize the rotational speed of quick reduction lift rotor, when the rotational speed reduces to the low-speed state, control advancing mechanism mobile control fixed propeller mechanism fixes a position the lift rotor, so that the lift rotor is fixed in the position that keeps parallel with the wing, thereby make the lift rotor not only can the reduction resistance, can also play the effect of glide vane, further reduce the resistance when patrolling and navigating, improve the cruise speed when patrolling and navigating, reach and improve whole cruise performance.

Drawings

Fig. 1 is a schematic perspective view showing a lift rotor in a rotating state;

fig. 2 is a schematic perspective view showing a stopped state of a lift rotor;

FIG. 3 is a partial exploded view of an embodiment of the recoil mechanism;

FIG. 4 is a schematic partial cross-sectional view of an embodiment of a pitch control apparatus;

FIG. 5 is a schematic view in partial section showing a paddle control propulsion mechanism;

FIG. 6 is an enlarged view of part A of FIG. 4;

fig. 7 is a partially enlarged view of portion B in fig. 4.

Reference numerals: 1. a body; 11. an airfoil; 12. a tail wing; 13. connecting the auxiliary frame; 14. a thrust rotor; 15. a cabin cavity; 16. a moving groove; 17. sealing the cover; 2. a nacelle; 3. a paddle control device; 4. a lift rotor; 5. a drive mechanism; 51. a drive motor; 52. a drive shaft; 53. a wheel groove; 6. a paddle control propulsion mechanism; 61. a propulsion motor; 62. a screw rod is pushed; 63. a guide slide bar; 64. a pusher member; 65. advancing the lug; 7. a speed reduction mechanism; 71. an active reduction wheel; 72. a friction deceleration wheel; 73. an inner support; 74. an outer support; 75. a yielding groove; 76. a restoring elastic member; 77. a force-increasing elastic member; 78. a slot; 8. a fixed paddle mechanism; 81. a fixed-paddle propulsion member; 82. a fixed paddle pin; 83. a position control elastic member; 84. a return elastic member; 85. a pin slot; 9. a position retreating mechanism; 91. a back-off motor; 92. and a position-withdrawing screw rod.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples. In which like parts are designated by like reference numerals. It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "bottom" and "top," "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.

Referring to fig. 1 to 3, a specific embodiment of an electric take-off and landing composite wing aircraft according to the present invention includes a fuselage 1 and wings 11 disposed on the fuselage 1, where the fuselage 1 includes a fuselage and an empennage 12 disposed at a tail portion of the fuselage, the wings 11 are provided with a connection sub-frame 13, the wings 11 are further provided with thrust rotors 14 for providing thrust, the thrust rotors 14 are used for providing power during cruise, the thrust rotors 14 are rotor structures in existing composite wings, and are not described herein, the connection sub-frame 13 is disposed along a forward direction of the fuselage 1 and perpendicular to the wings 11, an end portion of the connection sub-frame 13 is provided with a nacelle 2, the nacelle 2 is provided with a propeller control device 3 and a lift rotor 4 connected with the propeller control device 3, the propeller control device 3 is used for controlling the lift rotor 4 to provide vertical lifting force, so as to provide lifting force when vertical take-off and landing or hovering is required, the cabin cavity 15 has been seted up on connecting the subframe 13, be provided with in the cabin cavity 15 and move back a position mechanism 9, connect and set up the shifting chute 16 with cabin cavity 15 intercommunication along the axis direction on the subframe 13, move back a position mechanism 9 including moving back a position motor 91 and moving back a position lead screw 92, move back a position lead screw 92 and move back a coaxial fixed connection of motor 91, move back a position lead screw 92 and nacelle 2 threaded connection, the tip of connecting the subframe 13 is provided with the closing cap 17 that is used for shutoff cabin cavity 15, so that when moving back a position motor 91 and drive and move back a position lead screw 92 and rotate, control nacelle 2 along the sliding of shifting chute 16, thereby control lift rotor 4's position removes, make lift rotor 4 difficult and wing 11 to produce when starting and interfere.

Referring to fig. 2, 4 and 5, the propeller control device 3 includes a driving mechanism 5, a propeller control propulsion mechanism 6, a speed reduction mechanism 7 and a fixed propeller mechanism 8, the driving mechanism 5 is used for controlling the lifting rotor 4 to rotate or stall, the propeller control propulsion mechanism 6 is used for controlling the speed reduction mechanism 7 to perform speed reduction control on the lifting rotor 4, the propeller control propulsion mechanism 6 is also used for controlling the fixed propeller mechanism 8 to position or reposition the driving mechanism 5, when the fixed propeller mechanism 8 positions the driving mechanism 5, the driving mechanism 5 stops rotating to stop the lifting rotor 4, when the lifting rotor 4 stops rotating, the lifting rotor 4 is parallel to the wing 11, so that when the lifting rotor 4 is parallel to the wing 11, not only the resistance during cruising can be reduced, but also the cruising speed can be increased, the cruising performance can be improved, when the fixed propeller mechanism 8 repositions the driving mechanism 5, the driving mechanism 5 controls the lifting force rotor 4 to rotate, vertical lifting force is provided, and the whole body can take off and land vertically or hover in the air.

Referring to fig. 4 to 7, the driving mechanism 5 includes a driving motor 51 and a transmission shaft 52, the driving motor 51 is disposed on the nacelle 2, the transmission shaft 52 is coaxially and fixedly connected with an output shaft of the driving motor 51, the transmission shaft 52 is connected with the driving motor 51 through a coupler, the lift rotor 4 includes a rotor shaft and a lift blade connected with the rotor shaft, one end of the transmission shaft 52 far from the driving motor 51 is coaxially and fixedly connected with one end of the rotor shaft far from the lift blade, the transmission shaft 52 is hollow, and the paddle control propulsion mechanism 6 is disposed in the transmission shaft 52;

the propeller control propulsion mechanism 6 comprises a propulsion motor 61, a propulsion screw rod 62, a guide slide bar 63 and a propulsion piece 64, wherein the propulsion screw rod 62 is coaxially and fixedly connected with the propulsion motor 61, the propulsion screw rod 62 and the guide slide bar 63 are respectively penetrated and arranged along the axial direction of the propulsion piece 64, one end of a rotor shaft, which is far away from a lift paddle, is provided with a shaft groove, the end parts of the propulsion screw rod 62 and the guide slide bar 63 are inserted into the shaft groove, one end of a transmission shaft 52, which is far away from the rotor shaft, is provided with a base, the propulsion motor 61 is arranged on the base, one end of the guide slide bar 63, which is far away from the shaft groove, is connected with the base, the propulsion piece 64 is coaxially arranged with the transmission shaft 52, the outer wall array of the propulsion piece 64 is provided with a plurality of propulsion lugs 65, the propulsion motor 61 controls the forward rotation or reverse rotation of the propulsion screw rod 62, and controls the propulsion piece 64 to slide back and forth along the guide slide bar 63;

the deceleration mechanism 7 comprises a driving deceleration wheel 71, a friction deceleration wheel 72, an inner support 73 and an outer support 74, the outer support 74 is arranged on the nacelle 2, the inner support 73 is arranged in the transmission shaft 52, a plurality of abdicating grooves 75 are formed in the inner support 73 along the direction perpendicular to the axial direction of the transmission shaft 52, the plurality of abdicating grooves 75 are circumferentially arranged along the axial direction of the transmission shaft 52, the driving deceleration wheel 71 is connected with the abdicating grooves 75 in a sliding manner, a return elastic member 76 is further arranged in the abdicating grooves 75, the return elastic member 76 is arranged along the direction perpendicular to the axial direction of the transmission shaft 52, the return elastic member 76 is selected as a spring, one end of the return elastic member 76 is connected with the abdicating grooves 75, the other end is connected with the driving deceleration wheel 71, a wheel groove 53 for extending out of the driving deceleration wheel 71 is formed in the transmission shaft 52, so that when the propelling member 64 is controlled to move until the propelling lug 65 contacts with the driving deceleration wheel 71, the driving deceleration wheel 71 is gradually pushed to move along the abdicating grooves 75, so that the driving deceleration wheel 71 partially extends out of the wheel groove 53, the transmission shaft 52 rotates continuously to drive the driving deceleration wheel 71 to rotate synchronously, at the moment, the reset elastic member 76 is deformed by external force, so that the elastic potential energy for driving the driving deceleration wheel 71 to retract into the transmission shaft 52 is provided, the driving deceleration wheel 71 is a fixed wheel and does not rotate along the connection part with the abdicating groove 75 when being applied with external force, a plurality of friction deceleration wheels 72 are arranged on the outer bracket 74 in a circumferential array, the friction deceleration wheels 72 are rotating wheels, a boosting elastic member 77 is further arranged between the friction deceleration wheels 72 and the outer bracket 74, the boosting elastic member 77 is selected as a torsion spring, when the driving deceleration wheel 71 drives the friction deceleration wheel 72 to rotate, the boosting elastic member 77 is driven to deform, thereby increasing the friction force, increasing the deceleration resistance and achieving the effect of rapid deceleration, and when the driving deceleration wheel 71 is separated from the friction deceleration wheel 72, the force-increasing elastic member 77 drives the friction deceleration wheel 72 to rapidly return, so that frictional resistance is better provided under the subsequent friction action, and the lift rotor 4 can be rapidly decelerated.

Referring to fig. 2 to 7, the fixed-pitch mechanism 8 includes a fixed-pitch propulsion member 81, a fixed-pitch pin 82, a positioning elastic member 83, and a return elastic member 84, a straight hole is formed on the transmission shaft 52, the fixed-pitch propulsion member 81 and the return elastic member 84 are both disposed in the straight hole, the return elastic member is a spring, the return elastic member 84 is sleeved outside the fixed-pitch propulsion member 81, one end of the return elastic member 84 is connected to the straight hole, the other end of the return elastic member is connected to the fixed-pitch propulsion member 81, a pin slot 85 is formed at one end of the fixed-pitch propulsion member 81 facing the outer wall of the transmission shaft 52, the positioning elastic member 83 and the fixed-pitch pin 82 are both located in the pin slot 85, the positioning elastic member 83 is a spring, one end of the positioning elastic member 83 is connected to the pin slot 85, the other end of the positioning elastic member is connected to the fixed-pitch pin 82, the fixed-pitch pin 82 partially extends out of the pin slot 85 when not subjected to an external force, the fixed-pitch pin 82 can be completely pressed into the pin slot 85 when the external force is applied, the fixed-pitch pin 78 for inserting the fixed-pitch pin 82 is disposed on the bracket 74, the propulsion motor 61 controls the propulsion element 64 to move to abut against one end, far away from the fixed propeller pin 82, of the fixed propeller propulsion element 81, and then pushes the fixed propeller propulsion element 81 to move along the axial direction of the straight hole, at the moment, one end, far away from the propulsion element 64, of the fixed propeller propulsion element 81 does not penetrate out of the outer wall of the transmission shaft 52, and controls the fixed propeller pin 82 to rotate to correspond to the position of the slot 78 and then insert into the slot 78, so that the transmission shaft 52 is positioned and fixed, the lifting rotor 4 is positioned and fixed, and at the moment, the fixed position of the lifting rotor 4 is in a state parallel to the wing 11;

the fixed paddle pushing piece 81 is pushed to move along the straight hole by the pushing convex block 65 for a distance larger than the depth of the slot 78, so that when the pushing piece 64 is controlled to move to remove the pushing convex block 65 from abutting against the fixed paddle pushing piece 81, the return elastic piece 84 releases elastic potential energy to drive the fixed paddle pushing piece 81 to reset, the positioning pin is separated from the slot 78, the absorption on the transmission shaft 52 is removed, and the end part of the positioning pin, far away from the fixed paddle pushing piece 81, is contracted into the transmission shaft 52, so that the rotation of the transmission shaft 52 is not influenced, and the lifting rotor 4 can normally rotate;

the empennage 12 is also provided with a nacelle 2, a paddle control device 3 arranged on the nacelle 2 and a lifting rotor 4 connected with the paddle control device 3, so that more sufficient power can be provided when power for vertical lifting is required to be provided.

The working method of the electric take-off and landing composite wing aircraft in the embodiment comprises the following specific steps:

in an initial state:

the propulsion lug 65 on the propulsion element 64 is abutted against the fixed-propeller propulsion element 81, the fixed-propeller pin 82 is inserted into the slot 78, the lift rotor 4 is kept in a parallel state with the wing 11, the nacelle 2 is positioned at one end of the moving slot 16 far away from the cover 17, so that the nacelle 2 is close to the position of the wing 11, the lift rotor 4 can be used as a gliding wing, and the lift rotor 4 positioned on the empennage 12 is kept in a parallel state with the wing 11;

when starting 4 states of lift rotor:

the retreating motor 91 drives the retreating screw rod 92 to rotate, the nacelle 2 is driven to move to one end close to the sealing cover 17 along the moving groove 16, the lifting rotor 4 is far away from the wing 11, interference with the wing 11 is not easy to generate when the lifting rotor 4 rotates, when the lifting rotor 4 needs to be started to rotate, the propulsion motor 61 drives the propulsion screw rod 62 to rotate to drive the propulsion piece 64 to move, the propulsion lug 65 on the propulsion piece 64 is driven to be separated from the fixed-propeller propulsion piece 81, the return elastic piece 84 drives the fixed-propeller propulsion piece 81 to reset, the fixed-propeller pin 82 is driven to be separated from the slot 78, positioning of the lifting rotor 4 is released, the driving motor 51 drives the transmission shaft 52 to transmit, the lifting rotor 4 is driven to rotate, and power for vertical lifting is provided;

when the speed reduction is needed:

the propelling motor 61 drives the propelling screw rod 62 to rotate, the propelling piece 64 is controlled to move, the propelling lug 65 on the propelling piece 64 is driven to abut against the driving deceleration wheel 71, the driving deceleration wheel 71 is driven to extend out of the wheel groove 53, the extending part of the driving deceleration wheel 71 is in rotational friction with the friction deceleration wheel 72 arranged on the outer support 74, the boosting elastic piece 77 is driven to accumulate force in the rotational friction process, the friction resistance is improved, when the driving deceleration wheel 71 is not in rotational friction with the friction deceleration wheel 72, the boosting elastic piece 77 drives the friction deceleration wheel 72 to reset, when the rotating speed of the transmission shaft 52 is reduced to a preset speed, the preset speed represents the lowest speed when the transmission shaft 52 needs to be braked, and the propelling piece 64 is controlled to move, so that the propelling lug on the propelling piece 64 is moved to abut against the fixed-paddle propelling piece 81, and the fixed-paddle propelling piece 81 is pushed to move axially along the straight hole;

when the positioning pin does not correspond to the slot 78, the positioning pin is completely pressed into the pin slot 85, the position control elastic part 83 is deformed by external force, the transmission shaft 52 continues to rotate, when the positioning pin rotates to correspond to the slot 78, the position control elastic part 83 releases elastic force to push the positioning pin to be inserted into the slot 78, in the process, due to the fact that the rotating speed of the transmission shaft 52 is low, vibration is not prone to being generated when the positioning pin is inserted into the slot 78, the transmission shaft 52 is fixedly positioned, at the moment, the lifting force rotor 4 is located at the position horizontally arranged with the wing 11, the lifting force rotor 4 is fixed, and the lifting force rotor 4 plays a role of a glider.

The working process and the principle thereof are as follows:

the lift rotor wing 4 is controlled by the paddle control device 3 arranged on the nacelle 2, so that the lift force can be provided by driving the lift rotor wing 4 to rotate when the vertical lift force is required to be provided, the speed reduction mechanism 7 is controlled by controlling the propelling mechanism to perform speed reduction control when the cruise is required, the rotating speed of the lift rotor wing 4 is rapidly reduced, when the rotating speed is reduced to a low-speed state, the propelling mechanism is controlled to move and control the paddle fixing mechanism 8 to position the lift rotor wing 4 so that the lift rotor wing 4 is fixed at a position parallel to the wing 11, when the positioning is performed, only one slot 78 and one positioning pin are arranged, so that the transmission shaft 52 stops rotating when only the positioning pin is inserted into the slot 78, and the positioning and fixing effects are more stably performed, so that the lift rotor wing 4 not only can reduce the resistance, but also can perform the function of a glider wing, and the drag force during cruise is further reduced, the cruising speed during cruising is improved, and the whole cruising performance is improved.

The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the utility model may occur to those skilled in the art without departing from the principle of the utility model, and are considered to be within the scope of the utility model.

Claims (8)

1. The utility model provides an electronic take-off and landing composite wing aircraft, includes fuselage (1) and sets up wing (11) on fuselage (1), its characterized in that: be provided with on wing (11) and connect subframe (13), still be provided with thrust rotor (14) that are used for providing thrust on wing (11), connect subframe (13) and set up and perpendicular to wing (11) along fuselage (1) direction of advance, the tip of connecting subframe (13) is provided with nacelle (2), be provided with on nacelle (2) accuse oar device (3) and lift rotor (4) of being connected with accuse oar device (3), accuse oar device (3) is including actuating mechanism (5), accuse oar advancing mechanism (6), slowdown mechanism (7) and fixed oar mechanism (8), actuating mechanism (5) are used for control rotor (4) rotate or stall, accuse oar advancing mechanism (6) are used for controlling slowdown mechanism (7) and carry out slowdown control to lift rotor (4), accuse oar advancing mechanism (6) still are used for control fixed oar mechanism (8) are right actuating mechanism (5) location or release location When the fixed pitch mechanism (8) is used for positioning the driving mechanism (5), the driving mechanism (5) stops rotating so that the lifting rotor wing (4) stops rotating, when the lifting rotor wing (4) stops rotating, the lifting rotor wing (4) is parallel to the wing (11), and when the fixed pitch mechanism (8) is used for de-positioning the driving mechanism (5), the driving mechanism (5) controls the lifting rotor wing (4) to rotate.

2. The electric take-off and landing composite wing aircraft according to claim 1, wherein: actuating mechanism (5) include driving motor (51), transmission shaft (52), driving motor (51) set up on nacelle (2), the coaxial fixed connection of output shaft of transmission shaft (52) and driving motor (51), the one end and the coaxial fixed connection of lift rotor (4) that driving motor (51) were kept away from in transmission shaft (52), the inside cavity of transmission shaft (52), accuse oar advancing mechanism (6) set up in transmission shaft (52).

3. The electric take-off and landing composite wing aircraft according to claim 2, wherein: the paddle control propelling mechanism (6) comprises a propelling motor (61), a propelling screw rod (62), a guide slide rod (63) and a propelling piece (64), the propelling screw rod (62) is coaxially and fixedly connected with the propelling motor (61), the propelling screw rod (62) and the guide slide rod (63) are respectively arranged in a penetrating manner along the axial direction of the propelling piece (64), the propelling piece (64) is coaxially arranged with the transmission shaft (52), and a plurality of propelling lugs (65) are arranged on the outer wall of the propelling piece (64) in an array manner;

the speed reducing mechanism (7) comprises a driving speed reducing wheel (71), a friction speed reducing wheel (72), an inner support (73) and an outer support (74), the outer support (74) is arranged on the nacelle (2), the inner support (73) is arranged in the transmission shaft (52), a plurality of abdicating grooves (75) are formed in the inner support (73) along the axial direction perpendicular to the transmission shaft (52), the abdicating grooves (75) are circumferentially arrayed along the axial direction of the transmission shaft (52), the driving speed reducing wheel (71) is connected with the abdicating grooves (75) in a sliding manner, a wheel groove (53) for the driving speed reducing wheel (71) to extend out is formed in the transmission shaft (52), and a plurality of friction speed reducing wheels (72) are circumferentially arrayed on the outer support (74);

propelling movement motor (61) drive propulsion lead screw (62) rotate the drive propelling movement piece (64) removes, control when propelling movement lug (65) on propelling movement piece (64) contradict with initiative reducing gear (71), promote initiative reducing gear (71) are stretched out from race (53), drive when transmission shaft (52) rotate initiative reducing gear (71) synchronous rotation, when initiative reducing gear (71) rotate along with transmission shaft (52) respectively with a plurality of friction reducing gear (72) running friction, friction reducing gear (72) provide the deceleration resistance of lift rotor (4) when rubbing with initiative reducing gear (71).

4. The electric take-off and landing composite wing aircraft according to claim 3, wherein: still be provided with elastic component (76) that resets in the groove of stepping down (75), elastic component (76) that resets sets up along perpendicular to transmission shaft (52) axis direction, elastic component (76) one end that resets is connected with groove of stepping down (75), the other end with initiative reducing gear (71) is connected, propulsion (64) promote when initiative reducing gear (71) stretches out in the race (53), elastic component (76) that resets receive the exogenic action and hold the power deformation, provide the drive the elastic force that initiative reducing gear (71) resets.

5. The electric take-off and landing composite wing aircraft according to claim 4, wherein: and a force-increasing elastic piece (77) is also arranged between the outer bracket (74) and the friction speed-reducing wheel (72).

6. The electric take-off and landing composite wing aircraft according to claim 5, wherein: the fixed propeller mechanism (8) comprises a fixed propeller propelling part (81), a fixed propeller pin (82), a position control elastic part (83) and a return elastic part (84), a straight hole is formed in the transmission shaft (52), the fixed propeller propelling part (81) and the return elastic part (84) are arranged in the straight hole, the return elastic part (84) is sleeved outside the fixed propeller propelling part (81), one end of the return elastic part (84) is connected with the straight hole, the other end of the return elastic part is connected with the fixed propeller propelling part (81), one end, facing the outer wall of the transmission shaft (52), of the fixed propeller propelling part (81) is provided with a pin groove (85), the position control elastic part (83) and the fixed propeller pin (82) are both positioned in the pin groove (85), one end of the position control elastic part (83) is connected with the pin groove (85), the other end of the position control elastic part is connected with the fixed propeller pin (82), and the fixed propeller pin (82) partially extends out of the pin groove (85) when being free of external force, be provided with on outer support (74) and supply to decide oar round pin (82) and insert slot (78) of establishing, propulsion motor (61) control propulsion spare (64) remove to with decide oar propulsion spare (81) keep away from when deciding oar round pin (82) one end conflict decide oar propulsion spare (81) remove along straight hole axial direction, control decide oar round pin (82) rotate to correspond with slot (78) position when inserting establish extremely in slot (78).

7. The electric take-off and landing composite wing aircraft according to claim 1, wherein: the nacelle structure is characterized in that a nacelle cavity (15) is formed in the connecting auxiliary frame (13), a retreating mechanism (9) is arranged in the nacelle cavity (15), a moving groove (16) communicated with the nacelle cavity (15) is formed in the connecting auxiliary frame (13) along the axis direction, the retreating mechanism (9) is connected with the nacelle (2), and the retreating mechanism (9) is used for controlling the nacelle (2) to perform sliding motion along the moving groove (16).

8. The electric take-off and landing composite wing aircraft according to claim 7, wherein: the withdrawing mechanism (9) comprises a withdrawing motor (91) and a withdrawing screw rod (92), the withdrawing screw rod (92) is coaxially and fixedly connected with the withdrawing motor (91), the withdrawing screw rod (92) is in threaded connection with the nacelle (2), and a sealing cover (17) used for sealing the nacelle cavity (15) is arranged at the end part of the connecting subframe (13).

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