CN106516105B

CN106516105B - Aircraft oar face adjustment mechanism

Info

Publication number: CN106516105B
Application number: CN201610976788.9A
Authority: CN
Inventors: 杨国社; 赵伟
Original assignee: Helipeller General Aircraft Co ltd
Current assignee: Yang Haiyan
Priority date: 2016-11-08
Filing date: 2016-11-08
Publication date: 2023-07-04
Anticipated expiration: 2036-11-08
Also published as: CN106516105A

Abstract

The invention discloses an aircraft paddle surface adjusting mechanism, which comprises a bearing seat with a fork-shaped structure, wherein a ball cage jacket is arranged in the middle of the bearing seat, one end of the ball cage jacket is connected with a paddle shaft for installing a propeller, the other end of the ball cage jacket is connected with a shaft for installing a belt pulley, the whole system is driven by a belt, and the belt pulley is transmitted to the paddle shaft, and as the upper end and the lower end of the paddle shaft are connected through the ball cage jacket, the upper end of the paddle shaft can tilt around the ball cage jacket by a certain angle. The upper end of the bearing seat is provided with two cantilever push rods which are perpendicular to each other along the circumferential direction, the outer ends of the cantilever push rods are connected with the telescopic rods of the electric push rods through hinges, the whole bearing seat can turn around the center of the ball cage jacket under the action of the electric push rods, and the inclination of the bearing seat causes the inclination of the axis angle of the paddle shaft, so that the change of the angle of the rotating plane of the paddle is realized, and the purpose of controlling the direction of an aircraft is achieved.

Description

Aircraft oar face adjustment mechanism

Technical Field

The invention relates to the technical field of direction adjusting mechanisms of aircrafts, in particular to an aircraft paddle surface adjusting mechanism.

Background

The flight direction of the aircraft can be controlled by adjusting the paddle surface of the aircraft in the flight process, so that the stable flight of the aircraft is ensured.

The Chinese patent with the patent number ZL2013104235571 discloses a small-sized aircraft capable of taking off and landing on complex terrains, which comprises a main frame, two ducts, a transverse swing wing, a longitudinal swing wing, a direction control mechanism, an engine and a bracket, wherein the axes of the two ducts are parallel. The center of the inner cavity of the culvert is provided with a shaft seat, a paddle shaft is arranged in the shaft seat, and the shaft seat and the paddle shaft are in rotatable fit. The upper end of the propeller shaft is provided with a propeller, and the outer walls of the two ducts are connected by a connecting frame. The main frame is connected to the bottom of the connecting frame, and a seat is arranged on the front side of the main frame. The output shaft of the engine is connected with the two paddle shafts by a first transmission mechanism. The direction control mechanism is positioned on the main frame and is respectively connected with the transverse swing wings and the longitudinal swing wings by virtue of the second transmission mechanism. The direction control mechanism is positioned below the two propellers, so that a longitudinal rudder plate and a transverse rudder plate in the direction control mechanism are positioned below the rotating planes of the propellers. Because the longitudinal rudder plate and the transverse rudder plate in the direction control mechanism are positioned below the rotating plane of the propeller, when the aircraft flies, the air flow below the propeller acts on the rudder plate to change the gesture of the aircraft, thereby controlling the flying direction of the aircraft. Since the change of attitude of the aircraft is effected by the airflow under the propeller acting on the rudder plate, the airflow acting on the multiple plates consumes a part of the power. Theoretical calculation and test prove that the power of the aircraft can be reduced by more than 10 percent due to the blocking of the rudder plate. Therefore, the small aircraft has larger power loss and small effective lift force.

Disclosure of Invention

The invention aims to provide an aircraft paddle surface adjusting mechanism, which overcomes the defects in the prior art.

In order to achieve the technical purpose, the technical scheme of the invention is realized as follows:

the propeller surface adjusting mechanism of the aircraft comprises a bearing seat fixed at one end of a girder, wherein a first bearing and a second bearing are respectively arranged on the upper side and the lower side of the bearing seat; a ball cage jacket is arranged between the inner ring of the first bearing and the inner ring of the second bearing, a belt pulley is arranged between the first bearing and the second bearing, and the ball cage jacket is fixedly connected with the belt pulley; the upper end of the ball cage coat is fixedly connected with a collet, the upper surface of the collet is provided with a first steel ball, and the first steel ball is arranged at the central hole of the tail end of the paddle shaft; the middle part and the lower extreme of oar axle install axle sleeve and rolling element respectively, the both ends of axle sleeve install bearing three and bearing four, bearing three and bearing four fixed mounting in the axle bed, the axle bed pass through steel ball two and outer ball cover cooperation connection, outer ball cover fixed setting in the upper surface of bearing frame, the axle bed pass through one side of end cover fixedly connected with cantilever push rod, cantilever push rod hinged joint have the push rod, the push rod install on the push rod mount pad, push rod mount pad and bearing frame fixed connection.

Further, the bearing seat is of a fork-shaped structure, and the first bearing and the second bearing are respectively arranged on the upper side and the lower side of the fork-shaped structure.

Preferably, the support column is mounted inside the most distal end of the fork structure.

Furthermore, collars are arranged between the first bearing and the belt pulley and between the belt pulley and the second bearing.

Further, the upper surface of the bottom support is in an inner sphere shape, and the first steel ball is arranged at the lowest part of the inner sphere on the upper surface of the bottom support.

Further, the outer part of the shaft seat is of an outer spherical structure.

Further, the inner part of the outer spherical cover is of an outer spherical structure; an annular groove is formed in the inner side of the outer ball cover, and the second steel ball is arranged in the annular groove.

Preferably, the end cover is fixedly connected with the cantilever push rod through a second bolt.

Further, a shaft sleeve is arranged between the paddle shaft and the end cover.

Further, the outer ball cover is fixedly connected with the bearing seat through bolts.

After the technical scheme is adopted, the invention has the following beneficial effects: the aircraft direction control mechanism can reduce the power loss of a small aircraft, improve the effective lift force, and simultaneously, ensure that the control of the aircraft is more convenient and controllable. More precisely, a mechanism for changing the rotating plane of the propeller is adopted to achieve the purpose of controlling the aircraft.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic structural view of an aircraft blade adjustment mechanism according to an embodiment of the present invention;

in the figure: 1. a propeller; 2. a paddle shaft; 3. an end cap; 4. a shaft sleeve; 5. a shaft seat; 6. a second steel ball; 7. an outer ball cover; 8. a first bolt; 9. a first bearing; 10. a bearing seat; 11. a belt pulley; 12. a second collar; 13. a lower end cap; 14. a second bearing; 15. a ball cage coat; 16. a first collar; 17. a support column; 18. an electric push rod; 19. a bottom support; 20. a first steel ball; 21. a push rod mounting seat; 22. a rolling element; 24. a third bearing; 25. a shaft sleeve; 26. a bearing IV; 27. a cantilever push rod; 28. and a second bolt.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which are derived by a person skilled in the art based on the embodiments of the invention, fall within the scope of protection of the invention.

As shown in fig. 1, in the aircraft propeller surface adjusting mechanism according to the embodiment of the invention, a propeller 1 is fixed at the upper end of a propeller shaft 2, and further comprises a bearing seat 10 fixed at one end of a girder, wherein a first bearing 9 and a second bearing 14 are respectively arranged at the upper side and the lower side of the bearing seat 10; a ball cage jacket 15 is arranged between the inner ring of the first bearing 9 and the inner ring of the second bearing 14, a belt pulley 11 is arranged between the first bearing 9 and the second bearing 14, and the ball cage jacket 15 is fixedly connected with the belt pulley 11; the upper end of the ball cage coat 15 is fixedly connected with a bottom bracket 19, the upper surface of the bottom bracket 19 is provided with a first steel ball 20, and the first steel ball 20 is arranged at the central hole of the tail end of the paddle shaft 2; the middle part and the lower extreme of oar axle 2 install axle sleeve 25 and rolling element 22 respectively, the both ends of axle sleeve 25 install bearing three 24 and bearing four 26, bearing three 24 and bearing four 26 fixed mounting in axle bed 5, axle bed 5 pass through steel ball two 6 and be connected with outer spherical cover 7 cooperation, outer spherical cover 7 fixed setting at the upper surface at bearing frame 10, axle bed 5 pass through end cover 3 fixedly connected with two mutually perpendicular cantilever push rods 27, cantilever push rod 27 hinged joint have electric putter 18, electric putter 18 install on push rod mount pad 21, push rod mount pad 21 and bearing frame 10 fixed connection.

In one embodiment, the bearing seat 10 is a fork structure, and the first bearing 9 and the second bearing 14 are respectively mounted on the upper side and the lower side of the fork structure.

In one embodiment, the fork-like structure has a support post 17 mounted internally at its distal-most end.

In one embodiment, a collar one 16 is arranged between the bearing one 9 and the belt pulley 11; a second collar 12 is arranged between the belt pulley 11 and the second bearing 14.

In one embodiment, the upper surface of the bottom bracket 19 is in an inner sphere shape, and the first steel ball 20 is installed at the lowest part of the inner sphere on the upper surface of the bottom bracket 19.

In a specific embodiment, the outer portion of the shaft seat 5 is an outer spherical structure.

In one embodiment, the inner part of the outer spherical cover 7 is an outer spherical structure; an annular groove is formed in the inner side of the outer ball cover 7, and the second steel ball 6 is arranged in the annular groove.

In a specific embodiment, the end cover 3 and the cantilever push rod 27 are fixedly connected through a second bolt 28.

In a specific embodiment, a shaft sleeve 4 is arranged between the paddle shaft 2 and the end cover.

In a specific embodiment, the bearing seat 10 is fixedly connected with the outer ball cover 7 at the upper end thereof through a first bolt 8, and a lower end cover 13 is arranged at the lower end of the bearing seat 10.

The invention adopts a fork-shaped bearing seat 10, a ball cage jacket 15 is arranged in the middle of the bearing seat 10, one end of the ball cage jacket 15 is connected with a propeller shaft 2 for installing a propeller 1, the other end of the ball cage jacket 15 is connected with a shaft for installing a belt pulley 11, the whole system is driven by a belt and is transmitted to the propeller shaft 2 through the belt pulley 11, and the upper end and the lower end of the propeller shaft 2 are connected through the ball cage jacket 15, so that the upper end of the propeller shaft 2 can tilt around the ball cage jacket 15 for a certain angle. Two mutually perpendicular cantilever push rods 27 are arranged at the upper end of the bearing seat 10 along the circumferential direction, the outer ends of the cantilever push rods 27 are connected with telescopic rods of the electric push rods 18 through hinges, the whole bearing seat 10 can turn around the center of the ball cage jacket 15 under the action of the electric push rods 18, and the inclination of the axis angle of the propeller shaft 2 is caused due to the inclination of the bearing seat 10, so that the change of the rotation plane angle of the propeller 1 is realized, and the direction of an aircraft is controlled.

The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.

Claims

1. The propeller (1) is fixed at the upper end of a propeller shaft (2), and is characterized by further comprising a bearing seat (10) fixed at one end of a girder, wherein a first bearing (9) and a second bearing (14) are respectively arranged on the upper side and the lower side of the bearing seat (10); a ball cage jacket (15) is arranged between the inner ring of the first bearing (9) and the inner ring of the second bearing (14), a belt pulley (11) is arranged between the first bearing (9) and the second bearing (14), and the ball cage jacket (15) is fixedly connected with the belt pulley (11); the upper end of the ball cage coat (15) is fixedly connected with a bottom bracket (19), the upper surface of the bottom bracket (19) is provided with a first steel ball (20), and the first steel ball (20) is arranged at the central hole of the tail end of the paddle shaft (2); the middle part and the lower extreme of oar axle (2) install axle sleeve (25) and rolling element (22) respectively, the both ends of axle sleeve (25) install bearing three (24) and bearing four (26), bearing three (24) and bearing four (26) fixed mounting in axle bed (5), axle bed (5) pass through steel ball two (6) and outer ball cover (7) cooperation connection, outer ball cover (7) fixed setting in the upper surface of bearing frame (10), axle bed (5) pass through one side of end cover (3) fixedly connected with cantilever push rod (27), cantilever push rod (27) hinged joint have push rod (18), push rod (18) install on push rod mount pad (21), push rod mount pad (21) and bearing frame (10) fixed connection, bearing frame (10) be fork-shaped structure, bearing one (9) and bearing two (14) install respectively in fork-shaped structure's upside and downside, fork-shaped structure's distal end have one bearing (17) and one end is equipped with between bearing (16) and the support column (11); a second shaft collar (12) is arranged between the belt pulley (11) and the second bearing (14), the upper surface of the bottom support (19) is in an inner sphere shape, the first steel ball (20) is arranged at the lowest position of the inner sphere on the upper surface of the bottom support (19), the outer part of the shaft seat (5) is in an outer sphere structure, and the inner part of the outer sphere cover (7) is in an outer sphere structure; an annular groove is formed in the inner side of the outer ball cover (7), and the second steel ball (6) is arranged in the annular groove.

2. An aircraft blade adjustment mechanism according to claim 1, characterized in that the end cap (3) and the cantilever push rod (27) are fixedly connected by a second bolt (28).

3. An aircraft blade adjustment mechanism according to claim 1, characterized in that a bushing (4) is arranged between the shaft (2) and the end cap.

4. The propeller surface adjusting mechanism of claim 1, wherein the bearing seat (10) is fixedly connected with the outer spherical cover (7) at the upper end of the bearing seat through a first bolt (8), and a lower end cover (13) is arranged at the lower end of the bearing seat (10).