CN216636814U

CN216636814U - Aircraft propeller clamping and center-connection integrated motor tilting mechanism

Info

Publication number: CN216636814U
Application number: CN202123286221.4U
Authority: CN
Inventors: 杨新军; 陈梦飞; 李银华
Original assignee: Feiyang Haozhan Precision Hardware Shenzhen Co ltd
Current assignee: Feiyang Haozhan Precision Hardware Shenzhen Co ltd
Priority date: 2021-12-24
Filing date: 2021-12-24
Publication date: 2022-05-31
Anticipated expiration: 2031-12-24

Abstract

The utility model discloses an aircraft propeller blade clamp middle-connection integrated motor tilting mechanism, which relates to the technical field of propeller tilting and comprises a cantilever and a mounting base fixedly connected with an aircraft body, wherein one end of the cantilever is provided with a positioning base groove, a lift force motor is fixedly mounted in the positioning base groove, one end of the cantilever is provided with a diameter expanding head, a conduit is arranged in the mounting base, one end of the conduit extends into the positioning base groove, the other end of the conduit penetrates through the diameter expanding head and then is communicated with the mounting base, and the diameter expanding head is rotatably connected with the mounting base through a connecting mechanism. The beneficial effects of the utility model are: the direction of the cantilever is freely tilted so as to achieve the purpose of changing the driving direction of the propeller, the tilting torque is large, the loss is small, and the tilting mechanism is suitable for being used in a high-load state of an aerial aircraft.

Description

Aircraft propeller clamping and center-connection integrated motor tilting mechanism

Technical Field

The utility model relates to the technical field of propeller tilting, in particular to a tilting mechanism of a clamping and middle-connection integrated motor of an aircraft propeller.

Background

The propeller is used as a propelling mechanism of an aircraft and is a core part of the aircraft, wherein the propeller clamp is a part for connecting the motor and the propeller, and the driving direction of the propeller changes when the motor tilts by an angle.

The publication numbers are: CN206466175U is used for becoming motor tilting mechanism of modal aircraft discloses, a tilting mechanism, including drive arrangement, transmission, fixing base and mount pad, drive arrangement includes motor, reduction gear, little screw pitch lead screw, nut and bolt, transmission includes flange and angle sensor, the fixing base includes the bearing, drive arrangement's reduction gear and fixing base interconnect, drive arrangement's bolt assembly is on the flange, the bearing and the mutual suit of flange of fixing base, the flange is connected with the fixing base.

The driving direction of the screw of the aircraft is not one-dimensional, need carry out the change of certain angle as required in flight, once need vert the mechanism and cooperate it to carry out the change of angle, at present in the use, adopt worm gear transmission's mode, the cantilever that drives fixed screw verts, it has the auto-lock nature to have through the worm gear transmission, it dies to realize the lock of cantilever, but the torsion moment of worm gear is not high, but in flight, the screw can provide very big lift, the lift is all concentrated on the cantilever, the worm gear needs high torsion to come the effect this moment, just can realize the rotation to the cantilever, consequently, the loss to the worm gear is great, do not utilize for a long time.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a tilting mechanism of a middle-connection integrated motor of an aircraft propeller clamp, which can freely tilt a cantilever in the direction so as to achieve the purpose of changing the driving direction of a propeller, has large tilting torque and small loss, and is suitable for being used in a high-load state of an aerial aircraft.

In order to achieve the purpose, the utility model provides the following technical scheme: the utility model provides an aircraft propeller presss from both sides antithetical couplet integration motor mechanism that verts, including the cantilever and with aircraft fuselage fixed connection's mounting base, the location base groove has been seted up to the one end of cantilever, the inside fixed mounting in location base groove has the lift motor, the one end of cantilever is provided with the hole enlargement head, the inside of mounting base is provided with the conduit, the one end of conduit extends to in the location base groove, the other end of conduit runs through hole enlargement head back intercommunication mounting base, hole enlargement head with rotate through coupling mechanism between the mounting base and connect.

Preferably, the connecting mechanism comprises a positioning core, the positioning core is in sliding sleeve connection with the mounting base, a limit gear is arranged on the outer side of the positioning core, and a driving mechanism for driving the limit gear to rotate is arranged in the mounting base.

Preferably, one side of the limit gear is in sliding fit with the inner wall of the mounting base, and a flange plate is arranged on the mounting base.

Preferably, a through hole is formed in the positioning core, and one end of the conduit penetrates through the through hole.

Preferably, the driving mechanism comprises a driving motor, the driving motor is fixedly installed on the inner wall of the installation base, a driving gear is fixedly installed on an output shaft of the driving motor, and the driving gear and the limiting gear are meshed with each other.

Preferably, the cantilever and the expanding head are integrally arranged, and both the cantilever and the expanding head are arranged in a hollow structure.

Compared with the prior art, the utility model has the beneficial effects that: this antithetical couplet integration motor mechanism of verting in aircraft propeller clamp: the installation base is connected with the aircraft, rotate between installation base and the cantilever, the lift of screw is being born to the cantilever in flight, make the atress direction of location core upwards, consequently, receive at the location core, the ascending rotatory power of axial is less, can guarantee the steady of cantilever all the time, when needs the cantilever to vert, it is rotatory to drive driving gear and limit gear through driving motor, great gear ratio has between driving gear and the limit gear, torsion can be greater than the stress that the location core bore, consequently can vert the location core in step, make the direction of drive of screw change, can carry out verting of direction to the cantilever freely, in order to reach the purpose that changes screw direction of drive, it is big to vert the moment of torsion, the loss is less, be fit for using under aerial aircraft high load condition.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is an overall cross-sectional view of the present invention;

fig. 3 is a schematic structural diagram of the connecting mechanism of the present invention.

In the figure: 10. a cantilever; 11. positioning a base groove; 12. a lift motor; 13. an expanding head; 14. a conduit; 15. mounting a base; 16. a flange plate; 17. a positioning core; 18. a driving gear; 19. a drive motor; 20. a limit gear; 21. and a through hole.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution: an aircraft propeller and blade clamp middle-connection integrated motor tilting mechanism comprises a cantilever 10 and a mounting base 15 fixedly connected with an aircraft body, wherein one end of the cantilever 10 is provided with a positioning base groove 11, a lift motor 12 is fixedly mounted inside the positioning base groove 11, the lift motor 12 can be connected with a propeller through a blade clamp, the lift motor 12 provides driving force for the aircraft, one end of the cantilever 10 is provided with an expanding head 13, a conduit 14 is arranged inside the mounting base 15, one end of the conduit 14 extends into the positioning base groove 11, the conduit 14 is used for penetrating a wire, so that the wire can be observed into the aircraft from the inside of the cantilever 10, the wire is connected with the lift motor 12, the other end of the conduit 14 penetrates through the expanding head 13 and then is communicated with the mounting base 15, the mounting base 15 is used for being connected with the aircraft, the expanding head 13 is rotatably connected with the mounting base 15 through a connecting mechanism, the expanding head 13 is rotatably connected with the mounting base 15, and the expanding head 13 can be rotated to rotate the cantilever 10, so that the driving direction of the lift motor 12 can be changed.

Referring to fig. 2 and 3, the connecting mechanism includes a positioning core 17, the positioning core 17 is slidably sleeved with the mounting base 15, a limit gear 20 is disposed on an outer side of the positioning core 17, the mounting base 15 is connected with the aircraft, the mounting base 15 rotates with the cantilever 10, the cantilever 10 bears a lift force of the propeller in flight, so that a force bearing direction of the positioning core 17 is upward, and therefore, a force applied to the positioning core 17 in an axial direction is small, and the cantilever 10 is always stable, a driving mechanism for driving the limit gear 20 to rotate is disposed inside the mounting base 15, the driving mechanism includes a driving motor 19, the driving motor 19 is fixedly mounted on an inner wall of the mounting base 15, a driving gear 18 is fixedly mounted on an output shaft of the driving motor 19, the driving gear 18 is engaged with the limit gear 20, and the driving gear 18 can be driven to rotate by the driving motor 19, the driving gear 18 drives the limit gear 20 to rotate, a large gear ratio is arranged between the driving gear 18 and the limit gear 20, so that the torsion applied to the limit gear 20 can be larger than the stress borne by the positioning core 17, the positioning core 17 can be synchronously tilted, the positioning core 17 can drive the expanding head 13 and the cantilever 10 to rotate, the driving direction of the propeller is changed, the cantilever 10 can be freely tilted in the direction, the purpose of changing the driving direction of the propeller is achieved, the tilting torque is large, the loss is small, and the propeller is suitable for being used in a high-load state of an aerial aircraft

Referring to fig. 2, one side of the limit gear 20 is in sliding fit with the inner wall of the mounting base 15, a flange 16 is arranged on the mounting base 15, a through hole 21 is formed in the positioning core 17, one end of the wire conduit 14 penetrates through the through hole 21, the flange 16 is convenient to mount with an aircraft, and the through hole 21 is used for penetrating through the wire.

Referring to fig. 2, the cantilever 10 and the expanding head 13 are integrally disposed, and both the cantilever 10 and the expanding head 13 are disposed in a hollow structure, so as to have a greater strength, and the hollow structure has a function of reducing weight.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides an antithetical couplet integration motor mechanism of verting in aircraft screw oar clamp which characterized in that: including cantilever (10) and with aircraft fuselage fixed connection's mounting base (15), location base groove (11) have been seted up to the one end of cantilever (10), the inside fixed mounting of location base groove (11) has lift motor (12), the one end of cantilever (10) is provided with hole enlargement head (13), the inside of mounting base (15) is provided with conduit (14), the one end of conduit (14) extends to in location base groove (11), the other end of conduit (14) runs through hole enlargement head (13) back intercommunication mounting base (15), hole enlargement head (13) with rotate through coupling mechanism between mounting base (15) and connect.

2. The aircraft propeller clamp inline integrated motor tilting mechanism of claim 1, further comprising: the connecting mechanism comprises a positioning core (17), the positioning core (17) and the mounting base (15) are sleeved in a sliding mode, a limiting gear (20) is arranged on the outer side of the positioning core (17), and a driving mechanism for driving the limiting gear (20) to rotate is arranged inside the mounting base (15).

3. The aircraft propeller clamp inline integrated motor tilting mechanism of claim 2, further comprising: one side of limiting gear (20) with the inner wall of mounting base (15) is in sliding fit, be provided with ring flange (16) on mounting base (15).

4. The aircraft propeller clamp inline integrated motor tilting mechanism of claim 2, further comprising: a through hole (21) is formed in the positioning core (17), and one end of the wire conduit (14) penetrates through the through hole (21).

5. The aircraft propeller clamp inline integrated motor tilting mechanism of claim 2, further comprising: the driving mechanism comprises a driving motor (19), the driving motor (19) is fixedly installed on the inner wall of the installation base (15), a driving gear (18) is fixedly installed on an output shaft of the driving motor (19), and the driving gear (18) and the limiting gear (20) are meshed with each other.

6. The aircraft propeller clamp inline integrated motor tilting mechanism of claim 1, further comprising: the cantilever (10) and the expanding head (13) are integrally arranged, and the cantilever (10) and the expanding head (13) are both arranged in a hollow structure.