CN218498970U

CN218498970U - Assembly structure of aircraft propeller motor and electricity accent

Info

Publication number: CN218498970U
Application number: CN202222751105.3U
Authority: CN
Inventors: 张建壮
Original assignee: Helipeller General Aircraft Co ltd
Current assignee: Yang Haiyan
Priority date: 2022-10-19
Filing date: 2022-10-19
Publication date: 2023-02-17
Anticipated expiration: 2032-10-19

Abstract

The utility model discloses an assembly structure of an aircraft propeller motor and an electric speed regulator, which comprises an electric speed regulator and a motor, wherein two end surfaces of the electric speed regulator are respectively provided with a binding post I and a binding post II, the upper ends of two side surfaces before and after the electric speed regulator are both connected with an electric speed regulator upper rib, and the lower ends of the two side surfaces before and after the electric speed regulator are both connected with an electric speed regulator lower rib; one end of the electric controller is connected with the motor fixing seat through a screw four, the other end of the electric controller is connected with the cantilever flange through a screw five, and the motor fixing seat is connected with the bottom end of the motor through a screw two. The electric regulation of this application utilizes electricity to adjust up the rib, electricity and adjusts down the rib and increase rigidity, will adjust electricity simultaneously through the cantilever flange and integrate to the fixed cantilever of motor on, compact structure occupation space reduces, and can utilize the screw in the motion to dispel the heat.

Description

Assembly structure that aircraft screw motor and electricity were transferred

Technical Field

The utility model relates to a technical field of aircraft particularly, relates to an assembly structure that aircraft screw motor and electricity were transferred.

Background

At present, many rotor crafts that appear at home and abroad are very many, and wherein most many rotor motors' electricity is transferred and is all directly installed in the side of motor, below or fairing the inside, if direct mount is at the motor side, the increase windage that will be great, if direct mount is under the motor, then the heat dissipation of electricity is transferred is not good and has increased the windage, if electricity is transferred and is installed in the fairing the inside, the heat dissipation of electricity equally transferring also has very big hidden danger. The connecting structure is improved in order to overcome the defects.

SUMMERY OF THE UTILITY MODEL

To the above-mentioned technical problem among the correlation technique, the utility model provides an assembled structure that aircraft screw motor and electricity were transferred can solve above-mentioned problem.

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

the assembling structure of the propeller motor and the electric controller of the aircraft comprises the electric controller and a motor, wherein two end surfaces of the electric controller are respectively provided with a first binding post and a second binding post, the upper ends of two side surfaces before and after the electric controller are both connected with an electric controller upper rib, and the lower ends of the two side surfaces before and after the electric controller are both connected with an electric controller lower rib; one end of the electric controller is connected with the motor fixing seat through a screw four, the other end of the electric controller is connected with the cantilever flange through a screw five, and the motor fixing seat is connected with the bottom end of the motor through a screw two.

Further, it connects through screw three to electrically tune upward the rib electrically tune, electrically tune down the rib and connect through screw one electrically tune, electrically tune upward the rib with the both ends of transferring the rib all stretch out and have the projecting part of step form.

Furthermore, the motor fixing seat is of an L-shaped structure, a first connecting surface of the motor fixing seat is provided with a first inserting groove matched with the extending portion, and a through hole is formed in the center of a second connecting surface of the motor fixing seat.

Furthermore, one end of the cantilever flange is provided with a second insertion groove matched with the extension part, and the other end of the cantilever flange is connected with the cantilever; a cavity is arranged in the cantilever flange.

Furthermore, the first binding post penetrates through the first connecting surface and extends into the lower part of the motor, and the second binding post extends into the cavity.

The utility model has the advantages that: the electric regulation of this application utilizes electricity to adjust up the rib, electricity and adjusts down the rib and increase rigidity, will adjust electricity simultaneously through the cantilever flange and integrate to the fixed cantilever of motor on, compact structure occupation space reduces, and can utilize the screw in the motion to dispel the heat.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

The present invention will be described in further detail with reference to the accompanying drawings.

Fig. 1 is an exploded view of an assembly structure of an aircraft propeller motor and an electric regulator according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of an assembly structure of aircraft propeller motor and electricity accent in the embodiment of the utility model.

In the figure:

1. electrically adjusting; 2. electrically adjusting the upper rib; 3. electrically adjusting the ribs; 2-3, an extension part; 4. a cantilever flange; 5. a motor fixing seat; 5-1, through holes; 6. a motor; 7. a first screw; 8. a second screw; 9. a third screw; 10. a binding post I; 11. a second wiring terminal; 12. a fourth screw; 13. a fifth screw; 14. a cavity.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art all belong to the protection scope of the present invention.

As shown in fig. 1-2, according to the embodiment of the present invention, an assembly structure of an aircraft propeller motor and an electric tilt comprises an electric tilt 1 and a motor 6, two end surfaces of the electric tilt 1 are respectively provided with a first terminal 10 and a second terminal 11, the upper ends of two front and rear sides of the electric tilt 1 are both connected with an electric tilt upper rib 2, and the lower ends of two front and rear sides of the electric tilt 1 are both connected with an electric tilt lower rib 3; one end of the electric regulator 1 is connected with a motor fixing seat 5 through a screw four 12, the other end of the electric regulator 1 is connected with a cantilever flange 4 through a screw five 13, and the motor fixing seat 5 is connected with the bottom end of a motor 6 through a screw two 8.

The utility model provides an in an embodiment, two electricity are transferred and are gone up rib 2 and two electricity and adjust down rib 3 and fix through three 9 of screws and screw 7 respectively and constitute a rigidity cantilever on 1 is transferred to electricity, then through cantilever flange 4 electricity 1 integrated to the cantilever, borrow electricity and transfer 1 rigidity, the bulk rigidity of the cantilever of improvement, and reduced the windage of wind.

The utility model provides an in one embodiment, through the switching of motor fixing base 5, electricity is transferred 1 and is located the side below of motor 6, and electricity is transferred 1 promptly and is just in time located the below of screw, is used for electricity to transfer 1 self heat dissipation by the wind that is convenient for borrow the screw production, and electricity is transferred 1 cooling surface and is exposed completely, and the heat dissipation is transferred by 1 electricity of being convenient for.

In one embodiment of the utility model, the step surface (namely the extension part 2-3) at one end of the rib 2 and the electric adjusting rib 3 are inserted into the first inserting groove on the motor fixing seat 5, the extension part 2-3 is provided with a screw hole, and the screw four 12 passes through the screw hole to fix the extension part, thereby ensuring the connection and fastening of the electric adjusting 1 and the motor fixing seat 5; the step surfaces (namely the extension parts 2-3) at the other ends of the electric adjusting upper rib 2 and the electric adjusting lower rib 3 are inserted into the second inserting groove on the cantilever flange 4, the extension parts 2-3 are provided with screw holes, and a screw five 13 penetrates through the screw holes to fix the electric adjusting upper rib 2 and the electric adjusting lower rib 3, so that the electric adjusting 1 is ensured to be connected and fastened with the cantilever flange 4.

In one embodiment of the present invention, the outgoing line of the motor 6 passes through the first terminal 10 of the electric tuning 1 through the through hole 5-1 and the second terminal 11 of the electric tuning 1 extends into the inner side of the cantilever flange 4, avoiding the exposure of the outgoing line.

In one embodiment of the present invention, one side of the cantilever flange 4 connecting cantilever is circular, but not limited thereto, and the interface shape of the cantilever flange 4 can be adjusted according to the shape of the cantilever.

The above description is only for the preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The utility model provides an aircraft screw motor and package assembly of electricity accent, includes electricity accent (1) and motor (6), two terminal surfaces of electricity accent (1) are equipped with terminal one (10) and terminal two (11), its characterized in that respectively: the upper ends of the front side surface and the rear side surface of the electric regulator (1) are connected with electric regulator upper ribs (2), and the lower ends of the front side surface and the rear side surface of the electric regulator (1) are connected with electric regulator lower ribs (3); one end of the electric power controller (1) is connected with the motor fixing seat (5) through the fourth screw (12), the other end of the electric power controller (1) is connected with the cantilever flange (4) through the fifth screw (13), and the motor fixing seat (5) is connected with the bottom end of the motor (6) through the second screw (8).

2. The aircraft propeller motor and electric tilt assembly structure of claim 1, wherein: electrically transfer and go up rib (2) and connect through three (9) screws electricity and transfer (1), it connects through screw (7) electricity to transfer down rib (3) electricity (1), electrically transfer go up rib (2) with the both ends of transferring down rib (3) all stretch out and have the extension (2-3) of step form.

3. The aircraft propeller motor and electric tilt assembly structure of claim 2, wherein: the motor fixing seat (5) is of an L-shaped structure, a first connection surface of the motor fixing seat (5) is provided with a first insertion groove matched with the extension part (2-3), and the center of a second connection surface of the motor fixing seat (5) is provided with a through hole (5-1).

4. The structure of claim 3, wherein the structure comprises: one end of the cantilever flange (4) is provided with a second inserting groove matched with the extension part (2-3), and the other end of the cantilever flange is connected with a cantilever; a cavity (14) is arranged in the cantilever flange (4).

5. The aircraft propeller motor and electric tilt assembly structure of claim 4, wherein: the first terminal (10) penetrates through the first connection surface and extends below the motor (6), and the second terminal (11) extends into the cavity (14).