CN106628124B

CN106628124B - Automatic adjusting and balancing mechanism for left rotor wing and right rotor wing of double-rotor aircraft

Info

Publication number: CN106628124B
Application number: CN201610976790.6A
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: 2023-06-06
Anticipated expiration: 2036-11-08
Also published as: CN106628124A

Abstract

The invention relates to an automatic adjusting and balancing mechanism for left and right rotors of a double-rotor aircraft, which comprises a girder pipe and two rotor wing bodies, wherein the rotor wing bodies are symmetrically arranged at the left end and the right end of the girder pipe, each rotor wing body comprises a shaft seat, each shaft seat is fixedly connected with a half shaft, each half shaft is slidably connected in the girder pipe through a linear bearing, one end, far away from each shaft seat, of each half shaft is hinged with a telescopic rod of an electric push rod, each electric push rod is fixedly arranged in the girder pipe, each electric push rod is fixedly provided with a linear displacement sensor corresponding to each half shaft, and each linear displacement sensor and each electric push rod are electrically connected with an automatic flight control system. The beneficial effects of the invention are as follows: the force arm of the left rotor wing and the right rotor wing from the center of the aircraft can be effectively changed, and the purpose of left and right automatic balance is achieved.

Description

Automatic adjusting and balancing mechanism for left rotor wing and right rotor wing of double-rotor aircraft

Technical Field

The invention relates to the technical field of double-rotor aircraft, in particular to an automatic balance adjusting mechanism for left and right rotors of a double-rotor aircraft.

Background

At present, the control technology of the multi-rotor unmanned aerial vehicle is mature, the stability is strong, but the balance stability problem is faced for the double-rotor aircraft. The balance of the twin rotors includes front-to-back balance and left-to-right balance. For electric double-rotor wings, the left-right balance of the electric double-rotor wings is realized mainly by changing the rotating speed of the rotor wings, and for oil-driven double-rotor wings, torque-variable paddles are generally adopted, and the lift forces at the two ends of the paddles are different by changing the pitch of the paddles, so that the purpose of balance is achieved. However, the oil-driven fixed-torque double rotor wing has a problem of left-right balance.

Therefore, a balancing system capable of effectively solving the left-right balancing problem of the oil-driven fixed-torque double rotor wing is developed, and the balancing system becomes a problem to be solved urgently by the industry.

Disclosure of Invention

The invention provides an automatic balance adjusting mechanism for left and right rotors of a double-rotor aircraft, which overcomes the defects of the prior art.

The aim of the invention is realized by the following technical scheme:

the utility model provides an automatically regulated balance mechanism for rotor about two rotor crafts, includes girder pipe and two rotor main bodies, rotor main body symmetry sets up the left and right sides both ends at this girder pipe, the rotor main body includes the axle bed, axle bed fixedly connected with semi-axis, the semi-axis passes through linear bearing sliding connection in this girder pipe, the one end that this axle bed was kept away from to the semi-axis articulates there is electric putter's telescopic link, electric putter fixed mounting is in this girder pipe, fixed mounting has the linear displacement sensor that corresponds with this semi-axis on the electric putter, linear displacement sensor and electric putter all electricity are connected with automatic flight control system.

Further, the shaft seat is welded with a first bearing sleeve, and the shaft seat and the first bearing sleeve jointly form a cavity capable of clamping the half shaft.

Further, the first bearing sleeve is in sliding connection with a first bearing mounting seat fixedly mounted in the girder pipe through a first linear bearing.

Further, the two ends of the girder pipe are fixedly provided with girder pipe sleeves which can fix the bearing outer rings of the first bearing installation seats.

Further, a second bearing sleeve and a spline are further arranged on the half shaft, a second bearing mounting seat and a spline sleeve corresponding to the spline are arranged in the girder pipe, and the second bearing sleeve is in sliding connection with the second bearing mounting seat through a second linear bearing.

Further, an electric push rod mounting seat capable of fixing the electric push rod is fixedly arranged in the girder pipe.

Further, the telescopic end of the linear displacement sensor is fixedly connected to the second bearing sleeve.

Further, the left shaft seat and the right shaft seat are connected through a belt, and the belt is positioned between the outer part of the half shaft and the inner wall of the girder pipe.

The beneficial effects of the invention are as follows: the force arm of the left rotor wing and the right rotor wing from the center of the aircraft can be effectively changed, and the purpose of left and right automatic balance is achieved.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed 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 other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Figure 1 is a cross-sectional view of an automatically adjusting balancing mechanism for the left and right rotors of a dual rotor aircraft in accordance with an embodiment of the present invention.

In the figure:

1. a girder pipe; 2. an electric push rod mounting seat; 3. an electric push rod; 4. a linear displacement sensor; 5. a second linear bearing; 6. a second bearing mounting seat; 7. a second bearing sleeve; 8. a spline; 9. a spline housing; 10. a first bearing housing; 11. a first bearing mount; 12. a first linear bearing; 13. a half shaft; 14. a shaft seat; 15. a belt; 16. the girder is sleeved with a pipe sleeve.

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, an automatic balance adjustment mechanism for left and right rotors of a dual-rotor aircraft according to an embodiment of the present invention includes a girder pipe 1 and two rotor bodies, the rotor bodies are symmetrically disposed at left and right ends of the girder pipe 1, the rotor bodies include shaft seats 14, the shaft seats 14 are fixedly connected with half shafts 13, the half shafts 13 are slidably connected in the girder pipe 1 through linear bearings, one ends of the half shafts 13 far away from the shaft seats 14 are hinged with telescopic rods of electric push rods 3, the electric push rods 3 are fixedly mounted in the girder pipe 1, linear displacement sensors 4 corresponding to the half shafts 13 are fixedly mounted on the electric push rods 3, and the linear displacement sensors 4 and the electric push rods 3 are electrically connected with an automatic flight control system.

In a specific embodiment of the present invention, the shaft seat 14 is welded with the first bearing sleeve 10, and the shaft seat 14 and the first bearing sleeve 10 together form a cavity capable of clamping the half shaft 13.

In one embodiment of the present invention, the first bearing housing 10 is slidably connected to a first bearing mount 11 fixedly mounted inside the girder tube 1 through a first linear bearing 12.

In one embodiment of the present invention, the girder pipe sleeve 16 capable of fixing the bearing outer ring of the first bearing mount 11 is fixedly installed at both ends of the girder pipe 1.

In a specific embodiment of the present invention, the second bearing sleeve 7 and the spline 8 are further installed on the half shaft 13, the second bearing mounting seat 6 and the spline sleeve 9 corresponding to the spline 8 are installed inside the girder pipe 1, and the second bearing sleeve 7 is slidably connected with the second bearing mounting seat 6 through the second linear bearing 5.

In a specific embodiment of the present invention, the electric putter mount 2 capable of fixing the electric putter 3 is fixedly installed inside the girder pipe 1.

In one embodiment of the invention, the telescopic end of the linear displacement sensor 4 is fixedly connected to the second bearing housing 7.

In one embodiment of the invention, the left and right axle seats 14 are connected by a belt 15, the belt 15 being located between the outside of the axle half 13 and the inner wall of the girder tube 1.

In order to facilitate understanding of the above technical solutions of the present invention, the following describes the above technical solutions of the present invention in detail by a specific usage manner.

The fixing connection and the fixing installation mode adopted by the invention can be the conventional modes such as bolt fixing and welding.

The system mainly comprises a girder pipe 1, an electric push rod 3, a half shaft 13, a shaft seat 14 and the like. The girder pipe 1 is hollow tubular structure, has upper and lower two parts to form, has electric putter mount pad 2 at girder pipe internally mounted, and fixed mounting has electric putter 3 on the electric putter mount pad, and electric putter 3's telescopic link passes through the hinge with the inner end of semi-axis 13 and links to each other, and electric putter 3's upper end fixed mounting of shell has sharp displacement sensor 4, and the flexible end and the semi-axis 13 fixed connection of sharp displacement sensor 4. The second bearing sleeve 7 is arranged outside the inner end of the half shaft 13, and the second linear bearing 5 and the second bearing mounting seat 6 are arranged outside the second bearing sleeve 7. The middle section of the half shaft 13 is fixedly provided with a spline 8, and a spline housing 9 matched with the spline 8 is fixedly arranged in the girder pipe. The outer end internally mounted of girder pipe 1 has first bearing mount pad 11, and first linear bearing 12 is installed to the inside of first bearing mount pad 11, and the hole of first linear bearing 12 is sliding fit with the first bearing housing 10 of installing in semi-axis 13 outside. The girder pipe sleeve 16 is installed outside the outer end of the girder pipe 1. The outer end of the half shaft 13 is fixedly connected with the shaft seat 14. A belt 15 is provided between the outside of the half shaft and the inner wall of the girder.

The automatic flight control system adopts the existing flight control system, the automatic flight control system is used as a control center of the whole device, and the linear displacement sensor 4 and the electric push rod 3 are electrically connected with the automatic flight control system.

The invention mainly changes the force arm of the left rotor wing and the right rotor wing from the center of the aircraft so as to achieve the purpose of left-right automatic balance. The inside of both ends of girder pipe 1 all has the semi-axis 13 that can control the removal, and the inner end of semi-axis 13 links to each other with the telescopic link of electric putter 3, and the outer end of semi-axis 13 links firmly with axle bed 14, through electric putter 3 automatic control semi-axis 13 flexible to change the distance of axle bed 14 from the aircraft center. The automatic flight control system is used for controlling the operation of the electric push rod 3 according to the signal fed back by the linear displacement sensor 4, when the half shaft 13 is in the control process, if the electric push rod 3 at one end is retracted inwards, the electric push rod 3 at the other end extends outwards, so that the two shaft seats 14 are offset to one side at the same time, and the left and right sides of the aircraft are balanced.

In summary, by means of the technical scheme of the invention, the force arm of the left rotor wing and the right rotor wing from the center of the aircraft can be effectively changed, and the purpose of left-right automatic balance is achieved.

The present invention is not limited to the above-described preferred embodiments, and any person who can obtain other various products under the teaching of the present invention, however, any change in shape or structure of the product is within the scope of the present invention, and all the products having the same or similar technical solutions as the present application are included.

Claims

1. The utility model provides an automatically regulated balance mechanism for rotor about two rotor crafts, includes girder pipe (1) and two rotor main bodies, rotor main body symmetry sets up the left and right sides both ends in this girder pipe (1), rotor main body includes axle bed (14), its characterized in that, axle bed (14) fixedly connected with semi-axis (13), semi-axis (13) are through linear bearing sliding connection in this girder pipe (1), the telescopic link that has electric putter (3) is articulated to one end that this axle bed (14) was kept away from to semi-axis (13), electric putter (3) fixed mounting is in this girder pipe (1), fixed mounting has linear displacement sensor (4) that correspond with this semi-axis (13) on electric putter (3), linear displacement sensor (4) and electric putter (3) all are electrically connected with automatic flight control system, automatic flight control system is used for according to the signal of linear displacement sensor (4) feedback, control electric putter (3) operation, when semi-axis (13) are in control in the electric putter (3) in the other end, if electric putter (3) are followed one end, make the other end (14) make the electric putter is followed to one side to the balance.

2. An automatically adjusting balancing mechanism for the left and right rotors of a dual-rotor aircraft according to claim 1, wherein the shaft seat (14) is welded with a first bearing sleeve (10), and the shaft seat (14) and the first bearing sleeve (10) together form a cavity capable of clamping the half shaft (13).

3. An automatically adjusting balancing mechanism for the left and right rotors of a twin-rotor aircraft according to claim 2, wherein the first bearing housing (10) is slidably connected to a first bearing mount (11) fixedly mounted inside the main girder (1) by means of a first linear bearing (12).

4. An automatically adjusting balancing mechanism for the left and right rotors of a twin-rotor aircraft according to claim 3, wherein the two ends of the girder tube (1) are fixedly provided with a large Liang Guantao (16) capable of fixing the bearing outer ring of the first bearing mounting seat (11).

5. The automatic adjusting and balancing mechanism for the left rotor and the right rotor of the double-rotor aircraft according to claim 4, wherein a second bearing sleeve (7) and a spline (8) are further installed on the half shaft (13), a second bearing installation seat (6) and a spline sleeve (9) corresponding to the spline (8) are installed in the girder tube (1), and the second bearing sleeve (7) is in sliding connection with the second bearing installation seat (6) through a second linear bearing (5).

6. The automatic adjusting and balancing mechanism for the left rotor and the right rotor of the double-rotor aircraft according to claim 5 is characterized in that an electric push rod mounting seat (2) capable of fixing an electric push rod (3) is fixedly arranged in the girder tube (1).

7. An automatically adjusting balancing mechanism for the left and right rotors of a double-rotor aircraft according to claim 6, wherein the telescopic end of the linear displacement sensor (4) is fixedly connected to the second bearing sleeve (7).

8. An automatically adjusting balancing mechanism for the left and right rotors of a dual rotor aircraft according to claim 7, wherein the left and right shaft seats (14) are connected by a belt (15), said belt (15) being located between the outside of the half shaft (13) and the inner wall of the girder tube (1).