阅读说明：本技术 带有防水密封功能的直升机飞行操纵系统传动机构 (Helicopter flight control system transmission mechanism with waterproof sealing function ) 是由 白一尚 王景山 邓海侠 于 2020-04-30 设计创作，主要内容包括：本发明属于直升机操纵系统结构设计技术领域,具体涉及一种带有防水密封功能的直升机飞行操纵系统传动机构；包括支座(1)、扭轴(2)、摇臂(3)和轴承(6)；支座(1)为带法兰的盘形支座；扭轴(2)由密封配合的端盖(7)和扭轴管体(8)组成；摇臂(3)下端端部圆周周向具有盖伞结构的挡水凸缘；摇臂(3)固连在扭轴(2)两端；扭轴(2)穿过支座(1)的通孔并通过轴承(6)连接在支座(1)上,支座(1)固定在机体结构(5)上；支座(1)与摇臂(3)为间隙配合。本发明的传动机构能实现传递操纵指令功能的同时满足防水密封的效果且不会带来额外的摩擦力。(The invention belongs to the technical field of structural design of helicopter control systems, and particularly relates to a transmission mechanism of a helicopter flight control system with a waterproof sealing function; comprises a support (1), a torsion shaft (2), a rocker arm (3) and a bearing (6); the support (1) is a disk-shaped support with a flange; the torsion shaft (2) consists of an end cover (7) and a torsion shaft pipe body (8) which are in sealing fit; the circumference of the end part of the lower end of the rocker arm (3) is provided with a water retaining flange which covers an umbrella structure; the rocker arm (3) is fixedly connected with two ends of the torsion shaft (2); the torsion shaft (2) penetrates through a through hole of the support (1) and is connected to the support (1) through a bearing (6), and the support (1) is fixed on the machine body structure (5); the support (1) is in clearance fit with the rocker arm (3). The transmission mechanism can realize the function of transmitting the operation instruction, simultaneously meets the waterproof sealing effect and does not bring extra friction.)

1. Helicopter flight control system drive mechanism with waterproof sealing function, its characterized in that: the transmission mechanism of the helicopter flight control system comprises a support (1), a torsion shaft (2), a rocker arm (3) and a bearing (6);

the support (1) is a disc-shaped support with a flange; the torsion shaft (2) consists of an end cover (7) and a torsion shaft pipe body (8) which are in sealing fit; the circumference of the end part of the lower end of the rocker arm (3) is circumferentially provided with a water retaining flange which covers an umbrella structure;

the rocker arm (3) is fixedly connected with two ends of the torsion shaft (2); the torsion shaft (2) penetrates through a through hole of the support (1) and is connected to the support (1) through a bearing (6), and the support (1) is fixed on the machine body structure (5); the support (1) is in clearance fit with the rocker arm (3).

2. A helicopter flight control system drive with a watertight seal as claimed in claim 1 wherein: the support (1) is a high-strength metal piece.

3. A helicopter flight control system drive with a watertight seal as claimed in claim 1 wherein: the end cover (7) extends out of the mounting lug, and the mounting lug is provided with a through hole corresponding to the mounting hole in the torsion shaft tube body (8).

4. A helicopter flight control system drive with a watertight seal as claimed in claim 1 wherein: and sealant is coated on the periphery of the support (1), the joint of the end cover (7) and the torsion shaft tube body (8) and the joint of the support (1) and the bearing (6).

5. A helicopter flight control system drive with a watertight seal as claimed in claim 1 wherein: the outer diameter of the water retaining flange of the rocker arm (3) is larger than that of the bearing (6).

6. A helicopter flight control system drive with a watertight seal as claimed in claim 1 wherein: the end cover (7) is in threaded connection with the torsion shaft tube body (8).

7. A helicopter flight control system drive with a watertight seal as claimed in claim 1 wherein: the end cover (7) and the torsion shaft tube body (8) are assembled in a small gap mode and coated with waterproof sealant.

8. A helicopter flight control system drive with a watertight seal as claimed in claim 2 wherein: the support (1) is connected with the machine body structure (5) through a bolt.

Technical Field

The invention belongs to the technical field of structural design of helicopter control systems, and particularly relates to a transmission mechanism with a waterproof sealing function for a helicopter flight control system.

Background

The mechanical operating system transmission mechanism of the helicopter is generally composed of a bearing 6, a transmission torsion shaft 101 and a traditional rocker arm 102, and is shown in figure 1. The operating system line system generally penetrates through the head and the tail of the helicopter, is long in length and often needs to penetrate through a plurality of cabins. And often need sealed waterproof at different cabins juncture and helicopter inside and outside juncture, therefore helicopter control system drive mechanism often needs to have waterproof sealing function.

The conventional waterproof sealing means of the steering system are generally rubber sleeves or provided with a special waterproof cover. The waterproof cover occupies a large space and has a large weight, and the space on the helicopter is limited, so that the waterproof cover cannot be realized. The rubber sleeve has the advantages of simple structure and light weight; one end of the rubber sleeve is generally fixed on the bearing 6 or the machine body structure 5, and the other end of the rubber sleeve is sleeved on the movable device, so that extra friction force is inevitably brought; and the rubber sleeve has short service life and cannot meet the requirement of the same service life with other parts of the control system.

Disclosure of Invention

The purpose of the invention is: a helicopter flight control system transmission mechanism with a waterproof sealing function is designed to achieve the control system transmission mechanism with the waterproof sealing function, and the problems in the prior art are solved.

In order to solve the technical problem, the technical scheme of the invention is as follows:

a helicopter flight control system transmission mechanism with a waterproof sealing function comprises a support 1, a torsion shaft 2, a rocker arm 3 and a bearing 6;

the support 1: is a disk-shaped support with a flange;

the torsion shaft 2: the end cover 7 and the torsion shaft tube body 8 are in sealing fit;

the rocker arm 3: the circumference of the end part of the lower end is provided with a water retaining flange which covers the umbrella structure;

the rocker arm 3 is fixedly connected with two ends of the torsion shaft 2; the torsion shaft 2 penetrates through a through hole of the support 1 and is connected to the support 1 through a bearing 6, and the support 1 is fixed on the machine body structure 5; the support 1 is in clearance fit with the rocker arm 3.

The support 1 is a high-strength metal part and is connected with the machine body structure 5 through a bolt.

The end cover 7 extends out of the mounting lug, and the mounting lug is provided with a through hole corresponding to the mounting hole on the torsion shaft tube body 8.

And the sealant is sealed at the periphery of the support 1, the joint of the end cover 7 and the torsion shaft tube body 8 and the joint of the support 1 and the bearing 6.

The outer diameter of the water retaining flange of the rocker arm 3 is larger than that of the bearing 6.

In one implementation of a sealing engagement of the end cap 7 and the torque tube body 8, the end cap 7 and the torque tube body 8 are threaded.

In another implementation of the sealing fit between the end cap 7 and the torque tube 8, the end cap 7 and the torque tube 8 are assembled with a small gap and coated with a waterproof sealant.

The invention has the beneficial effects that:

1. the disc-shaped support with the flange, the rocker arm with the water retaining flange of the umbrella covering structure, the torsion shaft with the end cover and the sealant at the joint of each part are used, so that the function of transmitting the operation instruction can be realized, and the waterproof sealing effect can be simultaneously met;

2. the bearing transmission is adopted, and a waterproof cover or a rubber sleeve is omitted, so that the space is saved, and additional friction force cannot be brought;

3. all the structures are metal parts, have the same service life with other parts of the operating system, and are convenient for making a maintenance plan.

Drawings

In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.

FIG. 1 is a block diagram of a transmission mechanism of a prior art helicopter flight control system;

FIG. 2 is a block diagram of the helicopter flight control system transmission of the present invention;

FIG. 3 is a schematic view of a torsion bar according to the present invention

FIG. 4 is a schematic view of the mounting of the helicopter flight control system transmission of the present invention;

the device comprises a support 1, a torsion shaft 2, a rocker 3, a sealant 4, a body structure 5, a bearing 6, an end cover 7, a torsion shaft tube 8, a transmission torsion shaft 101 and a traditional rocker 102.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all 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.

Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.

In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.

Fig. 2 is a schematic structural diagram of a transmission mechanism of a helicopter flight control system with a waterproof sealing function, which comprises a support 1 with a waterproof structure, a torsion shaft 2 with a waterproof structure and a plurality of rocker arms 3 with a waterproof structure; the support 1 is a disk-shaped support with a flange; the schematic diagram of the torsion shaft 2 is shown in fig. 3, and consists of an end cover 7 and a torsion shaft tube body 8 which are in sealing fit; the circumference of the lower end part of the rocker arm 3 is provided with a water retaining flange which covers the umbrella structure.

The support 1 is fixed on the machine body, the torsion shaft 2 is connected on the support 1 through a bearing 6, and the rocker arm 3 is fixedly connected on the torsion shaft 2.

As shown in fig. 4, which is a schematic view of the installation of the transmission mechanism and the body structure 5 of the helicopter flight control system of the present invention, the support 1 with a thin-walled edge is fixed on the body structure 5 by bolts, and the joint of the support 1 and the body structure 5 is coated with a sealant 4. The rocker arm 3 with the water retaining flange is fixedly connected to the torsion shaft 2 with the end cover 7, the joint of the end cover 7 and the torsion shaft body 8 is coated with sealant, the end cover is arranged at the top of the torsion shaft outside the cabin, and the torsion shaft does not need to be covered with the end cover because the water is not required to be prevented in the cabin. The contact surfaces of the support, the torsion shaft and the bearing are coated with sealant to strengthen the sealing effect. The torsion shaft assembly fixedly connected with the rocker arm is connected with the support through a bearing 6. The operation command is input from one end of the rocker arm, is output from the other end of the rocker arm through the torsion shaft and the bearing, and plays a role in transmitting motion.

The original bearing 6 with the flange is directly connected with the machine body structure 5 through the flange, and the bearing 6 with the flange is fixed with the support 1 through the flange and is connected on the machine body structure 5 through the support 1; the sealing effect is achieved by the sealing means of the support 1. The invention is suitable for realizing the transmission of force and displacement at the outer junction in the engine room, can play a role in preventing water in a limited space and realizes the sealing effect of the engine room.

Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.