CN111516860B - Helicopter flight control system transmission mechanism with waterproof sealing function - Google Patents

Helicopter flight control system transmission mechanism with waterproof sealing function Download PDF

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Publication number
CN111516860B
CN111516860B CN202010363722.9A CN202010363722A CN111516860B CN 111516860 B CN111516860 B CN 111516860B CN 202010363722 A CN202010363722 A CN 202010363722A CN 111516860 B CN111516860 B CN 111516860B
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China
Prior art keywords
support
control system
torsion shaft
flight control
waterproof sealing
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CN202010363722.9A
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CN111516860A (en
Inventor
白一尚
王景山
邓海侠
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China Helicopter Research and Development Institute
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China Helicopter Research and Development Institute
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Priority to CN202010363722.9A priority Critical patent/CN111516860B/en
Publication of CN111516860A publication Critical patent/CN111516860A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C19/00—Aircraft control not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/18—Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings
    • F16J15/181—Sealings between relatively-moving surfaces with stuffing-boxes for elastic or plastic packings for plastic packings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sealing Devices (AREA)

Abstract

The invention belongs to the technical field of helicopter control system structural design, and particularly relates to 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 disc-shaped support with a flange; the torsion shaft (2) 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 with a cover umbrella structure; the rocker arms (3) are fixedly connected to the two ends of the torsion shaft (2); the torsion shaft (2) passes 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 control instruction, simultaneously can meet the waterproof sealing effect and can not bring extra friction force.

Description

Helicopter flight control system transmission mechanism with waterproof sealing function
Technical Field
The invention belongs to the technical field of helicopter control system structural design, and particularly relates to a helicopter flight control system transmission mechanism with a waterproof sealing function.
Background
The transmission mechanism of the mechanical control system of the helicopter is generally composed of a bearing 6, a transmission torsion shaft 101 and a traditional rocker arm 102, as shown in fig. 1. The steering system line generally runs through the head and tail of the helicopter, is long, and often needs to traverse a plurality of cabins. Sealing and waterproofing are often needed at the junctions between different cabins and the inside and outside of the helicopter, so that the transmission mechanism of the helicopter control system is often required to have a waterproof sealing function.
Conventional watertight seals for steering systems are typically rubber sleeves or provided with specialized watertight covers. The waterproof cover occupies large space and has the characteristic of large weight, and the waterproof cover cannot be realized due to limited space on the helicopter. The rubber sleeve has the advantages of simple structure and light weight; the rubber sleeve is generally fixed on the bearing 6 or the machine body structure 5 at one end and sleeved on the movable device at the other end, which entails additional friction force; and the service life of the rubber sleeve is shorter, and the requirement of the same service life with other parts of the operating system cannot be met.
Disclosure of Invention
The purpose of the invention is that: a helicopter flight control system transmission mechanism with a waterproof sealing function is designed to realize the control system transmission mechanism with the waterproof sealing function, so that the problems in the prior art are solved.
In order to solve the technical problem, the technical scheme of the invention is as follows:
the helicopter flight control system transmission mechanism with the waterproof sealing function 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 tube body 8 which are in sealing fit;
the rocker arm 3: a water retaining flange with a cover umbrella structure is circumferentially arranged at the lower end part;
the rocker arms 3 are fixedly connected to two ends of the torsion shaft 2; the torsion shaft 2 passes 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 a machine body structure 5; the support 1 is in clearance fit with the rocker arm 3.
The support 1 is a high-strength metal piece and is connected with the machine body structure 5 through bolts.
The end cover 7 is internally provided with a mounting lug which is provided with a through hole corresponding to the mounting hole on the torsion tube body 8.
And the sealant is arranged at the outer periphery of the support 1, at the joint of the end cover 7 and the torsion tube body 8 and at 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 the outer diameter of the bearing 6.
In one implementation of the 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 sealing engagement implementation of the end cap 7 and the torque tube body 8, the end cap 7 and the torque tube body 8 are assembled with a small gap and are coated with a waterproof sealant.
The beneficial effects of the invention are as follows:
1. the disc-shaped support with the flange, the rocker arm with the water retaining flange with the cover umbrella structure, the torsion shaft with the end cover and the sealant at the joint of all parts can realize the functions of transmitting the control instruction and simultaneously meet the waterproof sealing effect;
2. the bearing transmission eliminates a waterproof cover or a rubber sleeve, so that the space is saved and no extra friction force is brought;
3. all the structures are metal parts, and the service life of the metal parts is the same as that of other components of the control system, so that the maintenance plan can be conveniently formulated.
Drawings
In order to more clearly illustrate the technical solution of the implementation of the present invention, the following description will briefly explain the drawings that need to be used in the examples of the present invention. It is evident that the drawings described below are only some embodiments of the invention and that other drawings may be obtained from these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of a prior art helicopter flight control system transmission mechanism;
FIG. 2 is a block diagram of a helicopter flight control system transmission mechanism of the present invention;
FIG. 3 is a schematic view of a torsion shaft according to the present invention
FIG. 4 is a schematic diagram of the installation of the helicopter flight control system transmission mechanism of the present invention;
the device comprises a 1-support, a 2-torsion shaft, a 3-rocker arm, 4-sealant, a 5-engine body structure, a 6-bearing, a 7-end cover, an 8-torsion shaft tube body, a 101-transmission torsion shaft and a 102-traditional rocker arm.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.
Features of various aspects of embodiments of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the 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 for a better understanding of the invention by showing examples of the invention. The present invention is not limited to any particular arrangement and method provided below, but covers any modifications, substitutions, etc. of all product constructions, methods, and the like covered without departing from the spirit of the invention.
Well-known structures and techniques have not been shown in detail in the various drawings and the following description in order not to unnecessarily obscure the present invention.
Fig. 2 is a schematic structural view of a transmission mechanism of a helicopter flight control system with a waterproof sealing function, wherein the transmission mechanism 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 disc-shaped support with a flange; the torque shaft 2 is schematically shown in fig. 3 and consists of an end cover 7 and a torque shaft tube body 8 which are in sealing fit; the lower end of the rocker arm 3 is circumferentially provided with a water retaining flange of a cover umbrella structure.
The support 1 is fixed on the machine body, the torsion shaft 2 is connected to the support 1 through a bearing 6, and the rocker arm 3 is fixedly connected to the torsion shaft 2.
As shown in fig. 4, a schematic installation diagram of a transmission mechanism of a helicopter flight control system and a machine body structure 5 is shown, a support 1 with a thin-wall edge is fixed on the machine body structure 5 through bolts, and a joint of the support 1 and the machine body structure 5 is coated with 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 pipe body 8 is coated with sealant, the top of the out-cabin torsion shaft is provided with the end cover, and the end cover is not added to the torsion shaft because the out-cabin torsion shaft is not required to be waterproof. The contact surfaces of the support, the torsion shaft and the bearing are coated with sealant to strengthen the sealing effect. The torsion shaft component fixedly connected with the rocker arm is connected with the support through a bearing 6. The control command is input from one end rocker arm, and is output from the other end rocker arm through the torsion shaft and the bearing, so that the function of transmitting motion is realized.
The original flanged bearing 6 is directly connected with the machine body structure 5 through a flange, the flanged bearing 6 is fixed with the support 1 through the flange, and is connected with 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 transmitting force and displacement at the junction between the inside and outside of the engine room, can play a role in preventing water in a limited space and realize the sealing effect of the engine room.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered in the scope of the present invention.

Claims (7)

1. Helicopter flight control system drive mechanism with waterproof sealing function, its characterized in that: the helicopter flight control system transmission mechanism 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 tube 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 with a cover umbrella structure;
the rocker arms (3) are fixedly connected to two ends of the torsion shaft (2); the torsion shaft (2) passes 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 outer diameter of the water retaining flange of the rocker arm (3) is larger than the outer diameter of the bearing (6).
2. The helicopter flight control system transmission with waterproof sealing function of claim 1, wherein: the support (1) is a high-strength metal piece.
3. The helicopter flight control system transmission with waterproof sealing function of claim 1, wherein: the end cover (7) internally extends out of the mounting lug, and a through hole corresponding to the mounting hole on the torsion tube body (8) is formed in the mounting lug.
4. The helicopter flight control system transmission with waterproof sealing function of claim 1, wherein: the outer 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) are coated with sealant.
5. The helicopter flight control system transmission with waterproof sealing function of claim 1, wherein: the end cover (7) is in threaded connection with the torsion shaft tube body (8).
6. The helicopter flight control system transmission with waterproof sealing function of claim 1, wherein: the end cover (7) and the torsion tube body (8) are assembled in a small gap and are coated with waterproof sealant.
7. The helicopter flight control system transmission with waterproof sealing function of claim 2, wherein: the support (1) is connected with the machine body structure (5) through bolts.
CN202010363722.9A 2020-04-30 2020-04-30 Helicopter flight control system transmission mechanism with waterproof sealing function Active CN111516860B (en)

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CN110864046A (en) * 2019-12-27 2020-03-06 瓦房店轴承集团国家轴承工程技术研究中心有限公司 Claw type bearing sealing structure

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Publication number Priority date Publication date Assignee Title
CN107269839A (en) * 2017-05-23 2017-10-20 广州文冲船厂有限责任公司 A kind of stern tube bearing water lubrication sealing structure
EP3527838A1 (en) * 2018-02-19 2019-08-21 Pratt & Whitney Canada Corp. Seal and bearing assembly with bearing outer portion comprising a seal static portion
CN109533293A (en) * 2018-11-15 2019-03-29 中国直升机设计研究所 A kind of pull rod guiding mechanism for helicopter flight manipulation
CN110864046A (en) * 2019-12-27 2020-03-06 瓦房店轴承集团国家轴承工程技术研究中心有限公司 Claw type bearing sealing structure

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