CN216922716U

CN216922716U - Pilot isolation device of airplane hydraulic system

Info

Publication number: CN216922716U
Application number: CN202123399351.9U
Authority: CN
Inventors: 陶家进; 李书利; 曹红涛; 熊利
Original assignee: Yibin Sanjiang Machinery Co Ltd
Current assignee: Yibin Sanjiang Machinery Co Ltd
Priority date: 2021-12-30
Filing date: 2021-12-30
Publication date: 2022-07-08
Anticipated expiration: 2031-12-30

Abstract

The utility model discloses a pilot isolation device of an aircraft hydraulic system, relates to the field of aircraft hydraulic system manufacturing, and mainly aims to solve the problem that in the prior art, a control system needs to be operated manually, and because manual operation is not timely, oil flows into a closed power source, so that the power source fails. The main structure of the oil return device comprises a shell, wherein an oil return inlet, an oil return outlet and a pressure leading port are formed in the shell, the oil return inlet and the oil return outlet are communicated through an inner cavity of the shell, a valve assembly used for blocking the communication between the oil return inlet and the oil return outlet is arranged in the inner cavity of the shell, and the valve assembly is connected with a return spring and the pressure leading port. According to the pilot isolation device of the airplane hydraulic system, the pressure of the actuating mechanism is introduced into the pressure introduction port, the valve is automatically controlled to be opened and closed, a control system is not required to be arranged, and errors caused by manual operation are avoided.

Description

Pilot isolation device of airplane hydraulic system

Technical Field

The utility model relates to the field of aircraft hydraulic system manufacturing, in particular to a pilot isolation device for replacing a control system in an aircraft hydraulic system.

Background

The hydraulic system of the airplane takes oil as a working medium and drives an actuating mechanism to complete a whole set of device with specific operation actions by means of oil pressure. In order to ensure the reliable operation of the hydraulic system, in particular to improve the reliability of the hydraulic power source of the aircraft control system, two (or more) sets of mutually independent hydraulic power sources are mostly arranged on modern aircraft.

Because of the control needs or takes place emergency, need change the hydraulic power source, when changing the hydraulic power source, need close the oil return passageway, prevent that fluid from flowing into the power source of closing, cause the power source to damage. In the prior art, a control system is arranged for controlling the closing of an oil return passage, and the control system needs manual operation, so that the control system is easy to operate untimely, and oil flows into a closed power source, so that the power source fails.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a pilot isolation device of an aircraft hydraulic system, which solves the problems in the prior art.

In order to realize the purpose of the utility model, the technical scheme is as follows: a pilot isolation device of an aircraft hydraulic system is characterized by comprising a shell, wherein the shell is provided with an oil return inlet, an oil return outlet and a pressure guide port, the oil return inlet and the oil return outlet are communicated by a shell inner cavity, and the shell inner cavity is provided with a valve assembly for blocking the communication between the oil return inlet and the oil return outlet; a return spring is arranged between the valve component and the shell; the shell is provided with a pressure guiding opening, and the pressure of the pressure supply system applies force to the valve assembly through the pressure guiding opening) to compress the return spring.

The utility model is arranged on an oil return passage of an oil supply system and an actuating mechanism, an oil return inlet is connected with the actuating mechanism, an oil return outlet is connected with the oil supply system, a pressure supply system provides working force for the actuating mechanism, oil is returned through the oil return passage, and a pressure guide port is connected with the pressure supply system to guide the oil pressure of the pressure supply system. The return spring applies force to the valve assembly, so that the valve assembly blocks a passage between the oil return inlet and the oil return outlet, and the oil return inlet is not communicated with the oil return outlet; the pressure applied to the valve assembly by the pressure guide port is opposite to the force applied to the valve assembly by the reset spring, and when the pressure applied to the valve assembly by the pressure guide port is smaller than the force of the reset spring, the valve assembly blocks a passage between the oil return inlet and the oil return outlet, and the oil return inlet and the oil return outlet are not communicated; when the pressure of the pressure leading port on the valve assembly is larger than the force of the reset spring, the valve assembly is pushed open, and the oil return inlet is communicated with the oil return outlet.

Furthermore, the size of the valve assembly is matched with that of the inner wall of the shell, the inner wall of the shell is provided with a step surface facing the step of the end cover, the pressure leading port is arranged on the step, and the valve assembly is provided with a step surface matched with the step on the inner wall of the shell. The pressure oil flowing into the pressure guide port acts on the step surface of the valve assembly, and the pressure applied to the valve assembly is opposite to the force of the return spring.

Furthermore, the inner wall of the shell is provided with a step surface which is annular. The pressure oil flowing from the pressure leading port is contacted with the annular step surface uniformly, and the whole step surface is stressed uniformly.

Further, the shell comprises an end cover and a cavity, the end cover is detachably connected with the cavity, and the reset spring is arranged between the valve assembly and the end cover. The processing assembly and the later maintenance of earlier stage of being convenient for, the end cover is spacing to spring one end, inject the direction of motion of receiving the elastic force.

Further, a gasket is arranged between the return spring and the valve assembly. The quantity of the gaskets can be adjusted as required, the compression amount of the reset spring can be controlled, and the elasticity of the spring is controlled, so that the pressure value of a pressure supply system required by the isolation device is adjusted and communicated.

Further, valve subassembly includes chock plug and chock plug tail, and the step face sets up on the chock plug tail, and the chock plug tail links to each other with reset spring, and the chock plug setting is on oil return import and oil return export passageway, and the chock plug tail links to each other with coupling spring for the chock plug. The valve assembly adopts a split structure, so that the valve assembly is convenient to process and reduces the processing difficulty; the chock plug and the chock plug tail are connected through the spring, when the chock plug tail moves in position, the corresponding chock plug moves to bring buffering through the spring, so that the motion of the racing plug is more relaxed, and the oil return inlet and the oil return outlet are communicated and closed more stably.

Furthermore, the connecting spring is two springs with different elasticity which are mechanically applied. And the double springs are selected for connection, so that the elasticity and the stability of the springs are improved.

Further, the connecting spring is installed on the plug head through a spring seat. The spring seat is used for installation, so that the connection of the spring is firmer, and the spring slipping is avoided, and the mechanism is prevented from being out of order.

The utility model has the beneficial effects that:

the pressure of the actuating mechanism is introduced through the pressure introduction port, the valve is automatically controlled to be opened and closed, a control system is not required to be arranged, and the problem that oil flows into a closed power source to cause power source failure due to the fact that errors are generated by manual operation is avoided;

the utility model adopts the form of a direct-acting valve, the pressure directly acts on the valve pressure-sensing surface, the pressure is controlled by a spring, and the structure has no redundancy;

and thirdly, the valve assembly is of a split structure and is connected by a connecting spring, and when the piston displaces and is buffered by the spring, the movement of the whole valve assembly is relaxed, and the communication between the oil return inlet and the oil return outlet is closed more stably.

Drawings

FIG. 1: the utility model has a structure schematic diagram;

FIG. 2: the work flow of the utility model is shown schematically.

Reference numbers and corresponding part names in the drawings:

the hydraulic pressure control valve comprises a shell, an end cover, a cavity, a reset spring, a valve assembly, a plug tail, a connecting spring, a plug head, a spring seat, a pressure inlet, a pressure outlet, a pressure guiding opening, a gasket, a pressure guiding passage, a pressure supplying system, an execution mechanism and an oil returning passage, wherein the shell is 1, the end cover is 1-1, the cavity is 1-2, the reset spring is 2, the valve assembly is 3-1, the plug tail is 3-2, the connecting spring is 3-3, the plug head is 3-4, the spring seat is 4, the oil returning inlet is 5, the oil returning outlet is 6, the pressure guiding opening is 7, the gasket is 8, the pressure guiding passage is 9, the pressure supplying system is 10, and the execution mechanism is 11.

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.

Fig. 1 shows a pilot isolation device of an aircraft hydraulic system provided by the utility model, which comprises a housing 1, wherein the housing 1 comprises a cavity 1-2 and an end cover 1-1, the cavity 1-2 is cylindrical, one end of the cavity 1-2 is provided with an oil return inlet 4, and the other end of the cavity is in threaded connection with the end cover 1-1; an oil return outlet 5 is arranged on the side wall of the cavity 1-2, an oil return inlet 4 is communicated with the oil return inlet 5 through an inner cavity of the cavity 1-2, the inner wall of the cavity 1-2 is provided with an annular step with a step surface facing the end cover 1-1, and a pressure leading port 6 is arranged on the step surface and communicated with a pressure supply system; the valve component 3 for opening and closing a communication passage of the oil return inlet 4 and the oil return outlet 5 is arranged in the cavity 1-2, the reset spring 2 is arranged between the valve component 3 and the end cover (1-1), the valve component 3 is matched with the inner wall of the shell 1 in size, the valve component 3 is provided with an annular stress step surface matched with the annular step of the inner wall, and the elastic force applied to the valve component 3 by the reset spring 2 is opposite to the force applied to the valve component 3 by the pressure supply system through the pressure leading port 6. The valve assembly 3 comprises a plug head 3-3 and a plug tail 3-1, the step surface is arranged on the plug tail 3-1, the plug tail 3-1 is connected with a reset spring, the plug head is arranged on a passage of an oil return inlet and an oil return outlet, the plug tail is connected with the plug head through a connecting spring 3-2, the connecting spring 3-2 is connected with the plug head 3-3 through a spring seat 3-4, and the connecting spring 3-2 is two springs with different elasticity.

As shown in fig. 2, when the hydraulic actuator is used, the hydraulic actuator is arranged on oil return passages of an oil supply system 9 and an actuator 10, an oil return inlet is connected with the actuator, an oil return outlet is connected with the oil supply system 9, a pressure supply system 9 provides working force for the actuator 10, oil is returned through an oil return passage 11, and a pressure guide port 6 is connected with the pressure supply system 9 through a pressure guide passage 8 and introduces the oil pressure of the pressure supply system 9. When the pressure supply system 9 works, the system internal oil pressure of the pressure supply system 9 acts on the valve assembly 3, the oil pressure of the actuating mechanism 10 which flows back to the pressure supply system 9 acts on the valve assembly 3, the sum of the two oil pressures is greater than the elastic force of the return spring 3, the valve assembly 3 is pushed open, the oil return inlet 4 is communicated with the oil return outlet 5, and the oil return passage 11 acts. When the pressure supply system 9 fails, the rest of the pressure supply systems provide working force for the actuating mechanism 10, because the pressure supply system 9 does not work any more, the oil pressure in the system is zero, the pressure from the pressure supply system 9 is not applied to the tail valve assembly 3, the oil pressure applied to the valve assembly 3 by the actuating mechanism is less than the elastic force of the return spring 2, the valve assembly 3 closes the communication passage between the oil return inlet 4 and the oil return outlet 5, the oil return passage 11 is blocked, and the oil return after the oil supply to the actuating mechanism 10 by the rest of the pressure supply systems cannot flow through the oil return passage 11.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A pilot isolation device of an aircraft hydraulic system is characterized by comprising a shell (1), wherein an oil return inlet (4) and an oil return outlet (5) are arranged on the shell (1); the oil return inlet (4) and the oil return outlet (5) are communicated by the inner cavity of the shell (1); the inner cavity of the shell (1) is provided with a valve component (3) for opening and closing a communication channel between the oil return inlet (4) and the oil return outlet (5); a return spring (2) is arranged between the valve component (3) and the shell (1); the shell is provided with a pressure guiding opening (6), and the pressure of the pressure supply system applies force to the valve component (3) through the pressure guiding opening to compress the return spring (2).

2. The pilot isolation device of an aircraft hydraulic system according to claim 1, characterized in that the valve assembly (3) is matched with the inner wall of the shell (1) in size, the inner wall of the shell (1) is provided with a step surface facing the step of the end cover (1-1), the pressure guide port (6) is arranged on the step, and the valve assembly (3) is provided with a step surface matched with the step on the inner wall of the shell.

3. The pilot isolation device of an aircraft hydraulic system according to claim 2, characterized in that the inner wall of the housing (1) is provided with a step surface in the shape of a ring.

4. The pilot isolation device of an aircraft hydraulic system according to claim 3, characterized in that the housing (1) comprises an end cap (1-1) and a cavity (1-2), the end cap (1-1) is detachably connected with the cavity (1-2), and the return spring is arranged between the valve assembly (3) and the end cap (1-1).

5. Pilot isolation device for an aircraft hydraulic system according to claim 1, characterised in that a spacer (7) is provided between the return spring (2) and the flap assembly (3).

6. The pilot isolation device of an aircraft hydraulic system according to any one of claims 1 to 5, characterized in that the valve assembly (3) comprises a plug head (3-3) and a plug tail (3-1), the step surface is arranged on the plug tail (3-1), the plug tail (3-1) is connected with the return spring (2), the plug head (3-3) is arranged on a passage between the oil return inlet (4) and the oil return outlet (5), and the connecting spring (3-2) is arranged between the plug tail (3-1) and the plug head (3-3).

7. The pilot isolator of an aircraft hydraulic system according to claim 6, characterized in that the connecting spring (3-2) is two springs of different elasticity.

8. An aircraft hydraulic system pilot isolator according to claim 6, characterised in that the connecting spring (3-2) is mounted on the plug head (3-3) by means of a spring seat (3-4).