CN110985470B - Hydraulic flow control device for turning of servo valve controlled aircraft - Google Patents
Hydraulic flow control device for turning of servo valve controlled aircraft Download PDFInfo
- Publication number
- CN110985470B CN110985470B CN201911358603.8A CN201911358603A CN110985470B CN 110985470 B CN110985470 B CN 110985470B CN 201911358603 A CN201911358603 A CN 201911358603A CN 110985470 B CN110985470 B CN 110985470B
- Authority
- CN
- China
- Prior art keywords
- valve
- oil
- load
- control device
- way
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
- F15B13/021—Valves for interconnecting the fluid chambers of an actuator
Abstract
The invention belongs to the field of airplane turning fluid control, and relates to a servo valve controlled airplane turning hydraulic flow control device which comprises an electromagnetic valve (1), a first one-way valve (2), a change-over valve (3), a damping valve (4), a second one-way valve (5), a compensation valve (6), a safety valve (7), a third one-way valve (8) and a servo valve (9). The invention relates to a servo valve control type airplane turning hydraulic flow control device, which is a servo control type airplane turning hydraulic flow device, realizes the switching between a turning state and a non-turning state through a switching valve, realizes overpressure unloading protection of the device through a safety valve, adopts a servo valve to control the flow of hydraulic flow in the turning state under the turning state, provides damping force under the turning state under the non-turning state through a damping valve, and provides oil liquid supplement through a compensation valve.
Description
Technical Field
Belongs to the field of airplane turning fluid control, and relates to a servo valve control airplane turning hydraulic flow control device.
Background
The turning of the airplane needs the turning device to realize the hydraulic flow control of the nose landing gear, so that the turning function of the nose landing gear is realized. Under the turning function, the hydraulic flow needs to be accurately controlled, and under the non-turning state, a turning device needs to provide certain damping force so as to reduce the swing of the airplane during the sliding process.
Disclosure of Invention
The purpose of the invention is: a hydraulic flow control device for turning of a servo valve controlled aircraft is provided.
The technical solution of the invention is as follows:
a hydraulic flow control device for a servo valve control airplane turning comprises an electromagnetic valve 1, a first one-way valve 2, a change-over valve 3, a damping valve 4, a second one-way valve 5, a compensation valve 6, a safety valve 7, a third one-way valve 8 and a servo valve 9;
the oil inlet is connected with an inlet of the electromagnetic valve 1 and an inlet of the change-over valve 3 at the same time, the electromagnetic valve 1 controls hydraulic oil to enter a control port of the change-over valve 3, the change-over valve 3 controls hydraulic oil to enter a servo valve 9, a reverse shut-off port of the first one-way valve 2 is connected with an oil return port of the electromagnetic valve 1 to block pressure damage of oil return pressure to the electromagnetic valve 1, two oil outlets of the change-over valve 3 are respectively communicated with two oil outlets of the servo valve 9 and a load 1 and a load 2 of a control device, two safety valves 7 are reversely connected between the load 1 and the load 2 in parallel, one ends of the two damping valves 4 are connected with the change-over valve 3, the other ends of the two damping valves are connected with the third one-way valve 8, the other end of the third one-way valve 8 is connected with the second one-way valve 5 and the compensation valve 6, and the second one-way valve 5 and the compensation valve 6 are connected with the oil return port of the control device in parallel.
In a turning state, hydraulic oil enters the control device from an oil inlet, firstly enters the electromagnetic valve 1, the electromagnetic valve 1 is opened, the hydraulic oil enters the conversion valve 3, the conversion valve 3 communicates the hydraulic oil at the oil inlet with the servo valve 9, the servo valve 9 adjusts the flow of the hydraulic oil according to a control instruction, the hydraulic oil passes through the conversion valve 3 and then is respectively output from the load 1 and the load 2, so that the turning flow is controlled, meanwhile, the conversion valve 3 blocks the communication of the damping valve 4 with the load 1 and the load 2, and when the hydraulic oil of the control device exceeds a set value of the safety valve 7, the hydraulic oil flows to a low-pressure end from one end of an overpressure load.
In a non-turning state, hydraulic oil enters the control device from an oil inlet, firstly enters the electromagnetic valve 1, the electromagnetic valve 1 is closed, the change-over valve 3 blocks the communication between the hydraulic oil at the oil inlet and the servo valve 9, in the state, the change-over valve 3 communicates the damping valve 4 with the load 1 and the load 2 to form a closed oil path, the third one-way valve 8 blocks the closed oil path from the return oil, at the moment, the damping valve 4 provides damping force for the oil entering and exiting from the load 1 and the load 2, and when the oil path formed by the damping valve 4, the load 1 and the load 2 is smaller than the set pressure of the compensating valve 6, pressure oil in the compensating valve 6 enters the oil path for providing damping through the third one-way valve 8.
The electromagnetic valve 1 is provided with a double-steel-ball sealing structure and can be respectively communicated with oil inlet and oil return.
The first one-way valve 2, the second one-way valve 5 and the third one-way valve 8 are of a one-way conduction structure sealed by spring steel balls.
The switch valve 3 has a switch structure of three steps and five chambers.
The damping valve 4 is provided with a structural device which is used for providing one-way damping in one way and provided with a variable-aperture spring cone valve.
The compensating valve 6 is provided with a sealed cavity for storing pressure liquid and a spring valve structure with one-way oil storage and one-way oil supplement.
The safety valve 7 has a spring valve structure for unloading overpressure.
The invention has the beneficial effects that: a servo valve control type airplane turning hydraulic flow control device is a servo control type airplane turning hydraulic flow device, switching between a turning state and a non-turning state is achieved through a switching valve, overpressure unloading protection of the device is achieved through a safety valve, the servo valve is used for controlling the flow of the hydraulic flow in the turning state, the damping valve provides damping force in the turning state and the compensation valve provides oil liquid supplement in the non-turning state.
Drawings
Fig. 1 is a servo valve controlled aircraft turning hydraulic flow control device in which 1 is a solenoid valve, 2 is a check valve, 3 is a change-over valve, 4 is a damping valve, 5 is a check valve, 6 is a compensation valve, 7 is a safety valve, 8 is a check valve, and 9 is a servo valve.
Detailed Description
The invention is described in further detail below with reference to the drawings.
Referring to fig. 1, a hydraulic flow control device for a servo valve controlled aircraft turning includes an electromagnetic valve 1, a first check valve 2, a switching valve 3, a damping valve 4, a second check valve 5, a compensation valve 6, a safety valve 7, a third check valve 8, and a servo valve 9;
the oil inlet is connected with an inlet of the electromagnetic valve 1 and an inlet of the change-over valve 3 at the same time, the electromagnetic valve 1 controls hydraulic oil to enter a control port of the change-over valve 3, the change-over valve 3 controls hydraulic oil to enter a servo valve 9, a reverse shut-off port of the first one-way valve 2 is connected with an oil return port of the electromagnetic valve 1 to block pressure damage of oil return pressure to the electromagnetic valve 1, two oil outlets of the change-over valve 3 are respectively communicated with two oil outlets of the servo valve 9 and a load 1 and a load 2 of a control device, two safety valves 7 are reversely connected between the load 1 and the load 2 in parallel, one ends of the two damping valves 4 are connected with the change-over valve 3, the other ends of the two damping valves are connected with the third one-way valve 8, the other end of the third one-way valve 8 is connected with the second one-way valve 5 and the compensation valve 6, and the second one-way valve 5 and the compensation valve 6 are connected with the oil return port of the control device in parallel.
Hydraulic oil enters the electromagnetic valve 1 and the servo valve 9 through an oil inlet of the device, the electromagnetic valve 1 realizes the switching between the turning state and the non-turning state of the switching valve 3, the servo valve 9 realizes the servo control on the turning flow when the switching valve 3 is switched to the turning state and transmits the turning flow to a controlled device through a port 1 of a load and a port 2 of the load, a reverse safety valve 7 is connected between the port 1 of the load and the port 2 of the load in parallel to protect the device from being damaged due to high-pressure hydraulic oil, the one-way valve 5 realizes the oil supplement of the hydraulic oil in the non-turning state, and the one-way valve 8 realizes the one-way sealing of an oil way which provides damping force in the non-turning state.
In a turning state, hydraulic oil enters the control device from an oil inlet, firstly enters the electromagnetic valve 1, the electromagnetic valve 1 is opened, the hydraulic oil enters the conversion valve 3, the conversion valve 3 communicates the hydraulic oil at the oil inlet with the servo valve 9, the servo valve 9 adjusts the flow of the hydraulic oil according to a control instruction, the hydraulic oil passes through the conversion valve 3 and then is respectively output from the load 1 and the load 2, so that the turning flow is controlled, meanwhile, the conversion valve 3 blocks the communication of the damping valve 4 with the load 1 and the load 2, and when the hydraulic oil of the control device exceeds a set value of the safety valve 7, the hydraulic oil flows to a low-pressure end from one end of an overpressure load.
In a non-turning state, hydraulic oil enters the control device from an oil inlet, firstly enters the electromagnetic valve 1, the electromagnetic valve 1 is closed, the change-over valve 3 blocks the communication between the hydraulic oil at the oil inlet and the servo valve 9, in the state, the change-over valve 3 communicates the damping valve 4 with the load 1 and the load 2 to form a closed oil path, the third one-way valve 8 blocks the closed oil path from the return oil, at the moment, the damping valve 4 provides damping force for the oil entering and exiting from the load 1 and the load 2, and when the oil path formed by the damping valve 4, the load 1 and the load 2 is smaller than the set pressure of the compensating valve 6, pressure oil in the compensating valve 6 enters the oil path for providing damping through the third one-way valve 8.
The electromagnetic valve 1 is provided with a double-steel-ball sealing structure and can respectively communicate oil inlet and oil return, the first one-way valve 2, the second one-way valve 5 and the third one-way valve 8 are provided with a one-way conduction structure sealed by spring steel balls, the change-over valve 3 is provided with a change-over structure of three steps and five cavities, the damping valve 4 is provided with a structural device for providing one-way damping for one way of a variable-aperture spring cone valve, the compensating valve 6 is provided with a closed cavity for storing pressure liquid and a spring valve structure for storing one-way oil and supplementing one-way oil, and the safety valve 7 is provided with a spring valve structure for unloading overpressure.
When the servo valve 9 is switched to the turning state by the switching valve 3, the output of the turning flow of the aircraft is controlled. And the system also comprises anti-parallel safety valves 7 respectively arranged at the outlets of the servo valves 9.
Claims (9)
1. The utility model provides a servo valve accuse aircraft turn hydraulic pressure flow control device which characterized in that: the device comprises an electromagnetic valve (1), a first one-way valve (2), a change-over valve (3), a damping valve (4), a second one-way valve (5), a compensation valve (6), a safety valve (7), a third one-way valve (8) and a servo valve (9);
wherein, the oil inlet is connected with the inlet of the electromagnetic valve (1) and the inlet of the conversion valve (3) at the same time, the electromagnetic valve (1) controls the hydraulic oil to enter the control port of the conversion valve (3), the conversion valve (3) controls the hydraulic oil to enter the servo valve (9), the reverse shut-off port of the first one-way valve (2) is connected with the oil return port of the electromagnetic valve (1) to block the pressure damage of the oil return pressure to the electromagnetic valve (1), the two oil outlets of the conversion valve (3) are respectively communicated with the two oil outlets of the servo valve (9) and the load 1 and the load 2 of the control device, the two safety valves (7) are reversely connected in parallel between the load 1 and the load 2, one ends of the two damping valves (4) are connected with the conversion valve (3), the other ends are connected with the third one-way valve (8), the other end of the third one-way valve (8) is connected with the second one-way valve (5), the compensating valve (6) is connected, and the second one-way valve (5) and the compensating valve (6) are connected in parallel and connected with an oil return port of the control device.
2. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein:
in a turning state, hydraulic oil enters the control device from the oil inlet, firstly enters the electromagnetic valve (1), the electromagnetic valve (1) is opened, the hydraulic oil enters the change-over valve (3), the change-over valve (3) communicates the hydraulic oil at the oil inlet with the servo valve (9), the servo valve (9) adjusts the flow of the hydraulic oil according to a control instruction and outputs the hydraulic oil from the load 1 and the load 2 respectively after passing through the change-over valve (3) so as to realize the control of turning flow, meanwhile, the change-over valve (3) blocks the communication of the damping valve (4) with the load 1 and the load 2, and when the hydraulic oil of the control device exceeds a set value of the safety valve (7), the hydraulic oil flows to a low-pressure end from one end of an overpressure load.
3. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein:
in a non-turning state, hydraulic oil enters the control device from the oil inlet, firstly enters the electromagnetic valve (1), the electromagnetic valve (1) is closed, the change-over valve (3) blocks the communication between the hydraulic oil in the oil inlet and the servo valve (9), in the state, the change-over valve (3) communicates the damping valve (4) with the load 1 and the load 2 to form a closed oil path, the third one-way valve (8) blocks the closed oil path from the return oil, at the moment, the damping valve (4) provides damping force for the oil entering and exiting from the load 1 and the load 2, and when the oil path formed by the damping valve (4), the load 1 and the load 2 is smaller than the set pressure of the compensating valve (6), pressure oil in the compensating valve (6) enters the oil path providing damping through the third one-way valve (8).
4. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein: the electromagnetic valve (1) is provided with a double-steel-ball sealing structure and can be respectively communicated with oil inlet and oil return.
5. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein: the first one-way valve (2), the second one-way valve (5) and the third one-way valve (8) are provided with one-way conduction structures sealed by spring steel balls.
6. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein: the switching valve (3) has a switching structure of three steps and five cavities.
7. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein: the damping valve (4) is provided with a structural device which is provided with a variable-aperture spring cone valve and is used for unidirectional damping.
8. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein: the compensating valve (6) is provided with a sealed cavity for storing pressure liquid and a spring valve structure for one-way oil storage and one-way oil supplement.
9. The servovalve aircraft turning hydraulic flow control device of claim 1, wherein: the safety valve (7) is provided with a spring valve structure for overpressure unloading.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911358603.8A CN110985470B (en) | 2019-12-25 | 2019-12-25 | Hydraulic flow control device for turning of servo valve controlled aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911358603.8A CN110985470B (en) | 2019-12-25 | 2019-12-25 | Hydraulic flow control device for turning of servo valve controlled aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110985470A CN110985470A (en) | 2020-04-10 |
| CN110985470B true CN110985470B (en) | 2022-05-13 |
Family
ID=70075470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911358603.8A Active CN110985470B (en) | 2019-12-25 | 2019-12-25 | Hydraulic flow control device for turning of servo valve controlled aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110985470B (en) |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101255879A (en) * | 2007-12-10 | 2008-09-03 | 兰州理工大学 | Steering preference type flux amplification valve |
| FR2959483B1 (en) * | 2010-04-28 | 2012-06-01 | Messier Bugatti | METHOD FOR MANAGING A FLOOR LINK OF AN AIRCRAFT |
| FR2960924B1 (en) * | 2010-06-04 | 2013-04-05 | Messier Bugatti | HYDRAULIC DISTRIBUTOR. |
| CN201745747U (en) * | 2010-07-16 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Teletype turning system capable of preventing out of control of airplane |
| CN202226056U (en) * | 2011-08-15 | 2012-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Control system for front landing gear |
| CN209467319U (en) * | 2018-10-19 | 2019-10-08 | 北京新兴东方航空装备股份有限公司 | Double redundancy electric actuator for aircraft nose wheel active Servo Control |
| CN110107554B (en) * | 2019-05-07 | 2020-10-02 | 中航飞机起落架有限责任公司 | Change-over valve and undercarriage turn control system |
-
2019
- 2019-12-25 CN CN201911358603.8A patent/CN110985470B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110985470A (en) | 2020-04-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103047208B (en) | Load-sensitive electro-hydraulic proportional multi-way valve | |
| CN108071629B (en) | Synchronous lifting hydraulic system with double multi-stage oil cylinders | |
| CN103899587B (en) | Synchronous jacking hydraulic control system | |
| CN102650304A (en) | Hydraulic synchronous driving system for adjusting unbalanced load based on proportional valve controlled energy accumulator | |
| CN108799212B (en) | A kind of emergency power power device of hydraulic system | |
| CN201610873U (en) | Multifunctional highly-integrated multi-way valve | |
| CN104632736A (en) | Two-degree-of-freedom rocking platform and hydraulic system thereof | |
| CN203114764U (en) | Load-sensitive electro-hydraulic proportional multi-way valve | |
| CN115949652A (en) | Hydraulic load simulation active and passive and multi-working-condition loading method and hydraulic system | |
| CN113107911A (en) | Trestle pitching hydraulic system with energy recovery and wave compensation motion functions | |
| CN110985470B (en) | Hydraulic flow control device for turning of servo valve controlled aircraft | |
| CN111911216A (en) | Directional flow valve with continuous flow adjusting function and control method thereof | |
| CN204878978U (en) | Hydraulic drive system of extra -large -size reservoir atmospheric valve | |
| CN105217508A (en) | A kind of hoist brake control system, method and hoisting crane | |
| CN212337750U (en) | Rotary balance valve and rotary hydraulic system | |
| WO2021169175A1 (en) | Oilway structure for achieving precise control of double-acting cylinder | |
| CN202923545U (en) | Loading and unloading switching device and load-sensitive hydraulic system | |
| CN107061377A (en) | A kind of heavy duty lifting electrohydraulic control system | |
| CN208474211U (en) | A kind of Full-hydraulic braking apparatus filling liquid valve group and its control system | |
| CN207879742U (en) | Can manual ftercompction hoisting system | |
| CN216278724U (en) | Closed pump control system capable of quickly releasing hydraulic energy | |
| CN203959756U (en) | The forklift gantry pipeline system of a kind of pair of governor valve | |
| CN106907518B (en) | Double-acting pneumatic reset electric open type actuating mechanism | |
| CN204436958U (en) | A kind of three-dimensional loads hydraulic pressure installation | |
| CN108691850B (en) | Ultrahigh pressure relief system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |