CN112173085A - Hydraulic control system and method for retraction and release of helicopter undercarriage - Google Patents
Hydraulic control system and method for retraction and release of helicopter undercarriage Download PDFInfo
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- CN112173085A CN112173085A CN202011020899.5A CN202011020899A CN112173085A CN 112173085 A CN112173085 A CN 112173085A CN 202011020899 A CN202011020899 A CN 202011020899A CN 112173085 A CN112173085 A CN 112173085A
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- port
- landing gear
- valve
- retraction
- electromagnetic valve
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- 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
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- 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
- F15B21/00—Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
- F15B21/04—Special measures taken in connection with the properties of the fluid
- F15B21/041—Removal or measurement of solid or liquid contamination, e.g. filtering
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- 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
Abstract
The invention belongs to the technical field of helicopter undercarriage control, and discloses a hydraulic control system for retraction and release of a helicopter undercarriage, which comprises: the landing gear emergency lowering system comprises a flow limiting valve, a landing gear lowering electromagnetic valve, a landing gear retracting electromagnetic valve, a landing gear emergency lowering electromagnetic valve, a first throttle valve, a second throttle valve, a third throttle valve, a conversion valve and an oil filter; the control device can realize the retraction control of the undercarriage, and has the function of controlling the undercarriage to be put down in an emergency when the hydraulic system is normally retracted and fails.
Description
Technical Field
The invention belongs to the technical field of helicopter undercarriage control, and particularly relates to a hydraulic control system for retraction and extension of a helicopter undercarriage.
Background
With the increase of the flight speed of the helicopter, higher requirements are put forward for reducing the aerodynamic resistance of the helicopter. The starting resistance of the landing gear of a common helicopter accounts for 15% -20% of the total resistance, and the aerodynamic resistance of the helicopter can be effectively reduced by adopting a retractable landing gear. At present, the extension and retraction of a helicopter undercarriage are mostly realized by adopting a hydraulic mode.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a hydraulic control system for retraction and extension of a landing gear of a helicopter, which can realize retraction and extension control of the landing gear and has a landing gear emergency lowering control function when the hydraulic system is normally retracted and extended and fails.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
Technical scheme one
A helicopter landing gear retraction hydraulic control system, said system comprising:
the landing gear emergency landing device comprises a flow limiting valve 1, a landing gear lowering electromagnetic valve 2, a landing gear retracting electromagnetic valve 3, a landing gear emergency lowering electromagnetic valve 4, a first throttle valve 5, a second throttle valve 6, a third throttle valve 7, a conversion valve 8 and an oil filter 10;
a port P0 is defined as a normal retraction pressure supply port of the landing gear, a port R0 is a retraction oil return port of the landing gear, and a port P1 is a pressure supply port for emergency lowering of the landing gear; the ports S1, S2 and S3 are pressure supply ports when the landing gear is folded, and the ports F1, F2 and F3 are oil return ports when the landing gear is folded;
defining a port P of an undercarriage down electromagnetic valve 2, an undercarriage retracting electromagnetic valve 3 and an undercarriage emergency down electromagnetic valve 4 as input ports, wherein a port A is a first outlet port, and a port B is a second outlet port;
the port P0 is communicated with an input port of the flow limiting valve 1, an output port of the flow limiting valve 1 is communicated with a port A of the landing gear lowering electromagnetic valve 2 and a port A of the landing gear retracting electromagnetic valve 3, a port P of the landing gear lowering electromagnetic valve 2 is communicated with a port A of the conversion valve 8, and a port T of the conversion valve 8 is respectively communicated with a port F1, a port F2 and a port F3;
the P port of the landing gear retraction electromagnetic valve 3 is respectively communicated with the input ports of a first throttle valve 5, a second throttle valve 6 and a third throttle valve 7, and the output ports of the first throttle valve 5, the second throttle valve 6 and the third throttle valve 7 are respectively communicated with the S1, the S2 and the S3 ports;
the port P1 is communicated with an input port of the oil filter 10, and an output port of the oil filter 10 is communicated with a port A of the landing gear emergency lowering solenoid valve 4;
the port R0 is communicated with the ports B of the landing gear lowering electromagnetic valve 2, the landing gear retracting electromagnetic valve 3 and the landing gear emergency lowering electromagnetic valve 4; and a port B of the conversion valve 8 is communicated with a port P of the landing gear emergency lowering electromagnetic valve 4.
Further, in the above-mentioned case,
the system further comprises: a pressure supply solenoid valve 12;
defining a port P of the pressure supply electromagnetic valve 12 as an input port and a port A as an outlet port;
the port P0 is also communicated with the port A of the pressure supply electromagnetic valve 12;
the port P1 is also in communication with the port P of the pressure supply solenoid valve 12.
Further, in the above-mentioned case,
the system further comprises: a safety valve 9, a pressure sensor 11;
a port P of the safety valve 9 is defined as an input port, and a port T is defined as a pressure relief port;
the output port of the oil filter 10 is also respectively communicated with the pressure sensor 11 and the port P of the safety valve 9;
the port R0 also communicates with the port T of the relief valve 9.
The second technical scheme is as follows:
a hydraulic control method for retraction and release of a helicopter landing gear, which is applied to the system in the first technical scheme, comprises the following steps:
when the undercarriage is retracted, the undercarriage retraction electromagnetic valve 3 is electrified, the port P is communicated with the port A, the port B is closed, the undercarriage extension electromagnetic valve 2 is powered off, the port P is communicated with the port B, and the port A is closed;
pressure oil is supplied to three landing gear retraction cavities from a port P0 through a port A, P of a landing gear retraction electromagnetic valve 3 and from ports S1, S2 and S3 respectively, landing gear return oil passes through a port F1, a port F2 and a port F3 through a switching valve 8T and a port A, and the landing gear is lowered from a port P and a port B of the electromagnetic valve 2 and returns to an onboard hydraulic oil tank through a port R0.
Further, when the landing gear is retracted in place, the landing gear retraction electromagnetic valve 3 is powered off.
Further, when the undercarriage is put down, the undercarriage putting down electromagnetic valve 2 is powered on, the port P is communicated with the port A, the port B is closed, the undercarriage retracting electromagnetic valve 3 is powered off, the port P is communicated with the port B, and the port A is closed;
the pressure oil is supplied to the three landing gear lower cavities from a port P0 through a port A, P of the landing gear lower electromagnetic valve 2, a port A and a port T of the conversion valve 8 and ports F1, F2 and F3 respectively;
the return oil of the landing gear passes through ports S1, S2 and S3, passes through ports P and B of the landing gear retraction electromagnetic valve 3, and returns to an onboard hydraulic oil tank through a port R0.
Furthermore, the first throttle valve 5, the second throttle valve 6 and the third throttle valve 7 respectively adjust the retraction speeds of the three landing gears through throttling, so that the three landing gears move coordinately and stably.
Further, when pressure of a port P0 is lost, the landing gear emergency lowering solenoid valve 4 is electrified, the port P is communicated with the port A, pressure oil passes through the oil filter 10 from the port P1, and the port A and the port P of the landing gear emergency lowering solenoid valve 4 and reaches the conversion valve 8, the conversion valve 8 is converted, the port B and the port T are communicated, the port A is closed, the pressure oil reaches the ports F1, F2 and F3 from the port T, and pressure is supplied to lowering cavities of the three landing gears respectively, so that the landing gear emergency lowering is realized.
Furthermore, when the pressure of the port P0 is lost and pressure needs to be supplied to other equipment using hydraulic energy on the machine, the pressure supply electromagnetic valve 12 is electrified, the port P and the port A are communicated, and pressure oil passes through the oil filter 10 and the pressure supply electromagnetic valve 12 from the port P1 to the port P0.
The undercarriage control assembly can be applied to helicopters adopting hydraulic retractable undercarriages, can provide undercarriage control functions, and has dual-redundancy undercarriage control. The invention adopts an integrated design and has the advantages of light weight, high reliability and good maintainability.
Drawings
FIG. 1 is a schematic block diagram of a hydraulic control system for retraction and extension of a landing gear of a helicopter according to an embodiment of the present invention;
1-a current limiting valve, 2-an undercarriage down electromagnetic valve, 3-an undercarriage up electromagnetic valve, 4-an undercarriage emergency discharge electromagnetic valve, 5-a throttle valve, 6-a throttle valve, 7-a throttle valve, 8-a conversion valve, 9-a safety valve, 10-an oil filter, 11-a pressure sensor and 12-a ground pressure supply electromagnetic valve.
Detailed Description
The principle of the landing gear retraction control assembly according to the present invention is shown in fig. 1. The port P0 is a pressure supply port for normal retraction of the landing gear, the port R0 is an oil retraction port for retraction of the landing gear, and the port P1 is a pressure supply port for emergency lowering of the landing gear. Ports S1, S2 and S3 are landing gear retraction pressure supply ports, and ports F1, F2 and F3 are landing gear retraction pressure supply ports.
The invention relates to an undercarriage retraction control assembly, which consists of a shell, a ground pressure supply electromagnetic valve 12, a safety valve 9, an oil filter 10, an undercarriage retraction electromagnetic valve 3, an undercarriage lowering electromagnetic valve 2, an undercarriage emergency lowering electromagnetic valve 4, a flow limiting valve 1, a conversion valve 8, a pressure sensor 11 and throttle valves 5,6 and 7 embedded in the shell.
Defining the P ends of the electromagnetic valves 2, 3 and 4 as input ports, the A end as a first outlet and the B end as a second outlet; defining the P end of the safety valve 9 as an input port and the T end as a pressure relief port; defining the P end of the electromagnetic valve 12 as an input port and the A end as an outlet; the end of the switching valve 8A, B is defined as an alternative inlet, and the T port is defined as an outlet.
The port P0 is communicated with the end A of the ground pressure supply electromagnetic valve 12 and the input end of the flow limiting valve 1, the output port of the flow limiting valve 1 is communicated with the ports 2 and 3A of the electromagnetic valve, the port 2P of the electromagnetic valve is communicated with the end A of the conversion valve 8, and the end T of the conversion valve 8 is respectively communicated with the ports F1, F2 and F3. The P port of the electromagnetic valve 3 is respectively communicated with the input ends of the throttle valves 5,6 and 7, and the output ends of the throttle valves 5,6 and 7 are respectively communicated with the S1, S2 and S3 ports.
The port P1 is communicated with the input end of the oil filter 10, and the output end of the oil filter 10 is respectively communicated with the port P of the pressure sensor 11 and the safety valve 9, the port P of the electromagnetic valve 12 and the port 4A of the electromagnetic valve.
The port R0 communicates with the port T of the relief valve 9 and the ports 2, 3, and 4B of the electromagnetic valves. The port B of the switching valve 8 is communicated with the port P of the electromagnetic valve 4.
According to the landing gear retraction control assembly, a port P0 is communicated with pressure oil of an onboard hydraulic system, a port R0 is communicated with return oil of the onboard hydraulic system, and the total flow distributed to the retraction of the landing gear by the onboard hydraulic system is limited through the flow limiting valve 1.
When the landing gear is retracted, the landing gear retraction electromagnetic valve 3 is electrified, pressure oil passes through the port P0, pressure is respectively supplied to the three landing gears through the ports S1, S2 and S3 by the landing gear retraction electromagnetic valve 3, and landing gear return oil passes through the landing gear lowering electromagnetic valve 2 through the ports F1, F2 and F3 and returns to an onboard hydraulic oil tank through the port R0.
When the landing gear is put down, the landing gear put-down electromagnetic valve 2 is electrified, pressure oil passes through the port P0, pressure is supplied to the three landing gears through the ports F1, F2 and F3 through the landing gear put-down electromagnetic valve 2 and the switching valve 8 respectively, landing gear return oil passes through the ports S1, S2 and S3, passes through the landing gear put-down electromagnetic valve 3 and returns to an onboard hydraulic oil tank through the port R0. The throttle valves 5,6 and 7 adjust the retraction speed of the landing gears, so that the three landing gears move coordinately and stably.
The undercarriage control assembly has a dual-redundancy undercarriage extension function, when the undercarriage normally extends and retracts and has a fault, the undercarriage emergency extension solenoid valve 4 is electrified, pressure oil passes through the oil filter 10, the safety valve 9, the pressure sensor 11 and the undercarriage emergency extension solenoid valve 4 from a port P1, and supplies pressure to three undercarriages through ports F1, F2 and F3 respectively, so that the undercarriage is put down emergently.
The invention relates to a landing gear retraction control assembly which simultaneously provides a ground pressure supply function for equipment using hydraulic energy on the aircraft, and pressure oil passes through an oil filter 10, a safety valve 9, a pressure sensor 11 and a ground pressure supply electromagnetic valve 12 from a port P1 to supply pressure for other equipment using hydraulic energy on the aircraft.
The undercarriage control assembly is designed in an integrated mode, and a ground pressure supply electromagnetic valve 12, an undercarriage retraction electromagnetic valve 3, an undercarriage extension electromagnetic valve 2, an undercarriage emergency extension electromagnetic valve 4 and a pressure sensor 11 are connected in a plug-in mode and are installed on a shell through screws. The safety valve 9, the oil filter 10, the flow limiting valve 1 and the conversion valve 8 are connected in a screw-in mode and are screwed into the shell through threads.
Claims (9)
1. A helicopter landing gear retraction hydraulic control system, said system comprising:
the landing gear emergency landing system comprises a flow limiting valve (1), a landing gear lowering electromagnetic valve (2), a landing gear retracting electromagnetic valve (3), a landing gear emergency lowering electromagnetic valve (4), a first throttle valve (5), a second throttle valve (6), a third throttle valve (7), a conversion valve (8) and an oil filter (10);
a port P0 is defined as a normal retraction pressure supply port of the landing gear, a port R0 is a retraction oil return port of the landing gear, and a port P1 is a pressure supply port for emergency lowering of the landing gear; the ports S1, S2 and S3 are pressure supply ports when the landing gear is folded, and the ports F1, F2 and F3 are oil return ports when the landing gear is folded;
defining a P port of an undercarriage down electromagnetic valve (2), an undercarriage retracting electromagnetic valve (3) and an undercarriage emergency down electromagnetic valve (4) as input ports, an A port as a first outlet port and a B port as a second outlet port;
the port P0 is communicated with an input port of a flow limiting valve (1), an output port of the flow limiting valve (1) is communicated with a port A of an undercarriage down electromagnetic valve (2) and an undercarriage up electromagnetic valve (3), the port P of the undercarriage down electromagnetic valve (2) is communicated with a port A of a conversion valve (8), and a port T of the conversion valve (8) is respectively communicated with ports F1, F2 and F3;
the P port of the landing gear retraction electromagnetic valve (3) is respectively communicated with the input ports of a first throttle valve (5), a second throttle valve (6) and a third throttle valve (7), and the output ports of the first throttle valve (5), the second throttle valve (6) and the third throttle valve (7) are respectively communicated with the S1, the S2 and the S3 ports;
the port P1 is communicated with an input port of the oil filter (10), and an output port A of the landing gear emergency lowering solenoid valve (4) of the oil filter (10) is communicated;
the port R0 is communicated with the ports B of the landing gear lowering electromagnetic valve (2), the landing gear retracting electromagnetic valve (3) and the landing gear emergency lowering electromagnetic valve (4); the port B of the conversion valve (8) is communicated with the port P of the landing gear emergency lowering electromagnetic valve (4).
2. A helicopter landing gear retraction hydraulic control system according to claim 1 wherein said system further comprises: a pressure supply solenoid valve (12);
a P port of the pressure supply electromagnetic valve (12) is defined as an input port, and an A port is defined as an outlet port;
the port P0 is also communicated with a port A of the pressure supply electromagnetic valve (12);
the port P1 is also communicated with a port P of a pressure supply electromagnetic valve (12).
3. A helicopter landing gear retraction hydraulic control system according to claim 1 wherein said system further comprises: a safety valve (9) and a pressure sensor (11);
a P port of the safety valve (9) is defined as an input port, and a T port is defined as a pressure relief port;
the output port of the oil filter (10) is also respectively communicated with the pressure sensor (11) and the port P of the safety valve (9);
the port R0 is also communicated with a port T of the safety valve (9).
4. A helicopter landing gear retraction hydraulic control method for use in a system according to any of claims 1 to 3, the method comprising:
when the undercarriage is retracted, the undercarriage retraction electromagnetic valve (3) is powered on, the port P is communicated with the port A, the port B is closed, the undercarriage extension electromagnetic valve (2) is powered off, the port P is communicated with the port B, and the port A is closed;
pressure oil is supplied to three landing gear retraction cavities from a port P0 through a port A, P of a landing gear retraction electromagnetic valve (3) and from ports S1, S2 and S3 respectively, landing gear return oil passes through a port T and a port A of a conversion valve (8) through ports F1, F2 and F3, and the port P and the port B of the landing gear retraction electromagnetic valve (2) return to an onboard hydraulic oil tank through a port R0.
5. A hydraulic helicopter landing gear retraction control method according to claim 4, characterized in that the landing gear retraction solenoid valve (3) is de-energized when the landing gear is retracted into position.
6. The hydraulic control method for the retraction and extension of the landing gear of the helicopter according to claim 4, characterized in that when the landing gear is retracted, the landing gear retraction solenoid valve (2) is energized, the port P is communicated with the port A, the port B is closed, the landing gear retraction solenoid valve (3) is de-energized, the port P is communicated with the port B, and the port A is closed;
the pressure oil is supplied to the three landing gear releasing cavities from a port P0, a port A and a port T of the switching valve (8) through a port A, P of the landing gear releasing electromagnetic valve (2), and ports F1, F2 and F3 respectively;
the return oil of the landing gear passes through ports S1, S2 and S3, passes through ports P and B of the landing gear retraction electromagnetic valve (3) and returns to an onboard hydraulic oil tank through a port R0.
7. The hydraulic control method for the retraction and extension of the landing gear of the helicopter according to claim 4, characterized in that the first throttle valve (5), the second throttle valve (6) and the third throttle valve (7) respectively adjust the retraction and extension speeds of three landing gears by throttling, so that the three landing gears move coordinately and stably.
8. The hydraulic control method for the retraction and extension of the landing gear of the helicopter according to claim 4, characterized in that when the pressure of the port P0 is lost, the landing gear emergency retraction solenoid valve (4) is energized, the port P is communicated with the port A, pressure oil passes through the oil filter (10) from the port P1, the port A and the port P of the landing gear emergency retraction solenoid valve (4) and reaches the conversion valve (8), the conversion valve (8) is converted, the port B and the port T are communicated, the port A is closed, and the pressure oil reaches the ports F1, F2 and F3 from the port T, so that the pressure oil is respectively supplied to the retraction chambers of the three landing gears, and the landing gear emergency retraction is realized.
9. The hydraulic control method for the retraction and extension of the landing gear of the helicopter according to claim 4, characterized in that when the pressure at port P0 is lost and pressure needs to be supplied to other equipment on the helicopter using hydraulic energy, the pressure supply solenoid valve (12) is energized, port P and port A are connected, and pressure oil passes through the oil filter (10) and the pressure supply solenoid valve (12) from port P1 to port P0.
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| CN202011020899.5A CN112173085B (en) | 2020-09-25 | 2020-09-25 | Hydraulic control system and method for retraction and release of helicopter undercarriage |
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| CN202011020899.5A CN112173085B (en) | 2020-09-25 | 2020-09-25 | Hydraulic control system and method for retraction and release of helicopter undercarriage |
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| CN112173085B CN112173085B (en) | 2023-03-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113928543A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter undercarriage control system that receive and releases |
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