CN112173085B - 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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- CN112173085B CN112173085B CN202011020899.5A CN202011020899A CN112173085B CN 112173085 B CN112173085 B CN 112173085B CN 202011020899 A CN202011020899 A CN 202011020899A CN 112173085 B CN112173085 B CN 112173085B
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Fluid-Pressure Circuits (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
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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, the present invention aims to provide a hydraulic control system for retraction and extension of a helicopter landing gear, which can realize the retraction and extension control of the landing gear and has a landing gear emergency extension control function when the hydraulic system fails to retract and extend normally.
In order to achieve the purpose, the invention adopts the following technical scheme to realize.
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;
defining a port P0 as a normal retraction pressure supply port of the undercarriage, a port R0 as an retraction oil return port of the undercarriage, and a port P1 as an emergency extension pressure supply port of the undercarriage; 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 an undercarriage down electromagnetic valve 2 and a port A of an undercarriage up electromagnetic valve 3, a 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 communicated with ports F1, F2 and F3 respectively;
the P port of the landing gear retraction electromagnetic valve 3 is respectively communicated with the input ports of the first throttle valve 5, the second throttle valve 6 and the 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 port, the S2 port and the S3 port;
the port P1 is communicated with an input port of the oil filter 10, and an output port undercarriage emergency lowering solenoid valve 4A of the oil filter 10 is communicated;
the port R0 is communicated with a port B of an undercarriage down electromagnetic valve 2, an undercarriage retracting electromagnetic valve 3 and an undercarriage emergency down 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.
In a further aspect of the present invention,
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 a port A of the pressure supply electromagnetic valve 12;
the port P1 is also communicated with a port P of the pressure supply electromagnetic 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 R0 port is also communicated with the T port 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 undercarriage retraction cavities through a port P0, a port A, P of the undercarriage retraction electromagnetic valve 3 and ports S1, S2 and S3 respectively, undercarriage oil return passes through a port F1, a port F2 and a port F3 and a port A of a conversion valve 8T, and the undercarriage retracts a port 2P and a port B of the electromagnetic valve 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 releasing cavities from the port P0, the port A, P of the landing gear releasing electromagnetic valve 2, the port A and the port T of the conversion valve 8 and the ports F1, F2 and F3 respectively;
the oil return of the undercarriage returns to the hydraulic oil tank on the aircraft through the ports S1, S2 and S3, the ports P and B of the undercarriage retraction electromagnetic valve 3 and the 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 undercarriage emergency lowering electromagnetic 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 undercarriage emergency lowering electromagnetic 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 undercarriages respectively, so that the undercarriage is put down emergently.
Further, when 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 connected, and pressure oil passes through the oil filter 10 from the port P1 and reaches the port P0 through the pressure supply electromagnetic valve 12.
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 helicopter landing gear 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 undercarriage, the port R0 is an oil return port for retraction of the undercarriage, and the port P1 is a pressure supply port for emergency retraction of the undercarriage. The ports S1, S2 and S3 are pressure supply ports for retracting the landing gear, and the ports F1, F2 and F3 are pressure supply ports for putting down the landing gear.
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 a throttle valve 5,6,7 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 conversion 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 communicated with the ports F1, F2 and F3 respectively. 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 is communicated with the port T of the safety valve 9 and the ports 2, 3 and 4B of the electromagnetic valve. The port B of the switching valve 8 is communicated with the port P of the electromagnetic valve 4.
According to the undercarriage 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 total flow distributed to the undercarriage retraction by the onboard hydraulic system is limited through the flow limiting valve 1.
When the undercarriage is retracted, the undercarriage retraction electromagnetic valve 3 is electrified, pressure oil passes through the port P0, the undercarriage retraction electromagnetic valve 3 supplies pressure to the three undercarriages through the ports S1, S2 and S3, return oil of the undercarriage returns to the onboard hydraulic oil tank through the ports F1, F2 and F3 and the undercarriage retraction electromagnetic valve 2, and the oil returns to the onboard hydraulic oil tank through the port R0.
When the undercarriage is put down, the undercarriage put-down electromagnetic valve 2 is electrified, pressure oil passes through the P0 port, the undercarriage put-down electromagnetic valve 2 and the conversion valve 8 respectively supplies pressure to the three undercarriages through the F1 port, the F2 port and the F3 port, and undercarriage return oil passes through the S1 port, the S2 port and the S3 port, passes through the undercarriage retraction electromagnetic valve 3 and returns to an onboard hydraulic oil tank through the R0 port. 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 lowering function, when the undercarriage normally retracts and retracts, the undercarriage emergency lowering electromagnetic valve 4 is electrified, pressure oil passes through the oil filter 10, the safety valve 9, the pressure sensor 11 and the undercarriage emergency lowering electromagnetic valve 4 from the port P1, and pressure is supplied to the three undercarriages through the ports F1, F2 and F3 respectively, so that the undercarriage is lowered in an emergency manner.
The undercarriage retraction control assembly simultaneously provides a ground pressure supply function for equipment using hydraulic energy on the aircraft, and pressure oil supplies pressure to other equipment using hydraulic energy on the aircraft 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.
The undercarriage control assembly related by the invention adopts an integrated design, 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 manner and are arranged 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 (2)
1. A helicopter landing gear retraction hydraulic control system, said system comprising:
the landing gear emergency release device comprises a flow limiting valve (1), a landing gear release electromagnetic valve (2), a landing gear retraction electromagnetic valve (3), a landing gear emergency release 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);
defining a P0 port as a normal retraction pressure supply port of the undercarriage, a R0 port as an retraction oil return port of the undercarriage, and a P1 port as an emergency lowering pressure supply port of the undercarriage; 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 the flow limiting valve (1), an output port of the flow limiting valve (1) is communicated with a port A of an undercarriage lowering electromagnetic valve (2) and an undercarriage retracting electromagnetic valve (3), the port P of the undercarriage lowering 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;
a port P of the undercarriage retraction electromagnetic valve (3) is respectively communicated with input ports of a first throttle valve (5), a second throttle valve (6) and a third throttle valve (7), and output ports of the first throttle valve (5), the second throttle valve (6) and the third throttle valve (7) are respectively communicated with ports S1, S2 and S3;
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 electromagnetic valve (4) of the oil filter (10) is communicated;
the R0 port is communicated with a port B of the undercarriage down electromagnetic valve (2), the undercarriage retracting electromagnetic valve (3) and the undercarriage emergency down 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);
the 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 a pressure supply electromagnetic valve (12);
the port P1 is also communicated with a port P of a pressure supply electromagnetic valve (12);
the 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 R0 port is also communicated with a T port of the safety valve (9);
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 the three undercarriage retraction cavities from a port P0 through a port A, P of the undercarriage retraction electromagnetic valve (3) and from ports S1, S2 and S3 respectively, undercarriage return oil passes through a port T and a port A of a conversion valve (8) through ports F1, F2 and F3, and the undercarriage is put down from the port P and the port B of the electromagnetic valve (2) and returns to an onboard hydraulic oil tank through a port R0;
when the undercarriage is put down, the undercarriage put-down electromagnetic valve (2) is electrified, the port P is communicated with the port A, the port B is closed, the undercarriage retraction electromagnetic valve (3) is powered off, the port P is communicated with the port B, and the port A is closed;
pressure oil is supplied to the three landing gear releasing cavities from a port P0, a port A, P of the landing gear releasing electromagnetic valve (2), a port A and a port T of the switching valve (8) and ports F1, F2 and F3 respectively;
the return oil of the undercarriage returns to the hydraulic oil tank on the aircraft through ports S1, S2 and S3, through ports P and B of the undercarriage retraction electromagnetic valve (3) and through port R0;
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;
when pressure at the port P0 is lost, the undercarriage emergency lowering solenoid valve (4) is powered on, 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 undercarriage emergency lowering solenoid valve (4) and reaches the conversion valve (8), the conversion valve (8) converts, 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 and respectively supplies pressure to the lowering cavities of the three undercarriages to realize the emergency lowering of the undercarriages;
when pressure at 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) from the port P1 and reaches the port P0 through the pressure supply electromagnetic valve (12).
2. A hydraulic helicopter landing gear retraction control system according to claim 1 wherein the landing gear retraction solenoid valve (3) is de-energised when the landing gear is retracted into position.
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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 true CN112173085B (en) | 2023-03-28 |
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| CN113928543B (en) * | 2021-11-19 | 2023-09-08 | 中国直升机设计研究所 | Helicopter undercarriage retraction control system |
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