CN111516858A - Electric servo actuator - Google Patents
Electric servo actuator Download PDFInfo
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- CN111516858A CN111516858A CN202010370554.6A CN202010370554A CN111516858A CN 111516858 A CN111516858 A CN 111516858A CN 202010370554 A CN202010370554 A CN 202010370554A CN 111516858 A CN111516858 A CN 111516858A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/504—Transmitting means with power amplification using electrical energy using electro-hydrostatic actuators [EHA's]
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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)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
The invention belongs to the field of flight control, and particularly relates to an electric servo actuator. On the basis of the existing servo actuator, a motor pump assembly, a mode conversion assembly and a system back pressure assembly are added to realize multi-mode control conversion. The safety requirement based on the airplane control surface non-similar actuation framework is met.
Description
Technical Field
The invention belongs to the field of flight control, and particularly relates to an electric servo actuator.
Background
At present, the control surface of the existing aircraft in China generally adopts a single actuator to drive and work, and the research on the control surface actuator of the civil aircraft is less. Based on the requirement of civil aircraft system security, the main flight control surface generally adopts two actuator drive work in civil aircraft design process, and after an actuator trouble, the safety of aircraft can be guaranteed in another actuator work, and this needs the actuator to switch work between a plurality of modals, and traditional electric hydraulic actuator can not satisfy the requirement under the civil aircraft security framework yet. Meanwhile, according to different airplane architectures, two actuators need to be designed into different power inputs to realize non-similar redundancy configuration.
Disclosure of Invention
The purpose of the invention is as follows: the electric servo actuator is provided to meet the requirement of dissimilar redundancy configuration mode conversion in the driving process of the double actuators of the main flight control plane of the civil aircraft.
The technical scheme is as follows:
in a first aspect, there is provided an electric servo actuator comprising: the hydraulic control system comprises a motor controller 1, a motor 2, a hydraulic pump 3, two pump port high-pressure selection valves 6, a modal electromagnetic valve 7, a modal conversion valve 8, an actuator cylinder linear displacement sensor 9, a hydraulic actuator cylinder 10 and an energy accumulator 15, wherein the two pump port high-pressure selection valves are hydraulic one-way valves, the modal electromagnetic valve is a two-position three-way electromagnetic valve, a control port is communicated with high-pressure oil when the hydraulic control system is powered on, and the control port is communicated with return oil when the hydraulic control system is powered off; the motor controller 1 is connected with the motor 2 through a cable, an output shaft of the motor is fixedly connected with an input port of the hydraulic pump 3, two load oil ports of the hydraulic pump are respectively connected with two oil inlets of the modal change-over valve 8 through two pipelines, and a first load port and a second load port of the modal change-over valve are respectively connected with a first oil pipe nozzle and a second oil pipe nozzle of the hydraulic actuating cylinder 10 through two pipelines; two load oil ports of the hydraulic pump are connected with inlets of two pump port high-pressure selection valves 6 through pipelines, an oil inlet of a modal solenoid valve 7 is connected with outlets of the two pump port high-pressure selection valves through a pipeline, an oil return port of the modal solenoid valve is connected with an energy accumulator 15 through a pipeline, and a control port of the modal solenoid valve is connected with a hydraulic control port of a modal change-over valve through a pipeline; the actuator cylinder linear displacement sensor 9 is arranged in the hydraulic actuator cylinder, an iron core of the actuator cylinder linear displacement sensor is fixedly connected with a piston of the actuator cylinder, and a coil of the actuator cylinder linear displacement sensor is fixedly connected with a cylinder body of the actuator cylinder.
Further, still include: two pump mouth anti cavitation valves 4, two pressurized strut anti cavitation valves 11, two pump mouth anti cavitation valves 4 and two pressurized strut anti cavitation valves 11 are hydraulic check valves, two load oil mouths of hydraulic pump pass through the exit linkage of pipeline with two pump mouth anti cavitation valves 4, the import of two pump mouth anti cavitation valves is connected with the energy storage ware through the pipeline, two oil nozzle mouths of hydraulic pressurized strut pass through two pipelines and are connected with the oil-out of two anti cavitation valves 11 respectively, the oil inlet of two anti cavitation valves passes through the pipeline and is connected with the energy storage ware.
Further, still include: the two overpressure protection valves 5 are overflow valves, two load oil ports of the hydraulic pump are connected with inlets of the two overpressure protection valves 5 through pipelines, and outlets of the two overpressure protection valves are connected with the energy accumulator through pipelines.
Further, the motor is a rare earth permanent magnet brushless direct current motor.
Furthermore, the hydraulic pump is a plunger hydraulic pump capable of working in two directions
Further, the energy accumulator is a spring piston type or a gas piston type energy accumulator.
Furthermore, the modal conversion valve is a hydraulic control two-position four-way valve, and is in a normal working position when receiving high-pressure oil for control, and is in a damping working position when no high-pressure oil is input.
Further, still include: the hydraulic control system comprises two actuating cylinder cavity high-pressure selection valves 12, a bypass electromagnetic valve 13 and a damping switching valve 14, wherein the modal switching valve is a hydraulic control two-position five-way valve which is in a normal working position when receiving high-pressure oil control, a first load port is communicated with a bypass port when no high-pressure oil is input, and a second load port is closed; a bypass port of the modal changeover valve is connected with an oil inlet of the damping changeover valve through a pipeline, and an oil outlet of the damping changeover valve is connected with a second oil pipe nozzle of the hydraulic actuator cylinder through a pipeline; an oil inlet of the bypass electromagnetic valve is connected with outlets of the two high-pressure selection valves through a pipeline, an oil return port of the bypass electromagnetic valve is connected with an inlet of the oil return back pressure valve through a pipeline, and a control port of the bypass electromagnetic valve is connected with a hydraulic control port of the damping switching valve through a pipeline; two oil pipe mouths of the hydraulic actuating cylinder are respectively connected with oil inlets of the two actuating cylinder cavity high-pressure selection valves through two pipelines.
Further, the damping switching valve is a hydraulic control two-position two-way valve, and is in communication with small damping when receiving high-pressure oil control and is in communication with large damping when no high-pressure oil is input.
Furthermore, the actuating cylinder cavity high-pressure selection valve is a hydraulic one-way valve, the bypass electromagnetic valve is a two-position three-way electromagnetic valve, the control port is communicated with high-pressure oil when the valve is powered on, and the control port is communicated with return oil when the valve is powered off.
The invention has the beneficial effects that: the electric servo actuator comprises two or three working modes, and can meet the requirement of a safety-based airplane control surface non-similar redundancy actuation framework.
Drawings
FIG. 1 is an electric servo actuator with two modes of operation
FIG. 2 is an electric servo actuator with three modes of operation
The hydraulic control system comprises a motor controller 1, a motor 2, a hydraulic pump 3, two pump port anti-cavitation valves 4, two overpressure protection valves 5, two pump port high-pressure selection valves 6, a mode electromagnetic valve 7, a mode conversion valve 8, a cylinder linear displacement sensor 9, a hydraulic cylinder 10, two cylinder anti-cavitation valves 11, two cylinder cavity high-pressure selection valves 12, a bypass electromagnetic valve 13, a damping switching valve 14 and an energy accumulator 15.
Detailed Description
The following detailed description is made with reference to the accompanying drawings.
The first embodiment is as follows:
the invention provides a bimodal electro-hydraulic servo actuator which is used for driving a main flight control plane on an airplane and pushing the airplane control plane to deflect so as to realize flight attitude adjustment. The actuator comprises two working modes, the actuator is driven by power input on the airplane in the normal working process, and the actuator is controlled by a superior control system to realize the output action of the actuator; when the power supply fails, the actuator is converted into a damping mode, two cavities of the actuator are in damping communication to inhibit the flutter of the control surface, and the control surface is prevented from freely moving along with the pneumatic load to influence flight safety. Belongs to the technical field of product structures.
The invention provides a bimodal electric servo actuator, which comprises a motor controller 1, a motor 2, a hydraulic pump 3, two pump port anti-cavitation valves 4, two overvoltage protection valves 5, two pump port high-pressure selection valves 6, a modal electromagnetic valve 7, a modal change-over valve 8, an actuator cylinder linear displacement sensor 9, a hydraulic actuator cylinder 10, two actuator cylinder anti-cavitation valves 11 and an energy accumulator 15, wherein the motor controller is connected with the motor controller 1; wherein: a motor controller 1 is connected with a motor 2 through a pass cable, an output shaft of the motor is fixedly connected with an input shaft of a hydraulic pump 3, two load oil ports of the hydraulic pump are respectively connected with two oil inlets of a modal change-over valve 8 through two pipelines, and two load ports of the modal change-over valve are respectively connected with two oil pipe nozzles of a hydraulic actuating cylinder 10 through two pipelines; two load oil ports of the hydraulic pump are connected with outlets of two pump port anti-cavitation valves 4 through pipelines, two load oil ports of the hydraulic pump are connected with inlets of two overvoltage protection valves 5 through pipelines, inlets of the two pump port anti-cavitation valves are connected with an energy accumulator 15 through pipelines, and outlets of the two overvoltage protection valves are connected with the energy accumulator through pipelines; two load oil ports of the hydraulic pump are connected with inlets of two pump port high-pressure selection valves 6 through pipelines, an oil inlet of a modal solenoid valve 7 is connected with outlets of the two pump port high-pressure selection valves through a pipeline, an oil return port of the modal solenoid valve is connected with an energy accumulator through a pipeline, and a control port of the modal solenoid valve is connected with a hydraulic control port of a modal change-over valve through a pipeline; two oil nozzles of the hydraulic actuating cylinders are respectively connected with oil outlets of two actuating cylinder anti-cavitation valves 11 through two pipelines, and oil inlets of 2 anti-cavitation valves are connected with an energy accumulator through pipelines; the actuator cylinder linear displacement sensor 9 is arranged in the hydraulic actuator cylinder, an iron core of the actuator cylinder linear displacement sensor is fixedly connected with a piston of the actuator cylinder, and a coil of the actuator cylinder linear displacement sensor is fixedly connected with a cylinder body of the actuator cylinder.
When the hydraulic actuator works normally, the electromagnetic valve is electrified, the modal conversion valve is in a normal working position, the motor controller receives an instruction and then controls the motor to work, and the actuating cylinder outputs the instruction; when the hydraulic actuator works in a fault, the electromagnetic valve is powered off, the modal conversion valve is in a damping working position, and the two cavities of the actuator cylinder are in damping communication at the modal conversion valve; and the motor controller receives a rotor position feedback signal of the motor and outputs 3 circuits to drive the motor to rotate according to the required rotating speed.
The motor is a rare earth permanent magnet brushless direct current motor and can output and work at different speeds; the hydraulic pump is a plunger hydraulic pump capable of working in two directions; the two pump port anti-cavitation valves are hydraulic one-way valves and control the flow direction of oil; the two overpressure protection valves are overflow valves, and when the pressure is higher than a set value, the valves are opened to release the pressure; the two high-pressure selection valves are hydraulic one-way valves, and the two one-way valves perform high-pressure selective output from two oil paths of the pump; the modal conversion valve is a hydraulic control two-position four-way valve, is in a normal working position when receiving high-pressure oil for control, and is in a damping working position when no high-pressure oil is input.
The actuator cylinder linear displacement sensor outputs different voltage values according to different positions under excitation power supply; a hydraulic actuator cylinder, wherein a linear displacement sensor is arranged inside the hydraulic actuator cylinder and used for indicating the output working position of the actuator cylinder; the two actuating cylinder anti-cavitation valves are hydraulic one-way valves and control the flow direction of oil; the modal electromagnetic valve is a two-position three-way electromagnetic valve, and the control port is communicated with high-pressure oil when the modal electromagnetic valve is powered on, and is communicated with return oil when the modal electromagnetic valve is powered off.
The actuator is mainly used for driving the control surfaces of an aircraft elevator, an aileron and a rudder of a civil large passenger plane and a transport plane, is suitable for a actuation configuration form driven by two actuators on the same control surface together, and has larger demand for future product equipment. The invention can be used for various actuators needing to work electrically, has advanced principle scheme and is easy to realize.
Example two:
the invention also provides a three-mode electric servo actuator which is used for driving the main flight control plane on the airplane and pushing the airplane control plane to deflect so as to realize the adjustment of the flight attitude. The actuator comprises three working modes, the actuator is driven by power input on the airplane in the normal working process, and the actuator is controlled by a superior control system to realize the output action of the actuator; when the follow-up work is needed, the mode is converted into a small damping communication mode, and the actuator and another actuator on the same control surface work in a follow-up manner; when damping work is needed, the actuator is converted into a large damping communication mode, two cavities of the actuator are communicated through large damping to restrain flutter of the control surface, and the control surface is prevented from freely moving along with the aerodynamic load to influence flight safety.
The invention provides a three-mode electric servo actuator, which comprises a motor controller 1, a motor 2, a hydraulic pump 3, two pump port anti-cavitation valves 4, two overpressure protection valves 5, two pump port high-pressure selection valves 6, a mode electromagnetic valve 7, a mode change-over valve 8, a cylinder linear displacement sensor 9, a hydraulic cylinder 10, two cylinder anti-cavitation valves 11, two cylinder cavity high-pressure selection valves 12, a bypass electromagnetic valve 13, a damping switch valve 14 and an energy accumulator 15, wherein: a motor controller 1 is connected with a motor 2 through a pass cable, an output shaft of the motor is fixedly connected with an input shaft of a hydraulic pump 3, two load oil ports of the hydraulic pump are respectively connected with two oil inlets of a modal change-over valve 8 through two pipelines, and two load ports of the modal change-over valve are respectively connected with two oil pipe nozzles of a hydraulic actuating cylinder 10 through two pipelines; two load oil ports of the hydraulic pump are connected with outlets of two pump port anti-cavitation valves 4 through pipelines, two load oil ports of the hydraulic pump are connected with inlets of two overvoltage protection valves 5 through pipelines, inlets of the two pump port anti-cavitation valves are connected with an energy accumulator 15 through pipelines, and outlets of the two overvoltage protection valves are connected with the energy accumulator through pipelines; two load oil ports of the hydraulic pump are connected with inlets of two high-pressure selection valves 6 through pipelines, an oil inlet of an electromagnetic valve 7 is connected with outlets of the two high-pressure selection valves through a pipeline, an oil return port of the electromagnetic valve is connected with an energy accumulator through a pipeline, and a control port of the electromagnetic valve is connected with a hydraulic control port of a modal change-over valve through a pipeline; a bypass port of the modal changeover valve is connected with an oil inlet of the damping changeover valve 14 through a pipeline, and an oil outlet of the damping changeover valve is connected with an oil inlet pipe nozzle of the hydraulic actuating cylinder 10 through a pipeline; an oil inlet of a bypass electromagnetic valve 13 is connected with outlets of the two pump port high-pressure selection valves 6 through a pipeline, an oil return port of the bypass electromagnetic valve is connected with an inlet of an oil return back pressure valve through a pipeline, and a control port of the bypass electromagnetic valve is connected with a hydraulic control port of the damping switching valve through a pipeline; two oil pipe nozzles of the hydraulic actuating cylinder are respectively connected with oil inlets of two actuating cylinder cavity high-pressure selection valves through two pipelines; two oil nozzles of the hydraulic actuating cylinders are respectively connected with oil outlets of two actuating cylinder anti-cavitation valves 11 through two pipelines, and oil inlets of the two actuating cylinder anti-cavitation valves are connected with an energy accumulator through pipelines; the actuator cylinder linear displacement sensor 9 is arranged in the hydraulic actuator cylinder, an iron core of the actuator cylinder linear displacement sensor is fixedly connected with a piston of the actuator cylinder, and a coil of the actuator cylinder linear displacement sensor is fixedly connected with a cylinder body of the actuator cylinder.
When the actuator cylinder works normally, the modal electromagnetic valve is electrified, the modal conversion valve is in a normal working position, the motor controller receives an instruction and then controls the motor to work, and the actuator cylinder outputs the instruction; the modal electromagnetic valve is powered off, the bypass electromagnetic valve is powered on, the modal conversion valve is in a communication working position, the damping switching valve is in a small damping working position, and the actuators are in small damping communication; the modal electromagnetic valve is powered off, the bypass electromagnetic valve is powered off, the modal conversion valve is in a communication working position, the damping switching valve is in a large damping working position, and the actuator is in large damping communication; and the motor controller receives a rotor position feedback signal of the motor and outputs 3 circuits to drive the motor to rotate according to the required rotating speed.
The motor is a rare earth permanent magnet brushless direct current motor and can output and work at different speeds; the hydraulic pump is a plunger hydraulic pump capable of working in two directions; the two pump port anti-cavitation valves are hydraulic one-way valves and control the flow direction of oil; the two overpressure protection valves are overflow valves, and when the pressure is higher than a set value, the valves are opened to release the pressure; the two high-pressure selection valves are hydraulic one-way valves, and the two one-way valves perform high-pressure selective output from two oil paths of the pump; the modal electromagnetic valve is a two-position three-way electromagnetic valve, and a control port is communicated with high-pressure oil when the modal electromagnetic valve is powered on and is communicated with return oil when the modal electromagnetic valve is powered off; the modal conversion valve is a hydraulic control two-position five-way valve, and is in a normal working position when receiving high-pressure oil for control, and is in a communication working position when no high-pressure oil is input.
The actuator cylinder linear displacement sensor outputs different voltage values according to different positions under excitation power supply; a hydraulic actuator cylinder, wherein a linear displacement sensor is arranged inside the hydraulic actuator cylinder and used for indicating the output working position of the actuator cylinder; the two actuating cylinder anti-cavitation valves are hydraulic one-way valves and control the flow direction of oil.
The two actuating cylinder cavity high-pressure selection valves are hydraulic one-way valves, and the two one-way valves perform high-pressure selective output from the actuating cylinder two-cavity oil circuits; the bypass electromagnetic valve is a two-position three-way electromagnetic valve, and a control port is communicated with high-pressure oil when the bypass electromagnetic valve is powered on and is communicated with return oil when the bypass electromagnetic valve is powered off; the damping switching valve is a hydraulic control two-position two-way valve, and is used for small damping communication when receiving high-pressure oil control and large damping communication when no high-pressure oil is input; the accumulator is a spring piston type or air pressure piston type accumulator, and has a liquid level monitoring function.
The actuator is mainly used for driving the control surfaces of an aircraft elevator, an aileron and a rudder of a civil large passenger plane and a transport plane, is suitable for a actuation configuration form driven by two actuators on the same control surface together, and has larger demand for future product equipment. The invention can be used for various actuators which need to work in an electro-hydraulic mode, and the principle scheme is advanced and easy to realize.
Claims (10)
1. An electric servo actuator, comprising: the hydraulic actuator comprises a motor controller (1), a motor (2), a hydraulic pump (3), two pump port high-pressure selection valves (6), a modal electromagnetic valve (7), a modal conversion valve (8), an actuator cylinder linear displacement sensor (9), a hydraulic actuator cylinder (10) and an energy accumulator (15), wherein the two pump port high-pressure selection valves are hydraulic one-way valves, the modal electromagnetic valve is a two-position three-way electromagnetic valve, a control port is communicated with high-pressure oil when the motor controller is powered on, and is communicated with return oil when the motor controller is powered off;
the motor controller (1) is connected with the motor (2) through a cable, an output shaft of the motor is fixedly connected with an input port of the hydraulic pump (3), two load oil ports of the hydraulic pump are respectively connected with two oil inlets of the modal change-over valve (8) through two pipelines, and a first load port and a second load port of the modal change-over valve are respectively connected with a first oil pipe nozzle and a second oil pipe nozzle of the hydraulic actuating cylinder (10) through two pipelines;
two load oil ports of the hydraulic pump are connected with inlets of two pump port high-pressure selection valves (6) through pipelines, an oil inlet of a modal electromagnetic valve (7) is connected with outlets of the two pump port high-pressure selection valves through a pipeline, an oil return port of the modal electromagnetic valve is connected with an energy accumulator (15) through a pipeline, and a control port of the modal electromagnetic valve is connected with a hydraulic control port of a modal change-over valve through a pipeline;
the actuator cylinder linear displacement sensor (9) is arranged inside the hydraulic actuator cylinder, an iron core of the actuator cylinder linear displacement sensor is fixedly connected with a piston of the actuator cylinder, and a coil of the actuator cylinder linear displacement sensor is fixedly connected with a cylinder body of the actuator cylinder.
2. The actuator according to claim 1, further comprising: two pump port anti-cavitation valves (4), two actuator cylinder anti-cavitation valves (11),
the two pump port anti-cavitation valves (4) and the two actuator cylinder anti-cavitation valves (11) are hydraulic one-way valves,
two load oil ports of the hydraulic pump are connected with outlets of two pump port anti-cavitation valves (4) through pipelines, inlets of the two pump port anti-cavitation valves are connected with an energy accumulator through pipelines,
two oil nozzles of the hydraulic actuating cylinder are respectively connected with oil outlets of two anti-cavitation valves (11) through two pipelines, and oil inlets of the two anti-cavitation valves are connected with an energy accumulator through pipelines.
3. The actuator according to claim 1, further comprising: two overpressure protection valves (5),
the overpressure protection valve is an overflow valve,
two load oil ports of the hydraulic pump are connected with inlets of two overvoltage protection valves (5) through pipelines, and outlets of the two overvoltage protection valves are connected with the energy accumulator through pipelines.
4. Actuator according to claim 1, wherein the electric motor (2) is a rare earth permanent magnet brushless dc motor.
5. Actuator according to claim 1, wherein the hydraulic pump (3) is a bi-directionally operable plunger hydraulic pump.
6. Actuator according to claim 1, wherein the accumulator (15) is a spring piston or a gas piston accumulator.
7. Actuator according to claim 1, wherein the modal converter valve (8) is a 2-to-4-way valve which is hydraulically controlled and is in the normal operating position when controlled by high pressure oil and in the damping operating position when no high pressure oil is input.
8. The actuator according to any one of claims 1 to 6, further comprising: 2 actuating cylinder cavity high pressure selection valves (12), a bypass electromagnetic valve (13) and a damping switching valve (14), wherein,
the modal conversion valve (8) is a hydraulic control two-position five-way valve, is in a normal working position when receiving high-pressure oil for control, a first load port is communicated with a bypass port when no high-pressure oil is input, and a second load port is closed;
a bypass port of the modal changeover valve (8) is connected with an oil inlet of the damping changeover valve through a pipeline, and an oil outlet of the damping changeover valve is connected with a second oil pipe nozzle of the hydraulic actuating cylinder through a pipeline;
an oil inlet of a bypass electromagnetic valve (13) is connected with outlets of the two high-pressure selection valves through a pipeline, an oil return port of the bypass electromagnetic valve is connected with an inlet of an oil return back pressure valve through a pipeline, and a control port of the bypass electromagnetic valve is connected with a hydraulic control port of the damping switching valve through a pipeline;
two oil pipe mouths of the hydraulic actuating cylinder (10) are respectively connected with oil inlets of the two actuating cylinder cavity high-pressure selection valves through two pipelines.
9. Actuator according to claim 8, wherein the damping switch valve (14) is a two-position two-way valve which is hydraulically controlled, with a small damping communication when receiving a control with high pressure oil and a large damping communication when no high pressure oil is input.
10. Actuator according to claim 8, wherein the actuator chamber high pressure selector valve (12) is a hydraulic one-way valve, the bypass solenoid valve (13) is a two-position three-way solenoid valve, and the control port is connected to the high pressure oil when the valve is energized and to the return oil when the valve is de-energized.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010370554.6A CN111516858B (en) | 2020-04-30 | 2020-04-30 | Electric servo actuator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010370554.6A CN111516858B (en) | 2020-04-30 | 2020-04-30 | Electric servo actuator |
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| CN111516858A true CN111516858A (en) | 2020-08-11 |
| CN111516858B CN111516858B (en) | 2023-03-14 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112706913A (en) * | 2020-12-07 | 2021-04-27 | 沈阳飞机设计研究所扬州协同创新研究院有限公司 | Active thermal control distributed electro-hydraulic servo steering engine |
| WO2024148958A1 (en) * | 2023-01-09 | 2024-07-18 | 中国商用飞机有限责任公司 | Dual-mode hydraulic servo actuator |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH09328098A (en) * | 1996-04-10 | 1997-12-22 | Teijin Seiki Co Ltd | Control circuit for steering surface driving actuator |
| CN105523174A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator |
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2020
- 2020-04-30 CN CN202010370554.6A patent/CN111516858B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09328098A (en) * | 1996-04-10 | 1997-12-22 | Teijin Seiki Co Ltd | Control circuit for steering surface driving actuator |
| CN105523174A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Integrated control valve assembly-actuating cylinder separated hydraulic servo actuator |
Non-Patent Citations (1)
| Title |
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| 刘艺涛: "现代飞机作动系统余度设计和维修性分析", 《机床与液压》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112706913A (en) * | 2020-12-07 | 2021-04-27 | 沈阳飞机设计研究所扬州协同创新研究院有限公司 | Active thermal control distributed electro-hydraulic servo steering engine |
| CN112706913B (en) * | 2020-12-07 | 2022-03-11 | 沈阳飞机设计研究所扬州协同创新研究院有限公司 | Active thermal control distributed electro-hydraulic servo steering engine |
| WO2024148958A1 (en) * | 2023-01-09 | 2024-07-18 | 中国商用飞机有限责任公司 | Dual-mode hydraulic servo actuator |
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| Publication number | Publication date |
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| CN111516858B (en) | 2023-03-14 |
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