CN115145140B - A logic method for ground non-hydraulic protection of servo steering gear - Google Patents
A logic method for ground non-hydraulic protection of servo steering gear Download PDFInfo
- Publication number
- CN115145140B CN115145140B CN202210642156.4A CN202210642156A CN115145140B CN 115145140 B CN115145140 B CN 115145140B CN 202210642156 A CN202210642156 A CN 202210642156A CN 115145140 B CN115145140 B CN 115145140B
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- aircraft
- servo
- ground
- steering engine
- hydraulic protection
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000005283 ground state Effects 0.000 abstract description 6
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B9/00—Safety arrangements
- G05B9/02—Safety arrangements electric
-
- 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
- B64C13/40—Transmitting means with power amplification using fluid pressure
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- General Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The application belongs to the technical field of steering engine control of an aircraft servo actuating system, and relates to a steering engine ground non-hydraulic protection logic method, wherein the steering engine ground non-hydraulic protection logic is executed by designing software connected with a steering engine, the software receives the state of an aircraft in real time, and when the aircraft is in a ground state, all hydraulic systems of the aircraft are in a non-pressure state, the absolute value of a force driving coil control instruction exceeds a certain amplitude value, and the steering engine ground non-hydraulic protection logic is executed for more than a period of time; when the aircraft is in a flight state, any hydraulic system of the aircraft is in a pressure state, the absolute value of a control instruction of a driving coil is lower than a certain amplitude, the aircraft is in a continuous time, the servo steering engine ground no-hydraulic protection module is withdrawn, the situation that the servo steering engine is dry-burned for a long time when the pressure of the hydraulic system on the aircraft is not built is avoided, the service life of a product is prolonged, and the damage of the product is avoided.
Description
Technical Field
The application belongs to the technical field of steering engine control of an aircraft servo actuation system, and particularly relates to a ground hydraulic-pressure-free protection logic method of a servo steering engine.
Background
The servo actuating system is a system for controlling the deflection angle of a control surface on an aircraft and is used for controlling the flight direction of the aircraft to finish the flight actions such as pitching, rolling, yawing and the like. The servo actuating system adopts a controller to control a servo steering engine to distribute hydraulic flow to drive an actuating cylinder to move, and the controller collects position signals of the actuating cylinder to complete control closed loop. When the hydraulic pressure in the system is not established or is lower, the steering engine works for a long time but the actuating cylinder cannot move to the instruction position of the controller, so that the steering engine is dry-burned, the service life of the product is reduced, and even the damage is possibly caused.
Therefore, how to effectively protect the steering engine without hydraulic protection and ensure the service life of the steering engine is a problem to be solved.
Disclosure of Invention
The application aims to provide a logic method without hydraulic protection on the ground of a servo steering engine, which aims to solve the problem that equipment is easy to damage the steering engine due to dry combustion of the steering engine when no hydraulic protection exists in the prior art.
The technical scheme of the application is that the ground hydraulic protection logic method for the servo steering engine comprises the following steps:
setting software connected with the steering engine, judging the state of the aircraft, and executing the steering engine ground hydraulic protection-free logic by the software when the following conditions are met:
a) The software judges that the plane is in a ground state;
b) Software judges that all hydraulic systems of the aircraft are in a non-pressure state;
c) The absolute value of the control command of the force driving coil exceeds a certain amplitude value and lasts for more than a period of time;
Judging the state of the airplane again, and when the following conditions are met, exiting the steering engine ground hydraulic protection-free logic by the software:
a) The software judges that the aircraft is in a flight state;
b) Software judges that any hydraulic system of the aircraft is in a pressure state;
c) The absolute value of the control command of the force driving coil is lower than a certain amplitude value, the absolute value of the control command of the force driving coil is longer than a certain period of time, and the servo steering engine exits from the ground hydraulic protection module.
Preferably, when the steering engine ground is not started by the hydraulic protection logic, the amplitude of the driving command of the software limiting force driving coil is a safe amplitude.
Preferably, the safety amplitude is 9.5A.
Preferably, when the servo steering engine ground is not provided with hydraulic protection logic, the absolute value of the force driving coil control command exceeds 1A and lasts for more than 90 seconds.
Preferably, when the ground exiting the servo steering engine has no hydraulic protection logic, the limitation that the amplitude of the driving command of the force driving coil is a safe amplitude is canceled.
Preferably, the absolute value of the force driving coil control command is lower than 0.5A, the duration is more than 5s, and the ground exiting servo steering engine has no hydraulic protection logic.
According to the servo steering engine ground non-hydraulic protection logic method, the steering engine ground non-hydraulic protection logic is executed through the software connected with the steering engine, the state of the aircraft is received in real time through the software, when the situation that the aircraft is in a ground state, all hydraulic systems of the aircraft are in a non-pressure state, the absolute value of a force driving coil control instruction exceeds a certain amplitude value and lasts for more than a period of time is met, the steering engine ground non-hydraulic protection logic is executed, when the aircraft is judged to be in a flight state, any hydraulic system of the aircraft is in a pressure state and the absolute value of the driving coil control instruction is lower than a certain amplitude value and lasts for a period of time, the aircraft exits from the servo steering engine ground non-hydraulic protection module, the control is simple and stable, manual operation is not needed, the system can automatically judge, the situation that the servo steering engine is dry burned for a long time when the pressure of the hydraulic system on the aircraft is not built is avoided, the service life of products is prolonged, and the products are prevented from being damaged.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic overall flow chart of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
As shown in FIG. 1, assuming that an onboard system is a dual-redundancy hydraulic system, the steering engine type direct-drive servo valve steering engine is adopted, for example, the method comprises the following steps:
step S100, setting software connected with a steering engine, judging the state of the aircraft, and executing steering engine ground hydraulic-free protection logic by the software when the following conditions are met;
The servo steering engine ground non-hydraulic protection logic method is realized by software in a controller, is used for protecting a force driving coil of a steering engine and limiting the maximum working current of the force driving coil when an airplane is in a ground state and all hydraulic systems give an alarm, and comprises the following specific logic:
a) The software judges that the plane is in a ground state;
b) Software judges that all hydraulic systems of the aircraft are in a non-pressure state, and specifically, the software judges that the first hydraulic system and the second hydraulic system of the aircraft are in a non-pressure state;
c) The absolute value of the control command of the force driving coil exceeds a certain amplitude value and lasts for more than a period of time;
Preferably, when the servo steering engine ground is not provided with hydraulic protection logic, the absolute value of the force driving coil control command exceeds 1A and lasts for more than 90 seconds.
Preferably, when the steering engine ground hydraulic protection logic is not started, the amplitude of the driving instruction of the software limiting force driving coil is a safe amplitude, and the steering engine can be effectively protected through the steering engine ground hydraulic protection logic.
Preferably, the safety amplitude is 9.5A.
Step S200, judging the state of the airplane again, and when the following conditions are met, exiting the steering engine ground hydraulic protection-free logic by the software:
a) The software judges that the aircraft is in a flight state;
b) Software judges that any one hydraulic system of the aircraft is in a pressure state, specifically, software judges that more than 1 of the first and second hydraulic systems of the aircraft is in a pressure state;
c) The absolute value of the control command of the force driving coil is lower than a certain amplitude value, the absolute value of the control command of the force driving coil is longer than a certain period of time, and the servo steering engine exits from the ground hydraulic protection module.
Preferably, when the ground exiting the servo steering engine has no hydraulic protection logic, the limit that the amplitude of the force driving coil driving command is safe amplitude of 0.5A is canceled.
Preferably, the absolute value of the force driving coil control command is lower than 0.5A, the duration is more than 5s, and the ground of the servo steering engine exits from the hydraulic protection logic.
The application executes steering engine ground non-hydraulic protection logic through designing the software connected with the steering engine, the software receives the state of the aircraft in real time, when the aircraft is in the ground state, all the hydraulic systems of the aircraft are in the non-pressure state, the absolute value of the control instruction of the force driving coil exceeds a certain amplitude value and lasts for more than a period of time, the steering engine ground non-hydraulic protection logic is executed, when the aircraft is in the flight state, any hydraulic system of the aircraft is in the pressure state and the absolute value of the control instruction of the driving coil is lower than a certain amplitude value and lasts for a period of time, the servo steering engine ground non-hydraulic protection module is exited, the control is simple and stable, manual operation is not needed, the system can automatically judge, the long-time dry burning condition of the servo steering engine is avoided when the pressure of the hydraulic system on the aircraft is not built, the service life of the product is prolonged, and the damage of the product is avoided.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210642156.4A CN115145140B (en) | 2022-06-07 | 2022-06-07 | A logic method for ground non-hydraulic protection of servo steering gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210642156.4A CN115145140B (en) | 2022-06-07 | 2022-06-07 | A logic method for ground non-hydraulic protection of servo steering gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115145140A CN115145140A (en) | 2022-10-04 |
| CN115145140B true CN115145140B (en) | 2025-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210642156.4A Active CN115145140B (en) | 2022-06-07 | 2022-06-07 | A logic method for ground non-hydraulic protection of servo steering gear |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410283A (en) * | 2011-10-19 | 2012-04-11 | 无锡市海航电液伺服系统有限公司 | Servo actuator hydraulic protection module structure |
| CN106741861A (en) * | 2016-11-29 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of bipolar direct drive valve actuator current protection strategy |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6003811A (en) * | 1997-03-24 | 1999-12-21 | The Boeing Company | Aircraft servovalve current rate limiter |
| US10093408B1 (en) * | 2014-04-24 | 2018-10-09 | Eaton Intelligent Power Limited | Supervisory control and monitoring logic for a zonal hydraulic system under normal and emergency power conditions |
| US10196131B2 (en) * | 2016-02-16 | 2019-02-05 | The Boeing Company | Hydraulic system and method for an aircraft flight control system |
| CN106741865B (en) * | 2016-11-30 | 2019-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of airplane servo actuating system hydraulic control method |
| CN111056044B (en) * | 2019-12-27 | 2022-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane control surface double-hydraulic servo system detection method |
-
2022
- 2022-06-07 CN CN202210642156.4A patent/CN115145140B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102410283A (en) * | 2011-10-19 | 2012-04-11 | 无锡市海航电液伺服系统有限公司 | Servo actuator hydraulic protection module structure |
| CN106741861A (en) * | 2016-11-29 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of bipolar direct drive valve actuator current protection strategy |
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| CN115145140A (en) | 2022-10-04 |
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