CN111056044A - Airplane control surface double-hydraulic servo system detection method - Google Patents
Airplane control surface double-hydraulic servo system detection method Download PDFInfo
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- CN111056044A CN111056044A CN201911378743.1A CN201911378743A CN111056044A CN 111056044 A CN111056044 A CN 111056044A CN 201911378743 A CN201911378743 A CN 201911378743A CN 111056044 A CN111056044 A CN 111056044A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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 application belongs to the technical field of detection of double hydraulic servo systems of airplane control surfaces, and particularly relates to a detection method of double hydraulic servo systems of airplane control surfaces, wherein an airplane engine is started, and the following steps are sequentially carried out: the method comprises the steps of zero index detection, step detection of double hydraulic systems, cutting-off detection of a first electromagnetic valve, working detection of a second hydraulic system, cutting-off detection of a second electromagnetic valve, working detection of a first hydraulic system, fault return detection, reset detection and working detection of the double hydraulic systems.
Description
Technical Field
The application belongs to the technical field of detection of double hydraulic servo systems of airplane control surfaces, and particularly relates to a detection method of double hydraulic servo systems of airplane control surfaces.
Background
The double-hydraulic servo system for the airplane control surface is used for driving the airplane control surface, is a key system related to airplane flight safety, and ensures that the double-hydraulic servo system is intact before the airplane takes off, which is an important guarantee for the airplane to safely fly.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The present application is directed to a method for detecting a dual hydraulic servo system for an aircraft control surface, which overcomes or alleviates at least one of the disadvantages of the prior art.
The technical scheme of the application is as follows:
a method for detecting a double hydraulic servo system of an airplane control surface starts an airplane engine and sequentially comprises the following steps:
zero index detection: stopping the control surface of the airplane at a zero position, and performing zero index detection on each part of the double hydraulic servo system;
step detection of the double hydraulic system: positively deflecting the control surface of the airplane, applying a step instruction, and detecting the step characteristic of the double hydraulic servo system;
a first solenoid valve cutoff detection step: cutting off the first electromagnetic valve, and detecting whether the dual-hydraulic servo actuating system works normally or not; the first electromagnetic valve is a control valve of one hydraulic system in the double-hydraulic servo actuating system, and the hydraulic system is a first hydraulic system;
and a second hydraulic system working detection step: positively deflecting the control surface of the airplane, setting a first change range slope instruction, and detecting the working condition of the double hydraulic servo systems;
a second electromagnetic valve cut-off detection step: resetting the first electromagnetic valve, cutting off the second electromagnetic valve, and detecting whether the double-hydraulic servo actuating system works normally or not; the second electromagnetic valve is a control valve of the other hydraulic system in the double-hydraulic servo actuating system, and the hydraulic system is a second hydraulic system;
the first hydraulic system work detection step: reversely deflecting the control surface of the airplane to the negative direction, setting a second change range slope instruction, and detecting the working condition of the double hydraulic servo system;
and a fault detection step: deflecting the control surface of the airplane to a return-to-center position, cutting off the first electromagnetic valve, and detecting whether the double hydraulic servo system is normal in fault return;
resetting and detecting: deflecting the control plane of the airplane to a zero instruction position, setting a zero instruction, resetting the first electromagnetic valve and the second electromagnetic valve, and detecting whether the double hydraulic servo system works normally or not;
the working detection steps of the double hydraulic systems are as follows: deflecting the control surface of the airplane, setting a slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements.
According to at least one embodiment of the present application, in the second hydraulic system operation detection step, the first variation range ramp command is a 40% to 90% ramp command.
According to at least one embodiment of the present application, in the first hydraulic system operation detection step, the second variation range slope command is a 90% to-90% slope command.
According to at least one embodiment of the application, when the double-hydraulic-system work detection step is carried out, the following steps are carried out in sequence:
detecting the positive maximum deflection work of the double hydraulic systems: deflecting the control surface of the airplane to the maximum forward position, setting a slope instruction of a third variation range, and detecting whether the characteristics of the control surface of the airplane meet the design requirements;
detecting the negative maximum deflection work of the double hydraulic systems: deflecting the control surface of the airplane to a negative direction maximum position, setting a fourth change range slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements;
detecting the zero instruction position work of the double hydraulic systems: and deflecting the control surface of the airplane to a zero instruction position, setting a 0% instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements.
According to at least one embodiment of the present application, in the step of detecting the forward maximum deflection work of the dual hydraulic system, the third variation range ramp command is a 0% to 100% ramp command.
According to at least one embodiment of the present application, in the double-hydraulic-system negative-direction maximum-deflection work detection step, the fourth variation range ramp command is a 100% to-100% ramp command.
Drawings
FIG. 1 is a flow chart of a method for detecting a double hydraulic servo system of an aircraft control surface according to an embodiment of the application;
FIG. 2 is a schematic diagram of a change in a deflection position of an aircraft control surface in a method for detecting a dual hydraulic servo system of the aircraft control surface according to an embodiment of the application;
FIG. 3 is a diagram illustrating a first range-of-change ramp instruction provided by an embodiment of the present application;
FIG. 4 is a diagram illustrating a second range-of-change ramp instruction provided by an embodiment of the present application;
FIG. 5 is a diagram illustrating a third range ramp instruction according to an embodiment of the present application;
FIG. 6 is a diagram illustrating a fourth range ramp instruction provided in accordance with an embodiment of the present application;
wherein:
1-zero index detection; 2-double hydraulic system transition detection; 3-a first electromagnetic valve cut-off detection step; 4-detecting the work of the second hydraulic system; 5-a second electromagnetic valve cutting detection step; 6-detecting the work of the first hydraulic system; 7-detecting the fault during the return process; 8-resetting the detection step; 9-detecting the forward maximum deflection work of the double hydraulic systems; 10-detecting the negative maximum deflection work of the double hydraulic systems; 11-detecting the zero-instruction position work of the double hydraulic systems.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 6.
A method for detecting a double hydraulic servo system of an airplane control surface starts an airplane engine and sequentially comprises the following steps:
zero index detection: stopping the control surface of the airplane at a zero position, and performing zero index detection on each part of the double hydraulic servo system;
step detection of the double hydraulic system: the method comprises the steps that an airplane control surface is deflected in a forward direction, namely the airplane control surface is deflected to a certain position in the forward direction from a zero position, a step instruction is applied, and the step characteristic of a double-hydraulic servo system is detected;
a first solenoid valve cutoff detection step: cutting off the first electromagnetic valve, and detecting whether the dual-hydraulic servo actuating system works normally or not; the first electromagnetic valve is a control valve of one hydraulic system in the double-hydraulic servo actuating system, and the hydraulic system is a first hydraulic system; the first hydraulic system is cut off by cutting off the first electromagnetic valve.
And a second hydraulic system working detection step: the method comprises the steps that an airplane control surface is deflected forwards, namely the airplane control surface is continuously deflected to another forward position on the basis of the forward position, a first change range slope instruction is set, and the working condition of a double-hydraulic servo system is detected, namely the working condition of the double-hydraulic servo system under the condition that a first hydraulic system is cut off is detected;
a second electromagnetic valve cut-off detection step: resetting the first electromagnetic valve, cutting off the second electromagnetic valve, and detecting whether the double-hydraulic servo actuating system works normally or not; the second electromagnetic valve is a control valve of the other hydraulic system in the double-hydraulic servo actuating system, and the hydraulic system is a second hydraulic system; the pressure supply of a hydraulic system, namely the pressure supply of only the first hydraulic system of the double-hydraulic servo actuating system at the moment, detect the double-hydraulic servo actuating system works normally, namely detect the double-hydraulic servo actuating system works normally under the condition of only the first hydraulic system supplying pressure;
the first hydraulic system work detection step: the method comprises the steps that an airplane control surface is reversely deflected to the negative direction, namely the airplane control surface is deflected to a certain position from the positive direction position to the negative direction, a second change range slope instruction is set, the working condition of the double-hydraulic servo system is detected, the second electromagnetic valve is cut off at the moment, the double-hydraulic servo actuating system only supplies pressure to a first hydraulic system, and the working condition of the double-hydraulic servo system is detected, namely the working condition of the double-hydraulic servo actuating system under the condition that only the first hydraulic system supplies pressure is detected;
and a fault detection step: the method comprises the steps of deflecting the control plane of the airplane to a centering position, namely deflecting the control plane of the airplane from a negative position to a centering position, cutting off a first electromagnetic valve, and detecting whether the centering of the double-hydraulic servo system is normal or not;
resetting and detecting: the method comprises the steps of deflecting the control plane of the airplane to a zero instruction position, namely deflecting the control plane of the airplane to the zero instruction position from a return-to-middle position, setting a zero instruction, resetting a first electromagnetic valve and a second electromagnetic valve, namely returning the first hydraulic system and the second hydraulic system to supply pressure, and detecting whether a double-hydraulic servo system works normally or not;
the working detection steps of the double hydraulic systems are as follows: deflecting the control surface of the airplane, setting a slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements.
For the method for detecting the double hydraulic servo systems of the control surfaces of the airplane disclosed in the embodiment, a person skilled in the art can understand that the steps of the method for detecting the double hydraulic servo systems of the control surfaces of the airplane are sequentially performed before the airplane flies after the engine is started, and the main functions of the double hydraulic servo systems can be quickly and effectively detected once before the airplane flies according to the method for detecting the double hydraulic servo systems of the control surfaces of the airplane, so that the completeness of the double hydraulic servo systems can be actually judged, and corresponding measures can be taken timely to ensure the safe flight of the airplane.
For the method for detecting the dual hydraulic servo system of the control surface of the aircraft disclosed in the above embodiments, it can be further understood by those skilled in the art that please additionally explain why the method is not fast and effective
In some optional embodiments, in the second hydraulic system operation detection step, the first variation range ramp command is a 40% to 90% ramp command, and one is more specifically shown in fig. 3.
In some alternative embodiments, the second range of variation ramp command is a 90% to-90% ramp command in the first hydraulic system operation detection step, and is more particularly shown in fig. 4.
In some optional embodiments, when the double-hydraulic-system work detection step is performed, the following steps are sequentially performed:
detecting the positive maximum deflection work of the double hydraulic systems: deflecting the control surface of the airplane to a forward direction maximum position, namely deflecting the control surface of the airplane from a zero instruction position to the forward direction maximum position, setting a third change range slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements;
detecting the negative maximum deflection work of the double hydraulic systems: deflecting the control surface of the airplane to a negative direction maximum position, namely deflecting the control surface of the airplane from the positive direction maximum position to the negative direction maximum position, setting a fourth change range slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements;
detecting the zero instruction position work of the double hydraulic systems: and (3) deflecting the control surface of the airplane to a zero instruction position, namely deflecting the control surface of the airplane from a negative direction maximum position to a zero instruction position, setting a 0V instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements.
In some alternative embodiments, in the step of detecting the forward maximum deflection operation of the dual hydraulic system, the third variation range ramp command is a 0% to 100% ramp command, and a more specific embodiment is shown in fig. 5.
In some alternative embodiments, the dual hydraulic system negative-going maximum deflection work detection step has a fourth range ramp command of between 100% and-100% ramp command, as shown more particularly in fig. 6.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (6)
1. The method for detecting the double hydraulic servo systems of the control surfaces of the airplane is characterized in that an airplane engine is started, and the following steps are sequentially carried out:
zero index detection: stopping the control surface of the airplane at a zero position, and performing zero index detection on each part of the double hydraulic servo system;
step detection of the double hydraulic system: positively deflecting the control surface of the airplane, applying a step instruction, and detecting the step characteristic of the double hydraulic servo system;
a first solenoid valve cutoff detection step: cutting off the first electromagnetic valve, and detecting whether the dual-hydraulic servo actuating system works normally or not; the first electromagnetic valve is a control valve of one hydraulic system in the double-hydraulic servo actuating system, and the hydraulic system is a first hydraulic system;
and a second hydraulic system working detection step: positively deflecting the control surface of the airplane, setting a first change range slope instruction, and detecting the working condition of the double hydraulic servo systems;
a second electromagnetic valve cut-off detection step: resetting the first electromagnetic valve, cutting off the second electromagnetic valve, and detecting whether the double-hydraulic servo actuating system works normally or not; the second electromagnetic valve is a control valve of the other hydraulic system in the double-hydraulic servo actuating system, and the hydraulic system is a second hydraulic system;
the first hydraulic system work detection step: reversely deflecting the control surface of the airplane to the negative direction, setting a second change range slope instruction, and detecting the working condition of the double hydraulic servo system;
and a fault detection step: deflecting the control surface of the airplane to a return-to-center position, cutting off the first electromagnetic valve, and detecting whether the double hydraulic servo system is normal in fault return;
resetting and detecting: deflecting the control plane of the airplane to a zero instruction position, setting a zero instruction, resetting the first electromagnetic valve and the second electromagnetic valve, and detecting whether the double hydraulic servo system works normally or not;
the working detection steps of the double hydraulic systems are as follows: deflecting the control surface of the airplane, setting a slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements.
2. The aircraft control surface dual hydraulic servo system detection method according to claim 1,
in the second hydraulic system work detection step, the first change range slope command is a 40% -90% slope command.
3. The aircraft control surface dual hydraulic servo system detection method according to claim 1,
in the step of detecting the work of the first hydraulic system, the second change range slope command is a 90% -to-90% slope command.
4. The aircraft control surface dual hydraulic servo system detection method according to claim 1,
when the working detection steps of the double hydraulic systems are carried out, the following steps are carried out in sequence:
detecting the positive maximum deflection work of the double hydraulic systems: deflecting the control surface of the airplane to the maximum forward position, setting a slope instruction of a third variation range, and detecting whether the characteristics of the control surface of the airplane meet the design requirements;
detecting the negative maximum deflection work of the double hydraulic systems: deflecting the control surface of the airplane to a negative direction maximum position, setting a fourth change range slope instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements;
detecting the zero instruction position work of the double hydraulic systems: and deflecting the control surface of the airplane to a zero instruction position, setting a 0% instruction, and detecting whether the characteristics of the control surface of the airplane meet the design requirements.
5. The aircraft control surface dual hydraulic servo system detection method according to claim 4,
in the step of detecting the forward maximum deflection work of the double hydraulic systems, the slope command of the third change range is a 0% -100% slope command.
6. The aircraft control surface dual hydraulic servo system detection method according to claim 4,
in the step of detecting the negative maximum deflection work of the double hydraulic systems, the slope command of the fourth change range is a slope command of 100% -100%.
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