CN114148543B - Detection method of special maintenance detector for aircraft pneumatic actuator - Google Patents
Detection method of special maintenance detector for aircraft pneumatic actuator Download PDFInfo
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- CN114148543B CN114148543B CN202111275074.2A CN202111275074A CN114148543B CN 114148543 B CN114148543 B CN 114148543B CN 202111275074 A CN202111275074 A CN 202111275074A CN 114148543 B CN114148543 B CN 114148543B
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- 238000012423 maintenance Methods 0.000 title claims abstract description 27
- 238000001514 detection method Methods 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 10
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 230000001012 protector Effects 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 238000007689 inspection Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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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
-
- 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
- B64F5/40—Maintaining or repairing aircraft
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Abstract
The invention relates to the technical field of aircraft maintenance equipment, and discloses a special maintenance detector for an aircraft pneumatic actuator and a detection method thereof, wherein the special maintenance detector comprises the following steps: an energy supply device for supplying energy to an electric motor of the aircraft; the air source device is used for providing high-pressure air for an actuator of the aircraft; the control center is used for sending a starting and stopping instruction to the energy supply device, the air source device and an electromagnetic valve or a brake relay of an actuator of the aircraft; the control panel is used for judging whether a feedback signal is received or not; and the detection result is obtained according to whether the feedback signal is received or not. The invention has the following advantages and effects: according to the method, the energy supply device and the air source device are respectively connected, then the operation of the actuator is controlled by the control center according to the checking flow, and the damage condition of the actuator is judged according to the actual operation condition of the actuator and the state display of the control panel, so that the aim of detection can be achieved.
Description
Technical Field
The application relates to the technical field of aircraft maintenance equipment, in particular to a special maintenance detector for an aircraft pneumatic actuator and a detection method thereof.
Background
The actuator is an electro-pneumatic device, when the actuator fails, the aircraft does not have maintenance conditions, and when the aircraft is overhauled, the system controlled by the aircraft is separated, if a special driving detection instrument is not provided, the failure phenomenon of the actuator is difficult to reproduce, and the actuator is difficult to be driven in real time to perform failure analysis and function test after repair; the prior driving device for overhauling has the advantages of simple structure, single function, time and labor waste in detection, no protection, easy expansion of faults when the actuator is driven in a fault state, and easy occurrence of safety accidents.
Disclosure of Invention
Aiming at the defects in the prior art, the purpose of the application is to provide a special maintenance detector for an aircraft pneumatic actuator and a detection method thereof, which can rapidly and accurately judge the fault position of the aircraft pneumatic actuator.
In order to achieve the above purpose, on one hand, the technical scheme adopted is as follows:
the application provides a special detector of aircraft pneumatic actuator, include:
an energy supply device for supplying energy to an electric motor of the aircraft;
the air source device is used for providing high-pressure air for an actuator of the aircraft;
the control center is used for sending a starting and stopping instruction to the energy supply device, the air source device and an electromagnetic valve or a brake relay of an actuator of the aircraft;
the control panel is used for judging whether feedback signals of the motor and the motor limiting device of the aircraft are received after the energy supply device is started; judging whether a feedback signal of an electromagnetic valve of the actuator is received after the air source device is started; and after the brake relay is closed, whether a feedback signal is received or not; and the detection result is obtained according to whether the feedback signal is received or not.
Preferably, the motor is divided into a direct current motor and an alternating current motor;
the energy supply device comprises:
an intermediate frequency ac power supply for powering the ac motor;
a dc power supply for powering the dc motor.
Preferably, the power supply device further includes:
the interlocking protector is arranged between the medium-frequency alternating current power supply and the alternating current motor and between the direct current power supply and the direct current motor and is used for providing positive and negative rotation interlocking protection for the alternating current motor; .
And the power frequency alternating current power supply is used for supplying power to the interlocking protector.
Preferably, the integrated protector is arranged between the energy supply device and the motor, and is used for disconnecting the energy supply device from the motor when in overheat, overvoltage and overcurrent, and simultaneously providing time-limited quick-break protection.
Preferably, the control panel is further provided with a plurality of indicator lamps for indicating whether feedback signals of the motor, the motor limiting device, the electromagnetic valve of the actuator and the brake relay are received.
The application also provides a detection method of the special maintenance detector applied to the pneumatic actuator of the airplane, which comprises the following steps:
s1, connecting an energy supply device, an air source device, a control center and a control panel with corresponding equipment on an aircraft in a stop state, wherein the control panel receives a brake signal;
s2, the control center sends a closing instruction to the brake relay, and if the control panel does not receive a feedback signal, the brake relay is normal;
s3, starting the motor after the brake relay receives the closing instruction, judging whether the control panel receives a feedback signal of the motor limiting device in a first preset time period after receiving the motor feedback signal, and if so, enabling the brake relay to be normal;
s4, the control center sends signals to the actuator, and when the control panel receives feedback signals of the electromagnetic valve of the actuator and the actuator acts and stops within a second preset time, the actuator is normal.
Preferably, the step S1 includes:
s11, after the corresponding equipment is connected, the control panel judges whether a feedback signal of the brake relay is received, if yes, S2 is entered, and if not, a brake fault is prompted;
the step S2 further includes:
s21, after the control center sends a brake releasing instruction to the brake relay, the control panel judges whether a feedback signal for releasing the brake relay is received, if yes, the step S3 is entered, and if not, a brake fault is prompted.
Preferably, the step S3 is preceded by the following steps:
s31, after the brake relay starts the motor, the control panel judges whether a feedback signal of the motor is received, if no feedback signal exists, the motor is prompted to fail, and otherwise, the step S3 is carried out.
Preferably, the step S3 further includes:
s32, after the motor limiting device sends a signal to the control panel, the control panel judges whether a feedback signal of the brake relay is received, if yes, the step S33 is entered, and if not, a brake fault is prompted;
s33, after the brake relay signal is observed, counting a third preset time, observing whether the motor is stopped, if yes, entering a step S4, otherwise, prompting brake failure.
Preferably, the step S4 further includes the following steps:
s41, the control center sends a signal to the electromagnetic valve of the actuator, whether the output shaft of the actuator acts or not is observed, if yes, step S42 is carried out, and if not, the electromagnetic valve of the actuator is prompted to be damaged;
s42, counting a second preset time, observing whether the actuator stops acting within the second preset time, and prompting that the internal gas circuit is abnormal if the actuator does not stop acting.
The beneficial effects that technical scheme that this application provided brought include:
the special maintenance detector for the pneumatic actuator of the aircraft links the special maintenance detector to the actuator through the plug, and is respectively connected with the energy supply device and the air source device, then the actuator is operated through the control center according to the inspection flow, and the damage condition of the actuator is judged according to the actual operation condition of the actuator and the state display of the control panel, so that the detection purpose can be achieved.
According to the special maintenance detection method for the pneumatic actuator of the aircraft, the problem of driving control of the actuator after the pneumatic actuator is separated from the aircraft control system after the aircraft pneumatic actuator is stopped can be effectively solved, safety accidents caused by mistakenly touching the aircraft control system when the actuator is detected are avoided, expansion of faults of the actuator is effectively prevented, convenience is provided for fault maintenance of the actuator, maintenance time is saved, and maintenance cost is saved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of one embodiment of a method for dedicated repair detection of an aircraft pneumatic actuator of the present application.
Fig. 2 is a schematic flow chart of step S1 of another embodiment of a method for detecting dedicated maintenance of an aircraft pneumatic actuator in the present application.
FIG. 3 is a flow chart of step S2 of another embodiment of a method for dedicated maintenance inspection of an aircraft pneumatic actuator of the present application.
Fig. 4 is a schematic flow chart of step S3 of another embodiment of a method for detecting dedicated maintenance of an aircraft pneumatic actuator in the present application.
Fig. 5 is a schematic flow chart of step S4 of another embodiment of a method for detecting dedicated maintenance of an aircraft pneumatic actuator in the present application.
FIG. 6 is a circuit diagram of the connection of the medium frequency AC power source to the AC motor in one embodiment of the dedicated maintenance detector for the pneumatic actuator of the aircraft of the present application.
FIG. 7 is a circuit diagram of the connection of the power frequency AC power source to the AC motor for forward and reverse rotation control and interlock protection in one embodiment of the dedicated maintenance detector for the aircraft pneumatic actuator of the present application.
FIG. 8 is a circuit diagram of the connection of the DC power supply to the DC motor for forward and reverse rotation control and interlock protection in one embodiment of the dedicated maintenance detector for an aircraft pneumatic actuator of the present application.
FIG. 9 is a schematic diagram of a control center in one embodiment of a dedicated service detector for an aircraft pneumatic actuator in the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present invention will be further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The application provides an embodiment of a special detector for an aircraft pneumatic actuator, which comprises an energy supply device, an air source device, a control center and a control panel.
The energy supply device is used for supplying energy to the motor of the aircraft, in some embodiments, a storage battery with an inverter, in other embodiments, a connection circuit for connecting with a power grid is also used, generally, after the motor of the aircraft receives energy supply, the motor of the aircraft supplies energy to other mechanisms through an internal circuit or a mechanical structure of the aircraft so as to drive other components in the aircraft to operate, and only the motor of the aircraft needs to be supplied with energy.
The air source device is generally a pressure-adjustable air bottle, and in some embodiments, the air source device is an air pipe device used for connecting a high-pressure pipeline of the overhaul station and used for driving the actuator to operate, so that a supercharging device of the aircraft is not required to be started, and the fault range of the aircraft is prevented from being enlarged.
The control center is connected with various components of the aircraft actuator through signals as shown in fig. 8, so that the start of an aircraft control system is avoided, and misoperation is prevented. In some embodiments, the control can be performed by means of the circuit of the control device of the aircraft itself, and in other embodiments, the control can also be performed directly by connecting the control device to an energy supply device, an air source device, an electromagnetic valve of an actuator of the aircraft or a brake relay through a plug.
The control panel is integrated on one device in a general embodiment and the control center, and is mainly used for receiving feedback signals of whether the motor and the motor limiting device, the actuator electromagnetic valve and the brake electromagnetic valve of the airplane are started or not, and an operator can analyze according to the display condition of the control panel to quickly obtain the fault position.
In some types, in order to improve the safety of the actuator, a main system and an auxiliary system are generally provided for supplying power, the main system is driven by an ac motor, the auxiliary system is supplied by a dc motor, and a fault may occur in any one system, so that detection under any one system is also necessary.
Thus in some preferred embodiments, as shown in figures 5 and 7, the motor is divided into a dc motor and an ac motor, and the power supply means is divided into an intermediate frequency ac power supply for supplying power to the ac motor and a dc power supply for supplying power to the dc motor. Specifically, when the embodiment is applied to a pneumatic actuator for controlling the extension and retraction of a wing leading edge flap on a boeing B747 aircraft, the parameters of the intermediate frequency ac power supply are 110V 400hz, and the voltage of the dc power supply is 24V.
Further, as shown in fig. 5 and 6, in order to protect the ac motor, an interlock protector and a power frequency ac power supply for supplying power to the interlock protector are further provided in the power supply device of the present application. The interlocking protector is arranged between the motor and the energy supply device, provides interlocking protection, and avoids power supply short circuit caused by misoperation. The interlocking protector has two forms of hardware protection and software protection, wherein the hardware protection is divided into two paths, and one path is arranged between the medium-frequency alternating-current power supply and the alternating-current motor and is used for providing positive and negative rotation interlocking protection of the alternating-current motor; the other path is arranged between the direct current power supply and the direct current motor and used for providing positive and negative rotation interlocking protection of the direct current motor. And the interlocking protection between the alternating current motor and the direct current motor is realized by software.
In some cases, if the motor is over-pressurized, overheated, etc., damage is easily generated, and thus, an integrated protector is provided to detect the operation state of the motor, and the power supply device is disconnected from the motor when the motor is over-pressurized, over-flowed, and overheated, preventing the motor from being damaged, and also providing time-limited quick-break protection.
The control panel is also provided with a plurality of indicator lamps which are used for indicating whether the control panel receives feedback signals of the motor, the motor limiting device, the electromagnetic valve of the actuator and the brake relay, and a user can intuitively observe whether corresponding signals are received or not through the on-off change of the lamps.
The application also provides a detection method of the special maintenance detector applied to the pneumatic actuator of the airplane, as shown in fig. 1, comprising the following steps:
s1, connecting an energy supply device, an air source device, a control center and a control panel with corresponding equipment on an aircraft in a stop state, and receiving a brake signal by the control panel. Specifically, after the corresponding device is connected, whether the control panel receives a feedback signal of the brake relay is judged, if yes, S2 is entered, and if not, a brake fault is prompted.
S2, the control center sends a closing instruction to the brake relay, and if no feedback signal is received, the brake relay is normal.
In a further embodiment, as shown in fig. 2, the present step further includes the following steps:
s21, after the control center sends a brake releasing instruction to the brake relay, observing whether the control panel receives a brake relay releasing signal, if yes, entering a step S3, otherwise, prompting a brake fault.
S3, starting the motor by the brake relay, after receiving a motor feedback signal, observing whether the control panel receives a motor limiting device signal in a first preset time period, and if so, enabling the brake relay to be normal.
In a further embodiment, as shown in fig. 3, the present step further includes the following steps:
s31, after the brake relay starts the motor, observing whether the control panel receives a feedback signal of the motor, if not, prompting the motor to be faulty, otherwise, entering step S3.
S32, after the motor limiting device sends a signal to the control panel, observing whether the control panel receives a feedback signal of the brake relay, if yes, entering a step S33, otherwise, prompting a brake fault;
s33, after the brake relay signal is observed, counting a third preset time, observing whether the motor is stopped, if yes, entering a step S4, otherwise, prompting brake failure.
S4, the control center sends a signal to the actuator, whether the actuator acts or not is observed, and the actuator stops acting within a second preset time, and if the actuator acts after sending the signal and stops acting within the second preset time, the actuator is normal.
In a further embodiment, as shown in fig. 4, the present step further includes the following steps:
s41, the control center sends a signal to the electromagnetic valve of the actuator, whether the output shaft of the actuator acts or not is observed, if yes, step S42 is carried out, and if not, the electromagnetic valve of the actuator is prompted to be damaged;
s42, counting a second preset time, observing whether the actuator stops acting within the second preset time, and prompting that the internal gas circuit is abnormal if the actuator does not stop acting.
The application also provides a special maintenance detection method embodiment of the aircraft pneumatic actuator combined with the special maintenance detector embodiment of the aircraft pneumatic actuator, which is applied to the pneumatic actuator for controlling the wing leading edge flap to stretch and retract on the detected boeing B747 aircraft, and in the embodiment, whether the control panel receives a corresponding feedback signal is indicated by the on-off of an indicator light corresponding to the equipment, and the embodiment comprises the following steps:
the energy supply device, the air source device, the control center and the control panel are connected with corresponding equipment on the aircraft in a stop state, at this time, because the aircraft is in a normal braking state when in stop, a brake indicator lamp on the control panel should be lightened to indicate that a brake relay is in a working state, and if the brake relay is not lightened, a brake fault is indicated;
the control center of staff control sends a signal for releasing the brake to the brake relay, the brake relay releases the brake and sends two paths of signals, one path of signals is sent to the control panel and is represented as the brake indicator light is turned off, if the brake indicator light is not turned off, the brake fault is indicated, and the other path of signals is sent to the motor for starting the motor;
after the motor receives the starting signal of the brake relay, the motor is started and fed back to the control panel, the motor indicator lamp is turned on, if the motor indicator lamp is not turned on, the motor is indicated to be faulty, after the motor is started, in order to prevent the motor from stalling, the motor can automatically start the limiting device of the motor, the signal of the motor limiting device is received in a first preset time period, the first preset time period is carried out according to the signal of the airplane, the first preset time period is set to 15-20S in the embodiment, the motor indicator lamp is turned off, the motor limiting device indicator lamp is turned on, the brake indicator lamp is turned on, the parking lamp on the airplane control system is turned on, if the motor indicator lamp is not turned on, the motor is indicated to be faulty, if the motor limiting device indicator lamp is not turned on, the motor is indicated to be faulty, and if the brake indicator lamp is not turned on, the brake fault is indicated. If the motor limiting device is normal, the brake indicator light should be turned on and the motor indicator light should be turned off within a third preset time, otherwise, a brake failure is indicated, and the third preset time is set to be 1S in this embodiment.
After the brake indicator lights are turned on, the control center automatically sends out an instruction for starting the actuator, the electromagnetic valve of the actuator releases isolation of the air channel, the indicator lights of the electromagnetic valve of the actuator should be turned on, and otherwise, the electromagnetic valve of the actuator is indicated to be faulty. And then the actuator acts, the actuator acts very obviously, most positions in the overhaul field can be clearly observed, and when the electromagnetic valve indicator lamp of the actuator is on and the actuator does not act, the internal gas circuit of the actuator is prompted to fail.
The pneumatic actuator of the aircraft is internally provided with a certain structure for preventing the actuator from idling, so that the actuator should stop operating within a second preset time, and if the actuator does not stop within the second preset time, the control air path inside the actuator is indicated to have faults. The second preset time is set to 40S according to the model in the present embodiment.
In this embodiment, the first preset time period, the second preset time period and the third preset time period can all be timed through the control panel, so that the staff can check conveniently.
The present application is not limited to the above-described embodiments, and it will be apparent to those skilled in the art that modifications and variations can be made without departing from the principles of the present invention, and such modifications and variations are also considered to be within the scope of the present invention.
Claims (5)
1. The detection method of the special maintenance detector of the pneumatic actuator of the aircraft comprises an energy supply device, an air source device, a control center and a control panel, wherein the energy supply device is used for supplying energy to a motor of the aircraft; the air source device is used for providing high-pressure air for the actuator of the aircraft; the control center is used for sending a starting and stopping instruction to the energy supply device, the air source device and an electromagnetic valve or a brake relay of an actuator of the aircraft; the control panel is used for judging whether feedback signals of a motor and a motor limiting device of the aircraft are received after the energy supply device is started; judging whether a feedback signal of an electromagnetic valve of the actuator is received after the air source device is started; and after the brake relay is closed, whether a feedback signal is received or not; the detection result is obtained according to whether the feedback signal is received or not; the detection method is characterized by comprising the following steps of:
s1, connecting an energy supply device, an air source device, a control center and a control panel with corresponding equipment on an aircraft in a stop state, wherein the control panel receives a brake signal;
s2, the control center sends a closing instruction to the brake relay, and if the control panel does not receive a feedback signal, the brake relay is normal;
s3, starting the motor after the brake relay receives the closing instruction, judging whether the control panel receives a feedback signal of the motor limiting device in a first preset time period after receiving the motor feedback signal, and if so, enabling the brake relay to be normal;
s4, the control center sends a signal to the actuator, and when the control panel receives a feedback signal of the electromagnetic valve of the actuator and the actuator acts and stops within a second preset time, the actuator is normal.
2. The method according to claim 1, wherein the step S1 comprises:
s11, after the corresponding equipment is connected, the control panel judges whether a feedback signal of the brake relay is received, if yes, S2 is entered, and if not, a brake fault is prompted;
the step S2 further includes:
s21, after the control center sends a brake releasing instruction to the brake relay, the control panel judges whether a feedback signal for releasing the brake relay is received, if yes, the step S3 is entered, and if not, a brake fault is prompted.
3. The method according to claim 1, wherein said step S3 is preceded by the steps of:
s31, after the brake relay starts the motor, the control panel judges whether a feedback signal of the motor is received, if no feedback signal exists, the motor is prompted to fail, and otherwise, the step S3 is carried out.
4. The method according to claim 1, wherein the step S3 further comprises:
s32, after the motor limiting device sends a signal to the control panel, the control panel judges whether a feedback signal of the brake relay is received, if yes, the step S33 is entered, and if not, a brake fault is prompted;
s33, after the brake relay signal is observed, counting a third preset time, observing whether the motor is stopped, if yes, entering a step S4, otherwise, prompting brake failure.
5. The method according to claim 1, wherein the step S4 further comprises the steps of:
s41, the control center sends a signal to the electromagnetic valve of the actuator, whether the output shaft of the actuator acts or not is observed, if yes, step S42 is carried out, and if not, the electromagnetic valve of the actuator is prompted to be damaged;
s42, counting a second preset time, observing whether the actuator stops acting within the second preset time, and prompting that the internal gas circuit is abnormal if the actuator does not stop acting.
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| CN202111275074.2A CN114148543B (en) | 2021-10-29 | 2021-10-29 | Detection method of special maintenance detector for aircraft pneumatic actuator |
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