CN111470065A - Safety alarm device and method for airplane structural strength test - Google Patents
Safety alarm device and method for airplane structural strength test Download PDFInfo
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- CN111470065A CN111470065A CN202010366343.5A CN202010366343A CN111470065A CN 111470065 A CN111470065 A CN 111470065A CN 202010366343 A CN202010366343 A CN 202010366343A CN 111470065 A CN111470065 A CN 111470065A
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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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- G—PHYSICS
- G08—SIGNALLING
- G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
- G08B21/00—Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
- G08B21/18—Status alarms
- G08B21/24—Reminder alarms, e.g. anti-loss alarms
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- G—PHYSICS
- G08—SIGNALLING
- G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
- G08B7/00—Signalling systems according to more than one of groups G08B3/00 - G08B6/00; Personal calling systems according to more than one of groups G08B3/00 - G08B6/00
- G08B7/06—Signalling systems according to more than one of groups G08B3/00 - G08B6/00; Personal calling systems according to more than one of groups G08B3/00 - G08B6/00 using electric transmission, e.g. involving audible and visible signalling through the use of sound and light sources
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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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
- Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]
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- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Alarm Systems (AREA)
- Emergency Alarm Devices (AREA)
Abstract
The device comprises a coordinated loading control system, a PM66S chip, L ED lamps and an alarm power amplifier, wherein the coordinated loading control system can output a step signal, an overrun signal and an emergency signal, the PM66S chip is provided with four input ends, each input end is connected with the coordinated loading control system through different optical coupling isolators, the L ED lamps comprise four parts and are respectively connected with one output end of the PM66S chip, the four L ED lamps correspond to the four input ends of the PM66S chip one by one, the corresponding L ED lamps are lightened when the different input ends of the PM66S chip are triggered, the alarm power amplifier is connected with the output end of the PM66S chip, and when the test is paused or protected due to the steps, the overrun and the emergency, an alarm can be given in time to remind a worker to deal with faults in time.
Description
Technical Field
The application belongs to the technical field of airplane structural strength tests, and particularly relates to a safety alarm device and method for an airplane structural strength test.
Background
In the structural strength test of the airplane, particularly in the fatigue test, 24-hour uninterrupted operation is required, and in the operation process, the test is suspended or protected due to stepping, feedback out-of-tolerance, feedback out-of-limit, accidental emergency and the like, so that a worker is required to be on duty day and night. When the test is suspended or protected, the corresponding treatment can be carried out only after the test is found by an operator on duty, and the method consumes more manpower and material resources and has poorer intelligent degree. When the test is suspended or protected, the fault cannot be found timely due to limited energy of people, the test fault processing time is delayed, and the test operation efficiency is reduced.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a safety alarm device and a safety alarm method for an airplane structural strength test, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
the application provides an experimental safety alarm device of aircraft structural strength in a first aspect, includes:
the system comprises a coordinated loading control system, a synchronous coordinated loading control system and an event action hardware interface module, wherein the coordinated loading control system comprises a servo output module, a sensor input module, a synchronous coordinated control module and an event action hardware interface module, the servo output module is used for sending a command load to an airplane structure test piece for carrying out an airplane structure strength test, the sensor input module is used for receiving a feedback load of the airplane structure strength test, and the synchronous coordinated control module is used for outputting a step signal, an overrun signal and an emergency signal according to a preset design load, the command load and the feedback load;
the PM66S chip is provided with four input ends, each input end is connected with an event action hardware interface module of the coordinated loading control system through a different optical coupling isolator, and when the coordinated loading control system outputs different signals, the corresponding input end of the PM66S chip can be triggered through the optical coupling isolator;
l ED lamps, wherein the L ED lamps comprise four, and are respectively connected with one output end of the PM66S chip, the four L ED lamps are in one-to-one correspondence with the four input ends of the PM66S chip, and when different input ends of the PM66S chip are triggered, the corresponding L ED lamp is turned on;
and the alarm power amplifier is connected with the output end of the PM66S chip.
Optionally, the safety alarm device for the aircraft structural strength test is powered by a direct-current stabilized power supply.
Optionally, the step signal, the overrun signal, the out-of-tolerance signal, and the emergency signal output by the synchronous coordination control module according to a preset design load, the command load, and the feedback load includes:
when the difference value of the command load and the feedback load exceeds the design load, the synchronous coordination control module outputs a step signal;
when the feedback load exceeds a first safety threshold, the synchronous coordination control module outputs an overrun signal;
when the difference value of the command load and the feedback load exceeds a second safety threshold value, the synchronous coordination control module outputs an out-of-tolerance signal;
and when the coordinated loading control system automatically or actively triggers a protection signal, the synchronous coordinated control module outputs an emergency signal.
Optionally, the optical coupling isolator is a PC817 optical coupling isolator, and the optical coupling isolator includes a first optical coupling isolator, a second optical coupling isolator, a third optical coupling isolator, and a fourth optical coupling isolator.
Optionally, the PM66S chip includes four input terminals K1, K2, K3, and K4, an input terminal K1 is connected to the cooperative loading control system through the first optical coupling isolator, an input terminal K2 is connected to the cooperative loading control system through the second optical coupling isolator, an input terminal K3 is connected to the cooperative loading control system through the third optical coupling isolator, and an input terminal K4 is connected to the cooperative loading control system through the fourth optical coupling isolator.
Optionally, the L ED lamp includes L ED1, L ED2, L ED3, L ED4, the L ED1, the L ED2, the L ED3 and the L ED4 respectively displaying different colors.
Optionally, when the coordination loading control system outputs different signals, the alarm power amplifier plays different alarm prompt tones.
The second aspect of the present application provides an aircraft structural strength test safety alarm method, based on any one of the above aircraft structural strength test safety alarm devices, including:
when the coordinated loading control system outputs a step signal, the first optical coupler isolator triggers the K1 input end of a PM66S chip, a L ED1 lamp is turned on, and an alarm power amplifier plays a step alarm prompt tone;
when the coordinated loading control system outputs an out-of-tolerance signal, the second optical coupler isolator triggers the K2 input end of the PM66S chip, a L ED2 lamp is turned on, and an alarm power amplifier plays an out-of-tolerance alarm prompt tone;
when the coordinated loading control system outputs an overrun signal, the third optical coupler isolator triggers the K3 input end of a PM66S chip, a L ED3 lamp is turned on, and an alarm power amplifier plays an overrun alarm prompt tone;
when the coordinated loading control system outputs an emergency signal, the fourth optical coupler isolator triggers the K4 input end of the PM66S chip, the L ED4 lamp is turned on, and the alarm power amplifier plays an emergency alarm prompt tone.
The invention has at least the following beneficial technical effects:
according to the safety alarm device for the aircraft structural strength test, when the test is loaded, after the test is suspended or protected due to the occurrence of conditions, faults can be found in time and the operators on duty can be reminded to process the faults according to the classification of the fault types, so that the safety alarm device is simple in use of components and low in cost; the function of sounding and lighting alarm reminding is realized, and the fault finding speed is increased; the output interface of the coordinated loading control system is utilized to realize the automatic alarm function, so that the system is more intelligent; the existing coordinated loading control system is utilized to improve the test loading efficiency.
Drawings
FIG. 1 is a schematic view of an aircraft structural strength test safety warning device according to an embodiment of the present application;
FIG. 2 is a circuit diagram of an aircraft structural strength test safety warning device according to an embodiment of the present application;
fig. 3 is a control strategy diagram of a coordinated loading control system of an aircraft structural strength test safety alarm device according to an embodiment of the present application.
Wherein:
1-a first opto-isolator; 2-a second optocoupler isolator; 3-a third optocoupler isolator; 4-fourth opto-isolator.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 3.
The first aspect of the application provides an aircraft structural strength test safety alarm device which comprises a coordinated loading control system, a PM66S chip, a L ED lamp and an alarm power amplifier.
The coordinated loading control system comprises a servo output module, a sensor input module, a synchronous coordinated control module and an event action hardware interface module, wherein the servo output module is used for sending a command load to an airplane structure test piece for airplane structure strength test, the sensor input module is used for receiving a feedback load of the airplane structure strength test, the synchronous coordinated control module is used for obtaining the command load of the servo output module and the feedback load of the sensor input module and presetting a design load, finally, a control strategy is formulated according to the design load, the command load and the feedback load and step signals, overrun signals and emergency signals are output according to the control strategy, a PM66S chip is provided with four input ends, each input end is respectively connected with the event action hardware interface module of the coordinated loading control system through different optical couplers, when the coordinated loading control system outputs different signals, the input ends corresponding to PM66S chips can be triggered through the optical couplers, L ED lamps comprise four, each L ED lamp is respectively connected with one output end of a PM66S chip, the four 36S ED lamps are in one-to-one correspondence with the four input ends of the PM66 chips, when the PM 3566 is triggered by different PM L, and when the PM 3566 is connected with an alarm chip.
In one embodiment of the application, the safety alarm device for the aircraft structural strength test is powered by a direct-current stabilized power supply, and the specification of the direct-current stabilized power supply adopts DH1718E-5DC 0-35V 0-5A.
In one embodiment of the application, the accuracy of test loading is ensured through a preset design load, a command load and a feedback load of a sensor, and the coordinated loading control system can output different digital signals according to different events. In this embodiment, the control strategy of the coordinated loading control system is as follows: when the difference value of the command load and the feedback load exceeds the design load, the synchronous coordination control module outputs a step signal; when the feedback load exceeds a first safety threshold, the synchronous coordination control module outputs an overrun signal; when the difference value of the command load and the feedback load exceeds a second safety threshold value, the synchronous coordination control module outputs an out-of-tolerance signal; when the coordinated loading control system automatically or actively triggers the protection signal, the synchronous coordinated control module outputs an emergency signal. The coordinated loading control system sets different digital output signals connected to the system high through event actions, so that different digital signals trigger different alarm signals.
In an embodiment of the present application, the optical coupling isolator is a PC817 optical coupling isolator, and includes a first optical coupling isolator 1, a second optical coupling isolator 2, a third optical coupling isolator 3, and a fourth optical coupling isolator 4, and in order to drive a port for an alarm action of the cooperative loading control system, when the cooperative loading control system outputs different alarm signals, a corresponding input end of the PM66S chip can be triggered through the optical coupling isolators.
In one embodiment of the application, the PM66S chip comprises four input ends of K1, K2, K3 and K4, and respectively controls four different alarm types, in the embodiment, the L ED lamp comprises four alarm type display lamps, namely L ED1, L ED2, L ED3 and L ED4, and different optical couplers receive signals and then drive the PM66S chip to output corresponding L ED lamp signals.
Advantageously, in this embodiment, L ED1, L ED2, L ED3, and L ED4 each display different colors.
In one embodiment of the present application, the alarm power amplifier is a loudspeaker, which is specified to be L TE-1101J 24V DC, and plays different alarm tones when the device triggers different alarm types.
The second aspect of the present application provides an aircraft structural strength test safety alarm method, based on the above aircraft structural strength test safety alarm device, including:
when a stepping alarm occurs in a test, the coordinated loading control system outputs a stepping signal, the first optocoupler isolator 1 triggers the K1 input end of the PM66S chip, the L ED1 lamp is on, and the alarm power amplifier plays a stepping alarm prompt tone;
when an out-of-tolerance alarm occurs in a test, the coordinated loading control system outputs an out-of-tolerance signal, the second optical coupler isolator 2 triggers the K2 input end of the PM66S chip, a L ED2 lamp is on, and an alarm power amplifier plays an out-of-tolerance alarm prompt tone;
when the overrun alarm occurs in the test, the coordinated loading control system outputs an overrun signal, the third optical coupler isolator 3 triggers the K3 input end of the PM66S chip, the L ED3 lamp is turned on, and the alarm power amplifier plays an overrun alarm prompt tone;
when an emergency alarm occurs in a test, the coordinated loading control system outputs an emergency signal, the fourth optical coupler isolator 4 triggers the K4 input end of the PM66S chip, the L ED4 lamp is turned on, and the alarm power amplifier plays an emergency alarm prompt tone.
According to the safety alarm device and method for the aircraft structural strength test, a control circuit composed of components is connected with a coordinated loading control system, when the test normally runs, a diode in an optical coupling isolator is not electrified, and an alarm does not work; when stepping, transfinite, out of tolerance, emergency protection appear in experimental extreme point, coordinate loading control system and send corresponding alarm signal, the opto-isolator receives after the signal drive PM66S chip output and corresponds the pilot lamp signal to the corresponding alarm sound of broadcast reminds the staff in time to handle, thereby improves experimental operating efficiency.
According to the safety alarm device and method for the aircraft structural strength test, when the test is suspended or protected due to the four reasons of stepping, out-of-tolerance, out-of-limit and emergency, the alarm can be given in time, and workers are reminded to deal with faults in time. The application has the advantages that the used components are simple, and the cost is low; the function of sounding and lighting alarm reminding is realized, and the fault finding speed is increased; the output interface of the coordinated loading control system is utilized to realize the automatic alarm function, so that the system is more intelligent; the existing coordinated loading control system is utilized to improve the test loading efficiency.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides an experimental safety alarm device of aircraft structural strength which characterized in that includes:
the system comprises a coordinated loading control system, a synchronous coordinated loading control system and an event action hardware interface module, wherein the coordinated loading control system comprises a servo output module, a sensor input module, a synchronous coordinated control module and an event action hardware interface module, the servo output module is used for sending a command load to an airplane structure test piece for carrying out an airplane structure strength test, the sensor input module is used for receiving a feedback load of the airplane structure strength test, and the synchronous coordinated control module is used for outputting a step signal, an overrun signal and an emergency signal according to a preset design load, the command load and the feedback load;
the PM66S chip is provided with four input ends, each input end is connected with an event action hardware interface module of the coordinated loading control system through a different optical coupling isolator, and when the coordinated loading control system outputs different signals, the corresponding input end of the PM66S chip can be triggered through the optical coupling isolator;
l ED lamps, wherein the L ED lamps comprise four, and are respectively connected with one output end of the PM66S chip, the four L ED lamps are in one-to-one correspondence with the four input ends of the PM66S chip, and when different input ends of the PM66S chip are triggered, the corresponding L ED lamp is turned on;
and the alarm power amplifier is connected with the output end of the PM66S chip.
2. The aircraft structural strength test safety warning device of claim 1, wherein the aircraft structural strength test safety warning device is powered by a direct current stabilized power supply.
3. The aircraft structural strength test safety warning device of claim 1, wherein the synchronous coordination control module is configured to output a step signal, an overrun signal, an out-of-tolerance signal and an emergency signal according to a preset design load, the command load and the feedback load, and comprises:
when the difference value of the command load and the feedback load exceeds the design load, the synchronous coordination control module outputs a step signal;
when the feedback load exceeds a first safety threshold, the synchronous coordination control module outputs an overrun signal;
when the difference value of the command load and the feedback load exceeds a second safety threshold value, the synchronous coordination control module outputs an out-of-tolerance signal;
and when the coordinated loading control system automatically or actively triggers a protection signal, the synchronous coordinated control module outputs an emergency signal.
4. The aircraft structural strength test safety warning device of claim 3, wherein the optical coupling isolator is a PC817 optical coupling isolator, and comprises a first optical coupling isolator (1), a second optical coupling isolator (2), a third optical coupling isolator (3) and a fourth optical coupling isolator (4).
5. The aircraft structural strength test safety alarm device according to claim 4, wherein the PM66S chip comprises four input ends, namely K1, K2, K3 and K4, an input end K1 is connected with the coordinated loading control system through the first optical coupling isolator (1), an input end K2 is connected with the coordinated loading control system through the second optical coupling isolator (2), an input end K3 is connected with the coordinated loading control system through the third optical coupling isolator (3), and an input end K4 is connected with the coordinated loading control system through the fourth optical coupling isolator (4).
6. An aircraft structural strength test safety warning device according to claim 5, wherein the L ED lamps comprise L ED1, L ED2, L ED3 and L ED4, and the L ED1, the L ED2, the L ED3 and the L ED4 respectively display different colors.
7. The aircraft structural strength test safety alarm device of claim 6, wherein when the coordinated loading control system outputs different signals, the alarm power amplifier plays different alarm prompt tones.
8. An aircraft structural strength test safety alarm method based on any one of claims 1 to 7, characterized by comprising the following steps:
when the coordinated loading control system outputs a step signal, the first optocoupler isolator (1) triggers the K1 input end of a PM66S chip, a L ED1 lamp is turned on, and an alarm power amplifier plays a step alarm prompt tone;
when the coordinated loading control system outputs an out-of-tolerance signal, the second optocoupler isolator (2) triggers the K2 input end of the PM66S chip, a L ED2 lamp is turned on, and an alarm power amplifier plays an out-of-tolerance alarm prompt tone;
when the coordinated loading control system outputs an overrun signal, the third optocoupler isolator (3) triggers the K3 input end of the PM66S chip, a L ED3 lamp is turned on, and an alarm power amplifier plays an overrun alarm prompt tone;
when the coordinated loading control system outputs an emergency signal, the fourth optical coupler isolator (4) triggers the K4 input end of the PM66S chip, the L ED4 lamp is turned on, and the alarm power amplifier plays an emergency alarm prompt tone.
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| CN202010366343.5A CN111470065B (en) | 2020-04-30 | 2020-04-30 | Safety alarm device and method for aircraft structural strength test |
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| CN113252331A (en) * | 2021-05-24 | 2021-08-13 | 中国飞机强度研究所 | Safety protection method for structural strength test of airplane component |
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