CN209956248U - Civil aircraft running state monitoring system - Google Patents
Civil aircraft running state monitoring system Download PDFInfo
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- CN209956248U CN209956248U CN201920721852.8U CN201920721852U CN209956248U CN 209956248 U CN209956248 U CN 209956248U CN 201920721852 U CN201920721852 U CN 201920721852U CN 209956248 U CN209956248 U CN 209956248U
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Abstract
The utility model discloses a civil aircraft running state monitoring system, concretely relates to civil aircraft field, including PLC controller and PC, PLC controller link is equipped with first sensor module, PLC controller link is equipped with second sensor module, PLC controller link is equipped with GPRS, the PC link is equipped with switch module, the switch module link is equipped with alarm indication module. The utility model discloses a divide into aircraft itself and external environment factor with measured data and classify, when appearing unusually, then the very first time is known to be the inside trouble of aircraft, still external environment's effect to quick location problem formulates the solution, and the monitoring to external environment simultaneously can play the effect of early warning, so that at any time according to the operation of external environment factor adjustment aircraft, has improved the security of aircraft operation.
Description
Technical Field
The utility model relates to a civil aircraft technical field, more specifically say, the utility model relates to a civil aircraft running state monitoring system.
Background
The aircraft is an apparatus flying in the atmosphere or the space (space) outside the atmosphere, and the aircraft is divided into 3 types: the aircraft flying in the atmosphere, such as balloons, airships, airplanes and the like, fly by the static buoyancy of air or the aerodynamic force generated by the relative motion of air, and fly in space, such as artificial earth satellites, manned spaceships, space detectors, space airplanes and the like, obtain the necessary speed to enter the space under the driving of a carrier rocket, then do orbital motion similar to the celestial body by means of inertia, and are apparatus flyers which are manufactured by human beings, can fly off the ground, fly in the space and are controlled by the human beings to fly in the atmosphere or out of the atmosphere (space).
Civil aircrafts are generally referred to as civil airplanes, and the aircrafts are mainly safe, so that the operation state of the aircrafts needs to be monitored when the aircrafts operate.
The monitoring system in the prior art has certain defects, for example, the monitoring results are not well classified, so that better classification alarm and early warning cannot be realized.
SUMMERY OF THE UTILITY MODEL
In order to overcome prior art's above-mentioned defect, the embodiment of the utility model provides a civil aircraft running state monitoring system, classify through dividing into aircraft itself and external environment factor with measured data, when appearing unusually, then the very first time is known to the inside trouble of aircraft, still external environment's effect, thereby quick location problem, formulate the solution, simultaneously to external environment's monitoring, can play the effect of early warning simultaneously, so that adjust the operation of aircraft according to external environment factor at any time, the security of aircraft operation has been improved, with the problem of proposing in solving above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: a civil aircraft running state monitoring system comprises a PLC and a PC, wherein a first sensor module is arranged at the connecting end of the PLC, a second sensor module is arranged at the connecting end of the PLC, GPRS is arranged at the connecting end of the PLC, a switch module is arranged at the connecting end of the PC, and an alarm indication module is arranged at the connecting end of the switch module;
the first sensor module comprises a first temperature sensor, a distance sensor, a vibration sensor and a level sensor;
the second sensor module comprises a second temperature sensor, a humidity sensor, a dust sensor, a wind speed sensor and an oxygen sensor;
the switch module comprises a first switch tube and a second switch tube;
the alarm indication module comprises a first alarm lamp and a second alarm lamp.
In a preferred embodiment, the PLC controller connection is provided with a semiconductor memory.
In a preferred embodiment, the PLC controller is configured to control system operation, the PC is configured to send a command, the first temperature sensor and the second temperature sensor are both configured to measure temperature, the distance sensor is configured to measure an obstacle distance, the vibration sensor is configured to measure an aircraft vibration value, the level sensor is configured to measure an aircraft level value, the humidity sensor is configured to measure air humidity, the dust sensor is configured to measure an air dust concentration, the wind speed sensor is configured to measure wind speed, the oxygen sensor is configured to measure oxygen content, the first switch tube and the second switch tube are both configured to control a circuit switch, the first alarm lamp and the second alarm lamp are both configured to alarm, and the semiconductor memory is configured to store data.
In a preferred embodiment, the first temperature sensor, the distance sensor, the vibration sensor and the level sensor connection end are all connected with the PLC controller connection end.
In a preferred embodiment, the second temperature sensor, the humidity sensor, the dust sensor, the wind speed sensor and the oxygen sensor are all connected with the PLC controller connection end.
In a preferred embodiment, the first switch tube and the second switch tube connection end are both connected to the PC connection end, the first switch tube connection end is connected to the first alarm lamp connection end, and the second switch tube connection end is connected to the second alarm lamp connection end.
The utility model discloses a technological effect and advantage:
1. by classifying the measured data into the aircraft and external environment factors, when the abnormal condition occurs, the fault inside the aircraft or the external environment is known at first time, so that the problem is quickly positioned, a solution is formulated, and meanwhile, the monitoring on the external environment can play a role in early warning, so that the operation of the aircraft can be adjusted at any time according to the external environment factors, and the operation safety of the aircraft is improved;
2. the measurement data is stored for the first time through the semiconductor memory, so that data analysis in the later period is facilitated, and data loss is prevented.
Drawings
Fig. 1 is a topological diagram of the present invention.
Fig. 2 is a unit diagram of the present invention.
Fig. 3 is a block diagram of a first sensor according to the present invention.
Fig. 4 is a block diagram of a second sensor according to the present invention.
Fig. 5 is a circuit diagram of the present invention.
The reference signs are: the system comprises a PLC (programmable logic controller) 1, a 2 PC (personal computer), a 3 first sensor module, a 4 second sensor module, a 5 GPRS (general packet radio service), a 6 switch module, a 7 alarm indication module, a 8 first temperature sensor, a 9 distance sensor, a 10 vibration sensor, a 11 level sensor, a 12 second temperature sensor, a 13 humidity sensor, a 14 dust sensor, a 15 wind speed sensor, a 16 oxygen sensor, a 17 first switch tube, a 18 second switch tube, a 19 first alarm lamp, a 20 second alarm lamp and a 21 semiconductor memory.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The civil aircraft running state monitoring system shown in the attached fig. 1-5 comprises a PLC controller 1 and a PC2, wherein the connection end of the PLC controller 1 is provided with a first sensor module 3, the connection end of the PLC controller 1 is provided with a second sensor module 4, the connection end of the PLC controller 1 is provided with a GPRS5, the connection end of the PC2 is provided with a switch module 6, the connection end of the switch module 6 is provided with an alarm indication module 7, the PLC controller 1 is an electronic device of digital operation designed specially for application in industrial environment, which adopts a programmable memory for storing therein instructions for performing operations such as logic operation, sequential operation, timing, counting and arithmetic operation, and can control various types of machinery or production processes through digital or analog input and output, the PC2 is a computer, the GPRS5 is a wireless data transmission technology;
the first sensor module 3 comprises a first temperature sensor 8, a distance sensor 9, a vibration sensor 10 and a level sensor 11, wherein the distance sensor 9, also called a displacement sensor, is one of sensors for sensing the distance between the distance sensor and an object to perform a preset certain function, and the vibration sensor 10 receives mechanical quantity and converts the mechanical quantity into electric quantity proportional to the mechanical quantity, and is also an electromechanical conversion device. So we sometimes call it a transducer, a vibration pickup, etc., said level sensor 11 being one of the angle sensors, whose function is TO measure the level of the support, also called tilt sensor, often called level or inclinometer in engineering, said first temperature sensor 8 and second temperature sensor 12 being of the type DS18B20 TO-92, said distance sensor 9 being of the type OPTEX-FA, said vibration sensor 10 being of the type LT0420ZDA, said level sensor 11 being of the type VL E4S;
the second sensor module 4 comprises a second temperature sensor 12, a humidity sensor 13, a dust sensor 14, a wind speed sensor 15 and an oxygen sensor 16, the first temperature sensor 8 and the second temperature sensor 12 are sensors capable of sensing temperature and converting into usable output signals, the humidity sensor 13 is an instrument for measuring humidity and composed of a humidity sensitive resistor, the humidity sensitive resistor is characterized in that a substrate is covered with a film made of a humidity sensitive material, when water vapor in air is adsorbed on the humidity sensitive film, the resistivity and the resistance of the element are changed, and the humidity can be measured by using the characteristic, the dust sensor 14 is an instrument for detecting the dust content in air, and the instrument for measuring the concentration of inhalable particles (PM10) in air and the concentration of respiratory dust, the total dust concentration and the dust mass concentration (mg/m3) in air, the wind speed sensor 15 adopts a high-performance wind speed sensor and a whole microcomputer detection controller, can simultaneously monitor and display the change of the measured wind speed, the oxygen sensor 16 is a gas detector, the sensor of the oxygen sensor adopts an electrochemical sensor, has sensitive reaction and is suitable for continuously detecting the percentage concentration of oxygen in the ambient air of industrial and mining enterprises, the model of the humidity sensor 13 is set to WLHT-1S-500, the model of the dust sensor 14 is set to PM1003, the model of the wind speed sensor 15 is set to FC-2A1, and the model of the oxygen sensor 16 is set to GAXT-X;
the switch module 6 comprises a first switch tube 17 and a second switch tube 18, the first switch tube 17 and the second switch tube 18 work in a cut-off region and a saturation region, which is equivalent to the cut-off and the conduction of a circuit, and have the functions of completing the cut-off and the cut-on;
the alarm indication module 7 comprises a first alarm lamp 19 and a second alarm lamp 20, wherein the first alarm lamp 19 and the second alarm lamp 20 are LED lamps;
the PLC controller 1 is used for controlling the system operation, the PC2 is used for sending instructions, the first temperature sensor 8 and the second temperature sensor 12 are used for measuring the temperature, the distance sensor 9 is used for measuring the distance of an obstacle, the vibration sensor 10 is used for measuring the vibration value of an aircraft, the level sensor 11 is used for measuring the level value of the aircraft, the humidity sensor 13 is used for measuring the air humidity, the dust sensor 14 is used for measuring the dust concentration of the air, the wind speed sensor 15 is used for measuring the wind speed, the oxygen sensor 16 is used for measuring the oxygen content, the first switch tube 17 and the second switch tube 18 are used for controlling a circuit switch, the first alarm lamp 19 and the second alarm lamp 20 are used for alarm indication, and the semiconductor memory 21 is used for storing data;
the connecting ends of the first temperature sensor 8, the distance sensor 9, the vibration sensor 10 and the horizontal sensor 11 are connected with the connecting end of the PLC controller 1;
the second temperature sensor 12, the humidity sensor 13, the dust sensor 14, the wind speed sensor 15 and the oxygen sensor 16 are all connected with the connecting end of the PLC controller 1;
the first switch tube 17 and the second switch tube 18 are connected with the PC2, the first switch tube 17 is connected with the first alarm lamp 19, and the second switch tube 18 is connected with the second alarm lamp 20.
The implementation mode is specifically as follows: the temperature inside the aircraft, the distance from the obstacle, the vibration of the aircraft and the numerical value of whether the aircraft keeps horizontal are measured through the first temperature sensor 8, the distance sensor 9, the vibration sensor 10 and the level sensor 11, data are sent to the PC2 through the GPRS5 through the PLC controller 1, if abnormal, the first switch tube 17 is controlled to be opened through the PC2, the first alarm lamp 19 is enabled to alarm in operation, the temperature, the humidity, the dust concentration, the wind speed and the oxygen content of the environment are measured through the second temperature sensor 12, the humidity sensor 13, the dust sensor 14, the wind speed sensor 15 and the oxygen sensor 16, data are sent to the PC2 through the GPRS5 through the PLC controller 1, if abnormal, the second switch tube 18 is controlled to be opened through the PC2, the second alarm lamp 20 is enabled to alarm in operation, the utility model classifies the measured data into the aircraft and external environmental factors, when the anomaly appears, the first time is known to be the fault inside the aircraft or the effect of the external environment, so that the quick positioning problem is solved, the solution is formulated, and meanwhile, the early warning effect can be simultaneously played on the monitoring of the external environment, so that the operation of the aircraft can be adjusted at any time according to the external environment factors, and the operation safety of the aircraft is improved.
The civil aircraft running state monitoring system shown in fig. 1, fig. 3 and fig. 5 further comprises a semiconductor memory 21, wherein a connection end of the semiconductor memory 21 is connected with a connection end of the PLC controller 1, and the semiconductor memory 21 is a memory using a semiconductor circuit as a storage medium.
The implementation mode is specifically as follows: the measurement data is stored for the first time by the semiconductor memory 21 so as to facilitate later data analysis and prevent data loss.
The utility model discloses the theory of operation:
with reference to the attached drawings 1-5 in the specification, measurement data are classified into the aircraft and external environment factors, when an abnormal condition occurs, the problem that the fault inside the aircraft or the external environment acts is known at the first time, so that the problem is quickly positioned, a solution is formulated, and meanwhile, the monitoring of the external environment can play a role in early warning, so that the operation of the aircraft can be adjusted at any time according to the external environment factors, and the operation safety of the aircraft is improved;
referring to the description of the drawings, fig. 1, fig. 3 and fig. 5, the measurement data is stored for the first time through the semiconductor memory 21 so as to facilitate the data analysis at the later stage and prevent the data loss.
The points to be finally explained are: first, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounted," "connected," and "connected" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be a direct connection, and "upper," "lower," "left," and "right" are only used to indicate a relative positional relationship, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed;
secondly, the method comprises the following steps: in the drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are referred to, and other structures can refer to the common design, and under the condition of no conflict, the same embodiment and different embodiments of the present invention can be combined with each other;
and finally: the above description is only for the preferred embodiment of the present invention and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The utility model provides a civil aircraft running state monitoring system, includes PLC controller (1) and PC (2), its characterized in that: the PLC is characterized in that a first sensor module (3) is arranged at the connecting end of the PLC (1), a second sensor module (4) is arranged at the connecting end of the PLC (1), a GPRS (general packet radio service) is arranged at the connecting end of the PLC (1), a switch module (6) is arranged at the connecting end of the PC (2), and an alarm indication module (7) is arranged at the connecting end of the switch module (6);
the first sensor module (3) comprises a first temperature sensor (8), a distance sensor (9), a vibration sensor (10) and a level sensor (11);
the second sensor module (4) comprises a second temperature sensor (12), a humidity sensor (13), a dust sensor (14), a wind speed sensor (15) and an oxygen sensor (16);
the switch module (6) comprises a first switch tube (17) and a second switch tube (18);
the alarm indication module (7) comprises a first alarm lamp (19) and a second alarm lamp (20).
2. The civil aircraft operating condition monitoring system according to claim 1, characterized in that: and a semiconductor memory (21) is arranged at the connecting end of the PLC (1).
3. The civil aircraft operating condition monitoring system according to claim 2, characterized in that: the PLC controller (1) is used for controlling the system to operate, the PC (2) is used for sending instructions, the first temperature sensor (8) and the second temperature sensor (12) are each used for measuring a temperature, the distance sensor (9) is used for measuring the distance of an obstacle, the vibration sensor (10) is used for measuring the vibration value of the aircraft, the level sensor (11) is used for measuring the aircraft level value, the humidity sensor (13) is used for measuring the air humidity, the dust sensor (14) is used for measuring the dust concentration of air, the wind speed sensor (15) is used for measuring the wind speed, the oxygen sensor (16) is used for measuring the oxygen content, the first switch tube (17) and the second switch tube (18) are both used for controlling the circuit to be switched, the first alarm lamp (19) and the second alarm lamp (20) are used for alarm indication, and the semiconductor memory (21) is used for storing data.
4. The civil aircraft operating condition monitoring system according to claim 1, characterized in that: the connecting ends of the first temperature sensor (8), the distance sensor (9), the vibration sensor (10) and the horizontal sensor (11) are connected with the connecting end of the PLC (1).
5. The civil aircraft operating condition monitoring system according to claim 1, characterized in that: and the second temperature sensor (12), the humidity sensor (13), the dust sensor (14), the wind speed sensor (15) and the oxygen sensor (16) are connected with the connecting end of the PLC (1).
6. The civil aircraft operating condition monitoring system according to claim 1, characterized in that: first switch tube (17) and second switch tube (18) link all are connected with PC (2) link, first switch tube (17) link is connected with first alarm lamp (19) link, second switch tube (18) link is connected with second alarm lamp (20) link.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920721852.8U CN209956248U (en) | 2019-05-20 | 2019-05-20 | Civil aircraft running state monitoring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920721852.8U CN209956248U (en) | 2019-05-20 | 2019-05-20 | Civil aircraft running state monitoring system |
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| Publication Number | Publication Date |
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| CN209956248U true CN209956248U (en) | 2020-01-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920721852.8U Expired - Fee Related CN209956248U (en) | 2019-05-20 | 2019-05-20 | Civil aircraft running state monitoring system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113740185A (en) * | 2021-08-16 | 2021-12-03 | 中国飞机强度研究所 | Structure is patrolled and examined to aircraft inner cabin structural damage among aircraft fatigue test |
| CN114954991A (en) * | 2021-12-10 | 2022-08-30 | 昆明理工大学 | Automatic transfer system of airport luggage handcart |
-
2019
- 2019-05-20 CN CN201920721852.8U patent/CN209956248U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113740185A (en) * | 2021-08-16 | 2021-12-03 | 中国飞机强度研究所 | Structure is patrolled and examined to aircraft inner cabin structural damage among aircraft fatigue test |
| CN113740185B (en) * | 2021-08-16 | 2024-05-03 | 中国飞机强度研究所 | Aircraft inner cabin structural damage inspection framework in aircraft fatigue test |
| CN114954991A (en) * | 2021-12-10 | 2022-08-30 | 昆明理工大学 | Automatic transfer system of airport luggage handcart |
| CN114954991B (en) * | 2021-12-10 | 2023-03-14 | 昆明理工大学 | Automatic transfer system of airport luggage handcart |
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| CF01 | Termination of patent right due to non-payment of annual fee |