CN112904789A - Aircraft structure temperature anomaly monitoring and early warning system - Google Patents
Aircraft structure temperature anomaly monitoring and early warning system Download PDFInfo
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- CN112904789A CN112904789A CN202110070677.2A CN202110070677A CN112904789A CN 112904789 A CN112904789 A CN 112904789A CN 202110070677 A CN202110070677 A CN 202110070677A CN 112904789 A CN112904789 A CN 112904789A
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- 238000012544 monitoring process Methods 0.000 title claims description 12
- 230000007246 mechanism Effects 0.000 claims abstract description 4
- 230000037361 pathway Effects 0.000 claims abstract description 3
- 239000000463 material Substances 0.000 claims description 9
- 239000000446 fuel Substances 0.000 claims description 3
- 230000001960 triggered effect Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 4
- 238000009413 insulation Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002086 nanomaterial Substances 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 239000002861 polymer material Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/048—Monitoring; Safety
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Abstract
The invention discloses an overtemperature early warning system for an aircraft, which comprises: a plurality of temperature sensitive units for detecting temperature information of an aircraft structure, the plurality of temperature sensitive units forming a temperature sensitive pathway; the control unit is used for receiving the temperature information transmitted by the temperature sensitive unit, and when the surface temperature of the structure exceeds a preset temperature area, the conductivity of the temperature sensitive passage is obviously changed and triggers the control unit to send an alarm mechanism; the alarm unit is used for receiving the alarm instruction signal transmitted by the control unit; the system also comprises a power supply unit which supplies electric energy for the system. The system detects the surface temperature of the aircraft structure, and sends out an alarm prompt signal when the temperature exceeds a temperature area, the early warning system has a simple circuit structure, does not need to accurately measure and feed back the temperature, and can timely and rapidly send out the alarm signal as long as the preset temperature area is reached.
Description
Technical Field
The invention relates to the technical field of structural state monitoring and early warning, in particular to an overtemperature early warning system for an aircraft.
Background
Aircrafts such as aircrafts, spacecrafts, rocket missiles and the like play an important role in national economy and national defense safety. In recent years, unmanned aerial vehicle application scenes are also increasing, including aerial photography, intelligent patrol, disaster site survey, post-disaster rescue and the like. The surface or the interior of the aircraft often suddenly enters an environment with abnormal temperature due to pneumatic heating, structural damage and the like, and if early warning is not made in time, accidents such as damage of instruments in the aircraft and even crash of the aircraft can be caused, so that it is very necessary to install an overtemperature monitoring and early warning system on the aircraft.
At present, temperature sensors such as thermocouples and optical fibers are commonly adopted in a temperature monitoring and early warning system, the hardware system of the contact type temperature sensor is complex, the robustness is low, a large amount of additional energy is needed, and the effectiveness and the measurement precision under the structural service environment (such as high temperature, severe vibration and the like) are difficult to guarantee.
Disclosure of Invention
According to the problem that prior art exists, the application discloses an overtemperature early warning system is provided for aircraft, and this system includes:
a plurality of temperature sensitive units for detecting temperature information of an aircraft structure, the plurality of temperature sensitive units forming a temperature sensitive pathway;
the control unit is used for receiving the temperature information transmitted by the temperature sensitive unit, and when the surface temperature of the structure exceeds a preset temperature area, the conductivity of the temperature sensitive passage is obviously changed and triggers the control unit to send an alarm mechanism;
the alarm unit is used for receiving the alarm instruction signal transmitted by the control unit;
the system also comprises a power supply unit which supplies electric energy for the system.
The temperature sensitive units are connected in series, parallel and series-parallel combination to form a temperature sensitive passage.
The temperature sensitive unit is made of a material with conductive performance, the electrical performance of the material in a specific temperature area is changed remarkably, and the on-off state of a temperature sensitive passage changes under extreme conditions, including power-on to power-off or power-off to power-on.
The power supply unit comprises a dry battery, a storage battery, a rechargeable battery, a fuel cell or a solar cell.
Due to the adoption of the technical scheme, the overtemperature early warning system for the aircraft is provided, when the system exceeds a preset temperature area, the temperature sensitive passage triggers a fusing mechanism, and the control unit sends an alarm signal to the alarm unit to realize temperature abnormity early warning. The early warning system has the advantages of simple circuit connection, capability of completely covering the aircraft, small energy requirement, low power consumption, high reliability, good anti-vibration effect, simple installation method and convenience in maintenance and replacement, and can effectively avoid the phenomenon of false alarm missing in abnormal temperature state. The monitoring and early warning system can protect the aircraft and internal instruments and equipment in the testing or service stage of the aircraft, and further reduce economic loss.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic circuit diagram of the early warning system of the present invention;
FIG. 2 is a schematic illustration of the installation of the present invention on an aircraft structure;
FIG. 3 is a schematic diagram of an embodiment 1 of a circuit connection of a temperature-sensitive cell in a temperature-sensitive path;
FIG. 4 is a schematic diagram of an embodiment 2 of the circuit connection of the temperature sensitive unit in the temperature sensitive path;
fig. 5 is a schematic diagram of embodiment 3 of circuit connection of a temperature-sensitive unit in a temperature-sensitive path.
In the figure: 1. the device comprises a power supply unit, a warning unit, a control unit, a temperature sensitive passage, a temperature sensitive unit, a heat insulation layer and a bearing layer, wherein the power supply unit 2, the warning unit 3, the control unit 4, the temperature sensitive passage 5, the temperature sensitive unit 7, the heat insulation layer and the bearing layer 8 are arranged on the bearing layer.
Detailed Description
In order to make the technical solutions and advantages of the present invention clearer, the following describes the technical solutions in the embodiments of the present invention clearly and completely with reference to the drawings in the embodiments of the present invention:
as shown in fig. 1, the overtemperature early warning system for the aircraft comprises a power supply unit 1, an alarm unit 2, a control unit 3, a temperature sensitive passage 4 and a temperature sensitive unit 5, wherein the power supply unit 1 provides electric energy for the system, the temperature sensitive units 5 are arranged on the surface, inside or laminated structure interface of the structure and are used for detecting the temperature information of the surface of the aircraft structure, a plurality of temperature sensitive units 5 form a temperature sensitive passage 4, a temperature area is stored in the control unit 3, when the temperature of the surface of the aircraft structure exceeds a preset temperature area, the control unit 3 controls the electrical conductivity of the temperature sensitive path 4 to change significantly, meanwhile, the control unit 3 sends out an alarm instruction and controls the alarm unit 2 to send out an alarm signal in time, overtemperature monitoring and early warning are realized, and the structure and internal instruments and equipment in the structure are prevented from being in a high-temperature high-risk environment.
Further, the temperature-sensitive path 4 includes a plurality of temperature-sensitive units 5 connected in series, parallel, series-parallel, and series-parallel combinations.
Further, the temperature-sensitive unit 5 is a light thin material capable of transmitting weak current, and the material may be denatured when meeting a specific temperature, resulting in a change in the electron transmission capability of the material.
Further, the power supply unit 1 is a small-sized power module including a dry cell, a storage battery, a rechargeable battery, a fuel cell, a solar cell, or the like.
Further, fig. 2 is a schematic view of the installation of the over-temperature warning system on the aircraft structure. The temperature sensitive passage 4 in the overtemperature early warning system can be arranged between a bearing layer 8 and a heat insulation layer 7 of the aircraft in a bonding mode. When the heat insulation layer 7 in a certain area is completely ablated or falls off accidentally, the temperature sensitive passage (exposed to a high-temperature environment) in the area is obviously changed in the conductivity of the temperature sensitive passage 4, the control unit 3 is triggered to alarm, and the alarm unit 2 sends out an alarm signal in time, so that overtemperature early warning is realized, and the structure and instruments and equipment in the structure are prevented from being in a high-temperature high-risk environment.
Fig. 3 is a circuit connection embodiment 1 of a temperature sensitive cell in a temperature sensitive path. The temperature sensitive units 5 are connected in series integrally to form a temperature sensitive passage 4 covering the whole area of the structure. When the temperature sensitive passage 4 is set to be in the power-on state, the control unit 3 sends a signal of 1, and the power-off state is 0. When the local area of the structure is over-temperature, the electrical property of a certain temperature sensitive unit is obviously changed, the power-on is changed into the power-off, and the alarm unit receives a signal 0 and sends an alarm signal.
Fig. 4 is a circuit connection embodiment 2 of a temperature sensitive cell in a temperature sensitive path. The temperature sensitive units 5 are connected in a row-column series mode to form a temperature sensitive passage 4, and the temperature sensitive passage covers the whole area of the structure. When the temperature sensitive channels 4 of each row and each column are set to be in the power-on state, the control unit 3 sends a signal of 1, and the power-off state is 0. When local overtemperature occurs, the electrical performance of a certain temperature sensitive unit is obviously changed, the state of the row and the column of the sensitive unit is changed from power-on to power-off, and the alarm unit receives a signal 0 and sends an alarm signal. And positioning the over-temperature position by the row and the column in the power-off state.
Fig. 5 shows a circuit connection embodiment 3 of the temperature-sensitive cell 5 in the temperature-sensitive path 4. A temperature sensitive unit is made of wires, nano materials, high polymer materials and the like to form a temperature sensitive passage 4, the whole area of the structure is covered, and the control unit 3 sends a signal 1 when the temperature sensitive passage 4 is in a power-on state and the power-off state is set to be 0. When the local area of the structure is over-temperature, the electrical property of the material is obviously changed from power-on to power-off, and the alarm unit receives the signal 0 and sends an alarm signal.
The system detects the surface temperature of the aircraft structure, and sends out an alarm prompt signal when the temperature exceeds a temperature area, the early warning system has a simple circuit structure, does not need to accurately measure and feed back the temperature, and can timely and rapidly send out the alarm signal as long as the preset temperature area is reached.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (4)
1. An aircraft structure temperature anomaly monitoring and early warning system, its characterized in that includes:
a plurality of temperature-sensitive units (5) for detecting temperature information of the aircraft structure, the plurality of temperature-sensitive units (5) constituting a temperature-sensitive pathway (4);
the control unit (3) is used for receiving the temperature information transmitted by the temperature sensitive unit (5), and when the temperature of the surface of the structure exceeds a preset temperature area, the conductivity of the temperature sensitive passage (4) is obviously changed and the control unit (3) is triggered to send an alarm mechanism;
the alarm unit (2) receives the alarm instruction signal transmitted by the control unit (3);
the system further comprises a power supply unit (1), wherein the power supply unit (1) supplies electric energy to the system.
2. The aircraft structure temperature anomaly monitoring and early warning system of claim 1, further characterized by: the temperature sensitive units (5) are connected in series, parallel and series-parallel combination to form a temperature sensitive passage.
3. The aircraft structure temperature anomaly monitoring and early warning system of claim 1, further characterized by: the temperature sensitive unit (5) is made of a material with conductive performance, the electrical performance of the material in a specific temperature area is changed remarkably, and in extreme cases, the on-off state of the temperature sensitive passage (4) is changed, namely the temperature sensitive passage is switched from power on to power off or from power off to power on.
4. The aircraft structure temperature anomaly monitoring and early warning system of claim 1, further characterized by: the power supply unit (1) comprises a dry cell, a storage battery, a rechargeable battery, a fuel cell or a solar cell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110070677.2A CN112904789A (en) | 2021-01-19 | 2021-01-19 | Aircraft structure temperature anomaly monitoring and early warning system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110070677.2A CN112904789A (en) | 2021-01-19 | 2021-01-19 | Aircraft structure temperature anomaly monitoring and early warning system |
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| CN112904789A true CN112904789A (en) | 2021-06-04 |
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| CN202110070677.2A Pending CN112904789A (en) | 2021-01-19 | 2021-01-19 | Aircraft structure temperature anomaly monitoring and early warning system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114646189A (en) * | 2022-03-10 | 2022-06-21 | 安特仪表集团有限公司 | Use method and system of intelligent electric meter, electronic equipment and storage medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090212976A1 (en) * | 2007-12-19 | 2009-08-27 | Airbus Deutschland Gmbh | Method and system for monitoring of the temperature of the surface of an aircraft |
| CN103279058A (en) * | 2013-05-04 | 2013-09-04 | 北京航空航天大学 | Optical fiber IMU (inertial measurement unit) data collecting system for unmanned aerial vehicle electric power routing inspection |
| CN105118220A (en) * | 2015-09-17 | 2015-12-02 | 杨珊珊 | Temperature early warning system and method for unmanned aircraft |
| CN105841841A (en) * | 2016-04-07 | 2016-08-10 | 中国航空工业集团公司西安飞机设计研究所 | Airplane surface temperature detection system |
| CN108120476A (en) * | 2017-12-15 | 2018-06-05 | 中国电子产品可靠性与环境试验研究所 | Unmanned plane actual time safety prior-warning device |
| CN108312861A (en) * | 2017-12-28 | 2018-07-24 | 广州亿航智能技术有限公司 | A kind of unmanned plane and its battery temperature control and method |
-
2021
- 2021-01-19 CN CN202110070677.2A patent/CN112904789A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090212976A1 (en) * | 2007-12-19 | 2009-08-27 | Airbus Deutschland Gmbh | Method and system for monitoring of the temperature of the surface of an aircraft |
| CN103279058A (en) * | 2013-05-04 | 2013-09-04 | 北京航空航天大学 | Optical fiber IMU (inertial measurement unit) data collecting system for unmanned aerial vehicle electric power routing inspection |
| CN105118220A (en) * | 2015-09-17 | 2015-12-02 | 杨珊珊 | Temperature early warning system and method for unmanned aircraft |
| CN105841841A (en) * | 2016-04-07 | 2016-08-10 | 中国航空工业集团公司西安飞机设计研究所 | Airplane surface temperature detection system |
| CN108120476A (en) * | 2017-12-15 | 2018-06-05 | 中国电子产品可靠性与环境试验研究所 | Unmanned plane actual time safety prior-warning device |
| CN108312861A (en) * | 2017-12-28 | 2018-07-24 | 广州亿航智能技术有限公司 | A kind of unmanned plane and its battery temperature control and method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114646189A (en) * | 2022-03-10 | 2022-06-21 | 安特仪表集团有限公司 | Use method and system of intelligent electric meter, electronic equipment and storage medium |
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