CN112904789A - Aircraft structure temperature anomaly monitoring and early warning system - Google Patents

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

Aircraft structure temperature anomaly monitoring and early warning system

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 anembodiment 1 of a circuit connection of a temperature-sensitive cell in a temperature-sensitive path;

FIG. 4 is a schematic diagram of anembodiment 2 of the circuit connection of the temperature sensitive unit in the temperature sensitive path;

fig. 5 is a schematic diagram ofembodiment 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 thepower supply unit 2, thewarning unit 3, thecontrol unit 4, the temperaturesensitive passage 5, the temperaturesensitive unit 7, the heat insulation layer and thebearing 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 apower supply unit 1, analarm unit 2, acontrol unit 3, a temperaturesensitive passage 4 and a temperaturesensitive unit 5, wherein thepower supply unit 1 provides electric energy for the system, the temperaturesensitive 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 temperaturesensitive units 5 form a temperaturesensitive passage 4, a temperature area is stored in thecontrol unit 3, when the temperature of the surface of the aircraft structure exceeds a preset temperature area, thecontrol unit 3 controls the electrical conductivity of the temperaturesensitive path 4 to change significantly, meanwhile, thecontrol unit 3 sends out an alarm instruction and controls thealarm 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, thepower 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 temperaturesensitive passage 4 in the overtemperature early warning system can be arranged between a bearinglayer 8 and aheat insulation layer 7 of the aircraft in a bonding mode. When theheat 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 temperaturesensitive passage 4, thecontrol unit 3 is triggered to alarm, and thealarm 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 acircuit connection embodiment 1 of a temperature sensitive cell in a temperature sensitive path. The temperaturesensitive units 5 are connected in series integrally to form a temperaturesensitive passage 4 covering the whole area of the structure. When the temperaturesensitive passage 4 is set to be in the power-on state, thecontrol 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 acircuit connection embodiment 2 of a temperature sensitive cell in a temperature sensitive path. The temperaturesensitive units 5 are connected in a row-column series mode to form a temperaturesensitive passage 4, and the temperature sensitive passage covers the whole area of the structure. When the temperaturesensitive channels 4 of each row and each column are set to be in the power-on state, thecontrol 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 acircuit 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 temperaturesensitive passage 4, the whole area of the structure is covered, and thecontrol unit 3 sends asignal 1 when the temperaturesensitive 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.

Embodiment 4, monitoring and early warning system need not controlunit 3 temperaturesensitive passageway 4 andalarm unit 2 lug connection, and when the local region of structure appears the overtemperature, the material electrical property is showing to change, changes the outage from circular telegram, and alarm unit sends 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)

Translated fromChinese

1.一种飞行器结构温度异常监测与预警系统，其特征在于包括：1. An aircraft structure temperature abnormality monitoring and early warning system is characterized in that comprising:用于检测飞行器结构的温度信息的多个温度敏感单元(5)，所述多个温度敏感单元(5)构成温度敏感通路(4)；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 passage (4);接收所述温度敏感单元(5)传送的温度信息的控制单元(3)，当结构表面温度超过预先设定的温度区域时，温度敏感通路(4)的导电性能显著改变并触发控制单元(3)发出报警机制；A control unit (3) that receives the temperature information transmitted by the temperature sensitive unit (5), when the surface temperature of the structure exceeds a preset temperature region, the electrical conductivity of the temperature sensitive path (4) is significantly changed and the control unit (3) is triggered ) to issue an alarm mechanism;接收所述控制单元(3)传送的报警指令信号的报警单元(2)；an alarm unit (2) that receives an alarm command signal transmitted by the control unit (3);该系统还包括供电单元(1)，所述供电单元(1)为该系统提供电能。The system also includes a power supply unit (1), which provides electrical energy for the system.2.根据权利要求1所述的一种飞行器结构温度异常监测与预警系统，其特征还在于：所述多个温度敏感单元(5)以串联、并联及串并联组合方式连接构成温度敏感通路。2 . An aircraft structure temperature abnormality monitoring and early warning system according to claim 1 , further characterized in that: the plurality of temperature sensitive units ( 5 ) are connected in series, parallel and series-parallel combination to form a temperature sensitive path. 3 .3.根据权利要求1所述的一种飞行器结构温度异常监测与预警系统，其特征还在于：所述温度敏感单元(5)由具有导电性能的材料制成、在特定温度区域材料的电性能发生显著改变，极端情况下温度敏感通路(4)的通断状态发生变化，包括通电变断电或断电变通电。3. An aircraft structure temperature abnormality monitoring and early warning system according to claim 1, characterized in that: the temperature sensitive unit (5) is made of a material with electrical conductivity, and the electrical properties of the material in a specific temperature region are Significant changes occur, and in extreme cases, the on-off state of the temperature-sensitive path (4) changes, including power-on to power-off or power-off to power-on.4.根据权利要求1所述的一种飞行器结构温度异常监测与预警系统，其特征还在于：所述供电单元(1)包括干电池、蓄电池、可再充电池、燃料电池或太阳能电池。4. An aircraft structure temperature abnormality monitoring and early warning system according to claim 1, further characterized in that: the power supply unit (1) comprises a dry cell, a storage battery, a rechargeable battery, a fuel cell or a solar cell.

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