CN215984619U - Aircraft fire alarm sensor detection device - Google Patents
Aircraft fire alarm sensor detection device Download PDFInfo
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- CN215984619U CN215984619U CN202121355116.9U CN202121355116U CN215984619U CN 215984619 U CN215984619 U CN 215984619U CN 202121355116 U CN202121355116 U CN 202121355116U CN 215984619 U CN215984619 U CN 215984619U
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Abstract
The utility model discloses a detection device of an aircraft fire sensor, which comprises at least two test channels for simulating the temperature of a fire scene and a switching device for switching the test channels of the fire sensor at different temperatures. The simulated firing scene has high temperature control precision on temperature fields, short preheating time and high switching response speed of the sensor in each temperature field, and can truly simulate various temperature fields under various fire scenes so as to detect the function and performance parameters of the fire alarm sensor in each scene; batch detection can be realized through a special detection clamp, and the test efficiency is improved; the detection process can realize full-automatic intelligent control, manual intervention is not needed, and labor cost and safety risk are reduced.
Description
Technical Field
The utility model belongs to an electrical test technology, and relates to fire alarm sensor detection of a fire protection system of an aircraft power device.
Background
A fire detection sensor in a fire protection system of an aircraft power plant needs to be detected by a special detection device before installation so as to verify the function, performance and reliability of the fire detection sensor. The existing fire sensor detection device has the following defects:
the method for simulating the temperature field environment of the fire scene has the following defects:
1. the method for simulating the environmental temperatures of different ignition scenes by changing the temperature of the test hearth has the advantages that the temperature rise/fall rate is slow, the temperature field change of the ignition scenes cannot be truly reflected, and the detection of parameters such as the alarm inertia time of a fire alarm sensor is influenced;
2. the method for simulating the environmental temperatures of different ignition scenes by adopting a temperature field switching mode needs manual switching, is low in switching speed, needs labor cost and has safety risk;
3. the temperature field with fixed temperature is realized by adopting the fan and the electric heating wire, and a more accurate test temperature field can be reached only by needing longer preheating time and preparation time;
4. the existing test hearth has low temperature control precision and cannot cover the detection range of a fire alarm sensor in various fire scenes.
Secondly, batch detection cannot be carried out: the existing detection device can only realize one-by-one detection, and the detection efficiency is low;
thirdly, the automation degree is low: the existing detection device needs manual control of work such as temperature field change, switching of a sensor in a temperature field, recording of a test result and the like, more labor cost needs to be spent, and meanwhile, the safety risk is caused due to the fact that the temperature of a test hearth is high.
Disclosure of Invention
In order to solve the technical problems, the technical scheme adopted by the utility model is as follows:
in one aspect, the embodiment of the utility model provides a detection device for an aircraft fire sensor, which comprises at least two test channels for simulating the temperature of a fire scene, and a switching device for switching the test channels of the fire sensor at different temperatures.
In an embodiment provided by the present invention, the test tunnel includes a high pressure fan to provide air velocity to the tunnel, and a heater to control the temperature of the duct. At least one temperature sensor is included for sensing the temperature of the tunnel, the temperature sensor being disposed in the tunnel downstream of the heater. Including a temperature equalizer disposed in the channel upstream of the temperature sensor. A pressure sensor is included and is disposed in the passageway downstream of the high pressure fan. The wind speed instrument is arranged in the channel at the downstream of the high-pressure fan.
In the embodiment provided by the utility model, the switching device comprises a pneumatic push rod, a sliding mechanism and a clamp; the fire alarm sensor to be detected is arranged on the sliding mechanism, and the pneumatic push rod is connected with the side face of the fire alarm sensor. And a channel clapboard is arranged on the sliding mechanism. The device comprises a cooling device for reducing the heat of air in a test channel; the cooling device is disposed downstream of the switching device. The device comprises a control system, wherein the control system is connected with a test channel and a switching device.
Another aspect of the embodiments of the present invention provides a method for detecting an aircraft fire sensor, including the following steps:
s100: respectively establishing test channels with different temperature intervals in the three test channels, wherein the temperature of each test channel is continuously adjustable in the temperature interval;
s200: in step S100, the same wind speed interval is set in each test channel, and the wind speed in each test channel is continuously adjustable;
s300: the switching device controls the fire alarm sensor to be tested to be switched in different testing channels.
Further, in step S100, the control accuracy of the temperature is ± 3 ℃.
Further, in step S200, the wind speed control accuracy is ± 5%.
Further, in step S300, the switching time is less than 1 second.
Compared with the prior art, the technical scheme of the utility model has the following advantages:
a) a plurality of test fields with controllable and stable temperature and wind speed can be simulated rapidly and simultaneously, the control precision of test conditions is higher, and the preheating time before the test is reduced;
b) the developed switching device can realize the instantaneous switching of the sensor under different test conditions, and can simulate various different ignition scenes more truly;
c) the purpose of batch detection can be realized by using the developed test fixture, and the test fixture can be adjusted according to the test quantity;
d) the test process is automatically controlled, test technical conditions can be preset according to test requirements, environmental simulation, flow control, data recording and the like in the detection process are automatically completed, and labor cost and safety risks are reduced.
Additional advantages, objects, and features of the utility model will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the utility model.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic overall structure diagram of an embodiment of the present invention.
Detailed Description
The present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the utility model by referring to the description text.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
As shown in fig. 1, the present invention provides a detection device for an aircraft fire sensor, which comprises at least two test channels for simulating the temperature of a fire scene, and a switching device for switching the test channels of the fire sensor at different temperatures.
It will be appreciated that in the embodiment provided by the present invention, the test tunnel comprises a high pressure fan 1 providing wind speed to the tunnel, and a heater 2 controlling the temperature of the tunnel.
Further, in the embodiment provided by the present invention, at least one temperature sensor 3 for detecting the temperature of the passage is included, and the temperature sensor 3 is disposed downstream of the heater 2 in the passage.
Further, in the embodiment provided by the utility model, the temperature equalizer 4 is included, and the temperature equalizer 4 is arranged in the channel and is upstream of the temperature sensor 4. If necessary, a plurality of temperature sensors 4 may be provided in each pipe, respectively placed upstream and downstream of the heater 2 and upstream of the temperature equalizer 4.
Further, in the embodiment provided by the utility model, the pressure sensor 5 is included, and the pressure sensor 5 is arranged in the channel downstream of the high-pressure fan 1.
Further, in the embodiment provided by the present invention, an anemometer 6 is included, and the anemometer 6 is disposed in the passage downstream of the high pressure fan 1.
It is understood that in the embodiment provided by the present invention, the switching device includes a pneumatic push rod 7, a sliding mechanism 8, and a clamp (not shown in the figure); the fire sensor 81 to be detected is arranged on the sliding mechanism 8, and the pneumatic push rod 7 is connected with the side surface of the fire sensor 81.
It should be noted that the clamp is customized to the sensor appearance and electrical connections to facilitate clamping of the sensor.
Further, in the embodiment provided by the present invention, the sliding mechanism 8 is provided with a channel partition plate, so that each air channel is kept independent and sealed.
Further, in the embodiment provided by the present invention, a cooling device 9 for reducing the heat of the air in the test channel is included; the cooling device 9 is arranged at the downstream of the switching device, and the cooling device is an air-water heat exchanger.
After high-temperature hot air passes through the testing section channel and the pipeline, heat in the air is transferred to cooling water by the air-water heat exchanger, and the cooled air (which can contain residual heat) returns to the fan to form a circulation loop
It is understood that in the embodiment provided by the utility model, a control system is included, and the control system is connected with the test channel and the switching device.
Optionally, in the embodiment provided by the present invention, the control system includes a test system 10 and an upper computer 11: the rear end of a high-pressure fan of each test channel is provided with a pressure/wind speed/temperature sensor, the rear end of a heater and the front end of a test fixture are provided with temperature sensors, the rear end of a wind heat exchanger is provided with a pressure/temperature monitoring sensor, signals of all the sensors are collected by a measurement and control industrial personal computer and a collection board card of an upper computer 11, and control instructions are sent to a fan frequency converter 12, a heater power regulation controller 13 and the like in an electrical control cabinet according to temperature and wind speed control requirements and a PID control technology;
optionally, in the embodiment provided by the present invention, the present invention further includes an electrical control cabinet, where the electrical control cabinet mainly includes a system power supply and protection device, a power adjustment controller, a fan frequency converter, and the like, and is used to supply power to each part, and simultaneously receive instructions of the test system and the upper computer, and perform adjustment control on the heater and the high-pressure fan of each test channel;
optionally, in the embodiment provided by the present invention, other supporting facilities are included: the system mainly comprises a power supply/control/test matching cable and a cooling pipeline of the wind-water heat exchanger, and also comprises a coating material of a pipeline system, so that the loss of heat is reduced as much as possible;
the utility model also provides a detection method of the aircraft fire alarm sensor, which comprises the following steps:
s100: respectively establishing test channels with different temperature intervals in the three test channels, wherein the temperature of each test channel is continuously adjustable in the temperature interval;
s200: in step S100, the same wind speed interval is set in each test channel, and the wind speed in each test channel is continuously adjustable;
s300: the switching device controls the fire alarm sensor to be tested to be switched in different testing channels.
Further, in the embodiment provided by the utility model, three temperature fields are established, the temperature of each temperature field is continuously adjustable in a temperature control range, and the control precision is +/-3 ℃; the wind speed of each test field is continuously adjustable within the range of 0-5 m/s, and the control precision is +/-5%; the switching time between temperature fields is less than 1 s; through switching of the temperature field, timing is started when the sensor enters the temperature field, and the alarm value and the alarm inertia time of the sensor are tested; the test conditions can be set in advance, except for necessary operations such as replacing the sensor, starting the test and the like, all the test processes have no human intervention, and the test results can be automatically stored; the number of tests per time is not less than 10.
Examples
Three sets of heaters with different powers, a high-pressure fan, a temperature equalizer and an air-water heat exchanger are used for establishing three test channels with different temperatures and wind speeds of 80-140 ℃, 340-360 ℃ and 640-650 ℃, a switching device is arranged on the test channels, the switching device comprises a pneumatic push rod, a sliding mechanism (comprising an air channel partition plate, so that each air channel is independent and sealed) and a fire sensor test fixture, the test fixture is controlled to move on the sliding mechanism through the pneumatic push rod, the positions of the test sensors in the three test channels are further controlled, meanwhile, the air channel partition plate can independently and hermetically seal each test channel, the fire sensor test fixture is customized according to the appearance and the electrical connection requirements of the sensors, and the test of 12 sensors can be carried out; the temperature field of 640-650 ℃ is heated by a two-stage heater, so that a stable temperature field is more easily generated, and the preheating time is shorter; all the test channels are connected by using a pipeline system;
the device comprises a high-pressure fan (capable of adjusting the air speed through a frequency converter in an electrical control cabinet) for blowing air to a heater (capable of controlling and adjusting the temperature through a power adjuster in the electrical control cabinet), stable temperature fields with different temperature ranges and air speed ranges are respectively established in a plurality of test channels (the quantity of the stable temperature fields can be adjusted according to the technical requirements of specific tested sensors), a switching device which is jointly composed of a pneumatic push rod, a sliding mechanism (comprising air channel partition plates and used for enabling each air channel to be independent and sealed) and a fire alarm sensor detection clamp is adopted, the rapid instantaneous switching of a plurality of tested fire alarm sensors in different temperature fields is realized, the starting time of a time switch and the time of the fire alarm sensors for sending alarm signals are recorded, and therefore the actual technical parameters such as the alarm inertia time, the alarm temperature value and the like of the fire alarm sensors are calculated. After high-temperature hot air passes through the testing section channel and the pipeline, heat in the air is transferred to cooling water by a cooling device (an air-water heat exchanger), and the cooled air (which can contain residual heat) returns to the fan to form a circulating loop.
Before implementation, three test conditions such as temperature, wind speed value and the like of a test field are set according to test requirements, the system automatically completes preheating, the replacement prompt of a tested piece is realized, after a test is started, all test processes are fully automatically completed, the device can automatically store test results, test data is analyzed and interpreted, and a production report is output.
While embodiments of the utility model have been disclosed above, it is not limited to the applications listed in the description and the embodiments. It can be applied to all kinds of fields suitable for the present invention. Additional modifications will readily occur to those skilled in the art. It is therefore intended that the utility model not be limited to the exact details and illustrations described and illustrated herein, but fall within the scope of the appended claims and equivalents thereof.
Claims (8)
1. The detection device for the fire alarm sensor of the airplane is characterized by comprising at least two test channels for simulating the temperature of a fire scene and a switching device for switching the test channels of the fire alarm sensor at different temperatures;
the test channel comprises a high-pressure fan for providing air speed for the channel and a heater for controlling the temperature of the pipeline;
the switching device comprises a pneumatic push rod, a sliding mechanism and a clamp; the fire alarm sensor to be detected is arranged on the sliding mechanism, and the pneumatic push rod is connected with the side face of the fire alarm sensor.
2. An aircraft fire sensor detection apparatus as claimed in claim 1 including at least one temperature sensor for sensing the temperature of the tunnel, said temperature sensor being disposed in the tunnel downstream of the heater.
3. An aircraft fire sensor detection apparatus as claimed in claim 2 including a temperature equalizer disposed in the passageway upstream of the temperature sensor.
4. An aircraft fire sensor detection unit as claimed in claim 2 including a pressure sensor disposed in the passageway downstream of the high pressure blower.
5. An aircraft fire sensor detection apparatus as claimed in claim 2 including an anemometer disposed in the passageway downstream of the high pressure fan.
6. An aircraft fire sensor testing device according to claim 1, wherein a channel partition is provided on said sliding mechanism.
7. An aircraft fire sensor detection unit as claimed in claim 1 including cooling means for reducing the heat of the air in the test channel;
the cooling device is disposed downstream of the switching device.
8. An aircraft fire sensor detection device as claimed in claim 1 including a control system, said control system being connected to the test channel and the switching means.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121355116.9U CN215984619U (en) | 2021-06-18 | 2021-06-18 | Aircraft fire alarm sensor detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121355116.9U CN215984619U (en) | 2021-06-18 | 2021-06-18 | Aircraft fire alarm sensor detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215984619U true CN215984619U (en) | 2022-03-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121355116.9U Active CN215984619U (en) | 2021-06-18 | 2021-06-18 | Aircraft fire alarm sensor detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215984619U (en) |
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2021
- 2021-06-18 CN CN202121355116.9U patent/CN215984619U/en active Active
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