CN114383756B - Temperature measurement sensing device for aircraft solar radiation test and parameter optimization method thereof - Google Patents
Temperature measurement sensing device for aircraft solar radiation test and parameter optimization method thereof Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 31
- 238000009529 body temperature measurement Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000005457 optimization Methods 0.000 title claims abstract description 11
- 238000004140 cleaning Methods 0.000 claims abstract description 71
- 239000000523 sample Substances 0.000 claims abstract description 43
- 230000001276 controlling effect Effects 0.000 claims description 16
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- 238000005259 measurement Methods 0.000 claims description 5
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
-
- B08B1/143—
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- B08B1/32—
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/08—Protective devices, e.g. casings
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/08—Protective devices, e.g. casings
- G01K1/12—Protective devices, e.g. casings for preventing damage due to heat overloading
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/16—Special arrangements for conducting heat from the object to the sensitive element
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20209—Thermal management, e.g. fan control
Abstract
The invention discloses a temperature measurement sensing device for aircraft solar radiation testing and a parameter optimization method thereof, belonging to the technical field of aircraft testing, wherein the device comprises a radiation shield, a temperature measurement component, a micro fan, a support component and a PLC (programmable logic controller); the radiation-proof shield comprises an outer radiation-proof shield and an inner radiation-proof shield which are sleeved together; the temperature measurement assembly comprises a temperature sensor probe, a heat conduction fin and a cleaning assembly, the temperature sensor probe and the micro fan are arranged in the inner radiation shield, the heat conduction fin is arranged on the temperature sensor probe, and the cleaning assembly is used for cleaning the heat conduction fin; the support component comprises a base and a vertical rod, one end of the vertical rod is connected with the outer radiation-proof cover, the other end of the vertical rod is connected with the base, an adjusting motor for driving the vertical rod to rotate is arranged in the base, and the PLC is electrically connected with the cleaning component and the adjusting motor respectively; the temperature testing device is reasonable in structural design, solves the problem of low temperature testing accuracy of the plane in the solar radiation environment, and is suitable for popularization and application.
Description
Technical Field
The invention relates to the technical field of airplane testing, in particular to a temperature measurement sensing device for airplane solar radiation testing and a parameter optimization method thereof.
Background
When the aircraft is used for a solar irradiation test in a laboratory climatic environment, in order to verify the reliability of the performance of each system of the aircraft at the corresponding environmental temperature and avoid the interference of solar radiation on a temperature sensor probe, an efficient temperature sensor is needed to provide accurate environmental temperature in time, the temperature is fed back to a temperature control system for temperature regulation, and the development of the solar irradiation test is promoted rapidly.
However, in the prior art, when the temperature sensor is used to measure the ambient temperature, the thermal effect of solar radiation may affect the temperature sensor probe, resulting in the measured temperature being higher than the actual ambient temperature. For environmental laboratories with very low air flow speed and natural condition solar irradiation tests, the traditional louver box has the defects of large volume and difficult installation, and the shadow of the louver box can influence the temperature measurement on the surface of a test piece; the shutter generally adopts the natural convection form of air, and the condition that test environment air velocity is very low and causes the air of device inside and outside to have asynchronous state has firstly increased measuring error, has secondly reduced the response speed of probe. The general radiation shield can effectively avoid direct radiation of the sun to the temperature sensor probe, but the reflectivity of the general radiation shield is difficult to reach 100%, so that the absorbed heat can affect the temperature sensor probe in a thermal radiation mode.
Disclosure of Invention
Aiming at the technical problems, the invention provides a temperature measurement sensing device for an aircraft solar radiation test and a parameter optimization method thereof.
The technical scheme of the invention is as follows: the temperature measurement sensing device for the airplane solar radiation test comprises a radiation shield, a temperature measurement component, a micro fan, a support component and a PLC (programmable logic controller); the radiation shield comprises an outer radiation shield and an inner radiation shield, both the outer radiation shield and the inner radiation shield are tubular structures, the inner radiation shield is movably sleeved inside the outer radiation shield, an airflow channel is formed between the inner radiation shield and the outer radiation shield, and the tail ends of the inner radiation shield and the outer radiation shield are movably clamped through a buckle;
the temperature measuring assembly comprises a temperature sensor probe, a plurality of heat conducting fins and a cleaning assembly, the temperature sensor probe is fixedly arranged inside the inner radiation shield through a first support, and the heat conducting fins are uniformly distributed outside the temperature sensor probe along the circumferential direction; the cleaning assembly is movably arranged in the inner radiation shield and is used for cleaning the surfaces of the heat conducting fins;
the miniature fan is arranged at the tail end of the inner radiation-proof cover through a second bracket;
The supporting component comprises a base and a vertical rod, the bottom end of the vertical rod is inserted into the base, an adjusting fluted disc is arranged at the bottom end of the vertical rod, the top end of the vertical rod is connected with the outer wall of the outer radiation shield, a rotating seat is arranged at the joint of the vertical rod and the base, an adjusting motor is arranged in the base, and an output shaft of the adjusting motor is provided with an adjusting gear which is meshed with the adjusting fluted disc;
the PLC controller is respectively and electrically connected with the cleaning assembly and the adjusting motor.
Further, the cleaning assembly comprises a cleaning sleeve, a connecting screw rod, a driving gear ring and a cleaning motor; the number of the cleaning sleeves and the connecting screw rods is consistent with that of the heat conducting fins, and sliding grooves corresponding to the heat conducting fins in number and position are formed in the first support; each cleaning sleeve is respectively clamped on each heat conduction fin in a sliding manner, a deflector rod is arranged on the side wall of each cleaning sleeve, the end part of the deflector rod penetrates through the corresponding sliding groove, and a threaded seat is arranged at the end part of the deflector rod; each connecting screw rod is rotatably clamped on one side, far away from the cleaning sleeve, of the first support, one end of each connecting screw rod is in threaded connection with each threaded seat, and the other end of each connecting screw rod is provided with a first small gear which is a bevel gear; the driving gear ring is rotationally clamped in the inner radiation shield and is respectively meshed and connected with each first pinion; the cleaning motor is fixedly arranged inside the inner radiation shield, a second pinion is arranged on an output shaft of the cleaning motor, the second pinion is in meshed connection with the driving gear ring, and the cleaning motor is electrically connected with the PLC; during the use, utilize the clean motor of PLC controller control to start, it is rotatory to drive the drive ring gear through the second pinion on the clean motor to make each first pinion drive the connecting screw who corresponds rotatory, the screw thread seat drives the clean cover through the driving lever and removes on the heat conduction fin this moment, realizes the cleanness to the heat conduction fin surface, improves the heat conduction effect of heat conduction fin.
Furthermore, the inner side of the cleaning sleeve is provided with the cleaning cotton layer, and the cleaning effect of the cleaning sleeve is favorably improved by arranging the cleaning cotton layer.
Furthermore, two long edges of the cleaning sleeve are connected through a movable block, the two long edges of the cleaning sleeve are respectively clamped in the movable block through inserting rods, each inserting rod is sleeved with a return spring, one end of each return spring is clamped with the inner wall of the corresponding inserting rod, and the other end of each return spring is abutted against the inner wall of the corresponding movable block; through setting up reset spring for two long limits of clean cover are close to each other under the effect of inserted bar, thereby have guaranteed the reliability of clean cover work.
Furthermore, the outer radiation shield is formed by connecting a plurality of arc-shaped expansion plates and a plurality of arc-shaped connecting plates end to end, the connecting plates are movably inserted into two adjacent expansion plates, and the expansion plates are formed by hinging a plurality of support plates; the buckle is extending structure, through setting up the outer radiation shield that forms by several expansion plate and connecting plate end to end connection, is favorable to adjusting airflow channel's effective area of admitting air according to actual solar radiation condition to effectively guarantee the synchronism of the inside and outside air of radiation shield.
Furthermore, flexible radiation-proof strips are arranged on the inner sides of the hinged positions of the two adjacent support plates; through setting up flexible radiation protection strip, be favorable to improving the radiation protection effect of extension board.
Furthermore, expansion support rods are slidably clamped at positions corresponding to the end parts of the inner radiation-proof covers and the expansion plates, one end of each expansion support rod is fixedly connected with the corresponding expansion plate, a rack is arranged at the other end of each expansion support rod, an expansion motor is arranged on the second support through a motor frame, a gear roller is arranged on an output shaft of the expansion motor, the gear roller is meshed with each rack, and the expansion motor is electrically connected with the PLC; during the use, utilize the fluted roller on the expansion motor to drive each rack and remove to make each expansion branch promote the outside expansion of expansion board that corresponds, improve the regulation efficiency of outer radiation shield.
Furthermore, the top end of the vertical rod is movably hinged with the outer wall of the outer radiation shield, the side wall of the vertical rod is movably hinged with an electric push rod, the other end of the electric push rod is movably hinged with the outer wall of the outer radiation shield, the electric push rod is electrically connected with the PLC, and the pitching angle of the radiation shield can be adjusted by utilizing the electric push rod, so that the radiation shield can be adaptively adjusted according to the direction of solar radiation.
Furthermore, the heat-conducting fins are sleeved on the temperature sensor probe through a heat-conducting sleeve; through setting up the heat conduction cover, can improve heat conduction fin's heat conduction effect to make the temperature sensor probe can reach the actual temperature of air fast, improve the response speed of temperature sensor probe.
The invention also provides a parameter optimization method of the temperature measurement sensing device for the aircraft solar radiation test, which comprises the following steps:
s1, moving the device to a position to be measured, and supplying power to each electric device of the device by using an external power supply;
s2, blocking solar radiation by using an outer radiation shield and generating heat energy at the same time;
s3, reflecting heat energy to the inside of the air flow channel by the inner radiation shield;
s4, controlling the micro fan to be started through the PLC, and controlling the wind speed of the micro fan to be 3.5-6.8 m/S; the convection of air in the inner radiation shield is accelerated, so that the air enters from the left side and is discharged from the right side of the inner radiation shield, and the influence of the heat radiation of the fan on the air temperature is reduced;
s5, generating heat by utilizing the continuous contact of the heat conduction fins with flowing air, transferring the heat to the temperature sensor probe, accelerating the actual temperature of the air measured by the temperature sensor probe, and controlling the response time of the temperature sensor probe to be 2-5 min, so that the temperature sensor probe makes quick and accurate response;
s6, measuring the temperature of the air under the irradiation of the sun according to the real-time reflection of the temperature sensor probe;
s7, controlling a regulating motor to start through a PLC (programmable logic controller) according to the sun irradiation direction and the wind direction of a measuring place, driving a regulating fluted disc on a vertical rod to rotate by utilizing a regulating gear on the regulating motor, driving a radiation shield to rotate by utilizing the vertical rod, regulating the direction of the radiation shield in real time, and controlling the included angle between the radiation shield and an initial position to be-30 degrees;
And S8, after the device is used for a period of time, the PLC controller controls the cleaning assembly to start, and the surfaces of the heat conducting fins are cleaned.
Compared with the prior art, the invention has the beneficial effects that:
firstly, the invention utilizes the radiation shield structure consisting of the outer radiation shield and the inner radiation shield to effectively block the influence of solar radiation on the temperature sensor probe, so that the temperature measured by the temperature sensor probe is closer to the actual temperature, thereby improving the accuracy of the temperature measurement result;
secondly, the invention utilizes the micro fan to form a forced convection environment in the air flow channel inside the radiation shield, so that the air inside and outside the radiation shield reaches a synchronous state, and meanwhile, the influence of heat dissipation on the measurement result when the micro fan operates is avoided;
thirdly, the heat conducting fins are distributed on the circumferential direction of the temperature sensor probe, so that the response speed of the temperature sensor probe is improved; meanwhile, the cleaning assembly is arranged on the heat conduction fins, so that the influence of impurities such as dust and the like attached to the heat conduction fins on the heat conduction efficiency of the heat conduction fins is reduced, and the measurement precision of the device is improved;
fourthly, the outer radiation shield and the inner radiation shield are connected through the buckle, so that the outer radiation shield and the inner radiation shield are more convenient to maintain, and the practicability of the radiation shield is improved; the invention solves the problems of low measurement precision, difficult installation and serious test interference of the traditional temperature sensor and improves the accuracy of temperature measurement in the process of aircraft solar radiation test.
Drawings
FIG. 1 is a flow chart of a parameter optimization method of the present invention;
FIG. 2 is a schematic structural view of embodiment 1 of the present invention;
FIG. 3 is a schematic structural view of example 9 of the present invention;
figure 4 is a schematic view of the connection of the outer radiation shield to the inner radiation shield of the present invention;
FIG. 5 is an enlarged schematic view at A of FIG. 4 of the present invention;
fig. 6 is a schematic view of the connection of the expansion struts of the present invention to expansion plates;
FIG. 7 is a schematic structural view of a connection plate of the present invention;
FIG. 8 is a schematic view of the connection of the first bracket of the present invention to the inner shield;
FIG. 9 is a schematic view of the connection of the connecting screw of the present invention to the first bracket;
FIG. 10 is a schematic view of the construction of the cleaning sleeve and heat conductive fins of the present invention;
wherein, 1-radiation shield, 10-outer radiation shield, 11-inner radiation shield, 12-airflow channel, 13-buckle, 14-expansion plate, 15-connecting plate, 150-supporting plate, 16-flexible radiation shield strip, 17-expansion supporting rod, 170-rack, 18-expansion motor, 180-motor rack, 181-toothed roller, 2-temperature measuring component, 20-temperature sensor probe, 200-first bracket, 2000-sliding groove, 21-heat conducting fin, 210-heat conducting sleeve, 22-cleaning component, 220-cleaning sleeve, 2200-driving lever, 2201-screw seat, 2202-cleaning cotton layer, 2203-movable block, 2204-inserted bar, 2205-reset spring, 221-connecting screw, 2210-first pinion, 222-driving gear ring, 223-cleaning motor, 2230-second pinion, 3-micro fan, 30-second bracket, 4-supporting component, 40-base, 41-vertical rod, 410-adjusting gear disc, 411-rotary seat, 42-adjusting motor, 420-adjusting gear and 43-electric push rod.
Detailed Description
Example 1
The temperature measurement sensing device for the aircraft solar radiation test shown in fig. 2 comprises a radiation shield 1, a temperature measurement component 2, a micro fan 3, a support component 4 and a PLC controller; the radiation shield 1 comprises an outer radiation shield 10 and an inner radiation shield 11, the outer radiation shield 10 and the inner radiation shield 11 are both tubular structures, the inner radiation shield 11 is movably sleeved inside the outer radiation shield 10, an airflow channel 12 is formed between the inner radiation shield 11 and the outer radiation shield 10, and the tail ends of the inner radiation shield 11 and the outer radiation shield 10 are movably clamped through a buckle 13; the inner radiation shield 11 and the outer radiation shield 10 are both made of stainless steel material with polished outer surfaces;
as shown in fig. 2, the temperature measuring assembly 2 includes a temperature sensor probe 20, 8 heat conducting fins 21 and a cleaning assembly 22, the temperature sensor probe 20 is fixedly disposed inside the inner radiation shield 11 through a first bracket 200, the number of the heat conducting fins 21 is 8, the heat conducting fins 21 are uniformly distributed outside the temperature sensor probe 20 along the circumferential direction, and the heat conducting fins 21 are made of aluminum material with high thermal conductivity; the cleaning assembly 22 is movably arranged inside the inner radiation shield 11 and is used for cleaning the surfaces of the heat conducting fins 21;
As shown in fig. 2, the micro fan 3 is arranged at the tail end of the inner radiation shield 11 through a second bracket 30;
as shown in fig. 2, the supporting assembly 4 includes a base 40 and an upright rod 41, the bottom end of the upright rod 41 is inserted into the base 40, and the bottom end of the upright rod 41 is provided with an adjusting fluted disc 410, the top end of the upright rod 41 is connected with the outer wall of the outer radiation shield 10, the joint of the upright rod 41 and the base 40 is provided with a rotating base 411, the base 40 is internally provided with an adjusting motor 42, and an output shaft of the adjusting motor 42 is provided with an adjusting gear 420 engaged with the adjusting fluted disc 410;
the PLC is respectively electrically connected with the cleaning component 22 and the adjusting motor 42; the PLC controller, temperature sensor probe 20, cleaning assembly 22 and adjustment motor 42 are all commercially available products.
Example 2
The embodiment describes a parameter optimization method of the temperature measurement sensing device for the aircraft solar radiation test in embodiment 1, which includes the following steps:
s1, moving the device to a position to be measured, and supplying power to each electric device of the device by using an external power supply;
s2, blocking solar radiation by the outer radiation shield 10 and generating heat energy at the same time;
s3, reflecting heat energy to the inside of the airflow channel 12 by the inner radiation shield 11;
s4, controlling the micro fan 3 to be started through the PLC, and controlling the wind speed of the micro fan 3 to be 3.5 m/S; the air convection inside the inner radiation shield 11 is accelerated, so that air enters from the left side and is discharged from the right side of the inner radiation shield 11, and the influence of the heat dissipation of the fan on the air temperature is reduced;
S5, generating heat by continuously contacting flowing air through the heat conduction fins 21, transferring the heat to the temperature sensor probe 20, accelerating the actual temperature of the air measured by the temperature sensor probe 20, and controlling the response time of the temperature sensor probe 20 to be 2min, so that the temperature sensor probe 20 can make quick and accurate response;
s6, measuring the temperature of the air under the irradiation of the sun according to the real-time reflection of the temperature sensor probe 20;
s7, controlling the start of the adjusting motor 42 through the PLC according to the sun irradiation direction and the wind direction of the measurement area, driving the adjusting fluted disc 410 on the upright rod 41 to rotate by using the adjusting gear 420 on the adjusting motor 42, driving the radiation shield 1 to rotate by using the upright rod 41, adjusting the direction of the radiation shield 1 in real time, and controlling the included angle between the radiation shield 1 and the initial position to be-30 degrees;
and S8, after the device is used for a period of time, the PLC controller controls the cleaning assembly 22 to start, and the surface of each heat conduction fin 21 is cleaned.
Example 3
The present embodiment is different from embodiment 2 in that:
in step S4, the wind speed of the micro fan 3 is controlled to be 6.8 m/S;
in step S5, the response time of the temperature sensor probe 20 is controlled to 5 min;
in step S7, the angle between the radiation shield 1 and the initial position is controlled to be 30 °.
Example 4
The present embodiment is different from embodiment 1 in that:
as shown in fig. 4, 5, 8, 9 and 10, the cleaning assembly 22 includes a cleaning sleeve 220, a connecting screw 221, a driving gear ring 222 and a cleaning motor 223; the number of the cleaning sleeves 220 and the number of the connecting screws 221 are corresponding to the number of the heat conducting fins 21, and the first bracket 200 is provided with sliding grooves 2000 corresponding to the number and the positions of the heat conducting fins 21; each cleaning sleeve 220 is respectively connected to each heat conducting fin 21 in a sliding and clamping mode, a shifting rod 2200 is arranged on the side wall of each cleaning sleeve 220, the end of the shifting rod 2200 penetrates through the corresponding sliding groove 2000, and a threaded seat 2201 is arranged at the end of the shifting rod 2200; each connecting screw rod 221 is rotatably clamped on one side of the first bracket 200 far away from the cleaning sleeve 220, one end of each connecting screw rod 221 is in threaded connection with each threaded seat 2201, the other end of each connecting screw rod 221 is provided with a first pinion 2210, and each first pinion 2210 is a bevel gear; the driving gear ring 222 is rotationally clamped inside the inner radiation shield 11 and is respectively meshed with each first pinion 2210; the cleaning motor 223 is fixedly arranged inside the inner radiation shield 11, a second pinion 2230 is arranged on an output shaft of the cleaning motor 223, the second pinion 2230 is meshed with the driving gear ring 222, and the cleaning motor 223 is electrically connected with the PLC; a cleaning cotton layer 2202 is arranged at the inner side of the cleaning sleeve 220; two long limits of clean cover 220 are passed through the movable block 2203 and are connected, and two long limits of clean cover 220 pass through inserted bar 2204 joint respectively inside the movable block 2203, all overlap on each inserted bar 2204 and be equipped with reset spring 2205, reset spring 2205 one end and inserted bar 2204 inner wall joint, the other end and movable block 2203's inner wall butt, and clean motor 223 is the product of selling.
Example 5
The present embodiment describes a parameter optimization method for a temperature measurement sensing device in an aircraft solar radiation test in embodiment 4, which is different from embodiment 2 in that:
in step S8, the PLC controller controls the cleaning motor 223 to start, and the second pinion 2230 on the cleaning motor 223 drives the driving gear ring 222 to rotate, so that each first pinion 2210 drives the corresponding connecting screw 221 to rotate, and at this time, the screw seat 2201 drives the cleaning sleeve 220 to move on the heat-conducting fins 21 through the shift lever 2200, thereby achieving the purpose of cleaning the surfaces of the heat-conducting fins 21.
Example 6
The present embodiment is different from embodiment 1 in that:
as shown in fig. 6 and 7, the outer radiation shield 10 is formed by connecting 4 arc-shaped expansion plates 14 and 4 arc-shaped connecting plates 15 end to end, the connecting plate 15 is movably inserted into two adjacent expansion plates 14, and the expansion plates 15 are formed by hinging 5 support plates 150; the buckle 13 is of a telescopic structure, and the inner sides of the hinged positions of the two adjacent support plates 150 are provided with flexible radiation-proof strips 16; the flexible radiation-proof strip 16 is arranged, so that the radiation-proof effect of the support plate 150 is improved; the equal slip joint in 11 tip of interior radiation protection cover and each expansion board 14 position correspondence department has expansion branch 17, each expansion branch 17 one end respectively with the expansion board 14 fixed connection who corresponds the department, each expansion branch 17 other end all is provided with rack 170, be provided with expansion motor 18 through motor frame 180 on the second support 30, be provided with fluted roller 181 on expansion motor 18's the output shaft, fluted roller 181 all meshes with each rack 170 and is connected, expansion motor 18 and PLC controller electric connection, expansion motor 18 is the product on the market.
Example 7
The present embodiment describes a parameter optimization method for a temperature measurement sensing device for aircraft solar radiation testing in embodiment 6, which is different from embodiment 2 in that:
in step S7, according to actual solar radiation conditions, the PLC controller controls the expansion motor 18 to start, and the toothed roller 181 on the expansion motor 18 drives each rack 170 to move, so that each expansion support rod 17 pushes the corresponding expansion plate 14 to expand outward, and the distance between the expansion plate 14 and the inner radiation shield 11 is controlled to be 4cm, thereby adjusting the effective air intake area of the air flow channel 12.
Example 8
This embodiment is different from embodiment 7 in that:
in step S7, the distance between the expansion board 14 and the inner radiation shield 11 is controlled to be 6 cm.
Example 9
The present embodiment is different from embodiment 1 in that:
as shown in fig. 3, the top end of the vertical rod 41 is movably hinged to the outer wall of the outer radiation shield 10, an electric push rod 43 is movably hinged to the side wall of the vertical rod 41, the other end of the electric push rod 43 is movably hinged to the outer wall of the outer radiation shield 10, the electric push rod 43 is electrically connected to the PLC controller, and the electric push rod 43 is a commercially available product.
Example 10
The method for optimizing the parameters of the temperature measurement sensing device for the aircraft solar radiation test in the embodiment 9 is different from the method in the embodiment 2 in that the method further comprises the steps of S9,
S9, controlling the electric push rod 43 to start through the PLC according to the measured solar radiation direction, adjusting the pitch angle of the radiation shield 1 through the electric push rod 43, and controlling the included angle between the radiation shield 1 and the horizontal plane to be-30 degrees.
Example 11
The present embodiment is different from embodiment 10 in that:
in step S9, the angle between the radiation shield 1 and the horizontal plane is controlled to be 30 °.
Example 12
The present embodiment is different from embodiment 1 in that:
as shown in fig. 4, the heat-conducting fins 21 are sleeved on the temperature sensor probe 20 through the heat-conducting sleeve 210.
Claims (8)
1. The temperature measurement sensing device for the airplane solar radiation test is characterized by comprising a radiation shield (1), a temperature measurement component (2), a micro fan (3), a support component (4) and a PLC (programmable logic controller); the radiation protection shield (1) comprises an outer radiation protection shield (10) and an inner radiation protection shield (11), the outer radiation protection shield (10) and the inner radiation protection shield (11) are both of tubular structures, the inner radiation protection shield (11) is movably sleeved inside the outer radiation protection shield (10), an airflow channel (12) is formed between the inner radiation protection shield (11) and the outer radiation protection shield (10), and the tail ends of the inner radiation protection shield (11) and the outer radiation protection shield (10) are movably clamped through a buckle (13);
The temperature measurement assembly (2) comprises a temperature sensor probe (20), a plurality of heat conduction fins (21) and a cleaning assembly (22), wherein the temperature sensor probe (20) is fixedly arranged inside the inner radiation shield (11) through a first support (200), the heat conduction fins (21) are arranged in a plurality, and the heat conduction fins (21) are uniformly distributed outside the temperature sensor probe (20) along the circumferential direction; the cleaning component (22) is movably arranged inside the inner radiation shield (11); the cleaning assembly (22) comprises a cleaning sleeve (220), a connecting screw rod (221), a driving gear ring (222) and a cleaning motor (223); the number of the cleaning sleeves (220) and the number of the connecting screws (221) are correspondingly consistent with that of the heat-conducting fins (21), and sliding grooves (2000) corresponding to the heat-conducting fins (21) in number and positions are formed in the first support (200); each cleaning sleeve (220) is respectively connected to each heat conduction fin (21) in a sliding and clamping mode, a shifting rod (2200) is arranged on the side wall of each cleaning sleeve (220), the end portion of the shifting rod (2200) penetrates through the corresponding sliding groove (2000), and a threaded seat (2201) is arranged at the end portion of the shifting rod (2200); each connecting screw rod (221) is rotationally clamped on one side, far away from the cleaning sleeve (220), of the first support (200), one end of each connecting screw rod (221) is in threaded connection with each threaded seat (2201), and the other end of each connecting screw rod is provided with a first pinion (2210); the driving gear ring (222) is rotationally clamped inside the inner radiation shield (11) and is respectively in meshed connection with each first pinion (2210); the cleaning motor (223) is fixedly arranged inside the inner radiation shield (11), a second pinion (2230) is arranged on an output shaft of the cleaning motor (223), and the second pinion (2230) is in meshed connection with the driving gear ring (222);
The micro fan (3) is arranged at the tail end of the inner radiation-proof cover (11) through a second bracket (30);
the supporting assembly (4) comprises a base (40) and a vertical rod (41), the bottom end of the vertical rod (41) is inserted into the base (40), an adjusting fluted disc (410) is arranged at the bottom end of the vertical rod (41), the top end of the vertical rod (41) is connected with the outer wall of the outer radiation shield (10), a rotating seat (411) is arranged at the joint of the vertical rod (41) and the base (40), an adjusting motor (42) is arranged in the base (40), and an output shaft of the adjusting motor (42) is provided with an adjusting gear (420) which is meshed with the adjusting fluted disc (410);
the PLC is respectively electrically connected with the cleaning motor (223) and the adjusting motor (42).
2. Temperature measuring and sensing device for aircraft solar radiation testing, according to claim 1, characterized in that a layer of cleaning cotton (2202) is arranged inside the cleaning sleeve (220).
3. The temperature measurement sensing device for the aircraft solar radiation test is characterized in that two long edges of the cleaning sleeve (220) are connected through a movable block (2203), the two long edges of the cleaning sleeve (220) are respectively clamped inside the movable block (2203) through an insertion rod (2204), each insertion rod (2204) is sleeved with a return spring (2205), one end of each return spring (2205) is clamped with the inner wall of the insertion rod (2204), and the other end of each return spring abuts against the inner wall of the movable block (2203).
4. The temperature measurement sensing device for aircraft solar radiation testing according to claim 1, characterized in that the outer radiation shield (10) is formed by connecting a plurality of arc-shaped expansion plates (14) and a plurality of arc-shaped connecting plates (15) end to end, the connecting plates (15) are movably inserted into two adjacent expansion plates (14), and the connecting plates (15) are formed by mutually hinging a plurality of supporting plates (150); the buckle (13) is of a telescopic structure.
5. The aircraft solar radiation test temperature measurement sensing device according to claim 4, wherein the flexible radiation protection strip (16) is arranged on the inner side of the hinge of two adjacent support plates (150).
6. The aircraft solar radiation test temperature measurement sensing device according to claim 4, wherein expansion support rods (17) are slidably clamped at positions corresponding to the end portions of the inner radiation shield (11) and the expansion plates (14), one end of each expansion support rod (17) is fixedly connected with the corresponding expansion plate (14), a rack (170) is arranged at the other end of each expansion support rod (17), an expansion motor (18) is arranged on the second support (30) through a motor frame (180), a toothed roller (181) is arranged on an output shaft of the expansion motor (18), the toothed roller (181) is meshed with the racks (170), and the expansion motor (18) is electrically connected with the PLC.
7. The temperature measurement sensing device for the aircraft solar radiation test is characterized in that the top end of the upright rod (41) is movably hinged with the outer wall of the outer radiation shield (10), the side wall of the upright rod (41) is movably hinged with an electric push rod (43), and the other end of the electric push rod (43) is movably hinged with the outer wall of the outer radiation shield (10); the electric push rod (43) is electrically connected with the PLC.
8. The parameter optimization method for the temperature measurement sensing device for the aircraft solar radiation test according to any one of claims 1 to 7, characterized by comprising the following steps:
s1, moving the device to a position to be measured, and supplying power to each electric device of the device by using an external power supply;
s2, blocking solar radiation by using the outer radiation-proof cover (10) and generating heat energy at the same time;
s3, reflecting heat energy to the inside of the air flow channel (12) by the inner radiation shield (11);
s4, controlling the micro fan (3) to be started through the PLC, and controlling the wind speed of the micro fan (3) to be 3.5-6.8 m/S; accelerating the air convection inside the inner radiation shield (11), so that air enters from the left side of the inner radiation shield (11) and is discharged from the right side;
s5, the heat conduction fins (21) are continuously contacted with flowing air to generate heat, the heat is transferred to the temperature sensor probe (20), the actual temperature of the air measured by the temperature sensor probe (20) is accelerated, the response time of the temperature sensor probe (20) is controlled to be 2-5 min, and the temperature sensor probe (20) can make quick and accurate response;
S6, measuring the temperature of the air under the irradiation of the sun according to the real-time reflection of the temperature sensor probe (20);
s7, controlling a regulating motor (42) to start through a PLC (programmable logic controller) according to the sun irradiation direction and the wind direction of a measurement place, driving a regulating fluted disc (410) on a vertical rod (41) to rotate by utilizing a regulating gear (420) on the regulating motor (42), driving the radiation shield (1) to rotate by utilizing the vertical rod (41), regulating the direction of the radiation shield (1) in real time, and controlling the included angle between the radiation shield (1) and the initial position to be-30 degrees;
and S8, after the device is used for a period of time, the PLC controller controls the cleaning assembly (22) to start, and the surface of each heat conduction fin (21) is cleaned.
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