CN113959595A - Missile tail flame jet flow distribution testing method and system - Google Patents
Missile tail flame jet flow distribution testing method and system Download PDFInfo
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Abstract
The invention relates to the field of radiation pyrometry, in particular to a missile tail flame jet flow distribution testing method and a system, wherein the system comprises a checking subsystem and a testing subsystem, and the testing subsystem comprises a processing module positioned at a background and a plurality of testing devices in wireless communication with the processing module; the checking subsystem checks a detection device on the testing device, and sends a testing signal to the testing subsystem after the detection device is checked to be qualified; the testing subsystem sets the testing device in a testing area behind the missile according to the distribution direction, and the method comprises the steps of carrying out multiple performance checks on the temperature sensor, after the testing is passed, arranging the temperature sensor in the area behind the tail flame of the missile through the testing device, carrying out temperature detection on the tail flame of the missile to obtain a testing temperature, and processing the testing temperature to obtain a temperature distribution diagram. The invention can measure the temperature from a plurality of angles and directions, and improves the comprehensiveness and the accuracy of the one-time missile tail flame temperature measurement.
Description
Technical Field
The invention relates to the field of radiation pyrometry, in particular to a missile tail flame jet flow distribution testing method and a system.
Background
The thermal launching is a launching mode that the missile flies away from a launching device by means of thrust generated by an engine of the missile, and is one of important launching modes of the missile. A large amount of high-temperature gas flow can be generated in the missile thermal launching process to form missile tail flames, so that surrounding launching facilities and equipment are easily affected. In order to accurately research the combustion of the solid propellant and the characteristics of a combustion flow field in an engine, the temperature distribution parameter test of the missile tail flame is very important.
At present, the temperature distribution test of the missile tail flame is carried out by a contact method and a non-contact method, the contact method carries out temperature measurement by a thermocouple, a thermal resistance thermometer and the like, the non-contact method mainly carries out temperature measurement by an optical method, and the temperature distribution obtained by the contact method is more real. However, the temperature of the tail flame of the missile is high, and because the temperature distribution range of the tail flame of the missile before the missile is launched is unknown, and the missile launching site may be on the hill, which is easy to cause site ignition, and also is easy to cause component damage in the temperature testing process to cause inaccurate measuring result, and after the missile is launched, due to the limitations of cost, actual requirements, actual operation factors and the like, characteristic analysis is difficult to perform according to the temperature distribution repeated test result during the actual launching of the missile, so that one-time temperature distribution test needs to be performed during the launching of the missile, the temperature distribution test range of the current contact method is predicted according to the power of the tested missile and the experience, the temperature distribution ranges of the tail flames of different types of missiles after being launched are different, and the temperature distribution range is different from the temperature distribution range of the tail flames of the actual missile, so that the problem that the measurement points are omitted in the current contact method temperature distribution test is easily caused.
Disclosure of Invention
The invention aims to provide a missile tail flame jet flow distribution testing system to solve the problem that measurement points are omitted in the existing contact method temperature distribution testing.
The missile tail flame jet flow distribution testing system in the scheme comprises a checking subsystem and a testing subsystem;
the testing subsystem comprises a processing module positioned at a background and a plurality of testing devices in wireless communication with the processing module, and a plurality of vertical measuring points are arranged in the vertical direction of the testing devices;
the checking subsystem is used for checking a detection device of the temperature on the testing device in a preset mode before missile launching, and sending a testing signal to the testing subsystem after the detection device is checked to be qualified;
and after receiving the test signal, the test subsystem arranges the test device in a test area behind the missile according to the distribution direction.
The beneficial effect of this scheme is:
before the temperature distribution test of the missile tail flame is carried out, a plurality of performance verification tests are carried out on a temperature detection device on a test device through a verification subsystem, so that the performance of a temperature sensor can be ensured to be capable of testing a temperature value before the temperature distribution test of the missile tail flame is carried out, and the temperature sensor can be prevented from being incapable of measuring the temperature value of the missile tail flame due to the performance problem of the temperature sensor; after the performance tests pass, the testing device is set according to the distribution directions, the detecting devices are arranged along the vertical direction, temperature values are measured in multiple directions of the three-dimensional space, the coverage of temperature measuring points is improved, the continuity and the accuracy of temperature measurement are improved on the premise that the temperature sensor can bear the temperature of the tail flame of the missile without being damaged, the temperature measurement is carried out from multiple angles and directions, the comprehensiveness of the temperature measurement is improved, and omission of the temperature measuring points of the tail flame of the missile is avoided.
Further, the detection device comprises a temperature sensor and a wire for transmitting detection data of the temperature sensor, the calibration subsystem comprises a calibration module, a temperature-resistant module, a simulation module and a control module, the calibration module is used for heating the temperature sensors according to preset conditions and detecting preset parameters, the temperature-resistant module is used for heating a high-temperature sleeve outside the wire and detecting line information of whether the wire is short-circuited, so as to obtain safe temperature at which the wire is not short-circuited, the simulation module is used for detecting detection capability information of the temperature sensors for the temperature of the tail flame emitted under the simulation conditions, the control module is used for obtaining the preset parameters, the safe temperature and the detection capability information and judging whether the temperature sensors and the high-temperature sleeve reach preset requirements or not according to the preset parameters, the safe temperature and the detection capability information, when the temperature sensors and the high-temperature sleeve reach the preset requirements, and the control module sends a test signal to the test subsystem.
The beneficial effects are that: the temperature sensor and the wire on the testing device can be accurately detected and temperature data can be transmitted by respectively testing multiple performances of the high-temperature sleeve outside the temperature sensor and the wire through the modules, and the temperature data required to be detected can be prevented from being omitted due to damage of the temperature sensor or the wire in the subsequent testing process.
Furthermore, the control module is located the testing arrangement, control module signal connection processing module, the testing arrangement sets up a plurality of temperature sensor after calibration module, temperature resistant module and simulation module test in vertical direction, control module obtains temperature sensor to the measuring value of guided missile tail flame temperature according to predetermineeing sampling frequency, testing arrangement sets up according to the distribution position, the distribution position is for using guided missile tail end face as horizontal starting point, launches the ray of a plurality of angle of predetermineeing along ground at the central point of tail end face from the guided missile center pin to set up a plurality of ground measurement point department on the ray.
The beneficial effects are that: the temperature sensor after being tested is arranged on the testing device to measure the temperature of the tail flame of the missile, the omission of temperature data caused by damage is avoided, a three-dimensional measuring space is formed by multi-point measurement in the horizontal direction and the vertical direction, the distribution of the measuring points can accurately cover the temperature measuring points of the tail flame of the missile, and the omission of the temperature distribution measuring points in the tail flame of the missile is avoided from the two aspects.
Further, testing arrangement includes the base and measures the pole setting, set up the cavity in the base, set firmly the extension seat that is used for supporting control module on the cavity inner wall, extend the seat and extend to center department, it is fixed to set up on the base to measure the pole setting, a plurality of vertical measuring point department that measures the pole setting sets up a plurality of temperature sensor.
The beneficial effects are that: each testing device is provided with a plurality of temperature sensors distributed in the vertical direction, multi-point measurement can be carried out in the vertical direction, a three-dimensional measuring space is formed together with ground measuring points, and the coverage comprehensiveness of the measuring points is improved.
Further, the calibration module and the simulation module perform calibration and inspection on the temperature sensor without the shell.
The beneficial effects are that: the shell of the temperature sensor is removed, and then the temperature sensor is calibrated and checked, so that temperature measurement delay caused by rapid heat absorption of most metal shells can be avoided, and the temperature sensor can be directly contacted with the missile tail flame to rapidly detect the temperature.
Furthermore, the simulation module includes the tail flame analog unit that is used for launching the tail flame and supports the emission support of tail flame analog unit, the simulation condition is that the tail flame of preset temperature is launched to the tail flame analog unit, temperature sensor is located the emission support below and carries out temperature detection.
The beneficial effects are that: the tail flame simulation unit is used for simulating the preset temperature launching tail flame, so that the detection performance of the temperature sensor can be accurately tested before the missile is launched, the temperature value of the temperature sensor can be tested in the missile launching process, and the temperature can be accurately measured in the missile launching process.
Furthermore, the processing module obtains the measured value of the temperature sensor to the temperature of the tail flame of the missile from the control module, establishes a temperature measurement error model according to preset parameters and corrects and compensates the measured value by using the temperature measurement error model, the processing module compares temperature step change curves in the preset parameters to establish a dynamic delay temperature measurement compensation model, the processing module utilizes the dynamic delay temperature measurement compensation model to perform response compensation on the measured value, and the processing module performs data fitting after correcting and compensating the measured value and performing response compensation and draws a temperature distribution map of the tail flame of the missile.
The beneficial effects are that: after the temperature sensor is calibrated, a temperature measurement error model is established according to preset parameters obtained through calibration, the measured value is calibrated and compensated by using the temperature measurement error model, the accuracy of the temperature measured value of the tail flame of the missile is improved, in addition, due to the limitation of physical properties such as specific heat capacity and volume, the influence of factors such as data sampling frequency and analog-to-digital conversion speed, in the temperature measurement process, the temperature sensor has certain delay on the measurement of the rapidly changing temperature, and the dynamic temperature measurement test can calibrate the measurement error of the temperature measurement test on the temperature rising edge.
Further, the preset sampling frequency is 2 ms.
The beneficial effects are that: the control module obtains the measured value according to the preset sampling frequency, the sampling interval is small, the control module can adapt to the smaller missile tail flame acting time, the temperature of the missile tail flame is accurately measured, and the omission of the measured value obtaining is avoided.
The missile tail flame jet flow distribution testing method comprises the following steps:
before the missile is launched, heating a plurality of temperature sensors according to preset conditions respectively, enabling the temperature sensors to detect preset parameters, detecting the detection capability information of the tail flame temperature of the launching of the temperature sensors under the simulation condition, acquiring the safe temperature of a lead without short circuit, heating a high-temperature sleeve outside the lead of the temperature sensors, detecting the line information of whether the lead is short-circuited, judging whether the temperature sensors and the high-temperature sleeve reach the preset requirements according to the preset parameters, the detection capability information and the safe temperature, and sending a test signal when the temperature sensors and the high-temperature sleeve reach the preset requirements;
after receiving the test signals, mounting a plurality of temperature sensors on a test device along the vertical direction, and arranging the test devices in a test area behind the missile according to the distribution direction;
in the missile launching process, a plurality of temperature sensors on a testing device at a plurality of ground measuring points are used for detecting the measured value of the missile tail flame temperature, data fitting is carried out on the measured value, and the temperature distribution map of the missile tail flame is drawn.
The beneficial effect of this scheme is:
before the actual temperature distribution test of the missile launching tail flame is carried out, the temperature sensor and the high-temperature sleeve outside the wire of the temperature sensor are tested, so that the temperature sensor and the high-temperature sleeve outside the wire of the temperature sensor can detect the temperature and transmit a temperature signal under the high-temperature condition of the missile tail flame, and the accuracy of the temperature distribution test is ensured from the test part; after the temperature sensor and the high-temperature sleeve thereof can bear the temperature of the tail flame of the missile, the temperature sensor is used for measuring the temperature in a three-dimensional space formed by a plurality of ground measuring points and a plurality of vertical measuring points, so that the distribution integrity and comprehensiveness of the measuring points are improved, and the temperature distribution measuring accuracy of the tail flame of the missile is improved.
Furthermore, before the missile tail flame is launched, a probe of the temperature sensor with the shell removed is heated for calibration and inspection.
The beneficial effects are that: the temperature sensor with the shell removed is used for detecting the temperature of the tail flame of the missile, the tail flame can be directly contacted for temperature measurement, and the interference of the shell on the temperature measurement can be avoided.
Drawings
FIG. 1 is a schematic block diagram of a missile tail flame jet flow distribution test system in a first embodiment of the invention;
FIG. 2 is a front view of a testing device in a missile tail flame jet distribution testing system according to a first embodiment of the invention;
FIG. 3 is a position distribution diagram of a testing device in the missile tail flame jet distribution testing system according to the embodiment of the invention.
Detailed Description
The following is a more detailed description of the present invention by way of specific embodiments.
Reference numerals in the drawings of the specification include: base 1, measurement pole setting 2, vertical measuring point 3, control module 4.
Example one
The missile tail flame jet flow distribution test system is shown in figure 1: the device comprises a checking subsystem and a testing subsystem, wherein the testing subsystem comprises a processing module positioned at a background and a plurality of testing devices in wireless communication with the processing module, and a plurality of vertical measuring points 3 are arranged in the vertical direction of the testing devices; the testing subsystem is used for testing the temperature detection device on the testing device in a preset mode before the missile is launched, the testing subsystem sends a testing signal to the testing subsystem after the detection device is qualified, and the testing subsystem sets the testing device in a testing area behind the missile according to the distribution direction after receiving the testing signal.
The detection device comprises a temperature sensor and a wire for transmitting detection data of the temperature sensor, the temperature sensor can measure the temperature by using the existing temperature measurement platinum resistor, the calibration subsystem comprises a calibration module, a temperature-resistant module, a simulation module and a control module 4, and the test subsystem comprises a processing module and a plurality of test devices which are positioned at the background.
The calibration module is used for heating the temperature sensors according to preset conditions and detecting preset parameters, wherein the heating is carried out by using the existing hot air gun under the condition that the temperature sensors or the lead and the high-temperature sleeve thereof are positioned at a certain temperature, the hot air gun can be used for a hot air unsoldering table product of the existing SBK850D model, and when the calibration module calibrates the temperature sensors, the preset conditions comprise a sensitivity condition, a static calibration condition and a dynamic temperature measurement condition; the sensitivity condition is that two temperature sensors are used as a group, the positions of the two temperature sensors are oppositely arranged, the temperature difference after the two temperature sensors measure the temperature is used as a preset parameter, and the temperature difference can be represented by the resistance value difference when the two temperature sensors detect the temperature; the static calibration condition is that the hot air gun heats the plurality of temperature sensors at a first temperature and a second temperature respectively, for example, thirty-six temperature sensors are heated at 200 ℃ and 350 ℃ respectively, and the static resistance value obtained by the temperature sensors under the static calibration condition is taken as a preset parameter; the dynamic temperature measurement condition is that the hot air gun heats the temperature sensor by a third temperature and a fourth temperature respectively, for example, the third temperature is 200 ℃, the fourth temperature is 350 ℃, then the temperature sensor is quickly moved out of an air outlet of the hot air gun, an infrared thermometer detects a temperature step change curve of the temperature sensor, the temperature step change curve is used as a preset parameter, each temperature sensor is in signal connection with different pins of the control module 4, and the control module 4 is in signal connection with the processing module.
The temperature resistant module is used for heating a high-temperature sleeve outside a wire and detecting line information of whether the wire is short-circuited, the safe temperature that the wire is not short-circuited is obtained, whether the wire is short-circuited is judged through a resistance value fed back from the temperature sensor by the control module 4, the short-circuit of the wire is judged when the resistance value variation of the temperature sensor received by the control module 4 is larger than a threshold value, whether the wire is short-circuited can also be detected through the existing universal meter, when the resistance is basically zero, the wire is identified to be short-circuited, the high-temperature sleeve outside the wire is heated by using a thermal spray gun, the spray gun can use a welding torch product of the existing H01-2 model, and the heating temperature is increased until the critical temperature of the short-circuited wire is detected as the safe temperature.
The simulation module is used for detecting the temperature sensor and carries out the sign to the transmission tail flame temperature detection ability information under the analog condition, the detection ability information carries out the transmission tail flame temperature that temperature sensor detected, the simulation module is including the tail flame analog unit who is used for the transmission tail flame and the launch support that supports the tail flame analog unit, the analog condition is the tail flame of the predetermined temperature of tail flame analog unit transmission, the available small-size rocket of tail flame analog unit, in order to carry out the simulation of guided missile tail flame, temperature sensor is located the launch support below and carries out temperature detection, the launch support is the shelf of cube form.
The control module 4 acquires preset parameters, the safety temperature and the detection capability information are sent to the testing subsystem, the control module 4 can use the existing STM32 series single chip microcomputer, the control module 4 judges whether the temperature sensor and the high-temperature sleeve reach the preset requirements according to the preset parameters, the safety temperature and the detection capability information, the preset requirements are that the sensitivity of the temperature sensor reaches the requirements, the detection capability information can detect that the tail flame temperature and the safety temperature are greater than the tail flame temperature actually required to be measured, for example, the safety temperature is greater than the tail flame temperature which is actually required to be measured and is 920 ℃, and the temperature difference of the two temperature sensors when the front side and the back side measure the temperature is less than or equal to 3 ℃ aiming at the condition that the sensitivity meets the preset requirements; when the temperature sensor and the high-temperature sleeve reach the preset requirements, the control module 4 carries out test information prompt, the test information prompt can be played through the buzzer, and the control module 4 sends a test signal to the processing module through the data line. By carrying out a plurality of tests on the temperature sensor, the performance of the temperature sensor for detecting the temperature of the tail flame of the missile can be evaluated from a plurality of aspects, the detection tolerance of the temperature sensor under the special condition of detecting the temperature of the tail flame of the missile is improved, and the damage probability is reduced.
As shown in fig. 2, the testing device includes a base 1 and a measuring upright rod 2, a cavity is formed in the base 1, an extending seat for supporting a control module 4 is welded on the inner wall of the cavity, the extending seat is in a long strip shape, the end of the extending seat extends to the center of the cavity, the measuring upright rod 2 is welded on the base 1, a plurality of temperature sensors are respectively arranged at a plurality of vertical measuring points 3 of the measuring upright rod 2, the height of the vertical measuring points 3 from the ground is set according to the actual demand, for example, two temperature measuring sensors are respectively arranged at the positions of the measuring upright rod 2 from the ground by 0.3m, 1m and 2.5m, six temperature sensors are arranged on one measuring upright rod 2, the sensor at 0.3m is used for measuring the heat flow temperature of the tail flame passing through a guide plate of a launching vehicle, and the sensor at 2.5m is used for measuring the heat influence of the tail flame on the lower part after the missile is lifted off.
As shown in fig. 3, a control module 4 is installed in the testing device, after receiving a testing signal, the testing device sets a plurality of temperature sensors tested by a calibration module, a temperature-resistant module and an analog module in the vertical direction, the control module 4 obtains the temperature value of the missile tail flame measured by the temperature sensor according to a preset sampling frequency, the measured value is represented by a resistance value, the preset sampling frequency is 2ms, the preset sampling frequency is very small compared with the common 10ms sampling frequency of the temperature sensor, the temperature value collected by the missile tail flame is prevented from being omitted, for example, three vertical measuring points 3 are arranged in the vertical direction, two temperature sensors are arranged at each vertical measuring point 3, the testing device is arranged at a plurality of ground measuring points of a plurality of preset angles by taking the missile tail end face as a horizontal starting point, the range of the preset angles is 0-90 degrees, the ground measuring points are arranged at equal intervals, the method comprises the steps that five ground measurement points are arranged when a preset angle is 90 degrees, three ground measurement points are arranged when the preset angle is smaller than 90 degrees, the preset angles are respectively 0 degree, 30 degrees, 60 degrees and 90 degrees, the preset angle is 0 degree of a ray perpendicular to the central axis of the missile on the left side, when the preset angle is 0 degree, 30 degrees and 60 degrees, testing devices are respectively arranged on the rays of 15m, 20m and 25m away from the central point of the tail end face of the missile at each preset angle, and when the preset angle is 90 degrees, the testing devices are respectively arranged on the rays of 15m, 20m, 25m, 30m and 35m away from the central point of the tail end face of the missile. Through the arrangement of the plurality of ground measuring points and the plurality of vertical measuring points 3, multi-level temperature detection of different detecting points can be carried out in a three-dimensional space, the coverage comprehensiveness and integrity of the detecting points are improved, and the detection of the temperature of the tail flame of the missile is more accurate.
The processing module obtains a measured value of the temperature sensor to the temperature of the tail flame of the missile from the control module 4, the processing module obtains preset parameters from the control module 4 through an existing serial port data line, the processing module establishes a temperature measurement error model according to static resistance values in the preset parameters, the temperature measurement error model is used for correcting and compensating the measured value, the processing module obtains difference values of the static resistance values obtained by measuring first temperatures by the plurality of temperature sensors according to an averaging mode or a standard deviation mode, then an actual resistance corresponding to the first temperature is obtained by adding the difference values to the resistance standard values, the temperature measurement error model is a corresponding relation table of the corrected actual resistance values and the temperatures, for example, the resistance standard value corresponding to 200 ℃ is 175.84 Ω, the difference value is 0.96, and then the temperature when the resistance value of the temperature sensor is 176.8 Ω is 200 ℃. The static parameters of the temperature measured by the temperature sensor are calibrated and compensated, so that a small amount of difference in the temperature detection process of the temperature sensor is reduced, and the detection accuracy of the temperature sensor is improved.
The processing module compares temperature step change curves in preset parameters to establish a dynamic delay temperature measurement compensation model, the temperature step change curve is a temperature change curve of a temperature sensor when the temperature sensor detects the tail flame of the missile, for example, the temperature change curve of the temperature sensor when the temperature value is detected to be increased from 25 ℃ of the current environment to 200 ℃, the processing module identifies the response time of the temperature change from the temperature step change curve as the dynamic delay temperature measurement compensation model, for example, the response time is the time delay required by the temperature sensor to be increased to the target temperature, the processing module performs response compensation on the measured value by using the dynamic delay temperature measurement compensation model, for example, the measurement time of the measured value is compressed according to the delayed response time in the dynamic delay temperature measurement compensation model, the processing module is in signal connection with a display module, and the display module is used for displaying, the display module may use an existing display.
The processing module carries out data fitting after correcting compensation and response compensation on the measured value, the data fitting is to form an image by the temperature of the missile tail flame corresponding to the obtained measured value, and a temperature distribution map of the missile tail flame is drawn, and the temperature distribution map can be drawn and formed by the existing MATLAB software.
The missile tail flame jet flow distribution test method based on the missile tail flame jet flow distribution test system comprises the following steps:
before the missile is launched, the temperature sensors are respectively heated according to preset conditions, for example, forty-two temperature sensors are needed during actual test, the temperature sensors with the quantity larger than the actual required quantity need to be heated and tested, each temperature sensor is enabled to detect preset parameters under the preset conditions, and the preset conditions comprise sensitivity conditions, static calibration conditions and dynamic temperature measurement conditions.
When the preset condition is a sensitivity condition, setting the two temperature sensors as a group, respectively heating the front side and the back side of the two temperature sensors, and heating the back side and the front side of the two temperature sensors, wherein the front side refers to that a probe of the temperature sensor is over against the tail flame of the missile, the back side refers to that the probe of the temperature sensor is not over against the tail flame of the missile, and the temperature difference after the temperature sensor measures the temperature is taken as a preset parameter, namely the temperature difference corresponding to the resistance value of the temperature sensor during measurement is taken as the preset parameter.
When the preset condition is a static calibration condition, the hot air gun is used for respectively heating the plurality of temperature sensors by the first temperature and the second temperature, the temperature sensors are used for temperature detection, and the corresponding static resistance value when the temperature sensors detect the temperature is used as a preset parameter.
When the preset condition is a dynamic temperature measurement condition, the temperature sensor is heated by the hot air gun at the third temperature and the fourth temperature respectively, then the temperature sensor is quickly moved out of an air outlet of the hot air gun, the temperature step change curve of the temperature sensor is detected by the infrared thermometer, and the temperature step change curve is used as a preset parameter.
The detection capability information of the tail flame emitted by the temperature sensors under the simulation condition is detected, namely, the tail flame with the preset temperature is emitted by the tail flame simulation unit to be used for the temperature sensors to detect the temperature, and whether the temperature sensors can accurately detect the preset temperature or not is used as the detection capability information.
The high-temperature sleeve outside the temperature sensor wire is heated through the thermal spray gun, the line information of whether the wire is short-circuited is detected, the safe temperature of the wire, which is not short-circuited under the heating condition, is obtained, the line information can be obtained through the control module 4, the resistance value of the temperature sensor is judged and formed, whether the temperature sensor and the high-temperature sleeve meet the preset requirement or not is judged according to the preset parameter, the detection capability information and the safe temperature, and when the temperature sensor and the high-temperature sleeve meet the preset requirement, a test signal is sent.
After receiving a test signal, a plurality of temperature sensors are installed on a testing device along the vertical direction, two temperature sensors are respectively arranged at a vertical measuring point 3 of a measuring vertical rod 2 of the testing device, which is a first distance, a second distance and a third distance from the ground, the first distance, the second distance and the third distance are sequentially increased in an increasing mode, if the first distance, the second distance and the third distance are 0.3m, 1m and 2.5m respectively, the plurality of testing devices are arranged in a testing area behind a missile according to a distribution direction, the distribution direction is that a tail end face of the missile is used as a horizontal starting point, a plurality of rays with preset angles are emitted from a central point of a central shaft of the missile on the tail end face along the ground, and a plurality of ground measuring points are arranged on the rays.
In the missile launching process, a plurality of temperature sensors on a testing device at a plurality of ground measuring points are used for detecting the measured value of the missile tail flame temperature, a temperature measurement error model is established according to preset parameters, the temperature measurement error model is used for correcting and compensating the measured value, the static resistance value obtained under the static calibration condition is subjected to difference calculation in a mode of averaging or standard deviation, then the resistance standard value is added with the difference value to obtain the actual resistance corresponding to the first temperature, and the temperature measurement error model is established according to a corresponding relation table of the corrected actual resistance value and the temperature.
And comparing the temperature step change curves of the two temperature sensors obtained under the dynamic temperature measurement condition, and taking the response time of the temperature change on the temperature step change curves as a dynamic delay temperature measurement compensation model.
And after the temperature measurement error model is used for correcting and compensating the measured value and the dynamic delay temperature measurement model is used for responding and compensating the measured value, forming an image of the missile tail flame temperature corresponding to the obtained measured value for data fitting, and drawing a temperature distribution map of the missile tail flame.
In view of the problems of missile launching cost and practical operation limitation, missile launching cannot be repeatedly carried out due to the fact that temperature distribution needs to be tested, so that temperature distribution testing needs to be accurately and completely completed once, in addition, the temperature distribution condition of the missile tail flame after missile launching is unknown, the temperature distribution testing mode of the missile tail flame is difficult, and if relevant conditions of testing are not accurately set, one-time testing opportunity is wasted. Therefore, in the first embodiment, before the missile is launched, the temperature bearing capacity of the temperature sensor and the temperature bearing capacity of the lead are tested and verified, after the test and verification are passed, the temperature values in a plurality of directions of the space are measured, the coverage of the temperature measuring points is improved, the continuity and the accuracy of temperature measurement are improved on the premise that the temperature sensor can bear the temperature of the tail flame of the missile and is not damaged, the temperature measurement is carried out from a plurality of angles and directions, and the comprehensiveness of temperature measurement in the process of one-time test is improved.
Based on the first embodiment, the reason why the measurement is not performed at present is that even if a sensor capable of measuring high temperature is selected, if the sensor is damaged in the process of detecting the temperature of the tail flame of the missile, the sensor cannot normally work, the sensor cannot be found in the tail flame of the missile, and the false phenomenon that the sensor can normally work is caused, so that the measurement of the temperature distribution of the tail flame of the missile is omitted. Aiming at the temperature value of the tail flame of the missile which can be detected by a temperature sensor, the existing method is generally carried out by utilizing a sensor product with certain detection performance, and the corresponding test operation cannot be added for verification; in addition, in the first embodiment, performance verification is performed on the corresponding temperature sensor before actual detection, and then the verified temperature sensor is used for detecting the temperature of the tail flame of the missile, that is, the temperature sensor is allowed to tolerate higher temperature before actual testing of the temperature of the tail flame of the missile.
Example two
The missile tail flame jet flow distribution testing system is different from the missile tail flame jet flow distribution testing system in that the calibration module and the simulation module carry out calibration and inspection on the temperature sensor without the shell, the calibration and inspection are the calibration operation of the calibration module and the simulation module in the embodiment I, in order to ensure that the internal structure of the temperature sensor is not damaged in the shell removing process, the temperature sensor is carried out by directly customizing a product without the shell to a manufacturer, and because the testing device has a certain distance from a jet orifice of the missile tail flame in the measuring process, the temperature measurement is carried out by using the temperatures of a spray gun and a hot air gun when the temperature sensor is tested, and the requirement of measuring the temperature of the missile tail flame after actual missile launching can be met.
According to the missile tail flame jet flow distribution testing method, before the missile tail flame is launched, a probe of a temperature sensor with a shell removed is heated for calibration and inspection, and the calibration and inspection are carried out according to the process in the first embodiment.
Because the temperature of the tail flame of the thermal launching missile is higher and has solid substances, the action time of the tail flame of the missile on the temperature sensor in the temperature distribution test process is very short, the measurement reaction speed of the temperature sensor on the temperature of the tail flame of the missile is required to be high, and the currently common temperature sensor has certain delay in the measurement process, the temperature measurement is carried out after the temperature sensor is removed from the shell, the temperature sensor is directly contacted with the tail flame, the delay of the temperature sensor for measuring the temperature of the tail flame of the missile is reduced, the reaction speed of the temperature measurement is improved, the omission of the temperature measurement is avoided, the measurement function of the temperature sensor after the shell is removed is tested, the measurement error caused by the damaged part after the shell is removed is avoided, the temperature sensor after the shell is removed is utilized for detecting the temperature of the tail flame of the missile, and the temperature can be directly contacted with the tail flame for measuring, the interference of the housing on the temperature measurement can also be avoided.
The problem of delay in detection of the temperature sensor is usually compensated by an algorithm, but cannot be solved by removing a shell, because the shell can protect internal components from being damaged and prolong the service life of the sensor when the temperature sensor is applied in industry. In the second embodiment, in the process of detecting the temperature distribution of the tail flame of the missile, the temperature sensor with the shell removed is specifically selected to detect the temperature through the action characteristics of the tail flame of the missile, so that the basic requirement of temperature detection can be met, meanwhile, the temperature detection delay is reduced, and the detection omission caused by the fact that the temperature sensor does not respond in a short time after the action of the tail flame of the missile is avoided.
The foregoing is merely an example of the present invention and common general knowledge of known specific structures and features of the embodiments is not described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (10)
1. A missile tail flame jet flow distribution test system comprises a checking subsystem and a test subsystem; the method is characterized in that:
the testing subsystem comprises a processing module positioned at a background and a plurality of testing devices in wireless communication with the processing module, and a plurality of vertical measuring points are arranged in the vertical direction of the testing devices;
the checking subsystem is used for checking a detection device of the temperature on the testing device in a preset mode before missile launching, and sending a testing signal to the testing subsystem after the detection device is checked to be qualified;
and after receiving the test signal, the test subsystem arranges the test device in a test area behind the missile according to the distribution direction.
2. The missile tail flame jet flow distribution test system of claim 1, wherein: the detection device comprises a temperature sensor and a lead for transmitting detection data of the temperature sensor, the calibration subsystem comprises a calibration module, a temperature-resistant module, a simulation module and a control module, the calibration module is used for heating the temperature sensors according to preset conditions and detecting preset parameters, the temperature-resistant module is used for heating a high-temperature sleeve outside the lead and detecting the line information of whether the lead is short-circuited or not to acquire the safe temperature of the lead without short circuit, the simulation module is used for detecting the detection capability information of the temperature sensor on the temperature of the launching tail flame under the simulation condition, the control module acquires the preset parameters, the safe temperature and the detection capability information, and judging whether the temperature sensor and the high-temperature sleeve meet the preset requirements or not according to the preset parameters, the safe temperature and the detection capability information, and when the temperature sensor and the high-temperature sleeve meet the preset requirements, the control module sends a test signal to the test subsystem.
3. The missile tail flame jet flow distribution test system of claim 2, wherein: the control module is located the testing arrangement, control module signal connection processing module, the testing arrangement sets up a plurality of temperature sensor after calibration module, temperature resistant module and simulation module test in vertical direction, control module acquires the measured value of temperature sensor to the guided missile tail flame temperature according to preset sampling frequency, testing arrangement sets up according to the distribution position, the distribution position is for using guided missile tail end face as horizontal starting point, launches the ray of a plurality of angle of predetermineeing along ground at the central point of tail end face from the guided missile center pin to set up a plurality of ground measurement point department on the ray.
4. The missile tail flame jet flow distribution test system of claim 1, wherein: the testing device comprises a base and a measuring vertical rod, a cavity is formed in the base, an extending seat used for supporting the control module is fixedly arranged on the inner wall of the cavity, the extending seat extends to the center, the measuring vertical rod is fixedly arranged on the base, and a plurality of temperature sensors are arranged at a plurality of vertical measuring points of the measuring vertical rod.
5. The missile tail flame jet flow distribution test system of claim 3, wherein: the calibration module and the simulation module perform calibration and inspection on the temperature sensor without the shell.
6. The missile tail flame jet flow distribution test system of claim 5, wherein: the simulation module is including the tail flame analog unit who is used for launching the tail flame and the emission support who supports the tail flame analog unit, the simulation condition is the tail flame of tail flame analog unit transmission default temperature, temperature sensor is located the emission support below and carries out temperature detection.
7. The missile tail flame jet flow distribution test system of claim 3, wherein: the processing module obtains a measured value of the temperature sensor on the temperature of the tail flame of the missile from the control module, a temperature measurement error model is established according to preset parameters, the temperature measurement error model is used for correcting and compensating the measured value, the processing module compares temperature step change curves in the preset parameters to establish a dynamic delay temperature measurement compensation model, the processing module utilizes the dynamic delay temperature measurement compensation model to perform response compensation on the measured value, and the processing module performs data fitting after the correction compensation and the response compensation on the measured value and draws a temperature distribution map of the tail flame of the missile.
8. The missile tail flame jet flow distribution test system of claim 3, wherein: the preset sampling frequency is 2 ms.
9. A missile tail flame jet flow distribution testing method is characterized by comprising the following steps:
before the missile is launched, heating a plurality of temperature sensors according to preset conditions respectively, enabling the temperature sensors to detect preset parameters, detecting tail flame temperature detection capability information of the temperature sensors under simulation conditions, heating a high-temperature sleeve outside a wire of the temperature sensors, detecting line information of whether the wire is short-circuited, acquiring safe temperature of the wire without short circuit, judging whether the temperature sensors and the high-temperature sleeve reach preset requirements according to the preset parameters, the detection capability information and the safe temperature, and sending test signals when the temperature sensors and the high-temperature sleeve reach the preset requirements;
after receiving the test signals, mounting a plurality of temperature sensors on a test device along the vertical direction, and arranging the test devices in a test area behind the missile according to the distribution direction;
in the missile launching process, a plurality of temperature sensors on a testing device at a plurality of ground measuring points are used for detecting the measured value of the missile tail flame temperature, data fitting is carried out on the measured value, and the temperature distribution map of the missile tail flame is drawn.
10. The missile tail flame jet flow distribution test method of claim 9, wherein the method comprises the following steps: before the missile tail flame is launched, the temperature sensor without the shell is calibrated and checked, a probe with the temperature sensor without the shell is heated, temperature-resistant check detected by the temperature sensor is obtained, the test temperature is compared with the heated temperature, and when the test temperature is equal to the heated temperature, the temperature measurement function of the temperature sensor is judged to be intact.
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