CN114509652B - Device and method for testing radio frequency discharge noise of aircraft electrostatic discharger - Google Patents
Device and method for testing radio frequency discharge noise of aircraft electrostatic discharger Download PDFInfo
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- CN114509652B CN114509652B CN202210407013.5A CN202210407013A CN114509652B CN 114509652 B CN114509652 B CN 114509652B CN 202210407013 A CN202210407013 A CN 202210407013A CN 114509652 B CN114509652 B CN 114509652B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/12—Testing dielectric strength or breakdown voltage ; Testing or monitoring effectiveness or level of insulation, e.g. of a cable or of an apparatus, for example using partial discharge measurements; Electrostatic testing
- G01R31/1227—Testing dielectric strength or breakdown voltage ; Testing or monitoring effectiveness or level of insulation, e.g. of a cable or of an apparatus, for example using partial discharge measurements; Electrostatic testing of components, parts or materials
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/26—Measuring noise figure; Measuring signal-to-noise ratio
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
Abstract
The invention relates to a test device and a test method for radio frequency discharge noise of an aircraft static discharger. The test device and the test method for the radio frequency discharge noise of the aircraft electrostatic discharger comprise a support, a DC program-controlled high-voltage power supply arranged on the support, a structure capacitor, a high-voltage cable, a fixed test piece bottom plate, a direct-reading microammeter, an equivalent load, a coaxial cable, a radio frequency noise real effective measurement controller, an optical fiber, a grounding bus bar, a base, a telescopic mechanism connected to the base, an adjusting mechanism arranged in the telescopic mechanism, a bracket connected to the top end of the telescopic mechanism, a noise receiving electrode and a high-voltage electrode connected to the bracket, a test piece electrode connected to the fixed test piece bottom plate and a plurality of universal wheels connected to the bottom of the support; the invention adopts the method of remote control, equivalent load and broadband gain amplification, effectively realizes reliable and stable discharge of the static discharger of the airplane, and meets the requirement of a high-frequency communication system and instruments on accurate radio frequency discharge signal power detection.
Description
Technical Field
The invention belongs to the technical field of aircraft electrostatic protection, and particularly relates to a test device and a test method for radio frequency discharge noise of an aircraft electrostatic discharger.
Background
During flight, the surface of the aircraft collides with dust, ice crystals, rain and other particles of material, and the successive collisions cause charges to be separated from the particles and transferred to the aircraft, thereby creating a large potential at the tip of the aircraft, and when the charges accumulated at the tip exceed a certain magnitude, thereby creating an excessive potential difference with the charged cloud in the surrounding air, electrostatic discharge can occur. In addition, when the aircraft is in air refueling, the potential difference formed between the two aircrafts due to static electricity can reach 300kV as the two aircrafts are charged respectively. The wide-spectrum electromagnetic field generated when the static charge is naturally dissipated is one of the main sources of antenna noise, the interference spectrum is up to 1000MHz, the electromagnetic field can pass through the skin surface and the opening of the airplane and is coupled with the avionics equipment, so the airborne equipment is sensitive to the static electricity, and the essence of the electromagnetic field is the sensitivity of main circuit elements in the airborne equipment to the broadband radio frequency field generated by the static electricity. When static charges are accumulated at two ends of a leading-out wire of the device, the electrostatic discharge phenomenon is easy to occur particularly because the wire spacing is very small, and further the failures of airplane navigation, communication and computer control are caused, and even the detonation of weapon equipment such as missiles and the like is caused.
The experiment proves that the course error of the VHF omnidirectional beacon in the airplane can reach about 10 degrees under the influence of electrostatic discharge. Therefore, the problem of electrostatic protection of the aircraft is more and more concerned, and the static charge on the surface of the aircraft is discharged into the atmosphere, and the method for controllably discharging is to install an electrostatic discharger. The radio frequency discharge noise of the aircraft static discharger is reasonably designed and accurately measured, and a basis is provided for the protection performance of the static discharger, so that the electromagnetic interference generated by static discharge is reduced, and the influence of the electromagnetic interference on aircraft systems is minimized. The relevant standard stipulates that when the aircraft electrostatic discharger discharges with a current of 50 microamperes, the radio frequency total noise voltage (root mean square (rms) value) generated and coupled by the discharger should be attenuated by at least 40dB (trailing edge type) or 30dB (wing tip type), a plurality of measuring instruments and equipment are adopted in the traditional measuring method for combined testing, the requirement on the skill level of a tester is higher, the requirement on a shielding test field is strict, the operation is complex, time and labor are wasted, and measuring errors are easily caused, a high-voltage electrode and a noise receiving electrode in each measuring instrument mostly adopt a hemispherical copper shell with the diameter of 250mm and a hemispherical copper shell with the diameter of 500mm, and during position adjustment, the adjustment is mostly carried out by matching with manual support through limiting pieces such as limiting screws or screws, so that the workload is large, the precision is poor, and the electrode easily causes damage to workers if residual electricity exists, the safety is also poor.
Disclosure of Invention
The invention aims to solve the problems and provide a device and a method for testing the radio frequency discharge noise of the static discharger of the airplane, which have simple structure and reasonable design.
The invention realizes the purpose through the following technical scheme:
a test device and a method for radio frequency discharge noise test of an aircraft electrostatic discharger comprise a bracket, a DC program-controlled high-voltage power supply arranged on the bracket, a structure capacitor, a high-voltage cable, a fixed test piece bottom plate, a direct-reading microammeter, an equivalent load, a coaxial cable, a radio frequency noise real effective measurement controller, an optical fiber, a grounding bus bar, a base, a telescopic mechanism connected on the base, an adjusting mechanism arranged in the telescopic mechanism, a bracket connected at the top end of the telescopic mechanism, a noise receiving electrode and a high-voltage electrode connected on the bracket, a test piece electrode connected on the fixed test piece bottom plate and a plurality of universal wheels connected at the bottom of the bracket, wherein the output end of the DC program-controlled high-voltage power supply is respectively connected with the input ends of the structure capacitor and the radio frequency noise real effective measurement controller, the output end of the structure capacitor is connected with the input end of the high-voltage electrode through the high-voltage cable, the test piece electrode is connected with the direct-reading microammeter through a high-voltage cable, and a test current sampling resistor R is connected between the direct-reading microammeter and the structure capacitorSThe direct-reading microammeter is connected with the radio frequency noise real effective measurement controller through a coaxial cable,the equivalent load is used for converting the noise received by the noise receiving electrode into a voltage signal and transmitting the voltage signal to the radio frequency noise true and effective measurement controller, and the radio frequency noise true and effective measurement controller is connected with the test platform through an optical fiber;
the structure capacitor comprises a first program-controlled high-voltage switch K1, a second program-controlled high-voltage switch K2, a first high-voltage resistor R1, a second high-voltage resistor R2, a third high-voltage resistor R3 and a high-voltage capacitor CHVOne end of the first program-controlled switch K1 is connected with the positive output end of the DC program-controlled high-voltage power supply, the other end of the first program-controlled switch K1 is connected with one end of a first high-voltage resistor R1, and the other end of the first high-voltage resistor R1 is connected with a high-voltage capacitor CHVIs connected with one end of a second program-controlled switch K2, the other end of the second program-controlled switch K2 is connected with one end of a third high-voltage resistor R3, a high-voltage capacitor CHVThe other end of the third high-voltage resistor R3 and the other end of the third high-voltage resistor R3 are both connected with the negative output end of the DC program-controlled high-voltage power supply, and the negative output end of the DC program-controlled high-voltage power supply is connected to the grounding bus bar;
the telescopic mechanism comprises a fixed column connected to the base, a moving column slidably connected to the fixed column, an index ring sleeved outside the fixed column and a plurality of buffer mechanisms connected between the moving column and the fixed column, the adjusting mechanism is used for adjusting the moving column to reciprocate up and down along the axis of the fixed column, the buffer mechanisms are controlled to suck air from the outside and form a heat insulation layer when the moving column moves up, and the buffer mechanisms are controlled to exhaust air to the outside when the moving column moves down and provide buffer supporting force for the moving column together with the adjusting mechanism.
As a further optimization scheme of the invention, a first circular groove is arranged in the middle of the fixed column, a first annular chamber is arranged in the wall of the first circular groove, a second annular chamber is arranged in the middle of the inner wall of one side of the first annular chamber, a first oil duct is arranged at the bottom of the first annular chamber, a first wiring hole and a plurality of vent holes are arranged in the middle of the bottom end of the first circular groove, the vent holes are uniformly distributed around the first wiring hole, a wiring pipe and a plurality of stroke sleeves are connected to the bottom end of the first circular groove, an oil through groove matched with the stroke sleeves is arranged at the bottom end of the first circular groove, a second oil duct is arranged between the first oil ducts and the corresponding oil through groove, the movable column is positioned in the first circular groove, an adjusting chamber is arranged on the inner wall of the top end of the second annular chamber, and an axle hole penetrating through the outer wall of the fixed column is arranged on the inner wall of the adjusting chamber.
As a further optimization scheme of the invention, a second circular groove is arranged in the middle of the moving column, the top end of the second circular groove is connected with a cylinder and a plurality of support rods matched with the stroke sleeve, one end of each support rod is connected with a piston, the piston is positioned in the stroke sleeve, a second wiring hole is arranged in the cylinder, the second wiring hole penetrates through the moving column, and a plurality of buffer mechanisms are connected to the bottom end of the cylinder and are arranged corresponding to a plurality of vent holes.
As a further optimization scheme of the invention, the buffer mechanism comprises a buffer air bag connected to the bottom end of the cylinder, an airflow control plate connected to the inner wall of the vent hole, a plurality of air inlet holes and an air outlet hole which are arranged on the airflow control plate, the top end of the airflow control plate is connected with a plastic film covering the air inlet holes, only one end of the plastic film is connected with the top end of the airflow control plate, and one end of the buffer air bag is connected with the bottom end of the first circular groove and covers the corresponding vent hole.
As a further optimization scheme of the invention, the adjusting mechanism comprises an adjusting knob penetrating through the shaft hole, a ratchet wheel connected to the adjusting knob, a connecting plate connected to the inner wall of the top end of the adjusting cavity, a limiting claw connected to the connecting plate, a limiting rod connected to one end of the adjusting knob, a rotating shaft movably connected to the side wall of the adjusting cavity, a driving gear connected to the rotating shaft, a driving sleeve arranged in the first annular cavity, an annular gear connected to the outer wall of the driving sleeve, a moving ring in threaded connection with the inside of the driving sleeve, and an oil bag connected to the lower end of the moving ring, wherein the oil bag is communicated with the first oil duct, a sliding groove is arranged on the inner wall of the other side of the first annular cavity, a sliding block matched with the sliding groove is connected to the moving ring, and a limiting cavity matched with the limiting rod is arranged on the rotating shaft.
As a further optimization scheme of the invention, a first annular groove is formed in the bottom end of the first annular cavity, a second annular groove communicated with the first annular groove is formed in the position, close to the bottom, of the outer wall of the fixing column, a first annular piece matched with the first annular groove is connected to the bottom end of the driving sleeve, a second annular piece matched with the second annular groove is connected to the inner wall of the index ring, the first annular piece is connected with the second annular piece, and scale marks matched with the index ring are arranged on the outer wall of the fixing column.
A method for carrying out test on radio frequency discharge noise of an aircraft electrostatic discharger by adopting the device comprises the following steps:
s1, fixing the test piece on the fixed test piece base plate and connecting the test piece with the test piece electrode which passes through the direct-reading microampere meter and the test current sampling resistor RSThe device is connected to the grounding bus bar to form a current loop, the moving column is driven by the adjusting mechanism to drive the bracket, the high-voltage electrode and the noise receiving electrode to move upwards along the axis direction of the fixed column, and when one end of the test piece electrode is positioned at the center of the high-voltage electrode, the movement is stopped;
step S2, controlling the radio frequency noise true and effective measurement controller to perform self-checking;
step S3, initiating a handshake protocol to the DC program-controlled high-voltage power supply through the radio frequency noise true and effective measurement controller and initializing the voltage of the DC program-controlled high-voltage power supply to be 0V;
s4, the test platform remotely adjusts the current and voltage of the DC program-controlled high-voltage power supply through the radio frequency noise real effective measurement controller, simultaneously, a first remote switch K1 is started, and when the voltage of the DC program-controlled high-voltage power supply rises to more than 2KV, corona discharge is started between the high-voltage electrode and the test piece electrode;
step S5, gradually increasing the voltage of the DC program control high-voltage power supply until the display value of the direct-reading microammeter reaches a preset test current of 50 muA, and then the radio frequency noise real effective measurement controller starts to acquire radio frequency total noise voltage data and transmits the radio frequency total noise voltage data to the test platform;
and step S6, after data acquisition is completed, remotely closing the current and voltage of the DC program control high-voltage power supply by the test platform through the radio frequency noise real effective measurement controller, simultaneously starting the second remote switch K2, starting system discharge, disconnecting the first and second remote switches K1 and K2 after the discharge is finished, closing the system power supply, and adjusting the movable column through the adjusting mechanism to drive the bracket, the high-voltage electrode and the noise receiving electrode to move downwards along the axis direction of the fixed column until the reset is completed.
The invention has the beneficial effects that:
1) the invention adopts the method of remote control, equivalent load and broadband gain amplification, effectively realizes reliable and stable discharge of the static discharger of the airplane, and meets the requirement of a high-frequency communication system and instruments on accurate radio frequency discharge signal power detection;
2) the utility model discloses a wiring hole, including wiring hole, high-voltage electrode, noise receiving electrode, the wiring hole is equipped with the regulation mechanism, can be through the convenient position of regulation high-voltage electrode and noise receiving electrode of adjustment mechanism, can be accurate promote appointed height fast and form one deck air insulation layer all around in the wiring hole, the installation and the dismantlement of the test piece of being convenient for, the temperature that gives off when also preventing the downthehole cable of wiring from switching on constructs the influence to the regulator simultaneously, make its stable slow move down under the condition of contactless electrode simultaneously, it is impaired because of the deceleration is too fast to prevent overweight electrode, contactless electrode also can prevent that the remaining residual electricity of electrode from causing the damage to the staff simultaneously, the security is higher.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of the telescoping mechanism of the present invention;
fig. 3 is a cross-sectional view of a stationary post according to the present invention;
FIG. 4 is a cross-sectional view of the mobile column of the present invention;
FIG. 5 is an enlarged view taken at A of FIG. 2 in accordance with the present invention;
FIG. 6 is an enlarged view of the invention at B in FIG. 2;
FIG. 7 is an enlarged view of the invention at C of FIG. 2;
FIG. 8 is an enlarged view of the invention at D of FIG. 2;
FIG. 9 is a mating view of the ratchet and the spacing pawl of the present invention;
FIG. 10 is a mating view of the drive gear and ring gear of the present invention;
fig. 11 is a circuit connection schematic of the present invention.
In the figure: 1. a support; 2. a DC program-controlled high-voltage power supply; 3. a structure capacitance; 4. a high voltage cable; 5. fixing a test piece base plate; 6. a test piece electrode; 7. a high voltage electrode; 8. a noise receiving electrode; 9. a bracket; 10. a telescoping mechanism; 1001. fixing a column; 1002. moving the column; 1003. an index ring; 1004. a first circular groove; 1005. a first annular chamber; 1006. a second annular chamber; 1007. a first annular groove; 1008. a second annular groove; 1009. a first wiring hole; 1010. a wiring pipe; 1011. a travel sleeve; 1012. an oil groove is communicated; 1013. a vent hole; 1014. a first oil passage; 1015. a second oil passage; 1016. a conditioning chamber; 1017. a shaft hole; 1018. a second circular groove; 1019. a cylinder; 1020. a support bar; 1021. a second wiring hole; 1022. a piston; 1023. a buffer air bag; 1024. an airflow control panel; 1025. an exhaust hole; 1026. an air inlet; 1027. a plastic film; 11. an adjustment mechanism; 1101. adjusting a knob; 1102. a ratchet wheel; 1103. a connecting plate; 1104. a limiting claw; 1105. a rotating shaft; 1106. a limiting rod; 1107. a drive gear; 1108. a ring gear; 1109. a drive sleeve; 1110. an oil pocket; 1111. a moving ring; 1112. a slider; 12. a base; 13. a direct-reading microammeter; 14. an equivalent load; 15. a coaxial cable; 16. a radio frequency noise true effective measurement controller; 17. an optical fiber; 18. a universal wheel; 19. a ground bus bar.
Detailed Description
The present application will now be described in further detail with reference to the drawings, and it should be noted that the following detailed description is given for purposes of illustration only and should not be construed as limiting the scope of the present application, as these numerous insubstantial modifications and variations can be made by those skilled in the art based on the teachings of the present application.
Example 1
As shown in figure 1, the test device for the radio frequency discharge noise test of the aircraft electrostatic discharger comprises a support 1, a DC program-controlled high-voltage power supply 2 arranged on the support 1, a structure body capacitor 3, a high-voltage cable 4, a fixed test piece bottom plate 5, a direct-reading microammeter 13, an equivalent load 14, a coaxial cable 15, a radio frequency noise real effective measurement controller 16, an optical fiber 17, a grounding bus bar 19, a base 12, a telescopic mechanism 10 connected to the base 12, an adjusting mechanism 11 arranged in the telescopic mechanism 10 and a controller connected to the telescopic mechanism 10A bracket 9 at the top end of the mechanism 10, a noise receiving electrode 8 and a high-voltage electrode 7 which are connected on the bracket 9, a test piece electrode 6 which is connected on a fixed test piece bottom plate 5 and a plurality of universal wheels 18 which are connected at the bottom of the bracket 1, the output end of a DC program control high-voltage power supply 2 is respectively connected with the input ends of a structure capacitor 3 and a radio frequency noise true and effective measurement controller 16, the output end of the structure capacitor 3 is connected with the input end of the high-voltage electrode 7 through a high-voltage cable 4, the test piece electrode 6 is connected with a direct-reading microammeter 13 through the high-voltage cable 4, and a test current sampling resistor R is connected between the direct-reading microammeter 13 and the structure capacitor 3SThe direct-reading microammeter 13 is connected with a radio frequency noise real and effective measurement controller 16 through a coaxial cable 15, an equivalent load 14 is used for converting noise received by a noise receiving electrode 8 into a voltage signal and transmitting the voltage signal to the radio frequency noise real and effective measurement controller 16, and the radio frequency noise real and effective measurement controller 16 is connected with a test platform through an optical fiber 17;
as shown in fig. 11, the structure capacitor 3 includes a first program-controlled high-voltage switch K1, a second program-controlled high-voltage switch K2, a first high-voltage resistor R1, a second high-voltage resistor R2, a third high-voltage resistor R3, and a high-voltage capacitor CHVOne end of the first program-controlled switch K1 is connected with the positive output end of the DC program-controlled high-voltage power supply 2, the other end is connected with one end of a first high-voltage resistor R1, and the other end of the first high-voltage resistor R1 is connected with a high-voltage capacitor CHVIs connected with one end of a second program-controlled switch K2, the other end of the second program-controlled switch K2 is connected with one end of a third high-voltage resistor R3, a high-voltage capacitor CHVThe other end of the third high-voltage resistor R3 and the other end of the third high-voltage resistor R3 are both connected with the negative output terminal of the DC program-controlled high-voltage power supply 2, and the negative output terminal of the DC program-controlled high-voltage power supply 2 is connected to the ground bus bar 19;
the radio frequency noise real effective measurement controller 16 remotely controls the constant-current constant-voltage output of the DC program-controlled high-voltage power supply 2 through an RJ45 interface and is used for providing a 50KV positive-polarity adjustable test power supply for the radio frequency discharge noise test of the aircraft electrostatic discharger, the output end of the structure capacitor 3 is connected with the high-voltage electrode 7 through the high-voltage cable 4 and is used for simulating the dependence relationship between the electric potential and the discharge time of various types of aircraft, and the high-voltage capacitor CHVFor simulating the capacitance of an airplane body, the second high-voltage resistor R2 simulates an electrostatic dischargeThe resistance characteristics of the brush, the second program-controlled high-voltage switch K2 and the third high-voltage resistor R3 are used for controlling the release of the energy stored in the high-voltage capacitor.
Wherein, the high-voltage electrode 7 adopts a hemispherical copper shell with the diameter of 250mm, the noise receiving electrode 8 adopts a hemispherical copper shell with the diameter of 500mm, the distance between the high-voltage electrode 7 and the noise receiving electrode 8 is kept at 250mm, concretely, the bottom of the high-voltage electrode 7 and the middle part of the noise receiving electrode 8 are connected through an insulating part, the noise receiving electrode 8 is connected with a bracket 9, the noise receiving electrode 8 can drive the high-voltage electrode 7 to move in the same direction and in the same distance when moving, the test piece electrode 6 is inserted into the central position of the high-voltage electrode 7 to ensure that high-voltage corona discharge occurs between the high-voltage electrode 7 and the test piece electrode 6, noise signals generated by the corona discharge of the high-voltage electrode 7 realize signal coupling through the capacitance between the high-voltage electrode 7 and the noise receiving electrode 8, and the test piece electrode 6 is connected with one end of a direct-reading microammeter 13 through a high-voltage cable 4, the other end of the direct-reading microammeter 13 and the test current sampling resistor RSAnd the connection is used for displaying the test current, and simultaneously, the test current is connected with the radio frequency noise real effective measurement controller 16 through the coaxial cable 15.
The equivalent load 14 converts the noise received by the noise receiving electrode into a voltage signal, and includes a field-controlled divider resistor Rt and a coaxial equivalent capacitor CSHMatched load resistor RLThe noise receiving electrode is simultaneously connected with a field control divider resistor Rt and a coaxial equivalent capacitor CSHMatched load resistor RLThe first port of (1), a field control divider resistor Rt and a coaxial equivalent capacitor CSHMatched load resistor RLWhile the second port of the same is connected to the ground bus bar 19.
The radio frequency noise true and effective measurement controller 16 is connected to the test platform through an optical fiber 17 and used for enabling the microampere current synchronous acquisition module to acquire test current, noise voltage sequentially passes through the broadband radio frequency noise buffer module, the true and effective value power module is converted and then connected with the input end of the magnetic isolation interface module, the output end of the magnetic isolation interface module is connected with the input end of the measurement controller module, the measurement controller module sends acquisition information to the test platform through the optical fiber 17 to be displayed, and meanwhile, the measurement controller outputs signals to the magnetic isolation interface module to control the first high-voltage switch K1, the second high-voltage switch K2 and the constant-voltage and constant-current output of the DC program-controlled high-voltage power supply 2.
When the device is adopted to carry out the test of the radio frequency discharge noise of the electrostatic discharger of the airplane, the method comprises the following steps:
step S1, fixing the test piece on the fixed test piece bottom plate 5 and connecting the test piece electrode 6, connecting the test piece electrode 6 to the grounding bus bar 19 through the direct-reading microammeter 13 and the test current sampling resistor RS to form a current loop, driving the moving column 1002 through the adjusting mechanism 11 to drive the bracket 9, the high-voltage electrode 7 and the noise receiving electrode 8 to move upwards along the axis direction of the fixed column 1001, and stopping moving when one end of the test piece electrode 6 is positioned at the center position of the high-voltage electrode 7;
step S2, controlling the radio frequency noise true and valid measurement controller 16 to perform self-checking;
step S3, initiating a handshake protocol to the DC program-controlled high-voltage power supply 2 through the radio frequency noise true and valid measurement controller 16 and initializing the voltage of the DC program-controlled high-voltage power supply 2 to 0V;
step S4, the test platform remotely adjusts the current and voltage of the DC program-controlled high-voltage power supply 2 through the radio frequency noise real effective measurement controller 16, simultaneously, a first remote switch K1 is started, and when the voltage of the DC program-controlled high-voltage power supply 2 rises to be more than 2KV, corona discharge starts between the high-voltage electrode 7 and the test piece electrode 6;
step S5, gradually increasing the voltage of the DC program-controlled high-voltage power supply 2 until the display value of the direct-reading microammeter 13 reaches a preset test current of 50 muA, and then the radio frequency noise real effective measurement controller 16 starts to collect radio frequency total noise voltage data and transmits the data to the test platform;
step S6, after the data collection is completed, the test platform remotely turns off the current and voltage of the DC program-controlled high-voltage power supply 2 through the radio frequency noise real-valid measurement controller 16, simultaneously turns on the second remote switch K2, starts the system discharge, turns off the first and second remote switches K1 and K2 until the discharge is completed, turns off the system power supply, and adjusts the moving column 1002 through the adjusting mechanism 11 to drive the bracket 9, the high-voltage electrode 7, and the noise receiving electrode 8 to move downward along the axis direction of the fixed column 1001 until the reset is completed.
The test process effectively solves the problem that the radio frequency discharge noise of the aircraft electrostatic discharger is difficult to test, the reliable and stable discharge of the aircraft electrostatic discharger is effectively realized by adopting a method of remote control, equivalent load and broadband gain amplification, the requirement of a high-frequency communication system and an instrument on the detection of the radio frequency discharge accurate signal power is met, and the test platform controls the high voltage of 50KV through the optical fiber 17, so that the operation safety of testers is ensured.
As shown in fig. 2, the telescopic mechanism 10 includes a fixed column 1001 connected to the base 12, a movable column 1002 slidably connected in the fixed column 1001, an indicator ring 1003 sleeved outside the fixed column 1001, and a plurality of buffer mechanisms connected between the movable column 1002 and the fixed column 1001, the adjusting mechanism 11 is configured to adjust the movable column 1002 to reciprocate up and down along the axis of the fixed column 1001, the buffer mechanism is controlled to suck air from the outside and form a heat insulation layer when the movable column 1002 moves up, and the buffer mechanism is controlled to exhaust air to the outside when the movable column 1002 moves down and provide a buffer supporting force for the movable column 1002 together with the adjusting mechanism 11.
It should be noted that, because the high voltage electrode 7 and the noise receiving electrode 8 are made of copper, the weight of the high voltage electrode is large, when the high voltage electrode is adjusted, the adjusting mechanism 11 adjusts the moving column 1002 to move stably in the fixed column 1001, meanwhile, the telescopic mechanism 10 is provided with a wiring hole for the high voltage cable 4 to pass through, when the moving column 1002 moves upwards in the fixed column 1001, it is indicated that a test process needs to be performed, the moving column 1002 controls the buffer mechanism to suck air from the outside in the moving process, the buffer mechanisms expand and attach to each other after being inflated, an air thermal insulation layer can be formed around the high voltage cable 4, heat emitted when the high voltage cable 4 is powered on can be effectively isolated, the heat is prevented from being transferred to the adjusting mechanism 11 to affect the high voltage cable, and therefore, the influence of temperature change on test precision is reduced.
As shown in fig. 3, a first circular groove 1004 is disposed in the middle of a fixed column 1001, a first annular chamber 1005 is disposed in a wall of the fixed column 1001, a second annular chamber 1006 is disposed in the middle of an inner wall of one side of the first annular chamber 1005, a first oil passage 1014 is disposed at the bottom of the first annular chamber 1005, a first wiring hole 1009 and a plurality of vent holes 1013 are disposed in the middle of the bottom end of the first circular groove 1004, the plurality of vent holes 1013 are uniformly distributed around the first wiring hole 1009, a wiring pipe 1010 and a plurality of stroke sleeves 1011 are connected to the bottom end of the first circular groove 1004, an oil passage 1012 matching with the plurality of stroke sleeves 1011 is disposed at the bottom end of the first circular groove 1004, a second oil passage 1015 is disposed between the plurality of first oil passages 1014 and the corresponding oil passage 1012, the movable column 1002 is disposed in the first circular groove 1004, an adjustment chamber 1016 is disposed on an inner wall of the top end of the second annular chamber 1006, and a shaft hole 1017 penetrating through an outer wall of the fixed column 1001 is disposed on an inner wall of the adjustment chamber 1016.
As shown in fig. 4, a second circular groove 1018 is disposed in the middle of the moving column 1002, the top end of the second circular groove 1018 is connected with a cylinder 1019 and a plurality of support rods 1020 matched with the stroke sleeve 1011, one end of each support rod 1020 is connected with a piston 1022, the piston 1022 is located in the stroke sleeve 1011, a second wiring hole 1021 is disposed in the cylinder 1019, the second wiring hole 1021 penetrates through the moving column 1002, and a plurality of buffer mechanisms are connected to the bottom end of the cylinder 1019 and are disposed corresponding to the plurality of vent holes 1013.
It should be noted that the cylinder 1019 is located in the first circular groove 1004, the supporting rod 1020 and the piston 1022 are located in the stroke sleeve 1011, the piston 1022 is in close contact with the inner wall of the stroke sleeve 1011, the adjusting mechanism 11 can drive the piston 1022 to move up and down in the stroke sleeve 1011 and drive the supporting rod 1020 and the moving column 1002 to move in the same direction and at the same distance, when the cylinder 1019 moves upward along with the moving column 1002, the buffering mechanism is stretched, the buffering mechanism sucks air from the vent 1013, the buffering mechanism filled with air expands, and an air insulation layer is formed around the wiring pipe 1010.
As shown in fig. 8, the buffering mechanism includes a buffering airbag 1023 connected to the bottom end of the cylinder 1019, an air flow control plate 1024 connected to the inner wall of the vent 1013, a plurality of air inlet holes 1026 and an air outlet 1025 arranged on the air flow control plate 1024, the top end of the air flow control plate 1024 is connected with a plastic film 1027 covering the air inlet holes 1026, only one end of the plastic film 1027 is connected with the top end of the air flow control plate 1024, and one end of the buffering airbag 1023 is connected with the bottom end of the first circular groove 1004 and covers the corresponding vent 1013.
It should be noted that, during the moving process of the cylinder 1019, when the buffering airbag 1023 stretches, the internal air pressure increases and air is sucked from the outside, specifically, the air flows in from the vent 1013 and passes through the air flow control board 1024, during the air intake process of the air flow control board 1024, the plastic film 1027 is jacked up by the air flow, at this time, the air can enter the buffering airbag 1023 from the air inlet 1026 and the air outlet 1025 together, so as to achieve the effect of fast sucking the air to move in cooperation with the cylinder 1019, and at the same time, the buffering airbag 1023 filled with the air can form an air insulation layer around the wiring pipe 1010, which can effectively prevent the heat generated by the high voltage cable 4 in the wiring pipe 1010 when being powered on from transferring to the adjusting mechanism 11;
and in the process that the cylinder 1019 moves down, namely the process that the high voltage electrode 7 and the noise receiving electrode 8 move down, because of the electrode weight is great, under the condition that the staff does not contact the electrode, the buffering gasbag 1023 receives pressure and outwards discharges air at this moment, the air inside the buffering gasbag 1023 discharges to the air vent 1013 from the air current control panel 1024, compress tightly plastic film 1027 and cover the air inlet 1026 because of the air current direction, the air current can only slowly discharge from the exhaust hole 1025 at this moment, the gas discharge amount of the buffering gasbag 1023 is less, can play certain buffering effect, make the electrode move down slowly, and do not need to go to artifically support the electrode, can ensure that the electrode moves down the process is stable and can not bump, the security of staff has been improved simultaneously.
Wherein, as shown in fig. 5, 6, 7, 9 and 10, the adjusting mechanism 11 comprises an adjusting knob 1101 passing through the shaft hole 1017, a ratchet wheel 1102 connected to the adjusting knob 1101, a connecting plate 1103 connected to the top inner wall of the adjusting chamber 1016, a limiting claw 1104 connected to the connecting plate 1103, the utility model provides a spacing pole 1106 of connection at adjust knob 1101 one end, swing joint is at pivot 1105 on the lateral wall of regulation cavity 1016, connect drive gear 1107 on pivot 1105, locate drive sleeve 1109 in first annular chamber 1005, connect ring gear 1108 on drive sleeve 1109 outer wall, threaded connection is at the inside shift ring 1111 of drive sleeve 1109 and connect the oil pocket 1110 at shift ring 1111 lower extreme, oil pocket 1110 and first oil duct 1014 intercommunication, be equipped with the spout on the other side inner wall of first annular chamber 1005, be connected with the slider 1112 with spout matched with on the shift ring 1111, be equipped with the spacing chamber with spacing pole 1106 matched with on the pivot 1105.
It should be noted that, in the process of adjusting the position of the electrode, when the moving column 1002 is adjusted to move upwards, the adjusting knob 1101 drives the rotating shaft 1105 to rotate in the forward direction, that is, the rotating direction of the ratchet 1102 and the limiting pawl 1104 is not limited, at this time, the adjusting knob 1101 can drive the rotating shaft 1105 and the driving gear 1107 to rotate in the forward direction, the driving gear 1107 drives the ring gear 1108 and the driving sleeve 1109 to rotate in the forward direction, and the moving ring 1111 is limited by the slider 1112 and the sliding groove, so the driving sleeve 1109 can drive the moving ring 1111 screwed thereto to move downwards after rotating, the moving ring 1111 starts to press the oil bag 1110 when moving downwards, oil in the oil bag 1110 flows through the first oil passage 1014, the second oil passage 1015, the oil passage 1012 and finally flows into the stroke sleeve 1011, at this time, the oil can drive the piston 1022 to move upwards and drive the supporting rod 1020 to move upwards, so as to drive the moving column 1002, The bracket 9, the high-voltage electrode 7 and the noise receiving electrode 8 move upwards, the ratchet wheel 1102 receives the limiting effect of the limiting claw 1104, and the limiting claw 1104 can limit the reverse rotation after the upward moving process is finished, so that the effect of stable support is achieved;
in the process of controlling the electrode to move downwards, the adjusting knob 1101 is pulled outwards, because the adjusting knob 1101 is connected with the rotating shaft 1105 in a sliding manner through the limiting rod 1106, the distance between the adjusting knob 1101 and the rotating shaft 1105 can be adjusted without affecting the connection relationship between the adjusting knob 1101 and the rotating shaft 1105, the adjusting knob 1101 can still drive the rotating shaft 1105 to rotate, and vice versa, when the adjusting knob 1101 is pulled outwards, the ratchet 1102 and the limiting claw 1104 on the adjusting knob are separated, no limiting is performed, the self gravity of the high voltage electrode 7 and the noise receiving electrode 8 presses the bracket 9 and the moving column 1002, the moving column 1002 moves downwards and drives the cylinder 1019 and the supporting rod 1020 to move downwards, in the process, the piston re-presses the oil body into the oil bag 1110 and drives the moving ring 1111 to move upwards, in the process, the driving sleeve 1109 rotates reversely and provides a certain friction force for the moving ring 1111, and the friction force can be converted into a buffer force for buffering the electrode to move downwards, meanwhile, the slow exhaust process of the buffer air bag 1023 is matched, so that the electrode can be in a slow and stable descending process, the electrode is prevented from being damaged due to too fast descending, meanwhile, the electrode does not need to be manually supported to move downwards, and the safety is greatly improved.
As shown in fig. 2, 3, and 7, a first annular groove 1007 is disposed at the bottom end of the first annular chamber 1005, a second annular groove 1008 communicated with the first annular groove 1007 is disposed at a position, close to the bottom, of the outer wall of the fixing column 1001, a first annular member matched with the first annular groove 1007 is connected to the bottom end of the driving sleeve 1109, a second annular member matched with the second annular groove 1008 is connected to the inner wall of the index ring 1003, the first annular member is connected with the second annular member, and a scale mark matched with the index ring 1003 is disposed on the outer wall of the fixing column 1001.
It should be noted that, when the driving sleeve 1109 rotates, the first ring-shaped member, the second ring-shaped member and the index ring 1003 can be driven to rotate at the same angle, the driving sleeve 1109 can rotate at a designated angle to drive the moving ring 1111 to move downward for a designated distance, and after the moving ring 1111 moves downward for a designated distance, the moving piston 1022 can be driven to move a corresponding distance, the calculation method is the prior art, is similar to a screw rod moving mechanism, and performs calculation according to specific design, then the moving distance and the rotating angle are correspondingly defined, and the scale mark pointed by the index ring 1003 when rotating is the electrode moving distance, so that the electrode moving distance can be conveniently and visually checked and controlled by workers, the accuracy of the electrode moving distance is greatly improved, the comprehensive test verification method can meet comprehensive test verification of multiple performance parameters such as discharge current of the electrostatic discharge brush of the airplane, radio frequency discharge noise, continuous discharge, power consumption, electric flashover test and the like in the MIL-DTL-9129G standard.
In the description of the present invention, it is to be understood that the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention.
Claims (7)
1. The utility model provides an aircraft static discharger radio frequency discharge noise test testing arrangement which characterized in that: comprises a bracket, a DC program-controlled high-voltage power supply arranged on the bracket, a structure body capacitor, a high-voltage cable, a fixed test piece bottom plate, a direct-reading microammeter, an equivalent load, a coaxial cable, a radio frequency noise real-effective measurement controller, an optical fiber, a grounding bus bar, a base, a telescopic mechanism connected on the base, an adjusting mechanism arranged in the telescopic mechanism, a bracket connected at the top end of the telescopic mechanism, a noise receiving electrode and a high-voltage electrode connected on the bracket, a test piece electrode connected on the fixed test piece bottom plate and a plurality of universal wheels connected at the bottom of the bracket, the output end of the DC program-controlled high-voltage power supply is respectively connected with the input ends of the structure capacitor and the radio frequency noise real-effective measurement controller, the output end of the structure capacitor is connected with the input end of the high-voltage electrode through a high-voltage cable, the test piece electrode is connected with the direct-reading microammeter through the high-voltage cable, and a test current sampling resistor R is connected between the direct-reading microammeter and the structure capacitor.SThe direct-reading microammeter is connected with the radio frequency noise true and effective measurement controller through a coaxial cable, the equivalent load is used for converting noise received by the noise receiving electrode into a voltage signal and transmitting the voltage signal to the radio frequency noise true and effective measurement controller, and the radio frequency noise true and effective measurement controller is connected with the test platform through an optical fiber;
the structure capacitor comprises a first program-controlled high-voltage switch K1, a second program-controlled high-voltage switch K2, a first high-voltage resistor R1, a second high-voltage resistor R2, a third high-voltage resistor R3 and a high-voltage capacitor CHVOne end of the first program-controlled switch K1 is connected with the positive output end of the DC program-controlled high-voltage power supply, the other end of the first program-controlled switch K1 is connected with one end of a first high-voltage resistor R1, and the other end of the first high-voltage resistor R1 is connected with a high-voltage capacitor CHVIs connected with one end of a second program-controlled switch K2, the other end of the second program-controlled switch K2 is connected with one end of a third high-voltage resistor R3, a high-voltage capacitor CHVThe other end of the third high-voltage resistor R3 and the other end of the third high-voltage resistor R3 are both connected with the negative output end of the DC program-controlled high-voltage power supply, and the negative output end of the DC program-controlled high-voltage power supply is connected to the grounding bus bar;
the telescopic mechanism comprises a fixed column connected to the base, a moving column slidably connected to the fixed column, an index ring sleeved outside the fixed column and a plurality of buffer mechanisms connected between the moving column and the fixed column, the adjusting mechanism is used for adjusting the moving column to reciprocate up and down along the axis of the fixed column, the buffer mechanisms are controlled to suck air from the outside and form a heat insulation layer when the moving column moves up, and the buffer mechanisms are controlled to exhaust air to the outside when the moving column moves down and provide buffer supporting force for the moving column together with the adjusting mechanism.
2. The aircraft electrostatic discharger radio frequency discharge noise test testing device according to claim 1, wherein: the oil-circulating type oil-circulating device is characterized in that a first circular groove is arranged in the middle of the fixed column, a first annular cavity is arranged in the wall of the first circular groove, a second annular cavity is arranged in the middle of the inner wall of one side of the first annular cavity, a first oil duct is arranged at the bottom of the first annular cavity, a first wiring hole and a plurality of air holes are formed in the middle of the bottom of the first circular groove, the air holes are evenly distributed around the first wiring hole, the bottom of the first circular groove is connected with a wiring pipe and a plurality of stroke sleeves, an oil-circulating groove matched with the plurality of stroke sleeves is formed in the bottom of the first circular groove, a second oil duct is arranged between the plurality of first oil ducts and the corresponding oil-circulating grooves, the movable column is located in the first circular groove, an adjusting cavity is arranged on the inner wall of the top of the second annular cavity, and a shaft hole penetrating through the outer wall of the fixed column is formed in the inner wall of the adjusting cavity.
3. The aircraft electrostatic discharger radio frequency discharge noise test testing device according to claim 2, wherein: the middle part of removing the post is equipped with the second circular slot, and the top of second circular slot is connected with cylinder and a plurality of and stroke sleeve pipe matched with bracing piece, and the one end of bracing piece is connected with the piston, and the piston is located the stroke sleeve pipe, is equipped with the second wiring hole in the cylinder, and the second wiring hole runs through and removes the post, and a plurality of buffer gear connects in the cylinder bottom and sets up with a plurality of air vent is corresponding.
4. The aircraft electrostatic discharger radio frequency discharge noise test testing device according to claim 3, wherein: buffer gear is including connecting the buffering gasbag in the cylinder bottom, connecting the air current control panel on the air vent inner wall, locating a plurality of inlet port and an exhaust hole on the air current control panel, and the top of air current control panel is connected with the plastic film that covers the inlet port, and the plastic film only has one end to be connected with the top of air current control panel, the one end of buffering gasbag is connected with the bottom of first circular slot and covers corresponding air vent.
5. The aircraft electrostatic discharger radio frequency discharge noise test testing device according to claim 2, wherein: adjustment mechanism is including the adjust knob who passes the shaft hole, connect ratchet on adjust knob, connect connecting plate on adjust chamber top inner wall, connect spacing claw on the connecting plate, connect in the gag lever post of adjust knob one end, swing joint pivot on adjust chamber lateral wall, connect in the pivot drive gear, locate the indoor actuating sleeve of first annular chamber, connect the ring gear on the actuating sleeve outer wall, threaded connection at the inside shift ring of actuating sleeve and connect the oil bag at the shift ring lower extreme, oil bag and first oil duct intercommunication, be equipped with the spout on the opposite side inner wall of first annular chamber, be connected with on the shift ring with spout matched with slider, be equipped with in the pivot with the spacing cavity of gag lever post matched with.
6. The aircraft static discharger radio frequency discharge noise test testing device according to claim 5, wherein: the bottom of first annular chamber is equipped with first ring channel, and the position that the outer wall of fixed column is close to the bottom is equipped with the second ring channel with first ring channel intercommunication, and the telescopic bottom of drive is connected with the first loop forming element with first ring channel matched with, and the inner wall of index ring is connected with the second loop forming element with second ring channel matched with, and first loop forming element and second loop forming element are connected, are equipped with the scale mark with index ring matched with on the fixed column outer wall.
7. A method of performing an aircraft electrostatic arrester radio frequency discharge noise test using the apparatus of any of claims 1 to 6, comprising the steps of:
s1, fixing the test piece on the fixed test piece base plate and connecting the test piece with the test piece electrode which passes through the direct-reading microampere meter and the test current sampling resistor RSThe device is connected to the grounding bus bar to form a current loop, the moving column is driven by the adjusting mechanism to drive the bracket, the high-voltage electrode and the noise receiving electrode to move upwards along the axis direction of the fixed column, and when one end of the test piece electrode is positioned at the center of the high-voltage electrode, the movement is stopped;
step S2, controlling the radio frequency noise true and effective measurement controller to perform self-checking;
step S3, initiating a handshake protocol to the DC program-controlled high-voltage power supply through the radio frequency noise true and effective measurement controller and initializing the voltage of the DC program-controlled high-voltage power supply to be 0V;
s4, the test platform remotely adjusts the current and voltage of the DC program-controlled high-voltage power supply through the radio frequency noise real effective measurement controller, simultaneously, a first remote switch K1 is started, and when the voltage of the DC program-controlled high-voltage power supply rises to more than 2KV, corona discharge is started between the high-voltage electrode and the test piece electrode;
step S5, gradually increasing the voltage of the DC program control high-voltage power supply until the display value of the direct-reading microammeter reaches a preset test current of 50 muA, and then the radio frequency noise real effective measurement controller starts to acquire radio frequency total noise voltage data and transmits the radio frequency total noise voltage data to the test platform;
and step S6, after data acquisition is completed, remotely closing the current and voltage of the DC program control high-voltage power supply by the test platform through the radio frequency noise real effective measurement controller, simultaneously starting the second remote switch K2, starting system discharge, disconnecting the first and second remote switches K1 and K2 after the discharge is finished, closing the system power supply, and adjusting the movable column through the adjusting mechanism to drive the bracket, the high-voltage electrode and the noise receiving electrode to move downwards along the axis direction of the fixed column until the reset is completed.
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