An electromagnetic environment effect testing device and method for aero-engines

Abstract

This invention belongs to the field of engine testing technology, and specifically relates to a test device and method for electromagnetic environment effects of aero-engines. It includes a shielded room with a control room located on its side; a test platform is installed inside the shielded room, and the entire engine is mounted on the test platform; an electrical auxiliary system and a testing system are arranged outside the shielded room and connected to the entire engine; a power supply is located in the control room, and a line impedance network is located inside the shielded room, with its two ends connected to the power supply and the entire engine, respectively; test components are arranged inside the shielded room, and corresponding tests are conducted by activating the test components and the entire engine; this makes the test closer to actual operating conditions, and the related test results more realistic and reliable.

Description

Technical Field

[0001] This invention belongs to the field of engine testing technology, and specifically relates to a device and method for testing the electromagnetic environment effects of aero engines. Background Technology

[0002] As a crucial power source for aircraft, aero-engines must be designed with electromagnetic compatibility (EMC) in mind. This means the engine must be able to operate reliably in a specified electromagnetic environment without causing unacceptable electromagnetic interference to any equipment within that environment. Conducting EMC tests on aero-engines is a vital means of assessing and verifying the compliance of the engine, its electrical and electronic systems, and accessories with electromagnetic emissions and susceptibility. Aero-engine EMC tests primarily include conducted emission tests, conducted susceptibility tests, radiated emission tests, radiated susceptibility tests, lightning-induced transient susceptibility tests, and strong electromagnetic environment tests.

[0003] High-intensity radiation field testing is one of the test items in strong electromagnetic environment testing. It is an important means to verify that the engine can still operate in accordance with requirements after being exposed to a specific high-intensity radio frequency radiation environment. High-power microwave testing is one of the test items in strong electromagnetic environment testing. It is an important means to verify that the engine can survive and protect itself after being exposed to a specific high-power microwave environment. 25Hz~100kHz magnetic field radiation sensitivity testing is one of the test items in radiation sensitivity testing. It is an important means to verify that the engine can still operate in accordance with requirements after its outer surface and interconnecting cables are subjected to specified magnetic field radiation interference. Electrostatic discharge sensitivity testing is one of the test items in conducted sensitivity testing. It is an important means to verify that the engine can still operate in accordance with requirements after its outer surface is subjected to specified electrostatic discharge interference.

[0004] Existing engine tests typically focus on the engine's electrical and electronic systems and accessories, or combine the engine's electrical and electronic systems and accessories into a system as the test object, conducting tests on all accessories and systems with electrical characteristics or electrical interfaces belonging to the engine. Summary of the Invention

[0005] To address the above problems, this invention proposes a test device for the electromagnetic environment effects of aero-engines. This includes a shielded room, with a control room located on the side of the shielded room; The shielded room is equipped with a test platform, on which the complete engine is mounted. An electrical auxiliary system and a testing system are arranged outside the shielding room, and the electrical auxiliary system and the testing system are electrically connected to the engine. The control room is equipped with a power supply, and the shielded room is equipped with a line impedance network. The two ends of the line impedance network are connected to the power supply and the engine respectively. The shielded room is equipped with test components, and corresponding tests are conducted by activating the test components and the entire engine.

[0006] Furthermore, the test assembly includes a stirrer device one, a stirrer device two, and a field generating antenna; a field generator is installed in the control room; the field generating antenna is arranged opposite to the stirrer device one, and the field generating antenna is connected to the field generator through a feed cable.

[0007] Furthermore, the test assembly includes a transmitting antenna and a receiving antenna; radio frequency absorbing material is installed on the inner sidewall of the shielded room; a directional coupler, a microwave simulation source, a microwave control system, and a peak power meter are arranged in the control room; the transmitting antenna passes through the shielded room and is connected to the directional coupler, the other end of the directional coupler is connected to the microwave simulation source and the peak power meter respectively, and the other end of the peak power meter is connected to an attenuation component; the microwave simulation source is connected to the microwave control system; the receiving antenna is arranged on the test platform and is connected to the attenuation component; a turntable control system is also arranged in the control room, the test platform is a circular turntable, and the rotation control system is connected to the circular turntable.

[0008] Furthermore, the test assembly includes a radiating loop antenna, a signal generator, a current probe, and a measurement receiver, all housed within a shielded room. The radiating loop antenna is positioned close to the outer surface of the engine and is connected to the signal generator. The current probe is located on the connecting cable between the radiating loop antenna and the signal generator and is connected to the measurement receiver.

[0009] Furthermore, the test assembly includes a protective conductor, a grounding reference plane, a second power supply, an electrostatic gun power supply, and an electrostatic gun body; the protective conductor is installed on the inner wall of the shielded room near the control room, and is connected to the grounding reference plane; the grounding reference plane is installed on the side of the test platform near the protective conductor; the second power supply is connected to the protective conductor; one end of the electrostatic gun power supply is connected to the second power supply, and the other end is connected to the electrostatic gun body; the electrostatic gun body is connected to the grounding reference plane.

[0010] Furthermore, an engine mounting bracket is arranged on the test platform, and the entire engine is mounted on the engine mounting bracket.

[0011] This invention proposes a test method for electromagnetic environment effects of aero-engines, based on the aforementioned test device for electromagnetic environment effects of aero-engines, comprising: Configure and install the test components; Preheat the entire engine by powering it on; Start the test components to perform the test operation; The electrical auxiliary system simulates and remotely controls the overall operating status of the engine. The testing system monitors, displays, and records the overall operating status of the engine.

[0012] Furthermore, the test components are activated to perform test operations, including: The field generator applies a high-intensity radio frequency interference signal of a specific frequency to the entire engine; According to the corresponding set frequency, stirrer device one and stirrer device two rotate at the set speed; The overall operating status of the engine was evaluated during a complete rotation of stirrer device 1 and stirrer device 2 at different test frequencies.

[0013] Furthermore, the test components are activated to perform test operations, including: Preheating the microwave simulation source: Preheat the microwave simulation source to a stable operating state and set the test parameters; Radiation field measurement: Conduct radiation field measurements and record the results; Microwave irradiation and monitoring of performance indicators: The engine was subjected to high-power microwave irradiation, and the changes in the engine's overall performance indicators were monitored. Result comparison: Compare the measurement results with the changes in performance indicators. If the set requirements are not met, stop the test, make adjustments, and repeat the high-power microwave irradiation on the entire engine. Adjust the angle and direction: Adjust the rotation angle of the circular turntable or the pitch angle of the engine mounting bracket; then repeat the high-power microwave irradiation of the entire engine and compare the measurement results with the changes in performance indicators; Adjusting the polarization: Change the polarization of the transmitting antenna again, repeat the microwave irradiation and monitoring of changes in indicators, compare the results and adjust the angle and direction.

[0014] Furthermore, the test components are activated to perform test operations, including: The radiating loop antenna is positioned at a corresponding distance on the surface of the engine. The signal generator applies an interference current signal to the radiating loop antenna; The entire engine was scanned and tested within the corresponding frequency range; Monitor the sensitivity of the entire engine and record the test data.

[0015] Furthermore, the test components are activated to perform test operations, including: The entire outer surface of the engine is discharged using the electrostatic gun itself; At each test point, discharge N times with both positive and negative polarities; Monitor the sensitivity of the entire engine and record the test data.

[0016] Beneficial effects The advantages of this invention over the prior art are as follows: 1. This application ensures that the engine's electrical and electronic systems and accessories are all installed in the complete machine assembly state, and that each electrical and electronic system and accessory is operating under load conditions before the complete machine is ignited and run, making the test closer to the actual working conditions and the relevant test results more realistic and reliable.

[0017] 2. The high-intensity radiation field test conducted on the engine in this application, under the condition that the entire engine is preheated and all electrical and electronic systems and accessories are in the working state before engine ignition and operation, is closer to the actual working conditions. The engine's electrical and electronic systems and accessories are all in the installed state of the entire engine, and each electrical and electronic system and accessory is operating under the load conditions before the entire engine is ignited and operated. The relevant electrical stress and electromagnetic coupling factors can be more realistically reflected. It can directly reflect the electromagnetic compatibility characteristics of the engine after being exposed to specific high-intensity radio frequency radiation environment, high-power microwave environment, after the engine's outer surface and interconnecting cables are subjected to specified magnetic field radiation interference, and after the engine's outer surface is subjected to specified electrostatic discharge interference. The relevant test results are more realistic and reliable.

[0018] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A schematic diagram of the structure in Embodiment 1 of the present invention is shown.

[0021] Figure 2 A schematic diagram of the structure in Embodiment 2 of the present invention is shown.

[0022] Figure 3 A schematic diagram of the structure in Embodiment 3 of the present invention is shown.

[0023] Figure 4 A schematic diagram of the structure in Embodiment 4 of the present invention is shown.

[0024] In the diagram, 1. Shielded room; 2. Control room; 3. Test platform; 4. Engine assembly; 5. Electrical auxiliary system; 6. Testing system; 7. Filter 1; 8. Filter 2; 9. Power supply 1; 10. Filter 3; 11. Line impedance network; 12. Radiation loop antenna; 13. Signal generator; 14. Current probe; 15. Measurement receiver; 16. Engine mounting bracket; 17. Stirring Device 1; 18. Field Generating Antenna; 19. Feeder Cable; 20. Field Generator; 21. Stirring Device 2; 22. Uniform Field Space; 23. Radio Frequency Absorbing Material; 24. Transmitting Antenna; 25. Directional Coupler; 26. Microwave Analog Source; 27. Microwave Control System; 28. Peak Power Meter; 29. ​​Attenuation Component; 30. Receiving Antenna; 31. Turntable Control System; 32. Protective conductor; 33. Grounding reference plane; 34. Power supply II; 35. Static gun power supply; 36. Static gun body. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0026] Example 1: This application discloses an electromagnetic environment effect testing device for an aero-engine, comprising a shielded room 1, with a control room 2 arranged on the side of the shielded room 1; The shielded room 1 is equipped with a test platform 3, and the test platform 3 is equipped with an engine 4. An electrical auxiliary system 5 and a testing system 6 are arranged outside the shielded room 1. The electrical auxiliary system 5 and the testing system 6 are electrically connected to the engine 4. The control room 2 is equipped with a power supply 9, and the shielded room 1 is equipped with a line impedance network 11. The two ends of the line impedance network 11 are connected to the power supply 9 and the engine 4, respectively. The shielded room 1 is equipped with test components, and corresponding tests are conducted by activating the test components and the engine 4.

[0027] The test assembly includes a stirrer device 17, a stirrer device 21, and a field generating antenna 18; a field generator 20 is installed in the control room 2; the field generating antenna 18 is arranged opposite to the stirrer device 17, and the field generating antenna 18 is connected to the field generator 20 through a feed cable 19.

[0028] A control room 2 is arranged on the side of the shielded room 1. The shielded room 1 has a closed electromagnetic shielding structure, which can shield and isolate electromagnetic signals from the inside and outside. There are no unnecessary wave-absorbing materials inside the bottom, top, and side shielding layers of the shielded room 1, so as to ensure that electromagnetic waves can be reflected multiple times through the bottom, top, and side shielding layers of the shielded room 1, thereby extending the attenuation time. A conductive test bench (test platform 3) is installed inside the shielded room 1. The upper surface of the conductive test bench is designed to be a basically flat mounting surface and flush with the ground of the shielded room 1. The engine mounting bracket 16 is arranged and installed on the upper surface of the conductive test bench, and the engine 4 is installed on the engine mounting bracket 16.

[0029] An electrical auxiliary system 5 and a testing system 6 are arranged outside the shielded room 1. The connecting cables of the electrical auxiliary system 5 and the testing system 6 are connected to the engine 4 via interconnection filter 7 and interconnection filter 8 installed on the shielding layer of the shielded room 1, respectively. Interconnection filter 7 and interconnection filter 8 can filter out excess electromagnetic signals entering and leaving the shielded room 1 through the connecting cables.

[0030] Power supply 9 is located in control room 2. Its connecting cable is connected to the line impedance network 11 (i.e., line impedance stabilization network) installed in shielded room 1 via a power input filter mounted on the shielding layer of shielded room 1. The power input filter filters out excess electromagnetic signals entering and exiting shielded room 1 via the connecting cable. The other end of the line impedance network 11 is connected to the engine assembly 4. Agitator device 17 is vertically arranged in shielded room 1 near the corner of the shielding layer in front of the engine. Agitator device 17 can rotate along a centerline perpendicular to the floor of shielded room 1. Field generating antenna 18 is located near and facing agitator device 17. Field generating antenna 18 is connected to field generator 20 located in control room 2 via a reverberation chamber feed cable 19 through the shielding layer of shielded room 1. The agitator device 21 is horizontally arranged at the corner of the rear shielding layer and the top shielding layer inside the shielded room 1. The center line of the agitator device 21 is parallel to the top shielding layer and the rear shielding layer of the engine in the shielded room 1. The agitator device 21 can rotate along its own center line.

[0031] In the experimental apparatus of this invention, the operating status of the engine 4 is simulated and remotely controlled by the electrical auxiliary system 5. The operating status parameters of the engine 4 are monitored, displayed, and recorded by the testing system 6.

[0032] When conducting high-intensity radiation field tests on aero-engines, the field generator 20 generates an interference signal, which is transmitted to the field generating antenna 18 via the reverberation chamber feed cable 19. The interference signal generates a radio frequency radiation interference signal in the antenna radiation space through the field generating antenna 18. The boundary conditions of the metal cavity are continuously changed by the rotation of the first stirrer device 17 and the second stirrer device 21, so that the radio frequency radiation interference signal is reflected and scattered multiple times through the first stirrer device 17, the second stirrer device 21 and the inner shielding layer of the shielding chamber 1. Finally, a high spatial field strength, random polarization and statistical uniform electromagnetic field, i.e., uniform field space 22, is formed in the shielding chamber 1. The uniform field space 22 acts on the entire engine 4.

[0033] In Example 2, unlike Example 1, the test assembly includes a transmitting antenna 24 and a receiving antenna 30; the inner wall of the shielded room 1 is fitted with radio frequency absorbing material 23; the control room 2 contains a directional coupler 25, a microwave simulation source 26, a microwave control system 27, and a peak power meter 28; the transmitting antenna 24 passes through the shielded room 1 and is connected to the directional coupler 25, the other end of the directional coupler 25 is connected to the microwave simulation source 26 and the peak power meter 28 respectively, and the other end of the peak power meter 28 is connected to an attenuation element 29; the microwave simulation source 26 is connected to the microwave control system 27; the receiving antenna 30 is arranged on the test platform 3 and is connected to the attenuation element 29; the control room 2 also contains a turntable control system 31, the test platform 3 is a circular turntable, and the rotation control system is connected to the circular turntable.

[0034] The high-power microwave test apparatus for aero-engines consists of a control room 2 located on the side of a shielded room 1. The shielded room 1 has a closed electromagnetic shielding structure, capable of shielding and isolating electromagnetic signals from both inside and outside the room. Radio frequency absorbing material 23 is installed inside the side and top shielding layers of the shielded room 1. This material absorbs electromagnetic signals incident on the inner walls of the side and top shielding layers of the shielded room 1, preventing secondary reflections of the electromagnetic signals generated by the test equipment during high-power microwave testing, thus avoiding contamination and damage to the electromagnetic testing environment within the shielded room 1. A circular turntable (i.e., test platform 3) is installed inside the shielded room 1. The upper surface of the turntable is designed to be a basically flat mounting surface, flush with the floor of the shielded room 1. The turntable can rotate around its central axis in the horizontal plane and stop at any angle. The engine mounting bracket 16 is arranged and installed on the upper surface of the circular turntable. The engine mounting bracket 16 is designed to rotate 90 degrees or -90 degrees along a specific horizontal axis. The engine 4 is installed on the engine mounting bracket 16. By adjusting the rotation angle of the specific horizontal axis of the engine mounting bracket 16, the engine can be tilted down or tilted up 90 degrees relative to the horizontal plane.

[0035] Electrical and auxiliary systems and testing systems 6 are arranged outside the shielded room 1. The connecting cables of the electrical and auxiliary systems and testing systems 6 are connected to the engine 4 via filters 7 and 8 installed on the shielding layer of the shielded room 1. Filters 7 and 8 can filter out excess electromagnetic signals entering and leaving the shielded room 1 through the connecting cables.

[0036] Power supply 9 is located in control room 2. Its connecting cable is connected to filter 10 (installed on the shielding layer of shielded room 1) and line impedance network 11 (installed in shielded room 1). Filter 10 filters out excess electromagnetic signals entering and exiting shielded room 1 via the connecting cable. The other end of line impedance network 11 is connected to engine 4. Transmitting antenna 24 is located in shielded room 1 near engine 4. It is connected via a connecting cable through the shielding layer of shielded room 1 to directional coupler 25 located in control room 2. One end of directional coupler 25 is connected via a connecting cable to high-power microwave analog source 26, which is connected via a connecting cable to microwave control system 27. The other end of directional coupler 25 is connected via a connecting cable to peak power meter 28, which is connected via a connecting cable to attenuation element (i.e., attenuation element 29). The receiving antenna 30 and the engine 4 are arranged side by side on a circular turntable. The receiving antenna 30 and the engine are at the same distance from the transmitting antenna 24. The receiving antenna 30 is connected to the attenuation circuit via a connecting cable. The turntable control system 31 is located in the control room 2. The turntable control system 31 is connected to the circular turntable via a connecting cable through the shielding layer of the shielding room 1.

[0037] The engine's operating status is simulated and remotely controlled through electrical and auxiliary systems. Engine operating status parameters are monitored, displayed, and recorded via test system 6.

[0038] When conducting high-power microwave tests on aero engines, the microwave control system 27 controls the high-power microwave simulation source 26 to generate high-power microwave interference signals, which are then transmitted to the directional coupler 25. After passing through the directional coupler 25, the high-power microwave interference signals are transmitted to the transmitting antenna 24. The transmitting antenna 24 generates high-power microwave interference signals in the antenna radiation space, which act on the engine and the receiving antenna 30.

[0039] In Example 3, unlike Example 1, the test assembly includes a radiating loop antenna 12, a signal generator 13, a current probe 14, and a measurement receiver 15. The radiating loop antenna 12 is positioned near the outer surface of the engine assembly 4 and is connected to the signal generator 13. The current probe 14 is positioned on the connecting cable between the radiating loop antenna 12 and the signal generator 13 and is connected to the measurement receiver 15.

[0040] The 25Hz-100kHz magnetic field radiation susceptibility testing device for aero-engines consists of a control room 2 located on the side of a shielded room 1. The shielded room 1 has a closed electromagnetic shielding structure, capable of shielding and isolating electromagnetic signals from both inside and outside the room. A test platform 3 is installed inside the shielded room 1. The upper surface of the test platform 3 is designed as a basically flat mounting surface, flush with the floor of the shielded room 1. The entire engine 4 is mounted on the upper surface of the test platform 3.

[0041] An electrical auxiliary system 5 and a testing system 6 are arranged outside the shielded room 1. The connecting cables of the electrical auxiliary system 5 and the testing system 6 are connected to the engine via filters 7 and 8, which are installed on the shielding layer of the shielded room 1, respectively. Filters 7 and 8 can filter out excess electromagnetic signals entering and leaving the shielded room 1 through the connecting cables.

[0042] Power supply 9 is located in control room 2. Its connecting cable is connected to a line impedance stabilization network installed in shielded room 1 via filter 3 10 mounted on the shielding layer. Filter 3 10 filters out excess electromagnetic signals entering and exiting shielded room 1 via the connecting cable. The other end of the line impedance network 11 is connected to the engine assembly 4. A radiating loop antenna 12 is positioned in shielded room 1 near the outer surface of engine assembly 4, with a distance of 5 cm between the antenna and the surface. The antenna is connected to signal generator 13 via two connecting cables. A current probe 14 is positioned on a connecting cable between the radiating loop antenna 12 and signal generator 13. The current probe 14 is connected to measurement receiver 15 via a connecting cable.

[0043] The engine's operating status is simulated and remotely controlled via the electrical auxiliary system 5. The engine's operating status parameters are monitored, displayed, and recorded via the testing system 6.

[0044] When conducting a 25Hz to 100kHz magnetic field radiation sensitivity test of an aero-engine, the signal generator 13 generates an interference current signal which is transmitted to the radiating ring antenna 12. After the interference current signal passes through the radiating ring antenna 12, it generates magnetic field radiation near the radiating ring antenna 12. Then, the position and orientation of the radiating ring antenna 12 are adjusted to bring it closer to the outer surface of the engine or the interconnecting cable, so that the magnetic field radiation generated by the radiating ring antenna 12 acts on the outer surface of the engine or the interconnecting cable.

[0045] In Example 4, unlike Example 1, the test assembly includes a protective conductor 32, a grounding reference plane 33, a second power supply 34, an electrostatic gun power supply 35, and an electrostatic gun body 36. The protective conductor 32 is installed on the inner wall of the shielded room 1 near the control room 2, and is connected to the grounding reference plane 33. The grounding reference plane 33 is installed on the side of the test platform 3 near the protective conductor 32. The second power supply 34 is connected to the protective conductor 32. One end of the electrostatic gun power supply 35 is connected to the second power supply 34, and the other end is connected to the electrostatic gun body 36. The electrostatic gun body 36 is connected to the grounding reference plane 33.

[0046] The electrostatic discharge sensitivity testing device for aircraft engines consists of a control room 2 located on the side of a shielded room 1. The shielded room 1 has a closed electromagnetic shielding structure, capable of shielding and isolating electromagnetic signals from both inside and outside the room. A test platform 3 is installed inside the shielded room 1. The upper surface of the test platform 3 is designed as a basically flat mounting surface, flush with the floor of the shielded room 1. The engine is mounted on the upper surface of the test platform 3.

[0047] An electrical auxiliary system 5 and a testing system 6 are arranged outside the shielded room 1. The connecting cables of the electrical auxiliary system 5 and the testing system 6 are respectively connected to the engine 4 via filters 7 and 8 installed on the shielding layer of the shielded room 1. Filters 7 and 8 can filter out excess electromagnetic signals entering and leaving the shielded room 1 through the connecting cables.

[0048] Power supply 9 is located in control room 2. The connecting cable of power supply 9 is connected to the line impedance stabilization network installed in shielded room 1 via filter 3 10 installed on the shielding layer of shielded room 1. Filter 3 10 filters out excess electromagnetic signals entering and exiting shielded room 1 via the connecting cable. The other end of the line impedance network 11 is connected to the engine 4. Protective conductor 32 is installed on the side shielding layer of shielded room 1 near control room 2. Protective conductor 32 is connected to grounding reference plane 33 via a connecting cable. Grounding reference plane 33 is installed on the side of test platform 3 in shielded room 1 near protective conductor 32. Grounding reference plane 33 is 2m long along the engine axial direction and 0.3m long along the engine transverse direction. The distance between grounding reference plane 33 and test platform 3 along the engine transverse direction is 0.1m. Power supply 2 34 is installed in shielded room 1 and connected to protective conductor 32. Static gun power supply 35 and static gun are installed in shielded room 1. One end of static gun power supply 35 is connected to power supply 2 34 through a connecting cable. The other end of static gun power supply 35 is connected to static gun body 36 through a connecting cable. Static gun body 36 is connected to grounding reference plane 33 through a connecting cable.

[0049] The engine's operating status is simulated and remotely controlled through the electrical auxiliary system 5; the engine's operating status parameters are monitored, displayed, and recorded through the testing system 6.

[0050] When the test apparatus of the present invention conducts electrostatic discharge sensitivity tests on aero-engines, the power supply provides power to the electrostatic gun power supply 35, which converts the power supply into DC high voltage to supply the electrostatic gun body 36. The electrostatic gun discharges and acts on the outer surface of the engine by manually controlling the discharge switch of the electrostatic gun.

[0051] In one embodiment of the present invention, the electrical auxiliary system 5 and the testing system 6 are respectively connected to the host computer arranged in the control room 2 or the electrical auxiliary system 5 and the testing system 6 are arranged in the control room 2; the control room 2 can also be arranged at the bottom of the shielded room 1. When the control room 2 is arranged at the bottom of the shielded room 1, an overhead layer structure is designed below the bottom of the shielded room 1; the power supply 9 can also be arranged in other locations outside the shielded room 1 and outside the control room 2.

[0052] In one embodiment of the present invention, the field generator 20 may also be arranged in other locations in the unshielded room 1 and the non-control room 2; the electrical auxiliary system 5 may also provide the engine 4 with a simulated drive device and simulated load so that the working state of the engine 4 is as close as possible to the test load conditions when the engine 4 is ignited, and a high-intensity radiation field test is carried out under this state. In one embodiment of the present invention, the peak power meter 28 can be replaced by an oscilloscope or a detector plus an oscilloscope; the directional coupler 25, the high-power microwave simulation source 26, the microwave control system 27, the peak power meter 28, the attenuation component 29, and the turntable control system 31 can also be arranged in other locations outside the unshielded room 1 and the non-control room 2; the electrical auxiliary system 5 can also provide the engine as a whole with a simulated drive device and a simulated load so that the working state of the engine 4 is as close as possible to the test load conditions when the engine 4 is ignited, and high-power microwave tests can be carried out under this state; In one embodiment of the present invention, the electric auxiliary system 5 can also provide the engine 4 with a simulated drive device and a simulated load so that the working state of the engine 4 is as close as possible to the test load conditions when the engine 4 is ignited, and the magnetic field radiation sensitivity test of 25Hz to 100kHz can be carried out under this state.

[0053] This application proposes a test method for electromagnetic environment effects of aero-engines, based on the aforementioned test device for electromagnetic environment effects of aero-engines, including the configuration and installation of test components; Preheat the entire engine by energizing all four components; Start the test components to perform the test operation; The electrical auxiliary system 5 simulates and remotely controls the working status of the engine 4; The test system 6 monitors, displays, and records the working status of the engine 4.

[0054] In one embodiment of the present invention, activating the test component to perform a test operation includes: Field generator 20 applies a high-intensity radio frequency radiation interference signal of a specific frequency to the engine assembly 4; According to the corresponding set frequency, stirrer device 17 and stirrer device 21 rotate at the set speed; The working status of the engine 4 is evaluated during a complete rotation of the agitator device 17 and agitator device 21 at different test frequencies.

[0055] S1: Press Figure 1 The test configuration is as shown; S2: The engine unit 4 is powered on and preheated to ensure that all electrical, electronic systems and accessories of the engine unit 4 reach the normal operating state before engine ignition; S3: The control field generator 20 applies a high-intensity radio frequency radiation interference signal of a specific frequency to the engine unit 4. In the frequency band below 1 GHz, the stirrer device 17 and the stirrer device 21 rotate at a speed of 4 revolutions per minute, and above 1 GHz, they rotate at a speed of 2 revolutions per minute, or at a slower speed of 1 revolution per minute, continuously applying power; S4: At each test frequency, the operating state of the engine unit 4 must be evaluated during the complete rotation of the stirrer device 17 and the stirrer device 21. During the interference application process, the sensitivity of the engine unit 4 is monitored, and the test data is recorded; S5: The next test frequency is set according to the frequency step, and steps S3 to S4 are repeated until the upper limit of the test frequency is reached.

[0056] In one embodiment of the present invention, activating the test component to perform a test operation includes: Preheating microwave simulation source 26: Preheat microwave simulation source 26 to a stable operating state and set the test parameters; Radiation field measurement: Conduct radiation field measurements and record the results; Microwave irradiation and monitoring of performance changes: The engine 4 was subjected to high-power microwave irradiation, and the performance changes of the engine 4 were monitored. Result comparison: Compare the measurement results with the changes in performance indicators. If the set requirements are not met, stop the test and adjust before repeating the high-power microwave irradiation on the entire engine 4. Adjust the angle and direction: Adjust the rotation angle of the circular turntable or the pitch angle of the engine mounting bracket 16; then repeat the process of high-power microwave irradiation of the entire engine 4 and compare the measurement results with the changes in performance indicators; Adjusting the polarization: Change the polarization of the transmitting antenna 24 again, repeat the microwave irradiation and monitoring of changes in indicators, compare the results and adjust the angle and direction.

[0057] S1: Press Figure 2 The test configuration is as shown; S2: Preheat the high-power microwave simulation source 26 until it reaches a stable working state, and set the test parameters; S3: Measure the radiation field and record the measurement results; S4: Power on the engine 4 and preheat it so that all electrical, electronic systems and accessories of the engine 4 reach the normal working state before engine ignition; S5: Irradiate the engine 4 with high-power microwaves, monitor the changes in the performance indicators of the engine 4 during the test, record abnormal situations, and determine the safety margin; S6: Compare the measurement results and functional monitoring results with the criteria. If the requirements are not met, stop the test, find the cause and take corrective measures, and then repeat steps S4 to S5; S7: Adjust the rotation angle of the circular turntable or the pitch angle of the engine mounting bracket 16 to change the irradiation direction or position, and repeat steps S4 to S6 until all required irradiation directions or positions are achieved; S8: Change the polarization mode of the transmitting antenna 24, and repeat steps S4 to S7 until all required polarization modes are achieved.

[0058] In one embodiment of the present invention, activating the test component to perform a test operation includes: The radiating loop antenna 12 is positioned at a corresponding distance on the surface of the engine body 4; Signal generator 13 applies an interference current signal to radiating loop antenna 12; The entire engine 4 was scanned and tested within the corresponding frequency range; Monitor the sensitivity of the entire engine (4) and record the test data.

[0059] S1: Press Figure 3 The test configuration is as shown; S2: Power on and preheat the engine assembly 4 so that all electrical and electronic systems and accessories of the engine assembly 4 reach the normal operating state before engine ignition; S3: Place the radiating ring antenna 12 5cm away from the surface of each component and interconnecting cable of the engine assembly 4, keeping the ring plane of the radiating ring antenna 12 parallel to the test plane; S4: Control the signal generator 13 to apply a sufficient interference current signal to the radiating ring antenna 12 to generate a magnetic field strength at least 10dB greater than the test requirement limit, but not exceeding 19A (185dBpT), and scan the surface of each component and interconnecting cable of the engine assembly 4 in the frequency range of 25Hz to 100kHz; S5: Monitor the sensitivity of the engine assembly 4 during the interference application process, and record the test data.

[0060] In one embodiment of the present invention, activating the test component to perform a test operation includes: The electrostatic gun body 36 is used to discharge the entire outer surface of the engine. At each test point, discharge N times with both positive and negative polarities; Monitor the sensitivity of the entire engine (4) and record the test data.

[0061] Specifically, S1: according to Figure 4 The test configuration is shown below; S2: The engine assembly 4 is powered on and preheated so that all electrical, electronic systems and accessories of the engine assembly 4 reach the normal working state before the engine assembly 4 is ignited and operated; S3: The electrostatic gun body 36 is used to discharge the outer surface of each electronic device of the engine assembly 4 (outer surface of the assembly in the installed state) and all connectors respectively, and each test point is discharged 10 times for both positive and negative polarities; S4: During the interference application process, the sensitivity of the engine assembly 4 is monitored, and the test data is recorded at the same time.

[0062] The electromagnetic environment effect test device and test method for aero-engines disclosed in this application can conduct high-intensity radiation field tests, high-power microwave tests, 25Hz~100kHz magnetic field radiation sensitivity tests, and electrostatic discharge sensitivity tests on the entire engine 4. The test can complete the evaluation and verification of the engine and its electrical, electronic systems and accessories in a single test. Compared with the existing accessory or system-level high-intensity radiation field tests, the test frequency is reduced, which can shorten the test cycle and reduce the test cost to a certain extent.

[0063] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A test device for electromagnetic environment effects of aero-engines, characterized in that, It includes a shielded room (1), and a control room (2) is arranged on the side of the shielded room (1); The shielded room (1) is equipped with a test platform (3), and the test platform (3) is equipped with an engine (4). An electrical auxiliary system (5) and a testing system (6) are arranged outside the shielded room (1), and the electrical auxiliary system (5) and the testing system (6) are electrically connected to the engine (4). The control room (2) is equipped with a power supply (9), and the shielded room (1) is equipped with a line impedance network (11). The two ends of the line impedance network (11) are connected to the power supply (9) and the engine (4) respectively. The shielded room (1) is equipped with test components, and corresponding tests are conducted by starting the test components and the engine (4).

2. The electromagnetic environment effect testing device for aero-engines according to claim 1, characterized in that, The test assembly includes a stirrer device one (17), a stirrer device two (21), and a field generating antenna (18); a field generator (20) is installed in the control room (2); the field generating antenna (18) is arranged opposite to the stirrer device one (17), and the field generating antenna (18) is connected to the field generator (20) through a feed cable (19).

3. The electromagnetic environment effect testing device for aero-engines according to claim 1, characterized in that, The test assembly includes a transmitting antenna (24) and a receiving antenna (30); the inner wall of the shielded room (1) is equipped with radio frequency absorbing material (23); the control room (2) is equipped with a directional coupler (25), a microwave simulation source (26), a microwave control system (27), and a peak power meter (28); the transmitting antenna (24) passes through the shielded room (1) and is connected to the directional coupler (25), the other end of the directional coupler (25) is connected to the microwave simulation source (26) and the peak power meter (28) respectively, and the other end of the peak power meter (28) is connected to the attenuation component (29); the microwave simulation source (26) is connected to the microwave control system (27); the receiving antenna (30) is arranged on the test platform (3) and is connected to the attenuation component (29); the control room (2) is also equipped with a turntable control system (31), the test platform (3) is a circular turntable, and the rotation control system is connected to the circular turntable.

4. The electromagnetic environment effect testing device for aero-engines according to claim 1, characterized in that, The test assembly includes a radiating loop antenna (12), a signal generator (13), a current probe (14), and a measurement receiver (15) installed in a shielded room (1). The radiating loop antenna (12) is positioned close to the outer surface of the engine assembly (4) and is connected to the signal generator (13). The current probe (14) is located on the connecting cable between the radiating loop antenna (12) and the signal generator (13) and is connected to the measurement receiver (15).

5. The electromagnetic environment effect testing device for aero-engines according to claim 1, characterized in that, The test assembly includes a protective conductor (32), a grounding reference plane (33), a second power supply (34), an electrostatic gun power supply (35), and an electrostatic gun body (36). The protective conductor (32) is installed on the inner wall of the shielded room (1) near the control room (2), and the protective conductor (32) is connected to the grounding reference plane (33). The grounding reference plane (33) is installed on the side of the test platform (3) near the protective conductor (32). The second power supply (34) is connected to the protective conductor (32). One end of the electrostatic gun power supply (35) is connected to the second power supply (34), and the other end of the electrostatic gun power supply (35) is connected to the electrostatic gun body (36). The electrostatic gun body (36) is connected to the grounding reference plane (33).

6. A test apparatus for electromagnetic environment effects of an aero-engine according to claim 2 or 3, characterized in that, An engine mounting bracket (16) is arranged on the test platform (3), and the engine (4) is mounted on the engine mounting bracket (16).

7. A method for testing the electromagnetic environment effects of an aero-engine, based on the electromagnetic environment effect testing apparatus for an aero-engine according to any one of claims 1-6, characterized in that, include: Configure and install the test components; Preheat the entire engine (4) by powering it on; Start the test components to perform the test operation; The electrical auxiliary system (5) simulates and remotely controls the working status of the engine (4); The test system (6) monitors, displays and records the working status of the engine (4).

8. The method for testing the electromagnetic environment effects of an aero-engine according to claim 7, characterized in that, Start the test components to perform test operations, including: The field generator (20) applies a high-intensity radio frequency radiation interference signal of a specific frequency to the engine (4); According to the corresponding set frequency, stirrer device one (17) and stirrer device two (21) rotate at the set speed; The working status of the engine (4) is evaluated during a complete rotation of the agitator device 1 (17) and agitator device 2 (21) at different test frequencies.

9. The method for testing the electromagnetic environment effects of an aero-engine according to claim 7, characterized in that, Start the test components to perform test operations, including: Preheating the microwave simulation source (26): Preheat the microwave simulation source (26) to a stable working state and set the test parameters; Radiation field measurement: Conduct radiation field measurements and record the results; Microwave irradiation and monitoring index changes: The engine (4) was subjected to high-power microwave irradiation, and the performance index changes of the engine (4) were monitored. Result comparison: Compare the measurement results with the changes in performance indicators. If the set requirements are not met, stop the test and adjust before repeating the high-power microwave irradiation of the entire engine (4). Adjust the angle and direction: Adjust the rotation angle of the circular turntable or the pitch angle of the engine mounting bracket (16); repeat the process of high-power microwave irradiation of the entire engine (4) and compare the measurement results with the changes in performance indicators; Adjusting the polarization mode: Change the polarization mode of the transmitting antenna (24) again, repeat the microwave irradiation and monitoring index changes, result comparison and adjustment of angle direction.

10. The method for testing the electromagnetic environment effects of an aero-engine according to claim 7, characterized in that, Start the test components to perform test operations, including: Arrange the radiating ring antenna (12) at a corresponding distance on the surface of the engine (4); The signal generator (13) applies an interference current signal to the radiating loop antenna (12); The entire engine (4) was scanned and tested within the corresponding frequency range; Monitor the sensitivity of the engine (4) and record the test data.

11. The method for testing the electromagnetic environment effects of an aero-engine according to claim 7, characterized in that, Start the test components to perform test operations, including: The entire outer surface of the engine is discharged using the electrostatic gun body (36); At each test point, discharge N times with both positive and negative polarities; Monitor the sensitivity of the engine (4) and record the test data.

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