Aero-engine electric field radiation test system and method

Abstract

The present application belongs to the technical field of engine test, and particularly relates to an aero-engine electric field radiation test system and method, which comprises a shielding room, a signal generator, a control room, a measuring receiver and a data recording device arranged outside the shielding room; a transmitting antenna and a receiving antenna arranged inside the shielding room; the control room; a connecting cable of the signal generator connected with the transmitting antenna through the shielding room; the measuring receiver and the data recording device connected and then connected with the receiving antenna through the shielding room; a test platform installed in the shielding room; an engine whole machine and a dynamometer installed on the test platform, and an output end of the engine connected with an input end of the dynamometer; the electromagnetic compatibility characteristics of the engine whole machine, its electrical and electronic systems and accessories after the engine outer surface and the interconnecting cable are subjected to the interference of the specified electric field radiation can be directly reflected, and the relevant test results are more real and reliable.

Description

Technical Field

[0001] This invention belongs to the field of engine testing technology, and specifically relates to an electric field radiation testing system and method for aero-engines. Background Technology

[0002] As a crucial power source for aircraft, the electromagnetic compatibility (EMC) of aero-engines must be considered during their development. This means the aero-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, and lightning-induced transient susceptibility tests.

[0003] The 10kHz~40GHz electric field radiation sensitivity test is one of the test items in the radiation sensitivity test. It is an important means to verify that the engine can still operate in accordance with requirements after the engine's outer surface and interconnecting cables are subjected to specified electric field radiation interference.

[0004] The radiated emission test in the 10kHz to 18GHz electric field is one of the test items in the radiated emission test. It is an important means to assess and verify that the radiated emission level of the engine's outer surface and its cable interface meets the relevant standard and specification limits.

[0005] Existing tests for engine 10kHz–40GHz electric field radiation sensitivity and 10kHz–18GHz electric field radiation emission typically use the engine’s electrical and electronic systems and accessories as test objects, or use the engine’s electrical and electronic systems and accessories as a system as test objects. The tests are conducted on all accessories and systems with electrical characteristics or electrical interfaces belonging to the engine.

[0006] Existing accessory or system-level 10kHz–40GHz electric field radiation susceptibility tests and 10kHz–18GHz electric field radiated emission tests can only simulate the installation state of the engine's electrical and electronic systems and accessories as closely as possible to the engine's overall state. However, the installation locations of individual components, cable interfaces, shielding treatments, and operating environments differ from the actual engine state. Furthermore, these electrical and electronic systems and accessories are typically connected only to simulated drive devices or loads to approximate the test load conditions during engine ignition. The operating states of these components differ from the actual operating states of the engine during ignition, making it impossible to directly reflect the electromagnetic compatibility characteristics of the engine's 10kHz–40GHz electric field radiation susceptibility and 10kHz–18GHz electric field radiated emission. Consequently, the test results deviate from reality. Simultaneously, conducting separate 10kHz–40GHz electric field radiation susceptibility tests and 10kHz–18GHz electric field radiated emission tests on all accessories and systems with electrical characteristics or interfaces increases the test frequency, hindering the shortening of the test cycle and the reduction of test costs.

[0007] Therefore, a new testing system is needed to solve the above problems. Summary of the Invention

[0008] To address the aforementioned problems, this invention proposes an electric field radiation test system for an aero-engine, comprising a shielded room, a control room arranged outside the shielded room, and a transmitting antenna or a receiving antenna arranged inside the shielded room; When a transmitting antenna is installed inside a shielded room, a signal generator is installed outside the shielded room; the signal generator is connected to the transmitting antenna. Alternatively, when the receiving antenna is arranged inside the shielded room, a measuring receiver and a data recording device are arranged outside the shielded room. The measuring receiver and data recording device are connected and then pass through the shielded room to connect to the receiving antenna; A test platform is installed inside the shielded room; the test platform is equipped with an engine and a dynamometer, with the output end of the engine connected to the input end of the dynamometer. An electrical system and a testing system are arranged outside the shielding room, and the electrical system and the testing system are connected to the engine.

[0009] Furthermore, when the transmitting antenna is arranged inside the shielded room, it also includes a power amplifier room, in which a power amplifier is arranged; the connecting cable of the signal generator passes through the power amplifier room and is connected to the power amplifier.

[0010] Furthermore, an air intake shielding device and an exhaust shielding device are respectively installed on both sides of the shielding chamber; an exhaust ejector tube is installed on the end of the exhaust shielding device closest to the interior of the shielding chamber, and a test platform is installed on the end of the exhaust ejector tube furthest from the exhaust shielding device; radio frequency absorbing material is installed on the inner side wall and the top inner wall of the shielding chamber.

[0011] Furthermore, a shielding wall is installed on the side wall of the exhaust ejector tube, and the shielding wall is made of wave-absorbing material installed at one end of the exhaust ejector tube.

[0012] Furthermore, a dynamometer shielding device is installed around the dynamometer on the test platform; a shielded drive shaft device is installed between the dynamometer shielding device and the engine.

[0013] Furthermore, a fuel system, a lubricating oil system, a compressed air system, and a monitoring system are also arranged outside the shielded room; the electrical system and the testing system are all connected to the engine through filter components on the shielded room; the fuel system, the lubricating oil system, and the compressed air system are all connected to the engine through waveguide components on the shielded room; a camera is arranged inside the shielded room, and the connection cable of the monitoring system is connected to the camera through the shielded room.

[0014] Furthermore, a power supply is arranged in the control room; an impedance stabilization network is installed inside the shielded room; the connection cable of the power supply is connected to one end of the impedance stabilization network through the No. 3 filter on the shielded room, and the other end of the impedance stabilization network is connected to the engine.

[0015] Furthermore, when the transmitting antenna is arranged inside the shielded room, a sensing and display device is installed in the control room; an electric field sensor is arranged on the outer surface of the engine, and the electric field sensor passes through the shielded room and is connected to the sensing and display device.

[0016] This invention proposes a method for testing the electric field radiation sensitivity of an aero-engine, applied to the aforementioned aero-engine electric field radiation testing system, comprising: Configure and install the engine unit and the test system; The transmitting antenna is positioned on one side of the engine assembly; Ensure the shielded room is effectively sealed. Start the engine to its typical operating condition; The electric field strength is modulated by a signal generator; The signal generator scans the entire engine and records the test data; The testing system records whether the engine as a whole is sensitive; if sensitivity is detected, the sensitivity threshold level is determined and recorded. After the signal generator finishes scanning the entire engine, the engine stops. Try using a different transmitting antenna that transmits at a specific frequency, and conduct experiments with different types of transmitting antennas.

[0017] This invention proposes a method for testing the electric field radiation emission of an aero-engine, applied to the aforementioned aero-engine electric field radiation test system, comprising: Configure and install the engine unit and the test system; The receiving antenna is positioned on one side of the engine assembly; Ensure the shielded room is effectively sealed. Start the engine to its typical operating condition; The measurement receiver scans the entire engine and records the test data; After the measurement receiver finishes scanning the entire engine, the engine stops. Try a different receiving antenna that receives a specific frequency, and experiment with different types of receiving antennas.

[0018] Beneficial effects The advantages of this invention over the prior art are as follows: 1. Compared with existing accessory or system-level electric field radiation sensitivity tests, the test apparatus and test method for the electric field radiation sensitivity of the aero-engine in this application are closer to the actual operating conditions when the entire engine is in ignition operation. The electrical and electronic systems and accessories of the engine are all in the installed state of the whole engine, and each electrical and electronic system and accessory is operating under the load conditions of the whole engine ignition operation. The relevant electrical stress and electromagnetic coupling factors can be truly reflected. It can directly reflect the electromagnetic compatibility characteristics of the entire engine and its electrical and electronic systems and accessories after being subjected to specified electric field radiation interference on the outer surface of the engine and interconnecting cables. The relevant test results are more realistic and reliable.

[0019] 2. The test apparatus and test method for the electric field radiation sensitivity and emission test of the aero-engine of this application conduct electric field radiation sensitivity tests on the entire engine. The entire engine integrates the engine, its electrical and electronic systems and accessories into one unit. The test can complete the evaluation and verification of the engine, its electrical and electronic systems and accessories in a single test. Compared with the existing accessory or system-level 10kHz~40GHz electric field radiation sensitivity test and 10kHz~18GHz electric field radiation emission test, the test frequency is reduced, which can shorten the test cycle and reduce the test cost to a certain extent.

[0020] 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

[0021] 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.

[0022] Figure 1 A schematic diagram of the system structure in Embodiment 1 of the present invention is shown.

[0023] Figure 2 A flowchart of the method in Embodiment 1 of the present invention is shown.

[0024] Figure 3 A schematic diagram of the system in Embodiment 2 of the present invention is shown.

[0025] Figure 4 A flowchart of the method in Embodiment 2 of the present invention is shown.

[0026] In the diagram, 1. Shielded room; 2. Control room; 3. Power amplifier room; 4. Radio frequency absorbing material; 5. Exhaust shielding device; 6. Intake shielding device; 7. Exhaust ejector tube; 8. Test platform; 9. Shielding wall; 10. Engine assembly; 11. Dynamometer; 12. Dynamometer shielding device; 13. Shielded drive shaft assembly; 14. Electrical system; 15. Test system. 16. Fuel system; 17. Lubricating oil system; 18. Compressed air system; 19. Monitoring system; 20. Filter No. 1; 21. Filter No. 2; 22. Waveguide No. 1; 23. Waveguide No. 2; 24. Waveguide No. 3; 25. Camera; 26. Power supply; 27. Filter No. 3; 28. Impedance stabilization network; 29. ​​Electric field sensor; 30. Sensing and display device; 31. Transmitting antenna; 32. Signal generator; 33. Power amplifier; 34. Receiving antenna; 35. Measurement receiver; 36. Data recording device. Detailed Implementation

[0027] 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.

[0028] Example 1: The device for testing the 10kHz-40GHz electric field radiation susceptibility of the entire aero-engine 10 of the present invention, referenced. Figure 1 A control room 2 is arranged on the side of the shielded room 1, and a power amplifier room 3 is arranged inside the control room 2. Both the shielded room 1 and the power amplifier room 3 have a closed electromagnetic shielding structure, which can shield and isolate electromagnetic signals from the inside and outside. Radio frequency absorbing material 4 is installed inside the side shielding layer and the top shielding layer of the shielded room 1. The radio frequency absorbing material 4 can absorb electromagnetic signals that are directed towards the inner walls of the side and top shielding layers of the shielded room 1, thereby preventing the electromagnetic signals generated by the test piece or test equipment during electromagnetic compatibility testing from being reflected twice through the inner walls of the side and top shielding layers of the shielded room 1, thus preventing contamination and damage to the electromagnetic test environment inside the shielded room 1.

[0029] Directly behind shielded room 1 ( Figure 1 On the right side of the shielding layer, an exhaust shielding device 5 is installed. The exhaust shielding device 5 has an internal waveguide structure composed of numerous elongated holes, which can shield and isolate electromagnetic signals inside and outside the waveguide structure. The front of the shielding room 1 ( Figure 1 An air intake shielding device 6 is installed on the left side of the shielding layer. The air intake shielding device 6 has an internal waveguide structure composed of a large number of slender holes, which can shield and isolate electromagnetic signals inside and outside the waveguide structure. An exhaust ejector tube 7 is installed in front of the exhaust shielding device 5, and a test platform 8 is installed in front of the exhaust ejector tube 7. The upper surface of the test platform 8 is designed as a basically flat mounting surface and is flush with the ground (bottom) of the shielding room 1.

[0030] The shielding wall 9 is installed on both sides of the exhaust ejector tube 7 and close to the exhaust ejector tube 7. The shielding wall 9 can shield and isolate electromagnetic signals inside and outside the shielding wall 9. The outer side of the shielding wall 9 away from the exhaust ejector tube 7 is equipped with a wave-absorbing material, which can absorb electromagnetic signals emitted from inside the shielding chamber 1 towards the outer surface of the exhaust ejector tube 7. This prevents electromagnetic signals generated by the test piece or test equipment during electromagnetic compatibility testing from being reflected a second time through the outer surface of the exhaust ejector tube 7, thereby contaminating and damaging the electromagnetic test environment inside the shielding chamber 1.

[0031] The engine assembly 10 is mounted at the rear of the test platform 8, near the exhaust ejector 7. The dynamometer 11 is mounted at the front of the test platform 8, near the engine assembly 10. The dynamometer shielding device 12 is mounted around the dynamometer 11 and fixed to the test platform 8. The dynamometer shielding device 12 has a closed electromagnetic shielding structure, which can shield and isolate electromagnetic signals inside and outside the dynamometer shielding device 12. The outer side of the dynamometer shielding device 12 is equipped with absorbing material, which can absorb electromagnetic signals emitted from inside the shielding chamber 1 towards the outer surface of the dynamometer shielding device 12, thereby preventing secondary reflection of electromagnetic signals generated by the test piece or test equipment during electromagnetic compatibility testing through the outer surface of the dynamometer shielding device 12, thus preventing contamination and damage to the electromagnetic testing environment inside the shielding chamber 1. A shielded drive shaft assembly 13 is installed between the dynamometer shielding device 12 and the engine 10. The shielding shell of the shielded drive shaft assembly 13 is fixed to the shielding layer directly behind the dynamometer shielding device 12. The drive shafts inside the shielded drive shaft assembly 13 are connected to the power output end of the engine 10 and the power input end of the dynamometer 11, respectively. The electromagnetic shielding structure of the shielded drive shaft assembly 13 can shield and isolate electromagnetic signals entering and exiting the dynamometer shielding device 12 via the drive shaft assembly.

[0032] An electrical system 14, a testing system 15, a fuel system 16, a lubricating oil system 17, a compressed air system 18, and a monitoring system 19 are arranged outside the shielded room 1. The connecting cables of the electrical system 14 and the testing system 15 are connected to the engine 10 via filters 20 and 21, respectively, installed on the shielding layer of the shielded room 1. Filters 20 and 21 filter out excess electromagnetic signals entering and exiting the shielded room 1 via the connecting cables. The connecting pipes of the fuel system 16, the lubricating oil system 17, and the compressed air system 18 are connected to the engine 10 via waveguides 22, 23, and 24, respectively, installed on the shielding layer of the shielded room 1. Waveguides 22, 23, and 24 shield and isolate electromagnetic signals entering and exiting the shielded room 1 via the connecting pipes. The connecting cable of the monitoring system 19 is connected to a camera 25 installed inside the shielded room 1 via the shielding layer of the shielded room 1. The electrical system 14 and the test system 15 are connected to the fuel system 16, the lubricating oil system 17 and the compressed air system 18 respectively via connecting cables.

[0033] A power supply 26 is located inside the control room 2. The power supply 26's connecting cable is connected to an impedance stabilizing network 28 located inside the shielding room 1 via a third filter 27 mounted on the shielding layer of the shielding room 1. The third filter 27 filters out excess electromagnetic signals entering and exiting the shielding room 1 via the connecting cable. The other end of the impedance stabilizing network 28 is connected to the engine assembly 10. The distance between the impedance stabilizing network 28 and the rear edge of the engine assembly 10 along the axial direction of the engine assembly 10 is 3m. An electric field sensor 29 is located close to the outer surface of the engine assembly 10. The electric field sensor 29 is connected to a sensing and display device 30 located inside the control room 2 via a connecting cable through the shielding layer of the shielding room 1. A transmitting antenna 31 is located on the side of the engine assembly 10. The distance between the transmitting antenna 31 and the rear edge of the engine assembly 10 along the axial direction of the engine assembly 10 is 1.5m. The signal generator 32 is installed in the control room 2. The signal generator 32 is connected to the power amplifier 33 installed in the power amplifier room 3 via a connecting cable through the shielding layer of the power amplifier room 3. The power amplifier 33 is connected to the transmitting antenna 31 installed in the shielding room 1 via a connecting cable through the shielding layers of the power amplifier room 3 and the shielding room 1.

[0034] The shaft power output of the engine 10 during operation is absorbed and measured by the dynamometer 11. The exhaust gas generated by the engine 10 is discharged outside the shielded chamber 1 through the exhaust ejector 7 and the exhaust shielding device 5. The air required for the engine 10 to operate flows into the shielded chamber 1 from outside through the intake shielding device 6. The fuel consumed by the engine 10 is supplied through the fuel system 16 and its connecting pipelines. The lubricating oil required for the engine 10 is supplied and circulated through the lubricating oil system 17 and its connecting pipelines. The compressed air required for starting and running the engine 10 is supplied through the compressed air system 18 and its connecting pipelines. The operating status of the engine 10, fuel system 16, lubricating oil system 17, and compressed air system 18 is remotely controlled through the electrical system 14. The operating status parameters of the engine 10, fuel system 16, lubricating oil system 17, and compressed air system 18 are monitored, displayed, and recorded by the testing system 15. The test footage of the engine 10 is captured by the camera 25 and transmitted to the monitoring system 19 for recording and display.

[0035] The engine 10, the monitoring camera 25, the impedance stabilization network 28, the electric field sensor 29, and the transmitting antenna 31 are all arranged inside the shielded room 1. The impedance stabilization network 28 is the same as the line impedance stabilization network 28. The dynamometer 11 is arranged inside the shielded device of the dynamometer 11 in the shielded room 1. The electrical system 14, the testing system 15, the fuel system 16, the lubricating oil system 17, the compressed air system 18, the video monitoring system 19, the power supply 26, the electric field sensor 29, the display device, and the signal generator 32 are all arranged outside the shielded room 1 to minimize the influence of the external environment and the test equipment on the electromagnetic test environment and make the test results more realistic and reliable.

[0036] When the test apparatus of the present invention conducts a 10kHz to 40GHz electric field radiation sensitivity test on the entire aero-engine 10, the signal generator 32 simulates the generation of an interference signal. The interference signal is amplified by the power amplifier 33 and then output to the transmitting antenna 31. The amplified interference signal generates a spatial electromagnetic field through the transmitting antenna 31, which acts on the outer surface of the engine and the interconnecting cables.

[0037] Example 2: The experimental apparatus for radiating electric field emissions from an aero-engine 10 at 10kHz to 18GHz according to the present invention, referenced. Figure 3 The difference from Embodiment 1 is that there is no power amplifier room 3. The receiving antenna 34 is arranged on the side of the engine, and the lateral distance between the receiving antenna 34 and the outer surface of the engine is 1m. The measuring receiver 35 and the data recording device 36 are arranged in the control room 2. The receiving antenna 34 is connected to the measuring receiver 35 arranged and installed in the control room 2 through the shielding layer of the shielding room 1 via a connecting cable. The measuring receiver 35 is connected to the data recording device 36 via a connecting cable.

[0038] The engine unit 10, the monitoring camera 25, the impedance stabilization network 28, and the receiving antenna 34 are all arranged inside the shielded room 1. The dynamometer 11 is arranged inside the shielded device of the dynamometer 11 in the shielded room 1. The electrical system 14, the testing system 15, the fuel system 16, the lubricating oil system 17, the compressed air system 18, the video monitoring system 19, the power supply 26, the measuring receiver 35, and the data recording device 36 are all arranged outside the shielded room 1, so as to minimize the influence of the external environment and the test equipment on the electromagnetic test environment and make the test results more realistic and reliable.

[0039] When the test apparatus of the present invention conducts electric field radiation emission tests of aero-engines from 10kHz to 18GHz, it receives the radiation emission signals from the outer surface of the engine and the cable interface through the receiving antenna 34. The signals are then received and processed by the measuring receiver 35 and transmitted to the data recording device 36 for recording and storage.

[0040] In one embodiment of the present invention, the electrical system 14 and the test system 15 may be connected to a host computer arranged in the control room 2, or the electrical system 14 and the test system 15 may be arranged in the control room 2.

[0041] In one embodiment of the present invention, the power supply 26, the sensing and display device 30, the signal generator 32, the measurement receiver 35, and the data recording device 36 may also be arranged in other locations outside the unshielded room 1 and the non-control room 2.

[0042] In one embodiment of the present invention, the control room 2 may 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 structure is designed below the bottom of the shielded room 1.

[0043] In one embodiment of the present invention, the power amplifier room 3 may also be arranged outside the control room 2. When the power amplifier room 3 is arranged outside the control room 2, the power amplifier room 3 is designed to be arranged in a position that is adjacent to both the shielding room 1 and the control room 2.

[0044] In one embodiment of the present invention, it can also be used for engines with exhaust from the rear output side. When the test object is an engine with exhaust from the rear output side, the dynamometer 11, dynamometer shielding device 12, and shielded drive shaft device 13 of the test apparatus of the present invention are arranged and installed at the rear of the test platform 8 near the exhaust shielding device 5, and the engine body 10 is arranged and installed at the front of the test platform 8 near the intake shielding device 6. The exhaust ejector tube 7 is designed with an extended and curved structure so that the inlet of the exhaust ejector tube 7 is as close as possible to the exhaust port of the engine body 10.

[0045] In one embodiment of the present invention, it can also be used for engines that do not output shaft power. When the test object is an engine that does not output shaft power, the dynamometer 11, dynamometer shielding device 12, and shielded drive shaft device 13 of the test apparatus of the present invention can be modified.

[0046] In one embodiment of the present invention, it can also be used in engines where lubricating oil does not require external supply and circulation. When the test subject is an engine where lubricating oil does not require external supply and circulation, the lubricating oil system 17 and the second waveguide 23 of the test apparatus of the present invention can be tailored.

[0047] In one embodiment of the present invention, it can also be used to start and run engines that do not require compressed air. When the test subject is an engine that does not require compressed air to start and run, the compressed air system 18 and the third waveguide 24 of the test apparatus of the present invention can be modified.

[0048] In one embodiment of the present invention, other system equipment may be added according to the specific test requirements of the engine, such as hydraulic system, bleed air system, venting system, cooling water system, etc. The arrangement of the newly added system equipment and the electromagnetic shielding treatment of the connecting pipelines shall be arranged and treated with reference to the fuel system 16, lubricating oil system 17 and compressed air system 18 of the test device of the present invention.

[0049] In one embodiment of the present invention, it can also be used for static 10kHz-40GHz electric field radiation sensitivity tests or static 10kHz-18GHz electric field radiation emission tests when the engine is running without ignition. When conducting static 10kHz-40GHz electric field radiation sensitivity tests or static 10kHz-18GHz electric field radiation emission tests on the test apparatus of the present invention, the exhaust shielding device 5, intake shielding device 6, exhaust ejector tube 7, dynamometer 11, dynamometer shielding device 12, shielded drive shaft device 13, fuel system 16, lubricating oil system 17, compressed air system 18, monitoring system 19, waveguide 1 22, waveguide 23, waveguide 3 24, and camera 25 can be trimmed.

[0050] The 10kHz–40GHz electric field radiation susceptibility testing device and method for aero-engines of this invention, after debugging, calibration, and testing, demonstrates that the testing device can meet the requirements for aero-engine ignition and operation to typical working conditions. It can also apply electromagnetic interference signals as required by relevant electromagnetic compatibility (EMC) testing standards to the engine's outer surface and interconnecting cables. The testing environment and configuration meet the requirements of relevant EMC testing standards and specifications. The test results directly reflect the EMC characteristics of the entire engine's 10kHz–40GHz electric field radiation susceptibility. Compared to existing accessory or system-level 10kHz–40GHz electric field radiation susceptibility tests, this invention shortens the testing cycle and reduces testing costs to a certain extent.

[0051] The 10kHz–18GHz electric field radiated emission test apparatus and method for aero-engines of this invention, after debugging, calibration, and testing, demonstrates that the test apparatus can meet the requirements for aero-engine ignition and operation to typical working conditions. It can also test and record the radiated emission levels of the engine's outer surface and its cable interfaces according to relevant electromagnetic compatibility (EMC) testing standards. The test environment and configuration meet the requirements of relevant EMC testing standards and specifications, and the test results directly reflect the EMC characteristics of the 10kHz–18GHz electric field radiated emission of the entire engine. Compared to existing accessory or system-level 10kHz–18GHz electric field radiated emission tests, this invention shortens the test cycle and reduces test costs to a certain extent.

[0052] This invention provides a method for testing the electric field radiation sensitivity of an aero-engine, applied to the aforementioned aero-engine electric field radiation testing system, with reference to... Figure 2 When conducting the 10kHz~40GHz electric field radiation sensitivity test on the entire aero-engine, the test method and steps are as follows: (1) According to Figure 1 Perform the test configuration as shown; (2) Press Figure 1 The test configuration shown places a transmitting antenna 31 with a specific frequency range on one side of the engine; (3) ensure that the shielding room 1 is in an effective closed state; (4) start the engine 10 to a typical working state; (5) the signal generator 32 uses a 1kHz pulse with a 50% duty cycle to generate an electric field at the test start frequency until the effective value of the field strength reaches 200V / m; (6) the signal generator 32 scans the engine 10 within the frequency range applicable to the transmitting antenna 31 and records the test data; (7) the signal generator 32 monitors whether the engine 10 is sensitive during the scanning process, and if it is sensitive, it determines and records the sensitivity threshold level; (8) after the signal generator 32 finishes scanning, the engine 10 stops; (9) replace the transmitting antenna 31 with another transmitting antenna with a specific frequency range and repeat steps (2) to (8) until all tests in the frequency range of 10kHz to 40GHz are completed.

[0053] This invention provides a method for testing the electric field radiation emission of an aero-engine, applied to the aforementioned aero-engine electric field radiation testing system, with reference to... Figure 4 When conducting electric field radiation emission tests of the entire aero-engine (10 kHz to 18 GHz), the test methods and procedures are as follows: 1) According to Figure 3 Perform the test configuration as shown; 2) Press Figure 3 The test configuration shown involves placing a receiving antenna 34, which receives a specific frequency range, on one side of the engine assembly 10; 3) ensuring that the shielding room 1 is effectively sealed; 4) starting the engine assembly 10 to its typical operating state; 5) starting the measurement receiver 35 and scanning the engine assembly 10 within the frequency range applicable to the receiving antenna 34, while recording the test data; 6) after the measurement receiver 35 finishes scanning, stopping the engine assembly 10; 7) replacing the receiving antenna 34 with another receiving antenna that receives a specific frequency range, and repeating steps 2) to 6) until all tests in the 10kHz to 18GHz frequency range are completed.

[0054] 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. An electric field radiation test system for an aero-engine, characterized in that, It includes a shielded room (1), and a control room (2) is arranged outside the shielded room (1); a transmitting antenna (31) or a receiving antenna (34) is arranged inside the shielded room (1). When the transmitting antenna (31) is arranged inside the shielded room (1), a signal generator (32) is arranged outside the shielded room (1); the signal generator (32) is connected to the transmitting antenna (31); Alternatively, when a receiving antenna (34) is arranged inside the shielded room (1), a measuring receiver (35) and a data recording device (36) are arranged outside the shielded room (1); the measuring receiver (35) and the data recording device (36) are connected and pass through the shielded room (1) to connect with the receiving antenna (34); The shielded room (1) is equipped with a test platform (8); the test platform (8) is equipped with an engine (10) and a dynamometer (11), and the output end of the engine is connected to the input end of the dynamometer (11); An electrical system (14) and a testing system (15) are arranged outside the shielded room (1), and the electrical system (14) and the testing system (15) are connected to the engine (10).

2. The aero-engine electric field radiation test system according to claim 1, characterized in that, When the transmitting antenna (31) is arranged inside the shielded room (1), it also includes a power amplifier room (3), in which a power amplifier (33) is arranged; the connecting cable of the signal generator (32) passes through the power amplifier room (3) and connects to the power amplifier (33).

3. The aero-engine electric field radiation test system according to claim 1, characterized in that, An air intake shielding device (6) and an exhaust shielding device (5) are respectively installed on both sides of the shielding chamber (1); an exhaust ejector tube (7) is installed on one end of the exhaust shielding device (5) near the interior of the shielding chamber (1), and a test platform (8) is installed on the other end of the exhaust ejector tube (7) away from the exhaust shielding device (5); radio frequency absorbing material (4) is installed on both the inner wall and the top inner wall of the shielding chamber (1).

4. The aero-engine electric field radiation test system according to claim 3, characterized in that, A shielding wall (9) is installed on the side wall of the exhaust ejector tube (7), and the shielding wall (9) is installed with a wave-absorbing material at one end of the exhaust ejector tube (7).

5. The aero-engine electric field radiation test system according to claim 1, characterized in that, A dynamometer shielding device (12) is installed on the test platform (8) around the dynamometer (11); a shielded drive shaft device (13) is installed between the dynamometer shielding device (12) and the engine (10).

6. The aero-engine electric field radiation test system according to claim 1, characterized in that, The shielded room (1) is also equipped with a fuel system (16), a lubricating oil system (17), a compressed air system (18), and a monitoring system (19). The electrical system (14) and the testing system (15) are connected to the engine (10) through the filter assembly on the shielded room (1). The fuel system (16), the lubricating oil system (17), and the compressed air system (18) are connected to the engine (10) through the waveguide assembly on the shielded room (1). The shielded room (1) is equipped with a camera (25), and the connection cable of the monitoring system (19) is connected to the camera (25) through the shielded room (1).

7. The aero-engine electric field radiation test system according to claim 1, characterized in that, The control room (2) is equipped with a power supply (26); the shielding room (1) is equipped with an impedance stabilization network (28); the connection cable of the power supply (26) is connected to one end of the impedance stabilization network (28) through the No. 3 filter (27) on the shielding room (1), and the other end of the impedance stabilization network (28) is connected to the engine (10).

8. The aero-engine electric field radiation test system according to claim 7, characterized in that, When the transmitting antenna (31) is arranged inside the shielded room (1), the control room (2) is equipped with a sensing and display device (30); an electric field sensor (29) is arranged on the outer surface of the engine (10), and the electric field sensor (29) passes through the shielded room (1) and is connected to the sensing and display device (30).

9. A method for testing the electric field radiation sensitivity of an aero-engine, characterized in that, An electric field radiation test system for an aero-engine as described in any one of claims 1-8, comprising: Configure and install the complete engine (10) with the test system; The transmitting antenna (31) is positioned on one side of the engine assembly (10); Ensure that the shielded room (1) is in an effective sealed state; Start the engine to its typical operating condition; The electric field strength is modulated by the signal generator (32); The signal generator (32) scans the entire engine (10) and records the test data; The test system (15) records whether the engine (10) is sensitive. If it is sensitive, the sensitivity threshold level is determined and recorded. After the signal generator (32) finishes scanning the entire engine (10), the entire engine (10) stops. The experiment was conducted by replacing the transmitting antenna (31) with another transmitting antenna that transmits a specific frequency, and by using different types of transmitting antennas (31).

10. A method for testing the electric field radiation emission of an aero-engine, characterized in that, An electric field radiation test system for an aero-engine as described in any one of claims 1-8, comprising: Configure and install the complete engine (10) with the test system; The receiving antenna (34) is positioned on one side of the engine assembly (10); Ensure that the shielded room (1) is in an effective sealed state; Start the engine to its typical operating condition; The measuring receiver (35) scans the entire engine (10) and records the test data; After the measuring receiver (35) finishes scanning the entire engine (10), the entire engine (10) stops. Replace with another receiving antenna (34) that receives a specific frequency, and conduct experiments using different types of receiving antennas (34).

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