Aircraft starter generator detection system

Abstract

An aircraft starting generator detection system comprises a generator dragging platform connected with an aircraft generator to be detected, the generator dragging platform is electrically connected with a speed regulation power distribution cabinet, a frequency converter is arranged in the speed regulation power distribution cabinet to drive the generator dragging platform, the speed regulation power distribution cabinet is controlled by a test bench, and the output end of the aircraft generator to be detected is electrically connected with a load box. The test bench carries out data sampling on the frequency converter, the generator dragging platform, the to-be-detected aircraft generator and the load box. Meanwhile, the system is further provided with an adjustable load device and a wide-range rotating speed controller so as to meet the requirements under different test conditions, and the system has the advantages of being comprehensive in detection parameter, convenient in load adjustment, large in rotating speed range, safe, reliable and the like. Defects in an existing aircraft generator detection system can be effectively overcome, the comprehensiveness and accuracy of a detection result are improved, and a powerful guarantee is provided for safe flight of an aircraft.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation industry auxiliary tools, in particular to an aircraft starter generator detection system. Background Art

[0002] In the aviation industry, aircraft starter generators, as a core component of the aircraft's electrical system, are responsible for providing both initial startup power and subsequent stable power supply. However, with the continuous advancement of aviation technology and increasing demands for aircraft performance, higher standards and requirements are being placed on the inspection and maintenance of aircraft starter generators.

[0003] Currently, most aircraft generator detection systems on the market have the following defects:

[0004] Single-parameter testing: Traditional aircraft generator testing systems typically only monitor basic operating parameters, such as generator voltage and main generator current, but lack real-time monitoring of key parameters like excitation voltage and current. This makes it difficult for the system to provide comprehensive fault information and accurate diagnostics when a generator malfunctions.

[0005] Inconvenient load adjustment: Traditional detection systems have certain limitations in load adjustment and cannot achieve convenient load adjustment. This results in the inability to simulate the operation of the generator under different load conditions during the test, thus limiting the comprehensiveness and accuracy of the test results.

[0006] Limited speed range: Aircraft starter generators must operate at varying speeds to meet the demands of different flight phases. However, existing testing systems often only test within a limited speed range and fail to cover the full speed range of actual generator operation. This results in test results that fail to fully reflect the generator's performance at various speeds.

[0007] Inadequate safety and reliability: During the testing process, system safety and reliability are crucial to ensuring the safety of testers and equipment. However, traditional testing systems often have safety hazards and reliability issues, such as electrical safety and equipment stability during testing. These issues can lead to unexpected situations during testing, causing damage to testers and equipment. Summary of the Invention

[0008] The technical problem to be solved by the utility model is to provide an aircraft starting generator detection system, which can monitor the key parameters of the generator such as the generating voltage, main generating current, excitation voltage, excitation current, etc. in real time, so as to realize convenient load adjustment and greatly expand the speed range.

[0009] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0010] The aircraft starting generator detection system includes a generator dragging platform connected to the aircraft generator to be tested, the generator dragging platform is electrically connected to the speed distribution cabinet, the speed distribution cabinet is equipped with a frequency converter to drive the generator dragging platform, the speed distribution cabinet is controlled by the test bench, the output end of the aircraft generator to be tested is electrically connected to the load box, and the test bench samples data from the frequency converter, the generator dragging platform, the aircraft generator to be tested and the load box respectively.

[0011] The above-mentioned speed regulating distribution cabinet is equipped with a fan inverter, which drives the cooling fan to supply cooling air to the aircraft generator to be tested through the cooling duct. The fan inverter is controlled by the test bench.

[0012] The cooling fan is provided with a wind pressure sensor, which is electrically connected to the test bench.

[0013] The test bench is electrically connected to a voltage regulator, which is used to adjust the excitation of the aircraft generator to be tested.

[0014] The output end of the voltage regulator is connected to the excitation coil of the aircraft generator to be tested. The excitation circuit is provided with an excitation current rheometer A3 and an excitation voltmeter V3, which are located on the test bench.

[0015] The output end of the aircraft generator to be tested is provided with a main generator voltmeter V1 and a main generator ammeter A1, and the main generator voltmeter V1 and the main generator ammeter A1 are located on the test bench.

[0016] The load box is provided with a plurality of parallel load resistors, and the connection of the parallel load resistors is controlled by a switch on the load box.

[0017] A cooling fan is provided under the above-mentioned load box.

[0018] The generator traction platform is also provided with a lubricating oil pump, which is controlled by a switch on the test bench.

[0019] The utility model provides an aircraft starting generator detection system, which realizes real-time monitoring and accurate measurement of various parameters of the generator by adopting high-precision sensors and advanced signal processing technology. At the same time, the system is also equipped with an adjustable load device and a wide-range speed controller to meet the needs under different test conditions. It has the advantages of comprehensive detection parameters, convenient load adjustment, a large speed range, safety and reliability, etc., can effectively solve the defects of existing aircraft generator detection systems, improve the comprehensiveness and accuracy of detection results, and provide strong protection for the safe flight of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0021] Figure 1 This is a schematic diagram of the equipment layout of the aircraft starter generator detection system;

[0022] Figure 2 This is a schematic diagram of the DC power supply for the power distribution cabinet;

[0023] Figure 3 This is the connection diagram of the voltage regulator;

[0024] Figure 4 This is a circuit connection diagram for the generator dragging platform;

[0025] Figure 5 This is the control connection diagram of the cooling fan;

[0026] Figure 6 This is the connection diagram of the load box;

[0027] Figure 7 This is a connection diagram of the load resistor.

[0028] In the figure: aircraft generator 1, generator towing platform 2, prime mover 21, lubricating oil pump 22, speed control distribution cabinet 3, test bench 4, load box 5, distribution cabinet 6, cooling fan 7, cooling pipe 8, voltage regulator 9. DETAILED DESCRIPTION

[0029] like Figure 1-7 As shown in the figure, the aircraft starting generator detection system includes a generator dragging platform 2 connected to the aircraft generator 1 to be tested, the generator dragging platform 2 is electrically connected to the speed distribution cabinet 3, the speed distribution cabinet 3 is equipped with a frequency converter to drive the generator dragging platform 2, the speed distribution cabinet 3 is controlled by a test bench 4, the output end of the aircraft generator 1 to be tested is electrically connected to the load box 5, and the test bench 4 samples data from the frequency converter, the generator dragging platform 2, the aircraft generator 1 to be tested, and the load box 5 respectively.

[0030] The speed regulating and distribution cabinet 3 is provided with a fan frequency converter, which drives a cooling fan 7 to supply cooling air to the aircraft generator 1 to be tested through a cooling pipe 8 . The fan frequency converter is controlled by a test bench 4 .

[0031] The cooling fan 7 is provided with a wind pressure sensor, which is electrically connected to the test bench 4 .

[0032] The test bench 4 is electrically connected to a voltage regulator 9 , which is used to adjust the excitation of the aircraft generator 1 to be tested.

[0033] The output end of the voltage regulator 9 is connected to the excitation coil of the aircraft generator 1 to be tested. The excitation circuit is provided with an excitation current rheometer A3 and an excitation voltmeter V3. The excitation current rheometer A3 and the excitation voltmeter V3 are located on the test bench 4.

[0034] The output end of the aircraft generator 1 to be tested is provided with a main generating voltmeter V1 and a main generating ammeter A1 , and the main generating voltmeter V1 and the main generating ammeter A1 are located on the test bench 4 .

[0035] The load box 5 is provided with a plurality of parallel load resistors, and the connection of the parallel load resistors is controlled by switches on the load box 5 .

[0036] A cooling fan is provided under the load box 5 .

[0037] The generator traction platform 2 is further provided with a lubricating oil pump 22 , which is controlled by a switch on the test bench 4 .

[0038] Example:

[0039] This equipment is mainly used for testing the power generation performance of aircraft QF12-1 and QF-24 starter generators.

[0040] According to regulations, when generating electricity to an aircraft, the QF12-1 has a rated current of 400A and a rated power of 12kW; the QF-24 has a rated current of 800A and a rated power of 18kW. Accordingly, this device uses a 30kW variable frequency motor as the drive motor, capable of generating stable electricity from 4000rpm to 9000rpm.

[0041] The equipment mainly consists of generator dragging platform, speed regulating distribution cabinet, DC test bench, DC load box and cooling fan, etc. The connections between them are as follows Figure 1-7 As shown in .

[0042] The TY-9 voltage regulator controls the excitation current of the starter generator and can adjust the generator's output voltage value through the R1 resistor. The output of the starter generator is connected to the load box, and the load current to be tested is achieved through a combination of various resistor switches. During the test, various digital displays monitor the generator's generated voltage, main current, excitation voltage, excitation current, TY-9 coil current, etc. in real time.

[0043] The DC test bench can control the drag table, air cooling device and generator control, etc.

[0044] Table 1 Drag table control switches and display table

[0045]

[0046] Air cooling device control switch and display

[0047]

[0048] Table 2 DC measurement and control switch and display table

[0049]

[0050] The present invention can achieve the following experimental effects:

[0051] 1. Use variable frequency motor and speed increaser to drive the generator, with a wide adjustable speed range, stable speed and low noise.

[0052] 2. The output line of the generator is directly connected to the load box, which simplifies the line connection, facilitates testing and reduces interference.

[0053] 3. A fan is equipped to cool the generator, and a frequency converter controls the fan speed to ensure stable wind pressure. 4. The load box features a variety of settings, including 100A, 50A, 20A, 10A, 5A, 2A, and 1A, enabling precise control of load current. The load box has a maximum current of 700A, suitable for the 400A load of the QF12-1 and the 600A load of the QF-24.

[0054] 5. An axial flow fan is installed at the bottom of the load box, which automatically starts when the load box is connected to the load and cools the internal load resistor through strong air cooling.

[0055] 6. The bottom of the dragging platform is equipped with liftable moving wheels. The wheels can be lowered through the handle to support the equipment for easy movement and transfer.

Claims

1. Aircraft starter generator detection system, characterized in that, The invention comprises a generator dragging platform (2) connected to an aircraft generator (1) to be tested, the generator dragging platform (2) being electrically connected to a speed regulating and power distribution cabinet (3), a frequency converter being provided in the speed regulating and power distribution cabinet (3) for driving the generator dragging platform (2), the speed regulating and power distribution cabinet (3) being controlled by a test bench (4), an output end of the aircraft generator (1) to be tested being electrically connected to a load box (5), and the test bench (4) respectively sampling data from the frequency converter, the generator dragging platform (2), the aircraft generator (1) to be tested, and the load box (5).

2. The aircraft starter generator detection system according to claim 1, characterized in that: The speed regulating distribution cabinet (3) is provided with a fan frequency converter, which drives a cooling fan (7) to supply cooling air to the aircraft generator (1) to be tested through a cooling pipe (8), and the fan frequency converter is controlled by a test bench (4).

3. The aircraft starter generator detection system according to claim 2, characterized in that: The cooling fan (7) is provided with a wind pressure sensor, and the wind pressure sensor is electrically connected to the test bench (4).

4. The aircraft starter generator detection system according to claim 2, characterized in that: The test bench (4) is electrically connected to a voltage regulator (9), and the voltage regulator (9) is used to adjust the excitation of the aircraft generator (1) to be tested.

5. The aircraft starter generator detection system according to claim 4, characterized in that: The output end of the voltage regulator (9) is connected to the excitation coil of the aircraft generator (1) to be tested. The excitation circuit is provided with an excitation current rheometer A3 and an excitation voltmeter V3. The excitation current rheometer A3 and the excitation voltmeter V3 are located on the test bench (4).

6. The aircraft starter generator detection system according to claim 5, characterized in that: The output end of the aircraft generator (1) to be tested is provided with a main generating voltmeter V1 and a main generating ammeter A1, and the main generating voltmeter V1 and the main generating ammeter A1 are located on the test bench (4).

7. The aircraft starter generator detection system according to claim 6, characterized in that: The load box (5) is provided with a plurality of parallel load resistors, and the connection of the parallel load resistors is controlled by a switch on the load box (5).

8. The aircraft starter generator detection system according to claim 7, characterized in that: A cooling fan is provided under the load box (5).

9. The aircraft starter generator detection system according to claim 8, characterized in that: The generator dragging platform (2) is also provided with a lubricating oil pump (22), and the lubricating oil pump (22) is controlled by a switch on the test bench (4).

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