Aircraft generator test loading circuit and test method

Abstract

The present invention relates to the technical field of aircraft generators, and provides an aircraft generator test loading circuit and test method. The circuit tests the generator by setting at least two load loading units, and controlling the closing and opening of the unit switches and / or the switching switches in each load loading unit respectively through a main control system. The generator test circuit can adapt to various loading modes, reduce the impact on the generator and its entire system during the test process, reduce the failure rate of the generator and the test equipment, and improve the load control accuracy. The load adjustment time is shortened, the power consumption cost of the regulation process is reduced, and short-time precise closed-loop control is achieved. At the same time, the work efficiency of the generator test is improved, and the test cost is saved. The mutation process of the load loading system is shortened, and the load change situation in actual application is simulated to ensure that the generator is more stable and reliable in actual operation to adapt to the actual load mutation situation.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft generators, and in particular to an aircraft generator test loading circuit and a test method. Background Art

[0002] The aircraft generator loading system is mainly used to detect the performance indicators of aircraft generators. It can accurately measure the steady-state parameters of aircraft generators, including voltage, current, active power, reactive power, frequency and running time. Loading tests include steady-state test loading and transient test loading. Among them, steady-state test loading includes manual loading, automatic loading, constant power loading, constant resistance loading, band loading and other modes. Transient loading includes sudden addition / unloading test functions, which can automatically test the maximum value of the voltage, current, frequency and recovery time of the generator during the sudden addition / unloading of the load. At the same time, all steady-state and transient data can be accurately measured, and in conjunction with the main control system, all parameters of the aircraft generator can be automatically measured and various reports can be exported.

[0003] Figure 1 FIG. 1 is a schematic diagram of a circuit diagram of an aircraft generator loading system in the prior art. Figure 1 As shown, the loading test circuit includes an aircraft generator 1 (device under test), a voltage acquisition unit 2, a current acquisition unit 3, a gear switching switch 4, various load matrices 5 and a main control system 6. The existing generator loading test system circuits on the market can meet the performance index test function of generator loading. However, in terms of circuit control, the time of the generator load mutation process is not compressed to the shortest. At the same time, during the load switching process, the impact of the load circuit on the load regulation accuracy and the stability of the entire system is often ignored. In addition, in various loading modes, no higher requirements are made for the accuracy of various test loads, closed-loop control time, and impact current of the entire system. Summary of the invention

[0004] In view of the problems existing in the prior art, the present invention provides an aircraft generator test loading circuit and a test method.

[0005] A first aspect of the present invention provides an aircraft generator test loading circuit, comprising:

[0006] At least two parallel load loading units, the load loading unit comprising a unit switch, a switching switch and a load matrix connected in series in sequence; one end of the unit switch is electrically connected to the generator, and the other end is electrically connected to the switching switch;

[0007] A voltage collection unit, used for collecting the output voltage of the generator in real time;

[0008] A current collection unit, used for collecting the output current of the generator in real time;

[0009] A main control system, electrically connected to the voltage acquisition unit and the current acquisition unit, and configured to receive the voltage and current acquired by the voltage acquisition unit and the current acquisition unit;

[0010] The main control system is also electrically connected to the unit switches and the switching switches in each of the load loading units, respectively, and is used to control the closing and opening of the unit switches and / or the switching switches.

[0011] Optionally, there are two load loading units.

[0012] Optionally, a voltage collection point of the voltage collection unit is arranged at an output end of the generator.

[0013] Optionally, the load matrix is ​​used to simulate multiple types of loads.

[0014] Optionally, the load types simulated by the load matrices in different load loading units are the same or different.

[0015] Optionally, the voltage acquisition unit is a voltage sensor, and the current acquisition unit is a current sensor.

[0016] A second aspect of the present invention provides a method for testing an aircraft generator test loading circuit provided in the first aspect, the method comprising:

[0017] Based on the test power, pre-switching the gear position of the switching switch in the load loading unit;

[0018] Controlling the unit switches in the at least two parallel load loading units to close, and collecting the output voltage and output current of the generator in real time;

[0019] Testing is performed based on the collected output voltage and output current.

[0020] Optionally, the testing based on the collected output voltage and output current includes:

[0021] In the case of various loading / unloading mode tests, the operating power is calculated based on the collected output voltage and the output current, and based on the difference between the test power and the operating power, while keeping the unit switch in at least one of the load loading units in a closed state, the switching switch in another load loading unit is re-switched to a new gear position;

[0022] Control the unit switch in another load loading unit to close, and repeat the above steps until the difference between the working power and the test power meets the test requirements.

[0023] Optionally, the method further comprises:

[0024] In the case of a sudden addition function test, after the gear position of the switching switch in the load loading unit is switched in advance, the unit switch in the load loading unit is controlled to be closed;

[0025] In case of a sudden unloading function test, the unit switch in the load loading unit is directly controlled to be disconnected.

[0026] Optionally, in the method:

[0027] The main control system independently controls the unit switches in each load loading unit and the switching switches to close and open.

[0028] The present invention provides an aviation generator test loading circuit and test method. The circuit tests the generator by setting at least two load loading units, and controlling the closing and opening of the unit switches and / or the switching switches in each load loading unit respectively through a main control system. The generator test circuit can adapt to various loading modes, reduce the impact on the generator and its entire system during the test process, reduce the failure rate of the generator and the test equipment, and improve the load control accuracy. The load adjustment time is shortened, the power consumption cost of the regulation process is reduced, and short-time precise closed-loop control is achieved. At the same time, the work efficiency of the generator test is improved, and the test cost is saved. The mutation process of the load loading system is shortened, and the load change situation in actual application is simulated to ensure that the generator is more stable and reliable in actual operation to adapt to the actual load mutation situation. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0030] Figure 1 The present invention is a schematic diagram of a circuit diagram of an aircraft generator loading system in the prior art.

[0031] Figure 2 A schematic diagram of an aircraft generator test loading circuit provided by an embodiment of the present invention.

[0032] Figure 3 A schematic diagram of a testing method flow chart provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] At present, there are many types of generators in China, and the testing methods are relatively complete. However, in the aviation field, the loading test methods for domestic large aircraft generators are not perfect. In the existing aircraft generator loading test systems on the market, the load system is as follows: Figure 1 As shown in , the system structure includes a voltage and current acquisition loop, various gear switches, a load matrix and a main control system. In the steady-state test, the load continuously adjusts the gear to achieve closed-loop control in order to ensure accuracy. However, in the adjustment process, since each adjustment is to disconnect the original loading gear and re-switch the gear according to the calculation, the adjustment process time is prolonged, and it also affects the fluctuation of the entire circuit, causing serious impact on the generator and the entire circuit system, increasing the failure rate of the test system, and also affecting the control accuracy of the test system, resulting in inaccurate adjustment of the gear, and the adjustment time is prolonged; in the transient sudden addition / unloading experiment, the control response time of the entire system is relatively long, including the software control time, plus the action time of each switching gear switch, which prolongs the mutation process, thereby affecting the transient recovery time of the load, and cannot truly simulate the load change in actual application. In view of the above problems in the prior art, each embodiment of the present invention provides an aircraft generator test loading circuit. In the process of functional test verification of the aircraft generator, the sudden addition / unloading mode of the test process and the influence of multiple loading modes are optimized by optimizing and improving the system design circuit.

[0035] Figure 2 A schematic diagram of an aircraft generator test loading circuit provided by an embodiment of the present invention is shown in FIG. Figure 2 As shown, the embodiment of the present invention optimizes the circuit arrangement of the generator test loading system that can be used for aircraft generator testing. The test loading circuit includes at least two load loading units to optimize the sudden loading / unloading mode of the test process and the impact of multiple loading modes. Figure 2 For example, the circuit includes two load loading units connected in parallel. Each load loading unit includes a unit switch 7, a switching switch 4 and a load matrix 5, and the unit switch 7, the switching switch 4 and the load matrix 5 are connected in series in sequence. One end of the unit switch 7 is electrically connected to the generator 1 (device under test), and the other end is electrically connected to the switching switch 4.

[0036] In the embodiment of the present invention, a two-way unit switch 7 is provided to flexibly implement the sudden change process of the aircraft generator during the test process, compress its sudden change time to the shortest, simulate the actual load sudden change situation, ensure that the aircraft generator is stable and reliable during the actual application process, improve the transient response speed and mechanical performance, and adapt to the sudden change situation of the actual application scenario.

[0037] The prefabricated switching switches 4 for each gear provided in the embodiment of the present invention are used to realize prefabricated load loading, and cooperate with the two-way unit switch 7 to adjust the loading, improve the online loading accuracy, shorten the adjustment process, and shorten the test time; optimize the load adding / unloading process, adapt to various loading modes, so as to reduce the current impact on the test system.

[0038] The circuit also includes a voltage acquisition unit 2 for real-time acquisition of the output voltage of the generator 1. The current acquisition unit 3 is used to real-time acquisition of the output current of the generator 1. Optionally, the voltage acquisition unit 2 can be a voltage sensor, and the current acquisition unit 3 can be a current sensor. The high-precision current sensor collects the current at the output end of the generator in real time and feeds it back to the main control system 6.

[0039] Further, as shown in the figure, the voltage collection point of the voltage collection unit 2 is set at the output end of the generator 1. The voltage collection unit 2 can collect the voltage at the output end of the generator in real time, wherein the voltage collection point is the output end of the generator, so as to reduce the inaccurate voltage measurement caused by the impedance loss of the voltage signal due to the long test cable, thereby improving the accurate measurement of the generator output voltage and achieving precise regulation.

[0040] The circuit also includes a main control system 6, which is electrically connected to the voltage acquisition unit 2 and the current acquisition unit 3, and is used to receive the voltage and current collected by the voltage acquisition unit 2 and the current acquisition unit 3. The main control system 6 is also electrically connected to the unit switch 7 and the switching switch 4 in each load loading unit, and is used to control the closing and opening of the unit switch 7 and / or the switching switch 4. The main control system 6 in the embodiment of the present invention reads the system test electrical parameters in real time, and realizes load closed-loop control and adjustment according to the test requirements. It can also realize load protection and the safety of the equipment under test.

[0041] Further, the load matrix 5 is used to simulate multiple types of loads. The load matrix 5 in the embodiment of the present invention is used to simulate various types of load loading and provide various types of load forms for testing. Optionally, the load types simulated by the load matrices 5 in different load loading units can be the same or different.

[0042] The aircraft generator test loading circuit provided by the embodiment of the present invention tests the generator by setting at least two load loading units and controlling the closing and opening of the unit switches and / or the switching switches in each load loading unit respectively through the main control system. The generator test circuit can adapt to various loading modes, reduce the impact on the generator and its entire system during the test process, reduce the failure rate of the generator and the test equipment, and improve the load control accuracy. The load adjustment time is shortened, the power consumption cost of the regulation process is reduced, and short-time precise closed-loop control is achieved. At the same time, the work efficiency of the generator test is improved and the test cost is saved. The mutation process of the load loading system is shortened, and the load changes in actual applications are simulated to ensure that the generator is more stable and reliable in actual operation to adapt to the actual load mutation situation.

[0043] Figure 3 A flow chart of the test method provided in an embodiment of the present invention. In the test method provided in an embodiment of the present invention, the test loading circuit flexibly implements the impact of sudden load changes on the aircraft generator during the test process by setting unit switches, so as to test the ability of the aircraft generator to cope with sudden changes. According to the test requirements, the test power is confirmed, and the main control system calculates the corresponding parameters according to the test requirements, pre-sets the corresponding gears, and first switches the load to the system when the unit switch is not energized. Finally, the main switch is manually or automatically controlled with one button to achieve a sudden increase from 0 to 100% or a sudden unloading from 100% to 0, so as to simulate the sudden load in the worst case. The faster the switch action speed, the more realistic the simulated sudden effect is, so as to verify the response speed of the aircraft generator in dealing with sudden changes. Through the test, the stability and reliability of the aircraft generator in actual application are ensured, and at the same time, its mechanical properties are improved to adapt to sudden load changes. Figure 3 As shown, the method comprises the following steps:

[0044] Step 300: pre-switching the gear of the switching switch in the load loading unit based on the test power;

[0045] Step 301, controlling the unit switches in the at least two parallel load loading units to be closed, and collecting the output voltage and output current of the generator in real time;

[0046] Step 302: Perform a test based on the collected output voltage and output current.

[0047] In the test method provided in the embodiment of the present invention, the test power is first determined, for example, 120kw. Then, the demand parameters are determined according to the test power, such as what type and how large the load needs to be loaded. Then, the gear position of the switching switch in the pre-switched load loading unit is determined. Specifically, the switching switch in the load loading unit corresponding to the load to be loaded can be determined according to the load to be loaded, and the corresponding gear position can be switched so that the pre-determined switching switch gear is already in a closed state, so that the load can be loaded into the circuit loop after the unit switch is closed.

[0048] Then, the main control system can control the unit switches in at least two parallel load loading units to close, and collect the output voltage and output current of the generator in real time. Specifically, according to actual needs, the main control system can only control the unit switch in one load loading unit to close, or control the unit switches in two load loading units to close at the same time. The circuit collects the voltage and current at the output end of the generator through the voltage acquisition unit and the current acquisition unit respectively, and sends them to the main control system, so that the main control system can collect the output voltage and output current of the generator in real time. The main control system can subsequently test the generator based on the collected output voltage and output current. Specifically, the output voltage and output current can be obtained through the acquisition system to calculate the current power, power factor and other working parameters and compare them with the required parameters. If the deviation exceeds the allowable range, the control system performs closed-loop control until the test requirements are met, and then the performance test of the aircraft generator is carried out to achieve precise adjustment and meet the test requirements.

[0049] In the loading circuit of the embodiment of the present invention, two unit switches are set to adapt to various loading modes, reduce the impact on the aircraft generator and its entire system during the test process, reduce the failure rate of the generator and the test equipment, and improve the load control accuracy. Regardless of whether the load is loaded in manual mode, automatic mode, constant power mode, or constant resistance mode, the cooperation of the two sets of unit switches can reduce the current impact of sudden load on the aircraft generator and the entire system.

[0050] Further, in an embodiment of the method of the present invention, the testing based on the collected output voltage and the output current may include:

[0051] In the case of various loading / unloading mode tests, the working parameters such as working power and power factor are calculated based on the collected output voltage and output current and compared with the demand parameters. Based on the difference between the two, while keeping the unit switch in at least one load loading unit in a closed state, the switching switch in another load loading unit is re-switched to a new gear position;

[0052] Control the unit switch in another load loading unit to close, and repeat the above steps until the difference between the working power and the test power meets the test requirements.

[0053] Specifically, when performing various loading / unloading mode tests, the main control system needs to calculate the actual current working power of the generator by collecting the voltage at the output end of the aircraft generator (reducing the voltage drop of the cable impedance of the test cable to ensure that the output voltage of the test generator is more accurate) and the current. Then, the working power is compared with the test power, and the difference between the two is automatically calculated to determine whether the expected result is achieved. If the error is large, it needs to be adjusted again to achieve closed-loop control. In the process of re-adjustment, the main control system re-switches the switch in another load loading unit to a new gear while keeping the unit switch in at least one load loading unit in a closed state. That is, while keeping the gear of one load unchanged, the gear of another load is switched, so that the impact current of the entire system is reduced, which is equivalent to each adjustment being a band loading / unloading process, rather than a sudden loading / unloading process. At the same time, in a steady state, the speed of automatically calculating the difference is faster and more accurate, which improves the test accuracy and test speed.

[0054] The various loading / unloading modes described in the embodiments of the present invention include not only band loading / unloading modes, but other loading / unloading modes can also be programmed with band loading, thereby reducing the impact of various loading modes on the system.

[0055] Compared with the one-way loading system in the existing technology, during the adjustment process, it is necessary to unload the previous gear and then re-engage the new gear to ensure accuracy. Each loading and unloading is equivalent to a sudden loading / unloading process for the aircraft generator and the entire system, which increases the number and frequency of current impacts on the system and affects the performance of the aircraft generator during the test.

[0056] Furthermore, the method further comprises:

[0057] In the case of a sudden addition function test, after the gear position of the switching switch in the load loading unit is switched in advance, the unit switch in the load loading unit is controlled to be closed;

[0058] In case of a sudden unloading function test, the unit switch in the load loading unit is directly controlled to be disconnected.

[0059] It can be understood that when performing the sudden addition / sudden unloading function test, since the load loading unit in the aircraft generator test loading circuit provided by the embodiment of the present invention includes a unit switch, during the test, there is no need to frequently control the closing and opening of the switching switch. It is only necessary to directly control the closing and opening of the unit switch to quickly and flexibly simulate the sudden addition / sudden unloading scenario, shorten the test time, reduce the power consumption cost of the regulation process, achieve short-time precise closed-loop control, and at the same time improve the work efficiency of aircraft generator testing and save testing costs.

[0060] The test method provided by the embodiment of the present invention is based on the optimized aircraft generator test loading circuit, which can adapt to various loading modes, reduce the impact on the aircraft generator and its entire system during the test process, reduce the failure rate of the generator and the test equipment, and improve the load control accuracy. Shorten the load adjustment time, reduce the power consumption cost of the control process, achieve short-term precise closed-loop control, and at the same time improve the work efficiency of the aircraft generator test and save the test cost. Shorten the mutation process of the load loading system, simulate the load change in actual application, and ensure that the aircraft generator is more stable and reliable in actual operation to adapt to the actual load mutation.

[0061] Moreover, the main control system can independently control the closing and opening of the unit switches and switching switches in each load loading unit, with high control efficiency, accuracy and flexibility.

[0062] In the above implementations, for example, a 240kVA load can be divided into two parts, 180kVA and 60kVA. The switching switch can realize the switching of resistive load and inductive load by controlling the loading gear, and perform step-by-step loading and unloading. For example, the resistive load of 240kW is divided into two branches of 180kVA and 60kVA, and a unit switch is provided to realize the control of sudden addition / unloading under different powers of a single switch, meet the test point requirements of sudden addition / unloading and step-by-step loading and unloading functions, and meet the requirements of sudden addition / unloading load time less than or equal to 0.1s (configuration one 60kW unit switch action time is less than 30ms, configuration two 60kW total switch action time is less than 30ms). Similarly, the inductive load of 240kW is divided into two branches of 180kVA and 60kVA, and is equipped with a unit switch to realize the control of sudden addition / sudden unloading under different powers of a single switch, meeting the test point requirements of sudden addition / sudden unloading and step-by-step loading and unloading functions, and at the same time meeting the sudden addition / sudden unloading load time of less than or equal to 0.1s (configuration one 60kW unit switch action time is less than 30ms, configuration two 60kW total switch action time is less than 30ms).

[0063] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0064] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0065] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft generator test loading circuit, characterized in that: include: At least two parallel load loading units, the load loading unit comprising a unit switch, a switching switch and a load matrix connected in series in sequence; one end of the unit switch is electrically connected to the generator, and the other end is electrically connected to the switching switch; A voltage collection unit, used for collecting the output voltage of the generator in real time; A current collection unit, used for collecting the output current of the generator in real time; A main control system, electrically connected to the voltage acquisition unit and the current acquisition unit, and configured to receive the voltage and current acquired by the voltage acquisition unit and the current acquisition unit; The main control system is also electrically connected to the unit switch and the switching switch in each of the load loading units, and is used to control the closing and opening of the unit switch and / or the switching switch; The load matrix is ​​used to simulate multiple types of loads, and the load types simulated by the load matrices in different load loading units are the same or different.

2. The aircraft generator test loading circuit according to claim 1, characterized in that: There are two load loading units.

3. The aircraft generator test loading circuit according to claim 1 or 2, characterized in that: The voltage collection point of the voltage collection unit is arranged at the output end of the generator.

4. The aircraft generator test loading circuit according to claim 1, characterized in that: The voltage acquisition unit is a voltage sensor, and the current acquisition unit is a current sensor.

5. A test method based on the aircraft generator test loading circuit according to any one of claims 1 to 4, characterized in that: The method comprises: Based on the test power, pre-switching the gear position of the switching switch in the load loading unit; Controlling the unit switches in the at least two parallel load loading units to close, and collecting the output voltage and output current of the generator in real time; Testing is performed based on the collected output voltage and output current.

6. The testing method according to claim 5, characterized in that: The testing based on the collected output voltage and the output current includes: In the case of various loading / unloading mode tests, the operating power is calculated based on the collected output voltage and the output current, and based on the difference between the test power and the operating power, while keeping the unit switch in at least one of the load loading units in a closed state, the switching switch in another load loading unit is re-switched to a new gear position; Control the unit switch in another load loading unit to close, and repeat the above steps until the difference between the working power and the test power meets the test requirements.

7. The testing method according to claim 5, characterized in that: The method further comprises: In the case of a sudden addition function test, after the gear position of the switching switch in the load loading unit is switched in advance, the unit switch in the load loading unit is controlled to be closed; In case of a sudden unloading function test, the unit switch in the load loading unit is directly controlled to be disconnected.

8. The testing method according to claim 6 or 7, characterized in that: In the method: The main control system independently controls the unit switches in each load loading unit and the switching switches to close and open.

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