Load loading and unloading method and system for simulating electric load for aircraft generator test

Abstract

The invention relates to a loading and unloading method and system of an analog electric load for aircraft generator testing. The method comprises the steps that a, the output voltage and the output current of a generator are collected through a voltage sensor and a current sensor, so that the average output power of the generator within the preset duration before the current moment is obtained, and the preset duration is smaller than the overload protection time of the generator; b, comparing the target output power with the average output power to obtain a power difference value needing to be loaded or unloaded; c, under the condition that loading is needed, a proper simulation electric load is selected from the simulation electric loads which are not loaded to be loaded based on the power difference value to be loaded, and under the condition that unloading is needed, a proper simulation electric load is selected from the loaded simulation electric loads to be unloaded based on the power difference value to be unloaded. The average output power is equal to the target output power after loading or unloading is completed; and d, repeating the steps a-c before receiving a test termination instruction for the target output power.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the testing of aircraft generators, and in particular to a method and system for simulating the load of an electrical load for testing an aircraft generator. BACKGROUND

[0002] A simulating electrical load system is a key system required for the testing of an aircraft generator (for example, for airworthiness certification) of an aircraft such as a large passenger aircraft, which can provide a simulating electrical load required for testing to the aircraft generator, so that the aircraft generator can maintain a required power output state, and in turn, the working characteristics, cooling capacity, and the like of other systems of the aircraft (such as a power plant, an APU system, and a power supply system) can be verified under this power output state.

[0003] However, the existing simulating electrical load system has various defects and cannot be well matched with the aircraft body.

[0004] The present disclosure is improved in view of the above-mentioned factors, but is not limited thereto. SUMMARY

[0005] To this end, the present disclosure proposes a method and system for simulating the load of an electrical load for testing an aircraft generator in view of the requirement for automatic load increase and decrease of the simulating electrical load system. The method and system of the present disclosure propose a corresponding solution for the high-frequency and high-amplitude fluctuation characteristics of the aircraft body load, and preferably also provide an active constraint mechanism for the load gradient and three-phase imbalance, and more preferably also well meet the safety requirement under the scene where the test power is close to the protection threshold. Preferably, in the method and system of the present disclosure, the automatic load increase and decrease control of the onboard simulating electrical load can be optimized based on multiple targets, taking into account the characteristics of the complex changes of the high-frequency and high-amplitude of the aircraft body load, and the load gradient requirement, three-phase imbalance requirement, and the like, to realize stable and reliable load increase and decrease of the simulating electrical load system, avoid the occurrence of overload protection, power quality degradation, and the like, and effectively ensure the smooth progress of the aircraft testing and flight test.

[0006] According to a first aspect of the present disclosure, a method for adding and removing a simulated electrical load for aircraft generator testing is provided, comprising: a. collecting the output voltage and output current of the generator through a voltage sensor and a current sensor to obtain the average output power of the generator within a predetermined time period before a current moment, wherein the predetermined time period is less than the overload protection time of the generator; b. comparing the target output power with the average output power of the generator to obtain the power difference that needs to be loaded or unloaded; c. selecting a suitable simulated electrical load from the simulated electrical loads that have not been loaded to load based on the power difference when loading is required, and selecting a suitable simulated electrical load from the simulated electrical loads that have been loaded to unload based on the power difference when unloading is required, so that the average output power of the generator is equal to the target output power after loading or unloading is completed; and d. repeating steps ac before receiving a test termination instruction for the target output power.

[0007] According to an embodiment, the method further comprises unloading all loaded simulated electrical loads upon receiving a test termination instruction for the target output power.

[0008] According to another embodiment, step c also includes: when loading is required, selecting a simulated electric load that matches the power difference in the order of power consumption of the simulated electric loads that have not been loaded from large to small, first three-phase simulated electric load and then single-phase simulated electric load, so as to form a simulated electric load loading control sequence; when unloading is required, selecting a simulated electric load that matches the power difference in the order of power consumption of the loaded simulated electric loads from large to small, first three-phase simulated electric load and then single-phase simulated electric load, so as to form a simulated electric load unloading control sequence; and according to the simulated electric load automatic loading control sequence or the simulated electric load unloading control sequence, loading or unloading the simulated electric loads in the simulated electric load automatic loading control sequence or the simulated electric load unloading control sequence in sequence by driving the actuator.

[0009] According to another embodiment, step c also includes: if the simulated electric load loading control sequence includes a single-phase simulated electric load, the selected single-phase simulated electric load is loaded to the phase with the smallest current power among the three phases; if the simulated electric load unloading control sequence includes a single-phase simulated electric load, the load is unloaded from the phase in the order of the current power among the three phases from large to small.

[0010] According to another embodiment, after each simulated electric load is loaded or unloaded, and before the next simulated electric load is loaded or unloaded, a certain delay time is waited, wherein the delay time depends on the power variation gradient requirement of the generator.

[0011] According to another embodiment, during the execution of the method, at least one of the following is also executed in real time: detecting whether a termination instruction is received, and if the termination instruction is received, unloading all loaded simulated electrical loads and terminating the execution of the method; detecting whether any one of the power supply configuration and the output voltage range meets the requirements, and if not, unloading all loaded simulated electrical loads, terminating the execution of the method, and outputting an alarm; detecting the generator output power factor and / or three-phase imbalance, and when the output power factor and / or three-phase imbalance exceeds the allowable range of the power supply quality of the aircraft power system, unloading all loaded simulated electrical loads, terminating the execution of the method, and outputting an alarm; and detecting whether the average output power exceeds the overload protection power, and if so, unloading all loaded simulated electrical loads, terminating the execution of the method, and outputting an alarm.

[0012] According to another embodiment, the predetermined duration is less than or equal to the overload protection time minus the time required for signal acquisition, data calculation, signal transmission, and actuator actuation.

[0013] According to yet another embodiment, the simulated electric load includes a plurality of simulated electric loads set according to appropriate load capacities, wherein the appropriate load capacities include the load capacities of the simulated electric loads in a ratio of 8:4:2:1 or 10:5:2:1.

[0014] According to yet another embodiment, the average output power of the generator being equal to the target output power includes the power difference being within a predetermined range.

[0015] According to yet another embodiment, the generator test is based on a test plan comprising one or more target output powers that the generator needs to output, and wherein the method is performed sequentially for each of the one or more target output powers.

[0016] According to another embodiment, the test plan further includes an output duration for each target output power, and the method further includes repeating steps ac before the output duration of the target output power expires, and unloading all simulated electrical loads that have been loaded when the output duration of the target output power expires.

[0017] According to a second aspect of the present disclosure, a system for adding and removing a simulated electric load for testing an aircraft generator is provided, comprising: a simulated electric load; a collection device comprising a voltage sensor and a current sensor for collecting an output voltage and an output current of the generator; and a test control device, the test control device being configured to: a. obtain, based on the output voltage and output current of the generator collected by the collection device, an average output power of the generator within a predetermined time period before a current moment, wherein the predetermined time period is less than an overload protection time of the generator; b. compare a target output power with the average output power of the generator to obtain a power difference required for loading or unloading; c. select, based on the power difference, a suitable simulated electric load from unloaded simulated electric loads to load if loading is required, and select, based on the power difference, a suitable simulated electric load from loaded simulated electric loads to unload if unloading is required, so that after loading or unloading is completed, the average output power of the generator equals the target output power; and d. repeat steps ac until a test termination instruction for the target output power is received.

[0018] Aspects generally include methods, apparatus, systems, computer program products, and processing systems substantially as described herein with reference to and as illustrated by the accompanying figures.

[0019] The foregoing has broadly outlined the features and technical advantages of examples according to the present disclosure so that the following detailed description may be better understood. Additional features and advantages will be described hereinafter. The concepts and specific examples disclosed may be readily used as a basis for modifying or designing other structures for implementing the same purposes as the present disclosure. Such equivalent constructions do not depart from the scope of the appended claims. The characteristics of the concepts disclosed herein, both in terms of their organization and method of operation, as well as the associated advantages, will be better understood by considering the following description in conjunction with the accompanying drawings. Each of the figures is provided for illustration and description purposes and does not define limitations on the claims. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to understand in detail the manner in which the above-recited features of the present disclosure may be employed, reference may be made to various aspects of a more particular description of the content briefly summarized above, some of which are illustrated in the accompanying drawings. It should be noted, however, that the accompanying drawings illustrate only certain typical aspects of the disclosure and are not to be considered limiting of its scope, as the description may admit to other equally effective aspects. The same reference numerals in different drawings may identify the same or similar elements.

[0021] Figure 1 A schematic flow chart showing a method for adding and removing a simulated electric load for aircraft generator testing according to an exemplary embodiment of the present disclosure; and

[0022] Figure 2 A schematic block diagram of a load addition and reduction system for simulating an electric load for aircraft generator testing according to an exemplary embodiment of the present disclosure is shown. DETAILED DESCRIPTION

[0023] The inventors have recognized that during testing (especially flight testing), in order to ensure that the output power of the aircraft generator reaches a full load state, the aircraft generator outputs a portion of its power to the aircraft main equipment to ensure the power consumption of the aircraft main equipment, and the other portion of its power is output to the simulated electrical load system to achieve output power regulation. Since the load power of the aircraft main equipment will have the characteristics of complex changes with high frequency and high amplitude due to flight testing, and the aircraft main power system has an overload protection function, and the target output power value of the aircraft generator required during the flight testing process is very close to the protection threshold, in order to avoid triggering the overload protection due to the loading of the simulated electrical load system during the flight testing, it is necessary to be able to monitor the load of the aircraft main body in real time during the flight testing, and to enable the simulated electrical load system to dynamically follow the high frequency and high amplitude fluctuations of the aircraft main body electrical load, accurately control the loading amount of the simulated electrical load and reduce the load in a timely manner to maintain the stability of the output power of the aircraft generator.

[0024] The inventors also realized that in order to avoid the adverse effects of adding and removing electrical loads (especially high-power electrical loads) on the power supply quality of the aircraft power system, it is also necessary to control the simulated load loading gradient and three-phase imbalance (that is, the degree to which the power on the three phases is not equal to each other).

[0025] However, existing aircraft power supply test systems lack a solution for the high-frequency, high-amplitude fluctuations in aircraft loads. Furthermore, existing aircraft power supply test systems lack active constraints on load gradients and three-phase imbalance, and they also fail to adequately address safety requirements when the test power approaches protection thresholds.

[0026] To this end, the present disclosure addresses the need for automatic addition and reduction of loads in a simulated electric load system, and proposes a method and system for adding and reducing loads of a simulated electric load for aircraft generator testing. The method and system of the present disclosure propose corresponding solutions for the high-frequency, high-amplitude fluctuation characteristics of the load of the generator body, and preferably also provide an active constraint mechanism for the loading gradient and three-phase imbalance, and more preferably also well meet the safety requirements in the scenario where the test power is close to the protection threshold. Preferably, in the method and system of the present disclosure, the automatic addition and reduction control of the onboard simulated electric load can be optimized based on multiple objectives, comprehensively considering the complex change characteristics of the high frequency and high amplitude of the aircraft body load, as well as the addition and reduction gradient requirements, three-phase imbalance requirements and other factors, to achieve stable and reliable addition and reduction of loads of the simulated electric load system, avoid the occurrence of overload protection, power quality degradation and other situations, and effectively ensure the smooth progress of aircraft testing and flight tests.

[0027] The detailed description set forth below in conjunction with the accompanying drawings is intended as a description of various configurations and is not intended to represent the only configurations in which the concepts described herein may be practiced. This detailed description includes specific details to provide a thorough understanding of the various concepts. However, it will be apparent to those skilled in the art that these concepts may be practiced without these specific details.

[0028] refer to Figure 1 , which shows a schematic flow chart of a method 100 for adding and removing a simulated electric load for aircraft generator testing according to an embodiment of the present disclosure.

[0029] like Figure 1 As shown, in block 110 , the method 100 may include collecting the output voltage and output current of the generator by using a voltage sensor and a current sensor to obtain the average output power of the generator within a predetermined time period before the current moment.

[0030] In one embodiment of the present disclosure, the inventors considered the complex, high-frequency, and high-amplitude fluctuations in aircraft loads, which result in frequent and high-amplitude fluctuations in aircraft power consumption. Consequently, to maintain stable generator output power during flight testing, the simulated electrical load must be frequently and significantly loaded and unloaded. This is difficult and cumbersome to implement, hindering generator testing. To accommodate the dynamic nature of aircraft load fluctuations, the present disclosure does not use the aircraft generator's instantaneous output power to simulate load loading and unloading during flight testing. Instead, it performs "filtering" on the generator's output power, using the average output power over a predetermined period of time prior to the current moment. This effectively eliminates the impact of the high-frequency and high-amplitude fluctuations in the aircraft load. Furthermore, this embodiment effectively mitigates the effects of transient overloads in the generator's output power caused by transient increases in aircraft load, or signal delays, which can lead to misjudgments of overload protection and control delays.

[0031] In another embodiment of the present disclosure, the predetermined duration can be less than the overload protection time of the generator. This embodiment advantageously utilizes the overload protection logic of the aircraft generator (or power system), thereby ensuring that overload protection is met while minimizing the impact of high-frequency, high-amplitude fluctuations in the aircraft's load. For example, the overload protection logic can trigger overload protection when it detects that the aircraft generator output power exceeds the overload protection power S for a period of time t. Therefore, this embodiment of the present disclosure can calculate the average output power of the aircraft generator within the time t, and accordingly fully utilize the generator's overload protection time to advantageously eliminate the impact of factors such as instantaneous overload and signal delay.

[0032] In another embodiment of the present disclosure, considering that operations such as signal acquisition, data calculation, signal transmission, and actuator actuation all require a certain amount of time, the predetermined duration may be less than or equal to the generator overload protection time minus the time required for signal acquisition, data calculation, signal transmission, and actuator actuation. This more effectively ensures that the overload protection requirements of the aircraft generator are met.

[0033] It will be understood that the period of collecting the output voltage and output current of the generator by the method 100 is less than the predetermined time period. Preferably, the collection operation of the method 100 can be considered to be performed in "real time".

[0034] Continue to refer Figure 1 At block 120 , the method 100 may include comparing the target output power with the average output power of the generator to obtain a power difference required to load or unload.

[0035] In one embodiment of the present disclosure, when the target output power is greater than the average output power of the generator within a predetermined period of time before the current moment, the power difference between the two is the power difference that needs to be loaded, that is, it is necessary to increase the average output power of the generator by loading a simulated electric load so that it is equal to the target output power; or when the target output power is less than the average output power of the generator within a predetermined period of time before the current moment, the power difference between the two is the power difference that needs to be unloaded, that is, it is necessary to reduce the average output power of the generator by unloading the simulated electric load so that it is equal to the target output power.

[0036] In box 130, method 100 may include selecting a suitable simulated electric load to load from the simulated electric loads that have not been loaded based on the power difference value when loading is required, and selecting a suitable simulated electric load to unload from the simulated electric loads that have been loaded based on the power difference value when unloading is required, so that the average output power of the generator is equal to the target output power after loading or unloading is completed.

[0037] According to one embodiment of the present disclosure, when the target output power is greater than the average output power of the generator within a predetermined time period before the current moment, method 100 can determine that the simulated electric load needs to be loaded. In other words, the power difference between the two is the power difference that needs to be loaded; when the target output power is less than the average output power of the generator within a predetermined time period before the current moment, method 100 can determine that the simulated electric load needs to be unloaded. In other words, the power difference between the two is the power difference that needs to be unloaded.

[0038] According to an embodiment of the present disclosure, when loading is required, method 100 can select a simulated electric load that matches the power difference according to the power consumption of the simulated electric loads that have not been loaded, in the order of three-phase simulated electric loads first and then single-phase simulated electric loads, to form a simulated electric load loading control sequence, and then load the simulated electric loads in the simulated electric load automatic loading control sequence in sequence by driving the actuator according to the simulated electric load automatic loading control sequence; when unloading is required, method 100 selects a simulated electric load that matches the power difference according to the power consumption of the simulated electric loads that have been loaded, in the order of three-phase simulated electric loads first and then single-phase simulated electric loads, to form a simulated electric load unloading control sequence, and then unload the simulated electric loads in the simulated electric load unloading control sequence in sequence by driving the actuator according to the simulated electric load unloading control sequence. This is more advantageous because, generally speaking, the three-phase simulated electric loads are relatively large and are evenly loaded on the three phases, and their loading and unloading are conducive to the balance of the three-phase power supply.

[0039] In another embodiment of the present disclosure, when a single-phase simulated electric load is included in the simulated electric load loading control sequence or the simulated electric load unloading control sequence, the loading and unloading of the single-phase simulated electric load is completed while satisfying the three-phase power supply balance as much as possible. For example, if a single-phase simulated electric load is included in the simulated electric load loading control sequence, the selected single-phase simulated electric load is loaded to the phase with the smallest current power among the three phases, and if a single-phase simulated electric load is included in the simulated electric load unloading control sequence, the load is unloaded from the phase in the order of the current power in the three phases from large to small. According to this embodiment, unloading from the phase in the order of the current power in the three phases from large to small includes preferably unloading the single-phase simulated electric load from the phase with the largest current power among the three phases, and if it is unsuccessful (for example, there is no suitable single-phase electric load on the phase with the largest current power to meet the conditions), unloading is performed from the phase with the second largest current power among the three phases, and so on. This is further advantageous because it will make the power supply on the three phases more balanced. It will be understood that when multiple single-phase simulated electric loads are included in the simulated electric load loading control sequence or the simulated electric load unloading control sequence, in order to meet the three-phase power supply balance, it is possible to distribute these single-phase simulated electric loads on at least two of the three phases, which will not be elaborated here.

[0040] In another embodiment of the present disclosure, taking into account the power variation gradient requirement of the aircraft generator (e.g., a maximum of 10 kW / s), method 100 may include waiting for a certain delay time after each simulated electric load is loaded or unloaded and before the next simulated electric load is loaded or unloaded, wherein the delay time depends on the power variation gradient requirement of the generator. For example, each simulated electric load in the simulated electric load loading control sequence or the simulated electric load unloading control sequence may also have an associated delay time, that is, the waiting time after each simulated electric load is loaded or unloaded and before the next simulated electric load is loaded or unloaded. In this way, the present disclosure adds an active constraint mechanism for loading gradient, three-phase imbalance, etc., effectively eliminating voltage fluctuations or harmonic interference caused by the addition or removal of high-power loads.

[0041] In another embodiment of the present disclosure, taking into account the frequency of loading and unloading of the simulated electrical load, the delay in the operation of its actuator, the service life, etc., the average output power of the generator being equal to the target output power may include a power difference within a predetermined range. That is, when the power difference between the average output power of the generator and the target output power is within the predetermined range, the average output power of the generator is deemed equal to the target output power, and thus, there is no need to load or unload the simulated electrical load, thereby at least preventing the actuator from actuating frequently. In this embodiment, this predetermined range can be set based on the load capacity of the minimum simulated electrical load (i.e., equivalent to the power that the minimum simulated electrical load can consume, also known as the "granularity" of the simulated electrical load). For example, if the power that the minimum simulated electrical load that can be set can consume is 100W (100 watts), the predetermined range can be set to ±100W, so that when the power difference between the average output power of the generator and the target output power is within ±100W, the two are deemed equal. However, this is merely an example, and the upper and lower limits of the predetermined range can be set to be no less than the load capacity of the minimum simulated electrical load.

[0042] According to this embodiment, when the power difference between the average output power of the generator and the target output power is within a predetermined range, the method 100 can determine in box 130 that there is no need to perform loading and unloading of the simulated electric load and return to the step in box 110; when the target output power is greater than the average output power of the generator and exceeds the predetermined range, the method 100 can determine in box 130 that the simulated electric load needs to be loaded; when the target output power is less than the average output power of the generator and exceeds the predetermined range, the method 100 can determine in box 130 that the simulated electric load needs to be unloaded.

[0043] Further according to this embodiment, selecting a suitable simulated electric load to load from the simulated electric loads that have not yet been loaded based on the power difference so that the average output power of the generator after loading or unloading is equal to the target output power may include selecting a suitable simulated electric load to load so that the power difference between the average output power of the generator and the target output power after loading is completed falls within a predetermined range. Preferably, the suitable simulated electric load is selected to load so that the average output power of the generator after loading is completed does not exceed the target output power. For example, when the predetermined range is ±10kW and the target output power is 800kW, if the loading of different simulated electric loads allows the average output power of the generator to reach 795kW or 805kW (the power difference (±5kW) of both of which from the target output power falls within the predetermined range of ±10kW), then preferably a simulated electric load that allows the average output power of the generator to reach 795kW is selected for loading to avoid overloading.

[0044] Further according to this embodiment, selecting a suitable simulated electric load from the loaded simulated electric loads based on the power difference to unload so that the average output power of the generator is equal to the target output power after the unloading is completed may include selecting a suitable simulated electric load to unload so that the power difference between the average output power of the generator and the target output power after the unloading is completed falls within a predetermined range. Preferably, the suitable simulated electric load is selected to unload so that the average output power of the generator does not exceed the target output power after the loading is completed. For example, when the predetermined range is ±10kW and the target output power is 1000kW, if the unloading of different simulated electric loads allows the average output power of the generator to reach 996kW or 1007kW (the power differences of both of which with the target output power (-4kW and +7kW) fall within the predetermined range of ±10kW), then preferably, a simulated electric load that allows the average output power of the generator to reach 996kW is selected for unloading.

[0045] In another embodiment of the present disclosure, the predetermined range can be set depending on the required test accuracy and / or signal acquisition accuracy and / or design tolerance, etc. For example, if the design tolerance of the output power of the generator is 10kW, the upper and lower limits of the predetermined range can be set to be larger than this design tolerance, such as ±20kW, ±12kW, and so on. In this example, the load capacity of the minimum simulated electric load (i.e., the power that the minimum simulated electric load can consume) can be set depending on the required predetermined range. For another example, if the predetermined range can be set to ±800kW depending on the required test accuracy and / or signal acquisition accuracy and / or design tolerance, etc., the load capacity of the minimum simulated electric load can be correspondingly set to no more than 800kW.

[0046] It will be understood that the specific values ​​of the predetermined range and load capacity given above are merely exemplary, and any other suitable values ​​may be adopted, such as 750W, 13kW, 500kW, 3000kW, etc.

[0047] To better regulate the output power of the generator, the simulated electrical loads can include a plurality of simulated electrical loads set at appropriate load capacities (i.e., the electrical power that the load can consume). In one embodiment, the appropriate load capacities can include a ratio of the load capacities of the simulated electrical loads of 8:4:2:1. For example, if the load capacity of the smallest simulated electrical load is 800w, then the capacities of the respective other simulated electrical loads are 1600w, 3200w, and 6400w, respectively. In another embodiment of the present disclosure, the number of simulated electrical loads of respective load capacity sizes can be set as needed. Generally, the number of smallest simulated electrical loads is generally greater, while the number of largest simulated electrical loads is generally fewer. It will also be appreciated that the above ratio, the specific values, and the like of the load capacities of the simulated electrical loads are given by way of example only, and that the load capacities of the simulated electrical loads can be set in any other appropriate manner, such as a ratio of 10:5:2:1, or all of the simulated electrical loads can have the same load capacity, and the like, which will not be described further herein.

[0048] At block 140, the method 100 can include repeating the steps in blocks 110, 120, 130 until a test termination instruction for the target output power is received.

[0049] In one embodiment of the present disclosure, the method 100 can further include unloading all of the simulated electrical loads that have been loaded upon receiving the test termination instruction for the target output power to facilitate testing for a subsequent target output power, if any. In this embodiment, the unloading is also in the order from large to small, from three-phase to single-phase, and the unloading also meets the power change gradient requirement of the generator.

[0050] In another embodiment of the present disclosure, during the execution of method 100, at least one of the following is also executed in real time: detecting whether a termination instruction has been received, and if so, unloading all loaded simulated electrical loads and terminating the execution of method 100; detecting whether any of the power supply configuration and output voltage range meet requirements; if not, unloading all loaded simulated electrical loads, terminating the execution of method 100, and outputting an alarm; detecting the generator output power factor and / or three-phase imbalance; if the output power factor and / or three-phase imbalance exceeds the allowable power quality range of the aircraft power system, unloading all loaded simulated electrical loads, terminating the execution of method 100, and outputting an alarm; and detecting whether the average output power exceeds the overload protection power; if so, unloading all loaded simulated electrical loads, terminating the execution of method 100, and outputting an alarm. In this embodiment, the unloading is also carried out in a descending order and from three-phase to single-phase order, and the unloading also meets the power change gradient requirements of the generator. According to this embodiment, the aircraft may include multiple generators, and the power supply configuration may be the configuration specified by the current test. For example, one or more specific aircraft generators are outputting power for the test; the output voltage range may be a predetermined range determined by the test or the generator's characteristics. Therefore, whether the power supply configuration or output voltage range meets the requirements may include whether the generator currently being supplied is one or more specific aircraft generators, whether the output voltage range is within the predetermined range, and so on. According to this embodiment, the output alarm may include notifying the tester of the reason for test termination, such as the power supply configuration not matching the generator specified for the test, the average output power exceeding the overload protection level, and so on. It will be appreciated that the alarm may be output in any suitable form, such as a visual or auditory signal. In this way, the present disclosure provides more multi-dimensional safety monitoring, effectively meeting safety requirements in scenarios where the test approaches a protection threshold.

[0051] In another embodiment of the present disclosure, aircraft generator testing is based on a test plan (test requirements). In this embodiment, the test plan may include one or more target output powers that the generator needs to output (i.e., one or more target output powers that need to be tested for the generator), and method 100 is performed sequentially for each of the one or more target output powers. According to this embodiment, the test plan may also include an output duration for each target output power, and thus method 100 may also include repeating the steps described in blocks 110-130 before the output duration of each target output power expires, and optionally unloading all loaded simulated electrical loads when the output duration of the target output power expires. It will be understood that the output duration of each target output power represents the length of time that the test needs to be performed for that target output power.

[0052] Those skilled in the art will appreciate that, in the embodiments of the present disclosure, the addition and removal of the simulated electric load is performed automatically.

[0053] In another embodiment of the present disclosure, if unloading is required and it is found that the currently loaded simulated electrical load does not meet the conditions, execution of method 100 is terminated. For example, if the power difference indicates that a 90kW simulated electrical load needs to be unloaded, but the total power of the loaded simulated electrical load is only 10kW, it can be determined that the currently loaded simulated electrical load does not meet the conditions, and execution of method 100 of the present disclosure can be terminated. In this case, as a supplement, an alarm message can also be issued to the tester to inform him of the reason for the termination of execution of method 100.

[0054] In another embodiment of the present disclosure, in the event that unloading is required, if the power difference value cannot be satisfied simply by subtracting it from the already loaded simulated electric load, the closest simulated electric load with a higher power difference value is selected for unloading, and then a suitable simulated electric load is selected from the unloaded simulated electric loads to be loaded, the power of the suitable simulated electric load being equal to the difference between the power of the closest simulated electric load and the power difference value. For example, if the power difference value indicates that a 10kW simulated electric load needs to be unloaded, and the power of the closest simulated electric load among the already loaded simulated electric loads is 15kW, the 15kW simulated electric load can be selected for unloading, and a 5kW simulated electric load can be selected for loading, thereby satisfying the requirement of unloading the 10kW simulated electric load.

[0055] refer to Figure 2 , which shows a schematic diagram of a load addition and reduction system 200 for simulating an electric load for aircraft generator testing according to an exemplary embodiment of the present disclosure.

[0056] like Figure 2 As shown, the system 200 may include a simulated electric load 201, an acquisition device 203, and a test control device 205. It will be understood that although Figure 2 Three components (201, 203, 205) are shown in the figure. The system 200 may also include any other suitable components, such as an input device for the tester to input information or instructions, a display device for displaying test results, etc., a speaker for emitting alarm audio, etc., which are not repeated here.

[0057] In one embodiment of the present disclosure, the acquisition device 203 may include a voltage sensor and a current sensor for acquiring the output voltage and output current of the generator. It is understood that the acquisition device 203 may also include any other suitable device, such as a temperature sensor, etc., which will not be described in detail here.

[0058] In one embodiment of the present disclosure, the test control device 205 can be configured to: a. obtain the average output power of the generator within a predetermined time period before the current moment based on the output voltage and output current of the generator collected by the collection device 203, wherein the predetermined time period is less than the overload protection time of the generator; b. compare the target output power and the average output power of the generator to obtain the power difference that needs to be loaded or unloaded; c. when loading is required, select a suitable simulated electric load from the simulated electric loads that have not been loaded to load based on the power difference, and when unloading is required, select a suitable simulated electric load from the simulated electric loads that have been loaded to unload based on the power difference, so that the average output power of the generator is equal to the target output power after loading or unloading is completed; and d. repeat steps ac before receiving a test termination instruction for the target output power.

[0059] although Figure 2 , a simulated electrical load 201 is shown as a single block. To better regulate the output power of the generator, the simulated electrical load 201 may include multiple simulated electrical loads configured according to appropriate load capacities (i.e., the electrical power that the loads can consume). In one embodiment, the appropriate load capacity may include simulated electrical loads having a load capacity ratio of 8:4:2:1. For example, if the load capacity of the smallest simulated electrical load is 800W, the capacities of the corresponding other simulated electrical loads are 1600W, 3200W, and 6400W, respectively. In another embodiment of the present disclosure, the number of simulated electrical loads of corresponding load capacity can be set as needed. Generally speaking, the number of smallest simulated electrical loads is generally large, while the number of largest simulated electrical loads is generally small. It will also be understood that the above-mentioned ratios, specific values, etc. of the load capacities of the simulated electrical loads are provided merely as examples, and the load capacities of the simulated electrical loads may be configured in any other suitable manner, such as a load capacity ratio of 10:5:2:1, or the load capacities of all simulated electrical loads may be the same, and so on, which will not be further described here.

[0060] Therefore, the present disclosure proposes a method and system for increasing and decreasing loads of a simulated electrical load for aircraft generator testing. Preferably, the method can optimize the automatic increase and decrease of loads onboard an aircraft's simulated electrical load based on multiple objectives. This method comprehensively considers factors such as the generator's current average output power, the simulated electrical load state, three-phase imbalance, and overload protection time, and formulates reasonable strategies for generating increase and decrease load sequences, delays, and phase power compensation, ultimately achieving stable increase and decrease loads of the simulated electrical load.

[0061] To address the complex, high-frequency, and high-amplitude fluctuations in the aircraft's load, the disclosed method and system, combined with the power system's overload protection logic, filters the test generator's output power, eliminating the impact of high-frequency, high-amplitude fluctuations in the aircraft's load. To address the need for automatic load addition and removal, the disclosed method and system, after obtaining the current average output power, combines this with the target power required by the test or flight test subject to determine the required power level. When loading is required, the power difference between the unloaded simulated load and the required power level is compared sequentially, in descending order, first three-phase and then single-phase. When comparing with a single-phase load, the load corresponding to the lower power phase is prioritized to improve three-phase imbalance. When unloading is required, the power difference between the loaded simulated load and the required power level is compared sequentially, in descending order, first three-phase and then single-phase. When comparing with a single-phase load, the load corresponding to the higher power phase is prioritized to improve three-phase imbalance. After these comparisons are complete, an automatic load addition and removal control sequence is established. In response to the requirements for load addition and reduction gradients, the method and system disclosed herein, after forming an automatic load addition and reduction control sequence, drives the corresponding actuator to load or unload the simulated electrical load. When the actuator is actuated, it will set an appropriate delay time based on the load size and loading gradient in the sequence to avoid gradient exceeding the limit caused by the simultaneous actuation of multiple actuators.

[0062] In addition, during the load addition and reduction process, the method and system disclosed in the present invention also take a variety of safety measures to ensure the safety of load addition and reduction: real-time monitoring of the current output power of the generator, and comparing it with the overload protection power. If it exceeds the overload protection power, the simulated electric load is unloaded in time and an alarm is issued; real-time monitoring of the current output voltage of the generator, when the output voltage is higher or lower than the allowable voltage range of the generator, the simulated electric load is unloaded in time and an alarm is issued; monitoring of the output power factor and three-phase imbalance of the generator, when it exceeds the allowable range of the power supply quality of the aircraft power system, the simulated electric load is unloaded in time and an alarm is issued; monitoring of the voltage level and power supply configuration of the aircraft power system, when it does not meet the test power supply configuration, the simulated electric load is unloaded in time and an alarm is issued; and so on.

[0063] Thus, the method and system disclosed herein simulates the addition and removal of electrical loads according to the filtered generator output power (i.e., the average output power within a predetermined time period), thereby reducing the actuator actuation frequency, increasing system reliability and service life, preventing the simulated electrical load loading process from coupling with the increase in the aircraft's local load, and reducing the risk of generator output power overload; fully utilizing the generator overload logic trigger time (overload protection time) to increase the average generator output power without triggering overload protection, thereby ensuring the validity of the test point; setting the loading or unloading delay time according to the addition and removal of each load to ensure that the addition and removal gradient meets the power change gradient requirements of the generator; coarse adjustment by adding and removing three-phase loads can shorten the addition and removal time, and fine adjustment by adding and removing single-phase loads can improve the addition and removal accuracy and improve the three-phase imbalance of the power grid. Thus, the method and system disclosed herein can achieve at least one of the preferred goals of reducing the risk of power overload, reducing the impact on the aircraft power grid, improving the addition and removal accuracy, improving the three-phase imbalance, and extending the life of the actuator.

[0064] It will be appreciated that although the present application describes various embodiments in conjunction with a generator for an aircraft, the present application may also be applicable to generators for other equipment, such as generators for ships, vehicles, and the like.

[0065] The above detailed description includes references to the accompanying drawings, which form part of the detailed description. The accompanying drawings illustrate specific embodiments that can be put into practice by way of illustration. These embodiments are also referred to herein as "examples." Such examples may include elements other than those shown or described. However, examples that include the shown or described elements are also contemplated. In addition, examples using any combination or arrangement of those elements shown or described are also contemplated, or with reference to the specific examples (or one or more aspects thereof) shown or described herein, or with reference to other examples (or one or more aspects thereof) shown or described herein.

[0066] In the appended claims, the terms "including" and "comprising" are open-ended, that is, systems, apparatuses, articles, or processes that include elements in addition to those listed after such terms in a claim are considered to fall within the scope of that claim. Furthermore, in the appended claims, the terms "first," "second," and "third," etc. are used merely as labels and are not intended to indicate a numerical order to their objects.

[0067] In addition, the order of each operation explained in this specification is exemplary. In alternative embodiments, each operation can be performed in a different order than that shown in the drawings, and each operation can be combined into a single operation or split into more operations.

[0068] The above description is intended to be illustrative, not restrictive. For example, the examples described above (or one or more aspects thereof) may be used in conjunction with other embodiments. Other embodiments may be used, such as by a person of ordinary skill in the art after reviewing the above description. The abstract allows the reader to quickly determine the nature of the present disclosure. This abstract is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims. In addition, in the above specific embodiments, various features may be grouped together to make the disclosure smooth. However, the claims may not state every feature disclosed herein, as the embodiments may characterize a subset of the features. In addition, an embodiment may include fewer features than those disclosed in a particular example. Therefore, the appended claims are thereby incorporated into the specific embodiments, and a claim exists independently as a separate embodiment. The scope of the embodiments disclosed herein should be determined with reference to the appended claims and the full scope of equivalents to which such claims are entitled.

Claims

1. A method for adding and removing a simulated electric load for aircraft generator testing, comprising: a. collecting the output voltage and output current of the generator using a voltage sensor and a current sensor to obtain the average output power of the generator within a predetermined time period before a current moment, wherein the predetermined time period is less than the overload protection time of the generator; b. comparing the target output power with the average output power of the generator to obtain a power difference that needs to be loaded or unloaded; c. when loading is required, selecting a suitable simulated electric load from unloaded simulated electric loads based on the power difference to load, and when unloading is required, selecting a suitable simulated electric load from loaded simulated electric loads based on the power difference to unload, so that the average output power of the generator is equal to the target output power after loading or unloading is completed; and d. Repeat steps ac until a test termination instruction for the target output power is received.

2. The method according to claim 1, characterized in that The method further includes unloading all loaded simulated electric loads upon receiving a test termination instruction for the target output power.

3. The method according to claim 1, characterized in that Step c also includes: When loading is required, selecting a simulated electric load that matches the power difference in the order of the power consumption of the simulated electric loads that have not been loaded, first the three-phase simulated electric load and then the single-phase simulated electric load, to form a simulated electric load loading control sequence; When unloading is required, selecting a simulated electric load that matches the power difference in the order of the power consumption of the loaded simulated electric loads from large to small, first the three-phase simulated electric load and then the single-phase simulated electric load, to form a simulated electric load unloading control sequence; and According to the simulated electric load automatic loading control sequence or the simulated electric load unloading control sequence, the simulated electric load in the simulated electric load automatic loading control sequence or the simulated electric load unloading control sequence is loaded or unloaded in sequence by driving the actuator.

4. The method according to claim 3, characterized in that Step c also includes: If the simulated electric load loading control sequence includes a single-phase simulated electric load, the selected single-phase simulated electric load is loaded to the phase with the smallest current power among the three phases; If the simulated electric load unloading control sequence includes a single-phase simulated electric load, unloading is performed from the three phases in descending order of current power.

5. The method according to claim 3, characterized in that After each simulated electric load is loaded or unloaded, and before the next simulated electric load is loaded or unloaded, a certain delay time is waited, wherein the delay time depends on the power variation gradient requirement of the generator.

6. The method according to any one of claims 1 to 5, characterized in that During the execution of the method, at least one of the following is also performed in real time: detecting whether a termination instruction is received, and if the termination instruction is received, unloading all loaded simulated electric loads and terminating the execution of the method; detecting whether any one of the power supply configuration and the output voltage range meets the requirements; if not, unloading all loaded simulated electrical loads, terminating the execution of the method, and outputting an alarm; detecting an output power factor and / or three-phase imbalance of the generator, and when the output power factor and / or three-phase imbalance exceeds an allowable range of power supply quality of the aircraft power system, unloading all loaded simulated electrical loads, terminating execution of the method, and outputting an alarm; as well as It is detected whether the average output power exceeds the overload protection power. If it exceeds, all loaded simulated electric loads are unloaded, the execution of the method is terminated, and an alarm is output.

7. The method according to claim 1, characterized in that The predetermined duration is less than or equal to the overload protection time minus the time required for signal acquisition, data calculation, signal transmission, and actuator actuation.

8. The method according to claim 1, characterized in that The simulated electric load includes a plurality of simulated electric loads set according to appropriate load capacities, wherein the appropriate load capacities include the load capacities of the simulated electric loads in a ratio of 8:4:2:1 or 10:5:2:

1.

9. The method according to claim 1, characterized in that The average output power of the generator being equal to the target output power includes the power difference being within a predetermined range.

10. The method according to claim 1, characterized in that The generator test is based on a test plan, the test plan including one or more target output powers that the generator is required to output, and wherein the method is performed sequentially for each of the one or more target output powers.

11. The method according to claim 10, characterized in that The test plan also includes an output duration of each target output power, and the method further includes repeating steps ac before the output duration of the target output power expires, and unloading all loaded simulated electrical loads when the output duration of the target output power expires.

12. A system for adding and removing a simulated electric load for testing an aircraft generator, comprising: Simulate electrical loads; A collection device, comprising a voltage sensor and a current sensor for collecting the output voltage and output current of the generator; A test control device, the test control device being arranged to: a. obtaining, based on the output voltage and output current of the generator collected by the collection device, an average output power of the generator within a predetermined time period before a current moment, wherein the predetermined time period is less than an overload protection time of the generator; b. comparing the target output power with the average output power of the generator to obtain a power difference that needs to be loaded or unloaded; c. when loading is required, selecting a suitable simulated electric load from unloaded simulated electric loads based on the power difference to load, and when unloading is required, selecting a suitable simulated electric load from loaded simulated electric loads based on the power difference to unload, so that the average output power of the generator is equal to the target output power after loading or unloading is completed; and d. Repeat steps ac until a test termination instruction for the target output power is received.

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