Power supply device and power supply method for movable aircraft engine test bed

Abstract

The invention provides a power supply device and method for a movable aircraft engine test bed, and can be applied to the technical field of power supply circuits. The power supply device comprises a first power supply module used for supplying power to the movable aircraft engine test bed through a first power supply circuit; the second power supply module comprises an energy storage assembly, an energy storage branch circuit, a test generator and a transmission branch circuit, the first end of the energy storage branch circuit is connected with the energy storage assembly, the first end of the transmission branch circuit is connected with the test generator, and the second end of the energy storage branch circuit and the second end of the transmission branch circuit are connected with the movable engine test bed; the power supply module is used for supplying power to the movable engine test bed by the test generator through a second power supply circuit comprising a transmission branch circuit under the condition that the test generator serves as a power supply; and under the condition that the generated power of the test generator is greater than the load power of the movable aircraft engine test bed, the test generator supplies power to the energy storage assembly through a third power supply circuit comprising a transmission branch and an energy storage branch.

Description

Technical Field

[0001] This disclosure relates to the field of power supply current technology, and more specifically to a power supply device and power supply method for a mobile aircraft engine test stand. Background Technology

[0002] During ground testing of aircraft engines, load tests are required. In traditional engine load tests, not only is a resistor used as the engine load, but cooling water is also needed to meet the hydraulic load requirements of the engine's hydraulic load system.

[0003] However, using resistance to dissipate power or cooling water for heat dissipation not only leads to energy waste in the engine, but also to increased ambient temperature and increased energy consumption of the circulating water equipment. Summary of the Invention

[0004] In view of the above problems, this disclosure provides a power supply device and a power supply method for a mobile aircraft engine test stand.

[0005] According to a first aspect of this disclosure, a power supply device for a mobile aircraft engine test stand is provided, comprising: a first power supply module for supplying power to the mobile aircraft engine test stand via a first power supply circuit;

[0006] The second power supply module includes an energy storage component, an energy storage branch, a test generator, and a transmission branch. The first end of the energy storage branch is connected to the energy storage component, the first end of the transmission branch is connected to the test generator, and the second ends of the energy storage branch and the transmission branch are connected to the mobile engine test stand. It is used to supply power from the test generator to the mobile engine test stand via a second power supply circuit including the transmission branch when the test generator is the power source; and to supply power from the test generator to the energy storage component via a third power supply circuit including the transmission branch and the energy storage branch when the power output of the test generator exceeds the load power of the mobile aircraft engine test stand, until the rated capacity of the energy storage component is reached.

[0007] According to an embodiment of this disclosure, the second power supply module is further configured to supply power from the energy storage component to the mobile engine test stand via a fourth power supply circuit including the energy storage branch when the energy storage component is used as a power source.

[0008] According to an embodiment of this disclosure, the transmission branch includes a first converter connected to the test generator, used to enable the test generator to supply power to the mobile engine test stand through the second power supply branch when the test generator is used as a power source.

[0009] According to an embodiment of this disclosure, the energy storage branch includes a second converter connected to the energy storage component, used to enable the test generator to supply power to the energy storage component through the third power supply branch when the power generation is greater than the load power.

[0010] According to an embodiment of this disclosure, the second converter is also used to enable the energy storage component to supply power to the mobile engine test stand through the fourth power supply circuit.

[0011] A second aspect of this disclosure provides a power supply method for a mobile aircraft engine test stand, comprising: responding to receiving a first instruction to supply power using a first power supply module, supplying power to the mobile aircraft engine test stand through a first power supply circuit; and responding to receiving a preparation instruction to perform a load test on a test generator in a second power supply module, controlling the second power supply circuit and a third power supply circuit to be turned on, wherein the second power supply module further includes an energy storage component, an energy storage branch, and a transmission branch, a first end of the energy storage branch being connected to the energy storage component, a first end of the transmission branch being connected to the test generator, and a second end of the energy storage branch being connected to the test generator. The second end of the aforementioned transmission branch is connected to the aforementioned mobile engine test stand. The aforementioned second power supply circuit includes the aforementioned transmission branch, and the aforementioned third power supply circuit includes the aforementioned transmission branch and the aforementioned energy storage branch. In response to detecting the output voltage of the aforementioned test generator, the aforementioned test generator is used to supply power to the aforementioned mobile aircraft engine test stand through the aforementioned second power supply circuit. In response to detecting that the power generation of the aforementioned test generator is greater than the load power of the aforementioned mobile aircraft engine test stand, the aforementioned test generator is used to supply power to the aforementioned energy storage component through the aforementioned third power supply circuit until the rated storage capacity of the aforementioned energy storage component is reached.

[0012] According to an embodiment of this disclosure, the method further includes: in response to receiving a second instruction to supply power using the energy storage component, supplying power to the mobile aircraft engine test stand through the fourth power supply circuit using the energy storage component, wherein the fourth power supply circuit includes the energy storage branch.

[0013] According to an embodiment of this disclosure, the transmission branch includes a first converter connected to the test generator, and the method of supplying power to the mobile aircraft engine test stand through the second power supply circuit using the test generator includes: controlling the first converter to supply power to the mobile aircraft engine test stand through the second power supply branch.

[0014] According to an embodiment of this disclosure, the energy storage branch includes a second converter connected to the energy storage component, and the method of supplying power to the energy storage component through the third power supply circuit using the test generator includes: controlling the second converter to supply power to the energy storage component through the third power supply circuit.

[0015] According to an embodiment of this disclosure, the above-mentioned use of the energy storage component to supply power to the mobile aircraft engine test stand through the fourth power supply circuit includes: controlling the second converter device to enable the energy storage component to supply power to the mobile aircraft engine test stand through the fourth power supply circuit.

[0016] According to embodiments of this disclosure, by using the test generator as a power source when the test generator outputs voltage, and supplying power to the mobile engine test stand through a second power supply circuit, the energy generated during the loading test can be utilized, avoiding energy waste. Furthermore, by using the test generator to charge the energy storage components when the output power of the test generator exceeds the power consumption of the mobile aircraft test stand, the energy generated during the loading test can be fully utilized. Attached Figure Description

[0017] The foregoing contents, as well as other objects, features, and advantages of this disclosure, will become clearer from the following description of embodiments with reference to the accompanying drawings, in which:

[0018] Figure 1A The schematic diagram illustrates the architecture of a power supply device and a movable aircraft engine test stand according to embodiments of the present disclosure.

[0019] Figure 1B A schematic diagram illustrating the power supply device according to an embodiment of the present disclosure in a first operating state is shown.

[0020] Figure 1C A schematic diagram illustrating the power supply device according to an embodiment of the present disclosure in a second operating state is shown.

[0021] Figure 1D A schematic diagram illustrating the power supply device according to an embodiment of the present disclosure in a third operating state is shown.

[0022] Figure 2 A schematic diagram illustrating a second power supply module and a movable aircraft engine test stand according to a specific embodiment of the present disclosure; and

[0023] Figure 3 A flowchart illustrating a power supply method for a mobile aircraft engine test stand according to an embodiment of the present disclosure is shown schematically. Detailed Implementation

[0024] The embodiments of the present disclosure will now be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the disclosure. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the embodiments of the present disclosure for ease of explanation. However, it will be apparent that one or more embodiments may be practiced without these specific details. Furthermore, descriptions of well-known structures and techniques are omitted in the following description to avoid unnecessarily obscuring the concepts of the present disclosure.

[0025] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. The terms “comprising,” “including,” etc., as used herein indicate the presence of features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0026] All terms used herein (including technical and scientific terms) have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein are to be interpreted in a manner consistent with the context of this specification, and not in an idealized or overly rigid way.

[0027] When using expressions such as "at least one of A, B and C", they should generally be interpreted in accordance with the meaning that is commonly understood by those skilled in the art (e.g., "a system having at least one of A, B and C" should include, but is not limited to, a system having A alone, a system having B alone, a system having C alone, a system having A and B, a system having A and C, a system having B and C, and / or a system having A, B and C, etc.).

[0028] During ground testing of aircraft engines, load tests are required. The engine load consists of two main parts. The first part is the engine shaft driving the generator to rotate and generate electricity. This test process involves the generator generating electricity at different engine speeds with varying power outputs to verify the engine's performance under different power generation loads. The second part is the engine carrying a hydraulic load device. The purpose of this test is to verify the engine's performance under hydraulic loads.

[0029] The test engine load test involved a generator, with the generator's load being a resistor box. To accommodate different generator output power levels, the resistor box required multi-stage high-precision resistors. The engine's hydraulic load device needed cooling water to meet the hydraulic load requirements. In traditional engine loading systems, the energy of the engine load was consumed by either resistors or hydraulic loading with cooling water. This resulted in energy waste, increased ambient temperature, and increased energy consumption in the circulating water system.

[0030] Embodiments of this disclosure provide a power supply device for a mobile aircraft engine test stand, comprising: a first power supply module for supplying power to the mobile aircraft engine test stand via a first power supply circuit; and a second power supply module including an energy storage component, an energy storage branch, a test generator, and a transmission branch, wherein a first end of the energy storage branch is connected to the energy storage component, a first end of the transmission branch is connected to the test generator, and a second end of the energy storage branch and a second end of the transmission branch are connected to the mobile engine test stand. The second power supply module supplies power to the mobile engine test stand via a second power supply circuit including the transmission branch when the test generator is the power source; and supplies power to the energy storage component via a third power supply circuit including the transmission branch and the energy storage branch when the power output of the test generator exceeds the load power of the mobile aircraft engine test stand, until the rated capacity of the energy storage component is reached.

[0031] The embodiments of this disclosure directly drive a test generator to generate electricity during engine loading tests using an AC / DC generator or hydraulic pump. This generated energy is then converted into electrical energy to power the equipment on the mobile aircraft engine test stand. Excess energy is stored. This approach not only rationally utilizes and recycles generated energy but also reduces the need for bulky loading resistor cabinets, cooling ventilation, and cooling water circulation equipment, achieving energy conservation and environmental protection while serving as a model. Furthermore, the embodiments of this disclosure are applicable to different types of aircraft engine test stands, exhibiting high versatility and adaptability. Subsequent compatibility modifications are also very simple, reducing operating costs.

[0032] Figure 1A The schematic diagram illustrates the architecture of a power supply device and a movable aircraft engine test stand according to embodiments of the present disclosure.

[0033] like Figure 1A As shown, the power supply device 110 includes a first power supply module 111 and a second power supply module 112. The second power supply module 112 includes an energy storage component 1121, an energy storage branch, a test generator 1122, and a transmission branch. The first power supply module 111 and the second power supply module 112 can supply power to the mobile aircraft engine test stand 120.

[0034] like Figure 1A As shown, the first end of the energy storage branch is connected to the energy storage component 1121, the first end of the transmission branch is connected to the test generator 1122, and the second ends of the energy storage branch and the transmission branch are connected to the mobile engine test stand 120. It should be noted that the first and second ends of the energy storage branch and the transmission branch are relative, referring only to the end connected to a specific device or a specific line point.

[0035] like Figure 1AAs shown, the second end of the energy storage branch and the second end of the transmission branch are simultaneously connected to the mobile engine test stand 120, as in a “Y” shape.

[0036] According to embodiments of this disclosure, the first power supply circuit may include a first sub-power supply circuit and a second sub-power supply circuit, wherein the first sub-power supply circuit can supply power from the mains to the mobile aircraft engine test stand 120, and the second sub-power supply circuit can supply power from the diesel engine to the mobile aircraft engine test stand 120.

[0037] According to embodiments of this disclosure, the test generator 1122 may include an engine-loaded generator and a hydraulically loaded generator. Specifically, the engine-loaded generator may be a generator for verifying the performance of the engine under different power generation loads, and the hydraulically loaded generator may be a generator for verifying the performance of the engine under hydraulic loads.

[0038] According to embodiments of this disclosure, the energy storage component 111 may be a battery.

[0039] Figure 1B A schematic diagram illustrating a power supply device according to an embodiment of the present disclosure in a first operating state is shown.

[0040] like Figure 1B As shown, in the first working state, the first power supply module 111 can supply power to the mobile engine test stand 120 through the first power supply circuit, and the second power supply module 112 can supply power to the mobile engine test stand 120 by the test generator 1122 through the second power supply circuit including the transmission branch.

[0041] According to the embodiments of this disclosure, when the test generator 1122 outputs voltage, it can be when the test engine is loaded using the mobile aircraft engine test stand 120. Since the test engine drives the test generator 1122 to work, the test generator 1122 outputs voltage. At this time, the test generator 1122 can be used as a power source to supply power to the mobile aircraft engine test stand 120.

[0042] According to embodiments of this disclosure, when the output power of the test generator 1122 is less than the load power of the portable aircraft engine test stand 120, both the mains power or diesel generator and the test generator 1122 can be used as power sources. When the output power of the test generator 1122 is equal to the load power of the portable aircraft engine test stand 120, only the test generator 1122 can be used as a power source.

[0043] According to another embodiment of this disclosure, when the test generator 1122 is not outputting voltage, the portable aircraft engine test stand 120 can also be powered solely through the first power supply module 111.

[0044] Figure 1C A schematic diagram illustrating the power supply device according to an embodiment of the present disclosure in a second operating state is shown.

[0045] like Figure 1C As shown, in the second working state, the second power supply module 112 supplies power to the mobile aircraft engine test stand 120 through the test generator 1122 via the second power supply circuit, while simultaneously supplying power to the energy storage component through the test generator 1122 via the third power supply circuit, which includes a transmission branch and an energy storage branch, until the rated energy storage capacity of the energy storage component 1121 is reached.

[0046] According to embodiments of this disclosure, when the power output of the test generator 1122 is greater than the load power of the mobile aircraft engine test stand 120, it is not necessary to use the first power supply module 111 to supply power to the mobile engine test stand 120 through the first power supply circuit.

[0047] According to embodiments of this disclosure, by using the test generator as a power source when the test generator outputs voltage, and supplying power to the mobile engine test stand through a second power supply circuit, the energy generated during the loading test can be utilized, avoiding energy waste. Furthermore, by using the test generator to charge the energy storage components when the output power of the test generator exceeds the power consumption of the mobile aircraft test stand, the energy generated during the loading test can be fully utilized.

[0048] Figure 1D A schematic diagram illustrating a power supply device in a third operating state according to an embodiment of the present disclosure is shown.

[0049] like Figure 1D As shown, in the third working state, the second power supply module 112 supplies power to the movable engine test stand 120 through the energy storage component 1121 via the fourth power supply circuit including the energy storage branch.

[0050] According to the embodiments of this disclosure, the energy storage component 1121 can be used as a power source when the second power supply module 112 is used as the main power supply module, or the energy storage component 1121 can be used as a power source when the first power supply module 111 is used as the main power supply module and the first power supply module 111 is de-energized.

[0051] According to embodiments of this disclosure, when the energy storage capacity of the energy storage component 1121 reaches the rated energy storage capacity, the second power supply module 112 can be determined as the main power supply module and the energy storage component 1121 can be used as the power source. Alternatively, when the energy storage capacity of the energy storage component 1120 reaches the predetermined energy storage capacity, the second power supply module 112 can be determined as the main power supply module and the energy storage component 1121 can be used as the power source.

[0052] According to embodiments of this disclosure, when the energy storage component 1121 serves as a power source and the test generator 1122 outputs voltage, both the energy storage component 1121 and the test generator 1122 can simultaneously supply power to the mobile aircraft engine test stand 120. Furthermore, when the output power of the test generator 1122 exceeds the load power of the mobile aircraft engine test stand 120, the test generator 1122 can supply power to the mobile aircraft engine test stand 120 while simultaneously supplying power to the energy storage component 1121, without requiring the energy storage component 1121 to supply power to the mobile aircraft engine test stand 120.

[0053] According to embodiments of this disclosure, by utilizing energy storage components to power a mobile aircraft engine test stand, multiple modes for powering a mobile aircraft engine test stand are provided, thereby improving the reliability of power supply.

[0054] According to an embodiment of this disclosure, the transmission branch includes: a first converter device connected to the test generator, used to enable the test generator to supply power to the mobile engine test stand through the second power supply branch when the test generator is used as a power source.

[0055] According to embodiments of this disclosure, the first converter can be a power conversion system (PCS). Specifically, under the condition of the output voltage of the test generator, the phase-locked loop function of the first converter can extract electrical energy from the DC bus of the test generator according to the test requirements and convert it into AC power with the same voltage, phase sequence and phase angle as the 380V bus, and supply it to the load equipment of the AC bus movable aircraft engine test stand.

[0056] According to embodiments of this disclosure, by setting a first converter device in the transmission branch and utilizing the phase-locked loop function of the first converter device, the test generator supplies power to the mobile aircraft engine test stand, making full use of the energy generated by the load test.

[0057] According to an embodiment of this disclosure, the energy storage branch includes: a second converter connected to the energy storage module, used to enable the test generator to supply power to the energy storage module through a third power supply branch when the power generation is greater than the load power.

[0058] According to embodiments of this disclosure, the second converter can be an energy storage converter. Specifically, the second converter can store the electrical energy extracted by the first converter into an energy storage component.

[0059] According to embodiments of this disclosure, by installing a second converter in the energy storage branch, the test generator can supply power to the energy storage component when the power generation is greater than the load power, thus making full use of the energy generated by the load test.

[0060] According to embodiments of this disclosure, the second converter is also used to enable the energy storage component to supply power to the mobile engine test stand via a fourth power supply circuit.

[0061] According to embodiments of this disclosure, the phase-locked loop function of the second converter can be used to provide 380V 50Hz AC power with identical voltage, phase sequence, and phase angle to the AC bus based on the load conditions of the mobile aircraft engine test stand, in order to power the mobile aircraft engine test stand.

[0062] According to embodiments of this disclosure, by utilizing the phase-locked loop function of the second converter, the energy storage component can supply power to the mobile aircraft engine test stand. This not only makes full use of the energy generated by the load test, but also allows the energy storage component to be used as a backup power source, thereby improving the reliability of the power supply.

[0063] Figure 2 A schematic diagram of a second power supply module according to a specific embodiment of the present disclosure is shown.

[0064] like Figure 2 As shown, the second power supply module includes multiple test generators, such as engine-loaded generator 1G1, ..., engine-loaded generator 1Gn, hydraulic-loaded generator 2G1, hydraulic-loaded generator 2G2, a power extraction component for extracting power from the test generators, and a loading DC bus.

[0065] like Figure 2 As shown, the second power supply module includes a transmission branch connected to the loaded DC bus and an energy storage branch connected to the energy storage component. Specifically, the energy storage component can be a battery pack, which is equipped with lithium iron phosphate batteries, ternary lithium batteries, or lithium titanate batteries. To ensure the safe and reliable operation of the battery pack, it is equipped with a battery management and protection device, a cooling device, a fire suppression device, and DC switch protection components, etc.

[0066] like Figure 2 As shown, the energy storage branch includes fuse 1FU1, isolating circuit breaker 1QS1, fuse 1FU2, intermediate relay 1KM1, intermediate relay 1KM2, first filter component 1LCL1, second converter device 1PCS1, isolating circuit breaker 1QS2, and low-voltage circuit breaker 1QF3.

[0067] like Figure 2 As shown, the transmission branch includes fuse 2FU1, isolating circuit breaker 2QS1, fuse 2FU2, intermediate relay 2KM1, intermediate relay 2KM2, second filter component 2LCL1, first converter device 2PCS1, isolating circuit breaker 2QS2, and low-voltage circuit breaker 2QF3.

[0068] like Figure 2As shown, the energy storage components, energy storage branches, and transmission branches in the second power supply module can be housed in the energy storage system cabinet. The energy storage system cabinet also includes an isolation transformer 1B1, which isolates the inverter's high-frequency noise, preventing interference with surrounding equipment, reducing ground insulation, and improving the safety of the power supply device. It also prevents damage to equipment caused by voltage surges and other factors. The energy storage system cabinet is connected to the 380V AC bus via circuit breaker QF1. Furthermore, other power supply modules, such as the first power supply module, can be connected to the 380V AC bus via circuit breakers QF2, ..., QFn, to supply power to the mobile aircraft engine test stand via the 380V AC bus.

[0069] According to embodiments of this disclosure, when the second power supply module supplies power to the mobile aircraft engine test stand, the power supply device may further include a battery management system (BMS) and an energy management and control system (EMS).

[0070] According to embodiments of this disclosure, the BMS can be used to collect the operating status and parameters of the battery. The EMS, characterized by short communication latency, fast response speed, and reliable operation, is responsible for collecting the operating status of each device in the entire power supply system. The built-in energy management and monitoring program can internally allocate power to each PCS for execution according to actual operating needs, enabling functions such as networking energy storage components and storing battery information and alarm records. Furthermore, the EMS can also obtain the battery operating status and parameters collected by the BMS through communication with the BMS, and record system alarms and faults, facilitating real-time monitoring of system operation by the user.

[0071] The EMS needs to measure the power of the 380V AC bus power supply P1. Energy recovery is accomplished by controlling the output power P2 of 1PCS1 and the output power P3 of 2PCS1. Specifically, the DC power generated by the test generator is converted and sent to the DC load bus. 2PCS1 extracts the generated power from the DC load bus and converts it into 380V AC power, transmitting the extracted power value P3 to the EMS. The EMS then compares the measured power supply P1 with P3. If P3 ≤ P1, all the generated energy from P3 is fed back to the 380V AC bus to power loads such as portable aircraft engine test benches. If P3 ≥ P1, the excess energy from P3 - P1 must be used to charge the energy storage components to ensure that P3 - P2 = P1, thus preventing the power transmitted by the transmission branch from being fed back to the grid.

[0072] The second converter device 1PCS1 is used for battery charging and discharging. Since the PCS has a phase-locked loop function, it can provide the AC bus with 380V 50Hz AC power with the same voltage, phase sequence and phase angle according to the load conditions. It can also store the loaded generated power extracted by 2PCS1 according to the EMS command, thus meeting the power supply and energy storage functions of the mobile aircraft engine test stand.

[0073] The first converter device 2PCS1 is used to receive electrical energy from the generator loaded by the engine. It can extract electrical energy from the loaded DC bus and convert it into AC power with the same voltage, phase sequence and phase angle as the 380V AC bus, and supply the portable aircraft engine test bench load equipment of the AC bus.

[0074] Figure 3 A flowchart illustrating a power supply method for a mobile aircraft engine test stand according to an embodiment of the present disclosure is shown schematically.

[0075] like Figure 3 As shown, the method includes operations S310 to S340.

[0076] In operation S310, in response to receiving a first command to supply power using the first power supply module, power is supplied to the mobile aircraft engine test stand through the first power supply circuit.

[0077] In operation S320, in response to receiving a preparation command for loading a test on the test generator in the second power supply module, the second power supply circuit and the third power supply circuit are turned on.

[0078] When operating S330, in response to detecting the output voltage of the test generator, power is supplied to the mobile aircraft engine test stand via the second power supply circuit using the test generator.

[0079] In operation S340, in response to the detection that the power output of the test generator is greater than the load power of the mobile aircraft engine test stand, the test generator is used to supply power to the energy storage component through the third power supply circuit until the rated capacity of the energy storage component is reached.

[0080] According to an embodiment of this disclosure, the second power supply module further includes an energy storage component, an energy storage branch, and a transmission branch. The first end of the energy storage branch is connected to the energy storage component, the first end of the transmission branch is connected to the test generator, and the second ends of the energy storage branch and the transmission branch are connected to the mobile engine test stand. The second power supply circuit includes the transmission branch, and the third power supply circuit includes the transmission branch and the energy storage branch.

[0081] According to embodiments of this disclosure, the first instruction may be generated when the user instructs the first power supply module to act as the main power supply module, or it may be generated when the second power supply module acts as the main power supply module and the second power supply module is powered off.

[0082] According to embodiments of this disclosure, the power supply of the first power supply module may include mains power and a diesel generator, and the first power supply circuit may include a first sub-power supply circuit and a second sub-power supply circuit. The first sub-power supply circuit can supply power from the mains power to the mobile aircraft engine test stand, and the second sub-power supply circuit can supply power from the diesel engine to the mobile aircraft engine test stand.

[0083] According to embodiments of this disclosure, the preparation command can characterize the preparation for a load test on the test generator, and when the second power supply circuit and the third power supply circuit are turned on, the switches in the transmission branch and the energy storage branch can be closed.

[0084] According to embodiments of this disclosure, after the switches in the control transmission branch and the energy storage branch are closed, the converter device in the energy storage branch can also be controlled to prevent the energy storage component from supplying power to the mobile aircraft engine test stand.

[0085] According to embodiments of this disclosure, when the test generator outputs voltage, the test generator can supply power to the mobile aircraft engine test stand through the second power supply circuit. Specifically, the power supply from the test generator to the mobile aircraft engine test stand can be achieved by controlling the converter device in the second power supply circuit.

[0086] According to embodiments of this disclosure, after the test generator outputs voltage, the output power of the test engine and the load power of the mobile aircraft engine test stand can be detected in real time, and the output power and load power can be compared. Specifically, when the output power is less than the load power, the electrical energy generated by the test generator can be transmitted to the 380V bus for use by the mobile aircraft engine test stand. When the output power is greater than or equal to the load power, the excess electrical energy generated by the test engine can be used to charge the energy storage components, thereby reducing energy waste and preventing the electrical energy generated by the test engine from being fed back to the power grid.

[0087] According to embodiments of this disclosure, by controlling the second and third power supply circuits to be turned on upon receiving a preparation command, the test generator can be promptly used as a power source when the test generator outputs voltage. The test generator then supplies power to the mobile engine test stand through the second power supply circuit, thus fully utilizing the energy generated during the loading test. Furthermore, by using the test generator to charge the energy storage components when the output power of the test generator exceeds the power consumption of the mobile aircraft test stand, the energy generated during the loading test can be further fully utilized, avoiding energy waste.

[0088] According to embodiments of this disclosure, the power supply method further includes: in response to receiving a second instruction to supply power using an energy storage component, supplying power to the mobile aircraft engine test stand via a fourth power supply circuit using the energy storage component.

[0089] According to embodiments of this disclosure, the fourth power supply circuit includes an energy storage branch.

[0090] According to embodiments of this disclosure, the second instruction may be generated when the user instructs the second power supply module to act as the main power supply module, or it may be generated when the first power supply module acts as the main power supply module and the first power supply module is powered off.

[0091] According to embodiments of this disclosure, by utilizing energy storage components to power a mobile aircraft engine test stand, multiple modes for powering a mobile aircraft engine test stand are provided, thereby improving the reliability of power supply.

[0092] According to an embodiment of this disclosure, a test generator is used to supply power to a mobile aircraft engine test stand through a second power supply circuit, including: controlling a first converter device to enable the test generator to supply power to the mobile aircraft engine test stand through a second power supply branch.

[0093] According to embodiments of this disclosure, the transmission branch includes a first converter connected to the test generator, which can be an energy storage converter. Specifically, the first converter can extract electrical energy from the DC bus of the test generator according to the test requirements through the phase-locked loop function of the first converter and convert it into AC power with the same voltage, phase sequence, and phase angle as the 380V bus, to supply the load equipment of the portable aircraft engine test bench on the AC bus.

[0094] According to embodiments of this disclosure, the EMS can control a first converter device to extract and convert electrical energy from the DC bus of the test generator when the output voltage of the test generator is detected.

[0095] According to embodiments of this disclosure, by setting a first converter device in the transmission command, controlling the first converter device, and utilizing the phase-locked loop function of the first converter device, the test generator supplies power to the mobile aircraft engine test stand, making full use of the energy generated by the loading test.

[0096] According to an embodiment of this disclosure, power is supplied to the energy storage component via a third power supply circuit using a test generator, including: controlling a second converter device to supply power to the energy storage component via the third power supply circuit.

[0097] According to embodiments of this disclosure, the energy storage branch includes a second converter connected to the energy storage module, which can be an energy storage converter. Specifically, the EMS can control the second converter to store the electrical energy extracted by the first converter into the energy storage module.

[0098] According to embodiments of this disclosure, by setting a second converter in the energy storage branch, the test generator can supply power to the energy storage component when the power generation is greater than the load power, making full use of the energy generated by the load test while avoiding the backflow of excess power to the grid.

[0099] According to an embodiment of this disclosure, power is supplied to a mobile aircraft engine test stand via a fourth power supply circuit using an energy storage component, including: controlling a second converter device to supply power to the mobile aircraft engine test stand via the fourth power supply circuit.

[0100] According to embodiments of this disclosure, the EMS can control a second converter device to supply power from the energy storage component to the mobile aircraft engine test stand. Specifically, the phase-locked loop function of the second converter device can be used to provide 380V 50Hz AC power with identical voltage, phase sequence, and phase angle to the AC bus according to the load conditions of the mobile aircraft engine test stand, thereby supplying power to the mobile aircraft engine test stand.

[0101] According to embodiments of this disclosure, by utilizing the phase-locked loop function of the second converter, the energy storage component can supply power to the mobile aircraft engine test stand. This not only makes full use of the energy generated by the load test, but also allows the energy storage component to be used as a backup power source, thereby improving the reliability of the power supply.

[0102] According to embodiments of this disclosure, program code for executing the computer programs provided in embodiments of this disclosure can be written in any combination of one or more programming languages. Specifically, these computational programs can be implemented using high-level procedural and / or object-oriented programming languages, and / or assembly / machine languages. Programming languages ​​include, but are not limited to, languages ​​such as Java, C++, Python, "C", or similar programming languages. The program code can execute entirely on a user's computing device, partially on a user's device, partially on a remote computing device, or entirely on a remote computing device or server. In cases involving remote computing devices, the remote computing device can be connected to the user's computing device via any type of network, including a local area network (LAN) or a wide area network (WAN), or it can be connected to an external computing device (e.g., via the Internet using an Internet service provider).

[0103] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in a block diagram or flowchart, and combinations of blocks in a block diagram or flowchart, may be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0104] Those skilled in the art will understand that the features described in the various embodiments of this disclosure can be combined and / or combined in various ways, even if such combinations or combinations are not explicitly described in this disclosure. In particular, the features described in the various embodiments of this disclosure can be combined and / or combined in various ways without departing from the spirit and teachings of this disclosure. All such combinations and / or combinations fall within the scope of this disclosure.

[0105] The embodiments of this disclosure have been described above. However, these embodiments are for illustrative purposes only and are not intended to limit the scope of this disclosure. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of this disclosure, and all such substitutions and modifications should fall within the scope of this disclosure.

Claims

1. A power supply device for a movable aircraft engine testbed, comprising: a first power supply module for supplying power to the movable aircraft engine testbed through a first power supply circuit; a second power supply module comprising an energy storage assembly, an energy storage branch, a test generator and a transmission branch, a first end of the energy storage branch being connected to the energy storage assembly, a first end of the transmission branch being connected to the test generator, a second end of the energy storage branch and a second end of the transmission branch being connected to the movable engine testbed, for supplying power from the test generator to the movable engine testbed through a second power supply circuit comprising the transmission branch when the test generator is used as a power source, and for supplying power from the test generator to the energy storage assembly through a third power supply circuit comprising the transmission branch and the energy storage branch when the power generated by the test generator is greater than the load power of the movable aircraft engine testbed until the rated energy storage capacity of the energy storage assembly is reached.

2. The power supply device of claim 1, wherein, The second power supply module is further configured to supply power from the energy storage assembly to the movable engine testbed through a fourth power supply circuit comprising the energy storage branch when the energy storage assembly is used as a power source.

3. The power supply device of claim 1, wherein, The transmission branch comprises: a first current conversion device connected to the test generator, for supplying power from the test generator to the movable engine testbed through the second power supply branch when the test generator is used as a power source.

4. The power supply device of claim 1, wherein, The energy storage branch comprises: a second current conversion device connected to the energy storage assembly, for supplying power from the test generator to the energy storage assembly through the third power supply branch when the power generated by the test generator is greater than the load power.

5. The power supply device of claim 4, wherein, The second current conversion device is further configured to supply power from the energy storage assembly to the movable engine testbed through the fourth power supply circuit.

6. A power supply method for a movable aircraft engine testbed, comprising: in response to receiving a first instruction to supply power using a first power supply module, supplying power to the movable aircraft engine testbed through a first power supply circuit; in response to receiving a preparation instruction to load a test generator in a second power supply module for a test, controlling a second power supply circuit and a third power supply circuit to be turned on, wherein the second power supply module further comprises an energy storage assembly, an energy storage branch and a transmission branch, a first end of the energy storage branch being connected to the energy storage assembly, a first end of the transmission branch being connected to the test generator, a second end of the energy storage branch and a second end of the transmission branch being connected to the movable engine testbed, the second power supply circuit comprising the transmission branch, and the third power supply circuit comprising the transmission branch and the energy storage branch; in response to detecting the output voltage of the test generator, supplying power from the test generator to the movable aircraft engine testbed through the second power supply circuit; and in response to detecting that the power generated by the test generator is greater than the load power of the movable aircraft engine testbed, supplying power from the test generator to the energy storage assembly through the third power supply circuit until the rated energy storage capacity of the energy storage assembly is reached. In response to detecting that the power generation of the test generator is greater than the load power of the movable aircraft engine test stand, supplying power to the energy storage component by the third power supply circuit using the test generator until a rated energy storage capacity of the energy storage component is reached.

7. The method of claim 6, wherein, The power supply method further comprises: In response to receiving a second instruction to supply power using the energy storage component, supplying power to the movable aircraft engine test stand by the fourth power supply circuit using the energy storage component, wherein the fourth power supply circuit comprises the energy storage branch.

8. The method of claim 6, wherein, The transmission branch comprises a first variable current device connected to the test generator, and the supplying power to the movable aircraft engine test stand by the second power supply circuit using the test generator comprises: Controlling the first variable current device to supply power from the test generator to the movable aircraft engine test stand through the second power supply branch.

9. The method of claim 6, wherein, The energy storage branch comprises a second variable current device connected to the energy storage component, and the supplying power to the energy storage component by the third power supply circuit using the test generator comprises: Controlling the second variable current device to supply power from the test generator to the energy storage component through the third power supply circuit.

10. The method of claim 9, wherein, The supplying power to the movable aircraft engine test stand by the fourth power supply circuit using the energy storage component comprises: Controlling the second variable current device to supply power from the energy storage component to the movable aircraft engine test stand through the fourth power supply circuit.

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