Calibration method and system for load rod and dynamometer in high-altitude platform power conversion test

Abstract

The present invention discloses a calibration method and system for a load rod and a dynamometer in a power conversion test on a high-altitude platform. The method first determines the high-state torque value of the power conversion test according to different atmospheric conditions within the engine working envelope, and then calculates the required torque curve corresponding to different load rod positions under the atmospheric conditions based on the fitting relationship between the simulated atmospheric conditions, the helicopter's collective pitch angle and the total required torque. Then, the calibration straight line of the platform load rod position and the hydraulic dynamometer torque is determined in combination with the low-state torque value and the high-state torque value. Then, based on the calibration straight line, the torque value corresponding to the maximum load rod position is found and used as the torque value that needs to be calibrated for the dynamometer. The torque calibration value of the platform dynamometer can be quickly obtained according to different atmospheric conditions of the engine. The load rod angle of the high-altitude platform more realistically simulates the position of the collective pitch rod when the engine is working on the helicopter, and can realistically simulate the power conversion of the aviation turboshaft engine on the helicopter.

Description

Technical Field

[0001] The present invention relates to the technical field of high-altitude platform power conversion testing of aviation turboshaft engines, and in particular to a calibration method and system for a load rod and a dynamometer in a high-altitude platform power conversion test, electronic equipment, and a computer-readable storage medium. Background Art

[0002] Aviation turboshaft engines generally use constant power turbine speed control to maintain the helicopter's rotor speed at a fixed speed, that is, the reference value, which can effectively improve the aerodynamic efficiency of the engine power turbine and helicopter rotor, and prevent the helicopter and engine's rotational system from operating near the critical speed. Based on the constant power turbine speed control, the engine control system will make advance compensation for the engine's fuel supply according to the signal of the collective pitch lever, that is, perform collective pitch compensation, to adapt to the load changes caused by the change in rotor collective pitch. Figure 1 As shown in the figure, during the rapid upward or downward movement of the collective pitch lever, the helicopter rotor collective torque changes very rapidly, causing changes in the power turbine speed Np. The engine control system determines the target acceleration rate Ngdot0 of the gas generator rotor based on the difference between Np and the reference value Np0 and the collective pitch compensation requirement. The difference between Ngdot0 and the actual acceleration rate Ngdot is then used to determine the change in fuel flow rate ΔWf, adjusting parameters such as the gas generator speed Ng to prevent the power turbine and rotor speeds from exceeding acceptable ranges. When the turboshaft engine undergoes power conversion (pushing or pulling the load lever upward or downward within 1 second), the load lever angle CLP changes rapidly. To ensure that Np overshoot or droop meets control requirements, the CNC system performs feedforward control based on the load lever position change, preemptively changing the Ngdot reference and adjusting the fuel flow rate, thereby reducing engine speed overshoot and transition time. Therefore, during power conversion testing, simulating the corresponding load lever position while simulating the engine's high-state power is crucial to emulating real-world installation conditions.

[0003] During engine vehicle testing, a hydraulic dynamometer is typically connected to the power turbine shaft. By adjusting the load on the hydraulic dynamometer, the total power required by the flight platform is simulated. However, when conducting power conversion tests on complete turboshaft engines, no literature has yet published on how to adjust the hydraulic dynamometer in response to atmospheric conditions. Testers primarily focus on whether the engine power can reach the target value, rather than the load rod position corresponding to that power. For example, before conducting vehicle testing, the dynamometer torque corresponding to the maximum load rod position (90°) is calibrated based on work experience to ensure that the engine can be pushed to its maximum state. Generally, the torque calibration is not frequently changed. During the power conversion test, the dynamometer torque calibration is only appropriately modified when the overshoot or droop of Np fails to meet control requirements.

[0004] Years of test experience have shown that the aforementioned test method is generally feasible for ground-based vehicle testing, but it presents significant limitations when conducting power conversion tests on high-altitude platforms. This is because, during ground-based vehicle testing, the vehicle's intake pressure does not fluctuate significantly throughout the year, and the temperature typically fluctuates between 30°C and 40°C, with a typical minimum temperature of 0°C and a maximum temperature of 40°C. However, during high-altitude simulation testing, the engine's power conversion test must be conducted across the entire operating envelope, resulting in a greater fluctuation in intake temperature than on a ground-based vehicle. Furthermore, intake pressure also changes with increasing altitude, and atmospheric density fluctuates significantly more than on a ground-based vehicle. This influence of atmospheric density results in significant differences in the total power required by the flight platform at the same collective pitch angle. For example, at the same atmospheric temperature, the atmospheric density at 6 km altitude is approximately 47.2% of that at sea level; while the atmospheric density at sea level, at a maximum temperature of 50°C, is approximately 72.1% of that at a minimum temperature of -40°C. If the calibration relationship between the load rod and the dynamometer torque during the ground vehicle test is still used, when the engine is in a large state, the position of the load rod in the high-altitude vehicle test will be significantly different from the position of the collective pitch rod on the helicopter, and it will be impossible to truly simulate the power conversion of the aviation turboshaft engine on the helicopter. Summary of the Invention

[0005] The present invention provides a calibration method and system for a load rod and a dynamometer in a high-altitude platform power conversion test, an electronic device, and a computer-readable storage medium, which can quickly obtain the torque calibration value of the vehicle platform dynamometer according to different atmospheric conditions. In addition, the load rod angle of the high-altitude platform more realistically simulates the position of the collective pitch rod when the engine is working on a helicopter, so that the high-altitude platform power conversion test can realistically simulate the power conversion of an aviation turboshaft engine on a helicopter.

[0006] According to one aspect of the present invention, a method for calibrating a load rod and a dynamometer in a power conversion test on an aerial platform is provided, comprising the following steps:

[0007] Determine the high state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope;

[0008] Based on the atmospheric conditions during the power conversion test and the fitting relationship between the helicopter's collective pitch angle and the total required torque, the required torque curves corresponding to different load rod positions under the atmospheric conditions are calculated;

[0009] Obtain the low-state torque value of the power conversion test, and determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque based on the low-state torque value, high-state torque value and the required torque curve corresponding to different load rod positions;

[0010] The torque value corresponding to the maximum load rod position is determined on the calibration line between the platform load rod position and the hydraulic dynamometer torque, and the torque value is used as the torque value required for calibration of the hydraulic dynamometer.

[0011] Furthermore, the power conversion test is determined according to different atmospheric conditions within the engine operating envelope. The process of obtaining a high state torque value includes the following:

[0012] Limit values ​​for performance parameters are preset in the performance calculation model of an aviation turboshaft engine, and then different atmospheric conditions within the turboshaft engine's operating envelope are input into the performance calculation model for iterative calculation. When a certain performance parameter reaches the preset limit value, the engine state is determined to have reached a high state, and the torque value at this time is output as the high-state torque value.

[0013] Further, the performance parameters include gas generator rotor speed, gas turbine after-temperature and torque.

[0014] Furthermore, the required torque curve corresponding to different load rod positions under atmospheric conditions during the power conversion test is calculated based on the following formula:

[0015]

[0016] φ=-3.25+CLP×19

[0017] Where θ represents the total required torque of the helicopter, Δ represents the atmospheric density ratio, φ represents the collective pitch angle, CLP represents the load bar angle, Pa represents the atmospheric pressure during the power conversion test, which is converted from the operating altitude during the power conversion test, OAT represents the atmospheric temperature during the power conversion test, and A, B, C, and D are all constants.

[0018] Furthermore, the process of determining the calibration line of the vehicle platform load rod position and the hydraulic dynamometer torque based on the low state torque value, the high state torque value and the required torque curve corresponding to different load rod positions includes the following:

[0019] Determine the point corresponding to the high-state torque value on the required torque curve corresponding to different load rod positions, connect the point corresponding to the high-state torque value with the point corresponding to the low-state torque value, and use the straight line formed by the two points as the calibration line for the platform load rod position and the hydraulic dynamometer torque.

[0020] In addition, the present invention also provides a calibration system for a load rod and a dynamometer in a high-altitude platform power conversion test, comprising:

[0021] A high-state torque value determination module, used to determine the high-state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope;

[0022] The required torque calculation module is used to calculate the required torque curve corresponding to different load rod positions under the atmospheric conditions during the power conversion test and the fitting relationship between the helicopter's collective pitch angle and the total required torque;

[0023] The calibration line determination module is used to obtain the low-state torque value of the power conversion test and determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque based on the low-state torque value, high-state torque value and the required torque curve corresponding to different load rod positions;

[0024] The torque value calibration module is used to determine the torque value corresponding to the maximum load rod position on the calibration line of the vehicle platform load rod position and the hydraulic dynamometer torque, and use the torque value as the torque value required for calibration of the hydraulic dynamometer.

[0025] Furthermore, the required torque calculation module calculates required torque curves corresponding to different load rod positions under atmospheric conditions during the power conversion test based on the following formula:

[0026]

[0027] φ=-3.25+CLP×19

[0028] Where θ represents the total required torque of the helicopter, Δ represents the atmospheric density ratio, φ represents the collective pitch angle, CLP represents the load bar angle, Pa represents the atmospheric pressure during the power conversion test, which is converted from the operating altitude during the power conversion test, OAT represents the atmospheric temperature during the power conversion test, and A, B, C, and D are all constants.

[0029] Furthermore, the calibration line determination module determines the point corresponding to the high-state torque value on the required torque curve corresponding to different load rod positions, connects the point corresponding to the high-state torque value with the point corresponding to the low-state torque value, and uses the straight line formed by the two points as the calibration line of the vehicle platform load rod position and the hydraulic dynamometer torque.

[0030] In addition, the present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor is configured to execute the steps of the above method by calling the computer program stored in the memory.

[0031] In addition, the present invention also provides a computer-readable storage medium for storing a computer program for calibrating a load rod and a dynamometer in a high-altitude platform power conversion test, wherein the computer program executes the steps of the method described above when running on a computer.

[0032] The present invention has the following beneficial effects:

[0033] The present invention provides a method for calibrating a load rod and a dynamometer in a power conversion test on an altitude platform. The method first determines the high-state torque value of the power conversion test based on different atmospheric conditions within the engine operating envelope. Then, based on the atmospheric conditions during the test and the fitting relationship between the helicopter's collective pitch angle and the total required torque, the required torque curve corresponding to different load rod positions under the atmospheric conditions is calculated. Since the fitting relationship between the helicopter's collective pitch angle and the total required torque is obtained based on the helicopter's field test flight data, and the helicopter's lowest torque during actual flight is not the torque corresponding to 0° of the load rod, but is generally the torque corresponding to about 14°, but during the altitude platform test, the minimum torque should be the torque corresponding to 0° of the load rod. Therefore, the required torque curve corresponding to different load rod positions obtained at this time cannot be directly used for torque calibration of the hydraulic dynamometer. Therefore, after determining the low-state torque value based on the helicopter field test data, the high-state torque value and the required torque curve corresponding to different load rod positions are combined to determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque. Finally, based on the calibration line, the torque value corresponding to the maximum load rod position is found and used as the torque value that needs to be calibrated for the dynamometer. In this way, the torque calibration value of the vehicle dynamometer can be quickly obtained according to different atmospheric conditions of the engine. In addition, the load rod angle of the high-altitude platform more realistically simulates the position of the collective pitch rod when the engine is working on the helicopter, so that the power conversion test of the high-altitude platform can realistically simulate the power conversion of the aviation turboshaft engine on the helicopter.

[0034] In addition, the calibration system of the load rod and the dynamometer in the high-altitude platform power conversion test of the present invention also has the above advantages.

[0035] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0037] Figure 1 This is a schematic diagram of the control principle of a typical aviation turboshaft engine.

[0038] Figure 2 It is a flow chart of a calibration method of a load rod and a dynamometer in a high-altitude platform power conversion test according to a preferred embodiment of the present application.

[0039] Figure 3 It is a schematic diagram of the principle of determining the calibration straight line for the vehicle platform load rod position and the hydraulic dynamometer torque in the preferred embodiment of the present application.

[0040] Figure 4 It is a schematic diagram of the module structure of a calibration system for a load rod and a dynamometer in a high-altitude platform power conversion test according to another embodiment of the present application. DETAILED DESCRIPTION

[0041] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0042] Reference Figure 2 The preferred embodiment of the present application provides a calibration method for a load rod and a dynamometer in a high-altitude platform power conversion test, comprising the following:

[0043] Step S1: determining a high-state torque value of a power conversion test according to different atmospheric conditions within the engine operating envelope;

[0044] Step S2: Calculating required torque curves corresponding to different load bar positions under the atmospheric conditions during the power conversion test based on the fitted relationship between the helicopter's collective pitch angle and the required total torque;

[0045] Step S3: Obtain the low-state torque value of the power conversion test, and determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque based on the low-state torque value, the high-state torque value, and the required torque curve corresponding to different load rod positions;

[0046] Step S4: determining the torque value corresponding to the maximum load rod position on the calibration line between the platform load rod position and the hydraulic dynamometer torque, and using the torque value as the torque value required for calibration of the hydraulic dynamometer.

[0047] It can be understood that the calibration method of the load rod and dynamometer in the high-altitude platform power conversion test in this embodiment first determines the high-state torque value of the power conversion test based on different atmospheric conditions within the engine operating envelope, and then calculates the required torque curve corresponding to different load rod positions under the atmospheric conditions based on the atmospheric conditions during the test and the fitting relationship between the helicopter's collective pitch angle and the total required torque. Since the fitting relationship between the helicopter's collective pitch angle and the total required torque is obtained based on the helicopter's field test flight data, and the helicopter's minimum torque during actual flight is not the torque corresponding to 0° of the load rod, but generally the torque corresponding to about 14°, but in the high-altitude platform test, the minimum torque should be the torque corresponding to 0° of the load rod. Therefore, the required torque curve corresponding to different load rod positions obtained at this time cannot be directly used for the torque calibration of the hydraulic dynamometer. Therefore, after determining the low-state torque value based on the helicopter field test data, the high-state torque value and the required torque curve corresponding to different load rod positions are combined to determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque. Finally, based on the calibration line, the torque value corresponding to the maximum load rod position is found and used as the torque value that needs to be calibrated for the dynamometer. In this way, the torque calibration value of the vehicle dynamometer can be quickly obtained according to different atmospheric conditions of the engine. In addition, the load rod angle of the high-altitude platform more realistically simulates the position of the collective pitch rod when the engine is working on the helicopter, so that the power conversion test of the high-altitude platform can realistically simulate the power conversion of the aviation turboshaft engine on the helicopter.

[0048] It can be understood that in step S1, the process of determining the high-state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope includes the following:

[0049] Limit values ​​for performance parameters are preset in the performance calculation model of an aviation turboshaft engine, and then different atmospheric conditions within the turboshaft engine's operating envelope are input into the performance calculation model for iterative calculation. When a certain performance parameter reaches the preset limit value, the engine state is determined to have reached a high state, and the torque value at this time is output as the high-state torque value.

[0050] Specifically, a performance calculation model for an aircraft turboshaft engine is first established using aircraft engine performance calculation software such as GASTURB. This performance calculation model can calculate the corresponding overall thermodynamic performance of the aircraft engine after the user specifies reasonable input parameters. The process of establishing the aircraft turboshaft engine performance calculation model is prior art and will not be described in detail here. After presetting engine performance parameter limits in the aircraft turboshaft engine performance calculation model, different atmospheric conditions within the turboshaft engine's operating envelope are input into the performance calculation model for iterative calculation. When a performance parameter reaches the preset limit, the engine state is determined to have reached a high state, and the torque value at that time is output as the high-state torque value. The engine performance parameters include the gas generator rotor speed Ng, the gas turbine after-temperature (i.e., the gas turbine outlet temperature) T45, and the torque MKP. The atmospheric conditions within the turboshaft engine's operating envelope vary greatly. At sea level, a typical engine's operating temperature ranges from -40°C to 50°C, and the operating altitude ranges from sea level to 6 kilometers. Within this operating envelope, each engine performance parameter may reach its limit value first. Generally speaking, at low altitude and low temperature, the torque will reach its limit value first. Therefore, after inputting simulated atmospheric conditions (including operating temperature and operating altitude) and performance parameter limits corresponding to the high state into the performance calculation model, the engine is determined to have reached the high state when any of the gas generator rotor speed Ng, gas turbine outlet temperature T45, or torque MKP reaches the limit value, and the torque value calculated at this time is used as the high state torque value. For example, at a given operating altitude, operating temperature, and speed, the performance calculation model, based on the power and flow balance requirements for coaxial operation of the compressor and gas turbine, combines the parameters of the stator flow path components and locks the operating values ​​of the respective components in the characteristic data of the compressor and gas turbine. This can determine the cross-sectional parameters from the compressor to the gas turbine, including the gas turbine outlet temperature. Using the gas turbine outlet cross-sectional parameters and the power turbine characteristic data, the power turbine power and corresponding torque value are calculated. At the speed limit, if the calculated gas turbine outlet temperature or torque exceeds the given limit value, the performance calculation model iteratively reduces the speed until the gas turbine outlet temperature or torque does not exceed the limit value, and then outputs the torque value at this time as the high state torque value.

[0051] It can be understood that the present invention is based on an aviation turboshaft engine performance calculation model. After presetting the performance parameter limit values ​​of the engine in high state, the high-state torque value during the power conversion test can be accurately calculated according to different atmospheric conditions within the engine operating envelope.

[0052] It can be understood that in step S2, the model is determined according to the actual needs of the high-altitude platform power conversion test.The atmospheric conditions are simulated, and the relationship between the helicopter's collective pitch angle and the helicopter's total required torque is fitted based on the helicopter's field test data. This allows the required torque value corresponding to each load rod position under the simulated atmospheric conditions to be calculated, and further allows the required torque curve corresponding to different load rod positions under the atmospheric conditions to be obtained. Specifically, the required torque curve corresponding to different load rod positions under the atmospheric conditions during the power conversion test is calculated based on the following formula:

[0053]

[0054] φ=-3.25+CLP×19

[0055] Where θ represents the total required torque of the helicopter, Δ represents the atmospheric density ratio, φ represents the collective pitch angle, CLP represents the load bar angle, Pa represents the atmospheric pressure during the power conversion test, which is converted from the operating altitude during the power conversion test, OAT represents the atmospheric temperature during the power conversion test, and A, B, C, and D are all constants.

[0056] It can be understood that in the step S3, the low-state torque value is first determined based on the helicopter field test data, wherein the low state refers to the idle slow state of the engine. The process of determining the low-state torque value belongs to the prior art and will not be repeated here. Then, based on the low-state torque value, the high-state torque value and the required torque curve corresponding to different load rod positions, the calibration straight line of the vehicle load rod position and the hydraulic dynamometer torque is determined. The specific process is: determine the point corresponding to the high-state torque value on the required torque curve corresponding to different load rod positions, connect the point corresponding to the high-state torque value with the point corresponding to the low-state torque value, and use the straight line formed by the two points as the calibration straight line of the vehicle load rod position and the hydraulic dynamometer torque. Specifically, as Figure 3 As shown, first determine the low state torque point, that is, the point where the load rod angle is 0° and the torque value is the low state torque value, that is Figure 3 The first star point from left to right in the figure, and then find the corresponding point on the required torque curve corresponding to different load rod positions according to the high state torque value, that is, find the high state torque point, that is Figure 3The second star point from the left to right in the figure, then connecting the low-state torque point and the high-state torque point and extending them, forms a straight line that represents the calibration line between the vehicle test bench load rod position and the hydraulic dynamometer torque. It can be seen that during actual flight, the helicopter's lowest torque is not the torque corresponding to a load rod angle of 0°, but generally around 14°. Therefore, on the required torque curve corresponding to different load rod positions, fitted based on field test data, the load rod angle at the minimum torque point is not zero. However, during high-altitude test bench testing, the load rod angle corresponding to the minimum torque point should be 0°. During high-altitude test bench testing, the helicopter load is simulated using a hydraulic dynamometer load. The load rod position and the hydraulic dynamometer load are linearly related. The load rod angle varies between 0° and 90°, corresponding to a 0V to 10V output voltage to the hydraulic dynamometer. The hydraulic dynamometer automatically adjusts the water inlet and outlet valve positions based on the input voltage to determine the load on the hydraulic dynamometer. The load is linearly related to the input voltage. When the load rod angle is 0°, the hydraulic dynamometer simulates the minimum load, that is, the load in the idle and slow state. This load can be adjusted within a certain range by adjusting the water inlet and outlet valves of the hydraulic dynamometer. When the load rod angle is 90°, the hydraulic dynamometer simulates the maximum load. The maximum load is not fixed within the capacity of the hydraulic dynamometer and can be set according to the test requirements before the test. In addition, Figure 3 The horizontal axis represents the load rod angle, and the vertical axis represents the torque value, which is not reflected in the figure and is expressed in words here.

[0057] It can be understood that although the calibration straight line of the vehicle platform load rod position and the hydraulic dynamometer torque obtained by the present invention does not completely coincide with the required torque curve corresponding to different load rod positions of the helicopter, in the high state, the load rod position and hydraulic dynamometer torque value simulated by the high-altitude test bench are consistent with the load rod position and torque value of the helicopter. In the low state, under the same torque value conditions, the load rod angle of the high-altitude platform test is smaller than that of the helicopter. In this way, when conducting a power conversion test, the change amplitude of the load rod of the high-altitude platform is larger than that of the load rod of the helicopter, and the assessment of the power conversion test is more stringent, which ensures the smooth progress of the power conversion test.

[0058] It can be understood that in step S4, the torque value corresponding to the maximum load rod position (i.e. 90°) is found on the calibration line of the vehicle load rod position and the hydraulic dynamometer torque, and the torque value that needs to be calibrated for the vehicle hydraulic dynamometer under the current simulated atmospheric conditions can be obtained.

[0059] It can be understood that when it is necessary to obtain the calibrated torque value of the vehicle hydraulic dynamometer under other atmospheric conditions, it is only necessary to change the atmospheric conditions, so that the load rod position and the vehicle hydraulic dynamometer load can be calibrated within the entire engine working envelope, so that the high-altitude platform power conversion test can truly simulate the power conversion of the aviation turboshaft engine on the helicopter.

[0060] In addition, if Figure 4 As shown, another embodiment of the present invention further provides a calibration system for a load bar and a dynamometer in a high-altitude platform power conversion test, preferably using the calibration method described above, the calibration system comprising:

[0061] A high-state torque value determination module, used to determine the high-state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope;

[0062] The required torque calculation module is used to calculate the required torque curve corresponding to different load rod positions under the atmospheric conditions during the power conversion test and the fitting relationship between the helicopter's collective pitch angle and the total required torque;

[0063] The calibration line determination module is used to obtain the low-state torque value of the power conversion test and determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque based on the low-state torque value, high-state torque value and the required torque curve corresponding to different load rod positions;

[0064] The torque value calibration module is used to determine the torque value corresponding to the maximum load rod position on the calibration line of the vehicle platform load rod position and the hydraulic dynamometer torque, and use the torque value as the torque value required for calibration of the hydraulic dynamometer.

[0065] It can be understood that the calibration system of the load rod and dynamometer in the high-altitude platform power conversion test of this embodiment first determines the high-state torque value of the power conversion test based on different atmospheric conditions within the engine operating envelope, and then calculates the required torque curve corresponding to different load rod positions under the atmospheric conditions based on the atmospheric conditions during the test and the fitting relationship between the helicopter's collective pitch angle and the total required torque. Since the fitting relationship between the helicopter's collective pitch angle and the total required torque is obtained based on the helicopter's field test flight data, and the helicopter's minimum torque during actual flight is not the torque corresponding to 0° of the load rod, but generally the torque corresponding to about 14°, but in the high-altitude platform test, the minimum torque should be the torque corresponding to 0° of the load rod. Therefore, the required torque curve corresponding to different load rod positions obtained at this time cannot be directly used for the torque calibration of the hydraulic dynamometer. Therefore, after determining the low-state torque value based on the helicopter field test data, the high-state torque value and the required torque curve corresponding to different load rod positions are combined to determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque. Finally, based on the calibration line, the torque value corresponding to the maximum load rod position is found and used as the torque value that needs to be calibrated for the dynamometer. In this way, the torque calibration value of the vehicle dynamometer can be quickly obtained according to different atmospheric conditions of the engine. In addition, the load rod angle of the high-altitude platform more realistically simulates the position of the collective pitch rod when the engine is working on the helicopter, so that the power conversion test of the high-altitude platform can realistically simulate the power conversion of the aviation turboshaft engine on the helicopter.

[0066] The required torque calculation module calculates the required torque curve corresponding to different load rod positions under atmospheric conditions during the power conversion test based on the following formula:

[0067]

[0068] φ=-3.25+CLP×19

[0069] Where θ represents the total required torque of the helicopter, Δ represents the atmospheric density ratio, φ represents the collective pitch angle, CLP represents the load bar angle, Pa represents the atmospheric pressure during the power conversion test, which is converted from the operating altitude during the power conversion test, OAT represents the atmospheric temperature during the power conversion test, and A, B, C, and D are all constants.

[0070] Among them, the calibration line determination module determines the point corresponding to the high state torque value on the required torque curve corresponding to different load rod positions, connects the point corresponding to the high state torque value with the point corresponding to the low state torque value, and uses the straight line formed by the two points as the calibration line of the vehicle platform load rod position and the hydraulic dynamometer torque.

[0071] In addition, another embodiment of the present invention further provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor is configured to execute the steps of the above method by calling the computer program stored in the memory.

[0072] In addition, another embodiment of the present invention also provides a computer-readable storage medium for storing a computer program for calibrating a load rod and a dynamometer in a high-altitude platform power conversion test, wherein the computer program executes the steps of the method described above when running on a computer.

[0073] Common computer-readable storage media include: floppy disks, flexible disks, hard disks, magnetic tape, any other magnetic media, CD-ROMs, any other optical media, punch cards, paper tape, any other physical medium with a pattern of holes, random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), flash-erasable programmable read-only memory (FLASH-EPROM), any other memory chip or cartridge, or any other medium that can be read by a computer. Instructions can further be transmitted or received via a transmission medium. The term transmission medium may include any tangible or intangible medium that can be used to store, encode, or carry instructions for execution by a machine, and includes digital or analog communication signals or other intangible media that facilitate communication of such instructions. Transmission media include coaxial cables, copper wire, and fiber optics, including the wires of a bus used to transmit a computer data signal.

[0074] Those skilled in the art will appreciate that the embodiments of the present application can be provided as methods, systems, or computer program products. Therefore, the application can adopt the form of a complete hardware embodiment, a complete software embodiment, or an embodiment in combination with software and hardware. Moreover, the application can adopt the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) that contain computer-usable program code. The scheme in the embodiment of the present application can be implemented in various computer languages, for example, object-oriented programming language Java and literal translation scripting language JavaScript, etc.

[0075] The present application is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the steps in the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0076] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0077] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0078] Although the preferred embodiments of the present application have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present application.

[0079] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

[0080] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A calibration method for a load bar and a dynamometer in a high-altitude platform power conversion test, characterized in that: Includes the following: Determine the high state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope; Based on the atmospheric conditions during the power conversion test and the fitting relationship between the helicopter's collective pitch angle and the total required torque, the required torque curves corresponding to different load rod positions under the atmospheric conditions are calculated; Obtain the low-state torque value of the power conversion test, and determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque based on the low-state torque value, high-state torque value and the required torque curve corresponding to different load rod positions; The torque value corresponding to the maximum load rod position is determined on the calibration line between the platform load rod position and the hydraulic dynamometer torque, and the torque value is used as the torque value required for calibration of the hydraulic dynamometer.

2. The calibration method for the load rod and dynamometer in the high-altitude platform power conversion test according to claim 1, characterized in that: The process of determining the high-state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope includes the following: Limit values ​​for performance parameters are preset in the performance calculation model of an aviation turboshaft engine, and then different atmospheric conditions within the turboshaft engine's operating envelope are input into the performance calculation model for iterative calculation. When a certain performance parameter reaches the preset limit value, the engine state is determined to have reached a high state, and the torque value at this time is output as the high-state torque value.

3. The calibration method for the load rod and dynamometer in the high-altitude platform power conversion test according to claim 2, characterized in that: Performance parameters include gas generator rotor speed, gas turbine after-temperature, and torque.

4. The calibration method for the load rod and dynamometer in the high-altitude platform power conversion test according to claim 1, characterized in that: The required torque curve corresponding to different load rod positions under atmospheric conditions during the power conversion test is calculated based on the following formula: φ=-3.25+CLP×19 Where θ represents the total required torque of the helicopter, Δ represents the atmospheric density ratio, φ represents the collective pitch angle, CLP represents the load bar angle, Pa represents the atmospheric pressure during the power conversion test, which is converted from the operating altitude during the power conversion test, OAT represents the atmospheric temperature during the power conversion test, and A, B, C, and D are all constants.

5. The calibration method of the load rod and dynamometer in the high-altitude platform power conversion test according to claim 1, characterized in that: The process of determining the calibration line of the platform load rod position and the hydraulic dynamometer torque based on the low state torque value, the high state torque value and the required torque curve corresponding to different load rod positions includes the following: Determine the point corresponding to the high-state torque value on the required torque curve corresponding to different load rod positions, connect the point corresponding to the high-state torque value with the point corresponding to the low-state torque value, and use the straight line formed by the two points as the calibration line for the platform load rod position and the hydraulic dynamometer torque.

6. A calibration system for a load bar and a dynamometer in a high-altitude platform power conversion test, characterized in that: include: A high-state torque value determination module, used to determine the high-state torque value of the power conversion test according to different atmospheric conditions within the engine operating envelope; The required torque calculation module is used to calculate the required torque curve corresponding to different load rod positions under the atmospheric conditions during the power conversion test and the fitting relationship between the helicopter's collective pitch angle and the total required torque; The calibration line determination module is used to obtain the low-state torque value of the power conversion test and determine the calibration line of the vehicle load rod position and the hydraulic dynamometer torque based on the low-state torque value, high-state torque value and the required torque curve corresponding to different load rod positions; The torque value calibration module is used to determine the torque value corresponding to the maximum load rod position on the calibration line of the vehicle platform load rod position and the hydraulic dynamometer torque, and use the torque value as the torque value required for calibration of the hydraulic dynamometer.

7. The calibration system for the load rod and dynamometer in the high-altitude platform power conversion test according to claim 6, characterized in that: The required torque calculation module calculates the required torque curve corresponding to different load rod positions under atmospheric conditions during the power conversion test based on the following formula: φ=-3.25+CLP×19 Where θ represents the total required torque of the helicopter, Δ represents the atmospheric density ratio, φ represents the collective pitch angle, CLP represents the load bar angle, Pa represents the atmospheric pressure during the power conversion test, which is converted from the operating altitude during the power conversion test, OAT represents the atmospheric temperature during the power conversion test, and A, B, C, and D are all constants.

8. The calibration system for the load rod and dynamometer in the high-altitude platform power conversion test according to claim 6, characterized in that: The calibration straight line determination module determines the point corresponding to the high-state torque value on the required torque curve corresponding to different load rod positions, connects the point corresponding to the high-state torque value with the point corresponding to the low-state torque value, and uses the straight line formed by the two points as the calibration straight line for the platform load rod position and the hydraulic dynamometer torque.

9. An electronic device, characterized in that: The method comprises a processor and a memory, wherein a computer program is stored in the memory, and the processor is configured to execute the steps of the method according to any one of claims 1 to 5 by calling the computer program stored in the memory.

10. A computer-readable storage medium for storing a computer program for calibrating a load bar and a dynamometer in a high-altitude platform power conversion test, characterized in that: When the computer program is run on a computer, the steps of the method according to any one of claims 1 to 5 are executed.

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