Ground test method and device for high-altitude airship propulsion motor

Abstract

The application provides a high-altitude airship propulsion motor ground test method and device, comprising: obtaining operation condition parameter information of a high-altitude airship propulsion motor group to be tested; calculating a motor shaft end load spectrum and a test environment spectrum based on the operation condition parameter information; adjusting the environmental conditions of an environmental test chamber and the load conditions of each component in the high-altitude airship propulsion motor ground test device according to the test environment spectrum and the motor shaft end load spectrum, so as to perform a load operation test on the high-altitude airship propulsion motor group to be tested, and obtain a test result of the high-altitude airship propulsion motor group to be tested. According to the motor shaft end load spectrum and the test environment spectrum, the environmental conditions of the environmental test chamber and the load conditions of the ground test device are adjusted, so that the load conditions of the propulsion motor shaft end and the environment of the propulsion motor in the process of propelling the airship to hover are simulated in the ground simulation environment, and whether the propulsion motor can meet the flight condition requirements can be effectively tested.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, and in particular to a high-altitude airship propulsion motor ground test method and device. BACKGROUND

[0002] The propulsion motor of the high-altitude airship is mainly used to drive the propeller to rotate to generate thrust or pull to propel the high-altitude airship forward and turn. The main working environment of the propulsion motor is high-altitude low-temperature low-pressure environment. The load of the propulsion motor is the propeller, and the mechanical properties of the propeller are quite different from those of the conventional load, for example: the axial force generated by the propeller is proportional to the square of the rotational speed, and the torque required for the rotation of the propeller is proportional to the square of the rotational speed. In addition, since the diameter of the high-altitude propeller is large, the moment of inertia of the propeller is generally also large.

[0003] When the propulsion motor is actually applied to the high-altitude airship, two or more propulsion motors are usually installed on a propulsion support to jointly drive the propeller to generate a force to push the high-altitude airship forward, wherein a part of the propulsion motors (tension motors) are installed at the front of the propulsion support (upwind direction) to drive the propeller to generate a pull force, and a part of the propulsion motors (thrust motors) are installed at the rear of the propulsion support (upwind direction) to drive the propeller to generate a thrust. The directions of the pull force and the thrust are both along the direction of the forward movement of the high-altitude airship.

[0004] However, the current test method for the high-altitude airship propulsion motor rarely simulates the load conditions borne by the shaft end of the propulsion motor, so that whether the propulsion motor can meet the flight working condition requirements cannot be verified. SUMMARY

[0005] The present application provides a high-altitude airship propulsion motor ground test method and device, which aims to solve the problem that the current test method for the high-altitude airship propulsion motor cannot simulate the load conditions borne by the shaft end of the propulsion motor, so that whether the propulsion motor can meet the flight working condition requirements cannot be verified.

[0006] The present application provides a high-altitude airship propulsion motor ground test method, comprising:

[0007] Obtaining the operation condition parameter information of the high-altitude airship propulsion motor group to be tested;

[0008] Based on the operation condition parameter information, the motor shaft end load spectrum is calculated, and the test environment spectrum of the environmental test chamber is determined;

[0009] According to the test environment spectrum and the motor shaft end load spectrum, the environmental conditions of the environmental test chamber and the load conditions of each component in the high-altitude airship propulsion motor ground test device are adjusted to perform load operation test on the high-altitude airship propulsion motor group to be tested, and the test results of the high-altitude airship propulsion motor group to be tested are obtained.

[0010] The high-altitude airship propulsion motor group to be tested is installed in the high-altitude airship propulsion motor ground test device, and the high-altitude airship propulsion motor ground test device is placed in the environmental test chamber.

[0011] According to the high-altitude airship propulsion motor ground test method provided by the application, the test environment spectrum includes environmental temperature, atmospheric pressure, irradiance and airflow speed under different working condition time;

[0012] The motor shaft end load spectrum includes the rotating speed of the high-altitude airship propulsion motor group to be tested and the axial force, radial force, bending moment and torque borne by the shaft end of the high-altitude airship propulsion motor group to be tested under different working condition time.

[0013] According to the high-altitude airship propulsion motor ground test method provided by the application, the operating condition parameter information includes reference rotating speed, rated rotating speed of the high-altitude airship propulsion motor group to be tested and rotating speed instruction sending frequency under different working condition time;

[0014] The motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device is calculated based on the operating condition parameter information, and the method comprises the steps of:

[0015] Based on the rated rotating speed of the high-altitude airship propulsion motor group to be tested and the rotating speed instruction sending frequency, the adjustment amplitude and adjustment frequency of the high-altitude airship propulsion motor group to be tested are determined.

[0016] Based on the reference rotating speed under different working condition time, the adjustment amplitude and the adjustment frequency, the rotating speed of the high-altitude airship propulsion motor group to be tested under different working condition time is calculated.

[0017] According to the high-altitude airship propulsion motor ground test method provided by the application,

[0018] The operating condition parameter information further includes the tension coefficient of the propeller, working atmospheric density, diameter, weight, gravitational acceleration, axial acceleration and radial acceleration corresponding to different rated rotating speeds;

[0019] The motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device is calculated based on the operating condition parameter information, and the method comprises the steps of:

[0020] Based on the reference rotating speed under different working condition time, the tension coefficient, the working atmospheric density, the diameter, the weight, the axial acceleration and a preset safety coefficient, the axial force borne by the shaft end of the high-altitude airship propulsion motor group to be tested under different working condition time is calculated.

[0021] The radial force borne by the shaft end of the to-be-tested high-altitude airship propulsion motor set under different working condition times is calculated based on the reference rotating speed under the different working condition times, the gravity acceleration, the weight, the radial acceleration and the preset safety coefficient.

[0022] According to the high-altitude airship propulsion motor ground test method provided by the application, the operation condition parameter information further comprises a bending moment coefficient and a torque coefficient.

[0023] The motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device is calculated based on the operation condition parameter information, comprising:

[0024] The bending moment borne by the shaft end of the to-be-tested high-altitude airship propulsion motor set under different working condition times is calculated based on the rotating speed under the different working condition times, the diameter, the tension coefficient, the working atmospheric density, the bending moment coefficient and the preset safety coefficient.

[0025] The torque borne by the shaft end of the to-be-tested high-altitude airship propulsion motor set under different working condition times is calculated based on the rotating speed under the different working condition times, the working atmospheric density, the diameter, the torque coefficient and the preset safety coefficient.

[0026] According to the high-altitude airship propulsion motor ground test method provided by the application, the to-be-tested high-altitude airship propulsion motor set comprises a first to-be-tested motor and a second to-be-tested motor.

[0027] The environmental condition of the environmental test chamber and the load condition of each component in the high-altitude airship propulsion motor ground test device are adjusted according to the test environment spectrum and the motor shaft end load spectrum, comprising:

[0028] For any working condition time, the environmental condition of the environmental test chamber is adjusted to the environmental temperature, atmospheric pressure and irradiance corresponding to the working condition time according to the working condition time;

[0029] The airflow flow rate blown by a fan in the high-altitude airship propulsion motor ground test device onto the first to-be-tested motor is adjusted based on the airflow speed under the working condition time;

[0030] The axial suction force and the bending moment generated by an axial electromagnet in the high-altitude airship propulsion motor ground test device are adjusted based on the axial force and the bending moment under the working condition time;

[0031] The radial suction force generated by a radial electromagnet in the high-altitude airship propulsion motor ground test device is adjusted based on the radial force under the working condition time;

[0032] Based on the torque under the aforementioned operating conditions, the torque current generated by the second motor under test in the ground test device for the high-altitude airship propulsion motor is adjusted.

[0033] The present invention also provides a ground test device for a high-altitude airship propulsion motor, comprising:

[0034] The propulsion motor unit of the high-altitude airship under test is connected to the momentum disk via its output shaft.

[0035] An axial electromagnet is mounted on an axial electromagnet mounting bracket and is horizontally aligned with the momentum disk to generate axial attraction and bending moment.

[0036] A fan, mounted on the axial electromagnet mounting bracket, is used to generate airflow velocity;

[0037] A radial electromagnet, with its longitudinal plane facing the momentum disk, is used to generate radial attraction.

[0038] An eccentric counterweight is mounted on the momentum disk to generate static imbalance.

[0039] According to the present invention, a ground test device for a high-altitude airship propulsion motor is provided, wherein the axial electromagnet includes a first axial electromagnet and a second axial electromagnet, wherein:

[0040] The resultant force of the axial forces generated by the first axial electromagnet and the second axial electromagnet is the same as the axial attraction force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test.

[0041] The bending moment generated by the first axial electromagnet and the second axial electromagnet is the same as the bending moment borne by the shaft end of the propulsion motor unit of the high-altitude airship under test.

[0042] According to the present invention, a ground test device for a high-altitude airship propulsion motor is provided, wherein the radial electromagnet includes a first radial electromagnet and a second radial electromagnet; the resultant force of the radial attraction generated by the first radial electromagnet and the second radial electromagnet is the same as the radial force borne by the shaft end of the high-altitude airship propulsion motor unit under test.

[0043] According to the present invention, a ground test device for a high-altitude airship propulsion motor is provided, wherein the fan includes a first fan and a second fan, wherein the airflow velocity blown by the first fan and the second fan onto the first motor under test in the high-altitude airship propulsion motor assembly is the same as the flight speed of the high-altitude airship when it is running at high altitude.

[0044] The present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the ground test method for high-altitude airship propulsion motors as described above.

[0045] The ground testing method and apparatus for high-altitude airship propulsion motors provided by this invention calculates the motor shaft end load spectrum and determines the test environment spectrum of the environmental test chamber based on the operating condition parameter information. Then, according to the test environment spectrum and the motor shaft end load spectrum, the environmental conditions of the environmental test chamber and the load conditions of each component in the ground testing apparatus for high-altitude airship propulsion motors are adjusted. This achieves simultaneous simulation of the environmental conditions of the propulsion motor during the airship's stationary flight and the load conditions borne by the propulsion motor shaft end in a ground simulation environment. This solves the problem of insufficient simulation of the load conditions borne by the propulsion motor shaft end, which makes it impossible to verify whether the propulsion motor can meet the flight condition requirements. Attached Figure Description

[0046] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced one by one below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0047] Figure 1 This is a flowchart illustrating the ground testing method for the propulsion motor of a high-altitude airship provided by the present invention;

[0048] Figure 2 This is a schematic diagram of the test environment spectrum and motor shaft end load spectrum provided in the embodiments of the present invention;

[0049] Figure 3 A schematic diagram of the structure of the ground test device for high-altitude airship propulsion motor provided by the present invention.

[0050] Explanation of reference numerals in the attached figures:

[0051] 11: Tooling base; 12: First motor mounting bracket; 13: Second motor mounting bracket; 14: Axial electromagnet mounting bracket; 15: Radial electromagnet mounting bracket; 21: First motor under test; 22: Second motor under test; 3: Momentum disk; 41: First axial electromagnet; 42: Second axial electromagnet; 43: First radial electromagnet; 44: Second radial electromagnet; 51: First fan; 52: Second fan; 6: Eccentric counterweight. Detailed Implementation

[0052] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0053] The terminology used in one or more embodiments of the present invention is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. The singular forms “a,” “the,” and “the” used in one or more embodiments of the invention are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” used in one or more embodiments of the invention refers to and includes any or all possible combinations of one or more associated listed items.

[0054] It should be understood that although the terms first, second, etc., may be used to describe various information in one or more embodiments of the present invention, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, first may also be referred to as second without departing from the scope of one or more embodiments of the present invention, and similarly, second may also be referred to as first. Depending on the context, the word "if" as used herein may be interpreted as "when" or "when".

[0055] The following is combined Figures 1-2 The exemplary embodiments of the present invention will be described in detail below.

[0056] Figure 1 This is a flowchart illustrating the ground testing method for the propulsion motor of a high-altitude airship provided by this invention. Figure 1 As shown, the ground test method for the propulsion motor of the high-altitude airship includes:

[0057] Step 11: Obtain the operating condition parameters of the propulsion motor unit of the high-altitude airship under test;

[0058] It should be noted that the high-altitude airship propulsion motor unit under test includes a first motor under test and a second motor under test. The first motor under test is a tension motor, and the second motor under test is a thrust motor. The tension motor is used to drive the propeller to generate thrust, and the thrust motor is used to drive the propeller to generate thrust.

[0059] It should be further explained that the load borne by the propulsion motor shaft end during the airship's stationary flight mainly includes: the thrust or pull generated by the propeller, the gravity generated by the propeller's own weight, the centrifugal force caused by the propeller's eccentricity, the bending moment generated by the propeller's aerodynamic imbalance, and the additional load on the propulsion motor shaft end caused by the acceleration effect of the excitation generated by the propeller during rotation. In this embodiment, the operating condition parameter information includes environmental parameter information and load condition parameter information borne by the motor shaft end during the airship's stationary flight. Among them, the environmental parameter information includes parameters such as temperature, air pressure, irradiance, and airflow intensity under different operating conditions and time periods. The load condition parameter information includes the reference speed under different operating conditions and time periods, the rated speed and speed command transmission frequency of the propulsion motor unit of the high-altitude airship under test, the propeller's thrust coefficient, working atmospheric density, diameter, weight, gravitational acceleration, axial acceleration and radial acceleration corresponding to different rated speeds, bending moment coefficient and torque coefficient, the static imbalance of the propeller, and the moment of inertia under high-altitude operation.

[0060] Step 12: Based on the operating condition parameter information, calculate the motor shaft end load spectrum and determine the test environment spectrum of the environmental test chamber;

[0061] It should be noted that the motor shaft end load spectrum includes the rotational speed of the propulsion motor unit of the high-altitude airship under test under different operating conditions and the axial force, radial force, bending moment, and torque borne by the shaft end of the propulsion motor unit of the high-altitude airship under test. The test environment spectrum includes the ambient temperature, atmospheric pressure, irradiance, and airflow velocity under different operating conditions; wherein, the ambient temperature is divided into daytime temperature and nighttime temperature, and the irradiance is the solar irradiance of the propulsion motor at the actual operating altitude.

[0062] Specifically, such as Figure 2 As shown, Figure 2This is a schematic diagram of the test environment spectrum and motor shaft end load spectrum provided in this embodiment of the invention. Based on the temperature, air pressure, and irradiance at different flight conditions in the operating condition parameter information, the test environment spectrum is determined by the ambient temperature, atmospheric pressure, irradiance, and airflow velocity at different operating conditions in the environmental test chamber. Additionally, based on the rated speed of the high-altitude airship propulsion motor unit under test, the speed command transmission frequency, and the reference speed at different operating conditions, the speed of the high-altitude airship propulsion motor unit under test at different operating conditions is calculated. Based on the reference speed at different operating conditions, the tension coefficient, the working atmospheric density, the diameter, the weight, the axial acceleration, and the preset safety factor, the axial force borne by the shaft end of the high-altitude airship propulsion motor unit under test at different operating conditions is calculated. Based on the reference speed at different operating conditions, the working atmospheric density, the gravitational acceleration, the weight, and the radial acceleration at different operating conditions, the axial force borne by the shaft end of the high-altitude airship propulsion motor unit under test at different operating conditions is calculated. Based on a preset safety factor, the axial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time periods is calculated; based on the reference speed, diameter, tensile coefficient, working atmospheric density, bending moment coefficient, and preset safety factor under different operating conditions and time periods, the bending moment borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time periods is calculated; based on the speed, working atmospheric density, diameter, torque coefficient, and preset safety factor of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time periods, the torque borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time periods is calculated. It should be noted that the preset safety factor can be set according to actual conditions; preferably, the preset safety factor ranges from 1.5 to 3.

[0063] Step 13: Based on the test environment spectrum and the motor shaft end load spectrum, adjust the environmental conditions of the environmental test chamber and the load conditions of each component in the ground test device for the high-altitude airship propulsion motor to conduct a load operation test on the high-altitude airship propulsion motor set under test, and obtain the test results of the high-altitude airship propulsion motor set under test.

[0064] It should be noted that the high-altitude airship propulsion motor unit under test is installed in the high-altitude airship propulsion motor ground test device. During the test, the high-altitude airship propulsion motor ground test device is placed in the environmental test chamber to simulate the environmental conditions of the propulsion motor during the airship's stationary flight.

[0065] It should be noted that the ground test device for the high-altitude airship propulsion motor also includes a momentum disk, axial electromagnet, fan, radial electromagnet, and eccentric counterweight.

[0066] Specifically, based on the ambient temperature, atmospheric pressure, and irradiance under different operating conditions in the test environment spectrum, the environmental conditions in the environmental test chamber are adjusted according to different operating conditions. That is, for any operating condition, the ambient temperature, atmospheric pressure, and irradiance in the environmental test chamber are adjusted to the ambient temperature, atmospheric pressure, and irradiance under that operating condition in the test environment spectrum. Additionally, based on the airflow velocity in the motor shaft end load spectrum under operating conditions, the airflow velocity blown by the fan onto the first test motor in the ground test device for the high-altitude airship propulsion motor is adjusted. Based on the axial force and bending moment under operating conditions, the axial attraction force and bending moment generated by the axial electromagnet in the ground test device for the high-altitude airship propulsion motor are adjusted; based on the radial force under operating conditions, the radial attraction force generated by the radial electromagnet in the ground test device for the high-altitude airship propulsion motor is adjusted; and based on the torque under the current operating conditions, the torque current generated by the second test motor in the ground test device for the high-altitude airship propulsion motor is adjusted. Thus, in a ground simulation environment, the environment for the motor during the propulsion of the airship in stationary flight and the load borne by the propulsion motor shaft end are simultaneously simulated. Then, under environmental and load conditions, a load operation test is conducted on the high-altitude airship propulsion motor assembly under test to obtain the test results. Based on the test results, it is verified whether the propulsion motor can meet the flight operating conditions requirements. It should be noted that the adjustment process can be pre-set for automatic adjustment or manually adjusted.

[0067] According to the above-described scheme, this invention calculates the motor shaft end load spectrum and determines the test environment spectrum of the environmental test chamber based on the operating condition parameter information. Then, based on the test environment spectrum and the motor shaft end load spectrum, it adjusts the environmental conditions of the environmental test chamber and the load conditions of each component in the ground test device for the high-altitude airship propulsion motor. This achieves simultaneous simulation of the environment of the propulsion motor during the airship's stationary flight and the load conditions borne by the propulsion motor shaft end in a ground-simulated environment. This solves the problem of insufficient simulation of the load conditions borne by the propulsion motor shaft end, which prevents verification of whether the propulsion motor can meet the flight condition requirements.

[0068] In one embodiment of the present invention, calculating the motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device based on the operating condition parameter information includes:

[0069] Based on the rated speed of the propulsion motor unit of the airship under test and the speed command transmission frequency, the adjustment amplitude and adjustment frequency of the propulsion motor unit of the airship under test are determined; based on the reference speed under different operating conditions and time, the adjustment amplitude and the adjustment frequency, the speed of the propulsion motor unit of the airship under test under different operating conditions and time is calculated.

[0070] It should be noted that each propulsion motor is equipped with a corresponding rated speed at the factory. The adjustment range is determined based on the rated speed. Preferably, the adjustment range can be 5% of the rated speed. The adjustment frequency is determined based on the speed command sending frequency. The speed command sending frequency is specifically the sending frequency of the propulsion motor speed command during actual flight. Preferably, it can be 5 to 10 times the speed command sending frequency.

[0071] Specifically, the formula for calculating the rotational speed of the propulsion motor unit of the high-altitude airship under test is as follows:

[0072] n s =n si +n so sin(wt)

[0073] Where, n s n represents the rotational speed of the propulsion motor unit of the high-altitude airship under test. si Let n represent the reference speed under the i-th operating condition time. so represents the adjustment amplitude, and w represents the adjustment frequency. Understandably, when the base speed under the i-th operating condition is 200 and the adjustment amplitude is 20, the corresponding speed range of the propulsion motor unit of the high-altitude airship under test is 180 to 220.

[0074] In one embodiment of the present invention, calculating the motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device based on the operating condition parameter information includes:

[0075] Based on the reference speed, the tension coefficient, the working atmospheric density, the diameter, the weight, the axial acceleration, and the preset safety factor under different operating conditions, the axial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated.

[0076] Specifically, for any reference speed under any operating condition, the following steps are performed: Based on the reference speed, the tension coefficient, the working atmospheric density, the diameter, and a preset safety factor, the axial tension generated at the reference speed is calculated. Then, based on the reference speed, axial acceleration, and weight under the current operating condition, the additional axial force is calculated. The additional axial force can be determined based on the reference speed under the current operating condition. Further, based on the axial tension and the additional axial force, the axial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under that operating condition is calculated. The calculation formula is as follows:

[0077]

[0078] Where Ti represents the axial force borne under the i-th operating condition, and C TThe tensile strength coefficient is represented by ρ, the working atmospheric density is represented by n. si This represents the reference rotational speed under the i-th operating condition, where D represents the diameter (m). p Indicates weight, α xi This represents the axial acceleration, and k represents the preset safety factor. Indicates axial tensile force, m p α xi This refers to the additional axial force.

[0079] Based on the reference speed, gravitational acceleration, weight, radial acceleration, and preset safety factor under different operating conditions, the radial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated.

[0080] Specifically, for any reference speed under any operating condition, the following steps are performed: Gravity is calculated based on the preset safety factor, the gravitational acceleration, and the weight; an additional radial force is calculated based on the weight, the radial acceleration, and the reference speed under the operating condition; and then, based on the gravity and the additional radial force, the radial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test is calculated under the specified operating condition. The calculation formula is as follows:

[0081]

[0082] Among them, G pi Let g represent the radial force experienced during the i-th operating condition, g represent the gravitational acceleration, and α represent the radial force experienced during the i-th operating condition. yi This indicates radial acceleration.

[0083] Based on the reference speed, diameter, tension coefficient, working atmospheric density, bending moment coefficient, and preset safety factor under different operating conditions, the bending moment borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated.

[0084] Specifically, the following steps are performed for the reference speed under any operating condition and time:

[0085] Based on the reference speed, working atmospheric density, diameter, and torque coefficient under the specified operating time, the unbalanced aerodynamic torque on the propulsion motor shaft is calculated. Then, based on the unbalanced aerodynamic torque and the preset safety factor, the bending moment borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under the specified operating time is calculated. The formula for calculating the bending moment is as follows:

[0086]

[0087] Among them, C β Indicates the bending moment coefficient. This indicates an unbalanced aerodynamic torque.

[0088] Based on the rotational speed of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time, the working atmospheric density, the diameter, the torque coefficient, and the preset safety factor, the torque borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time is calculated.

[0089] Specifically, the following steps are performed for the rotational speed under any given operating condition:

[0090] Based on the rotational speed of the propulsion motor unit of the high-altitude airship under test during this operating condition, the working atmospheric density, the diameter, and the torque coefficient, the aerodynamic drag torque is calculated. Then, based on the aerodynamic drag torque and the preset safety factor, the torque borne by the shaft end of the propulsion motor unit of the high-altitude airship under test during this operating condition is calculated. The formula for calculating the torque is as follows:

[0091]

[0092] Among them, C q Indicates the torque coefficient. This represents the aerodynamic drag torque.

[0093] The embodiments of the present invention, through the above-described scheme, realize the calculation of the environmental conditions required in the ground test environment, the speed of the motor, and the various load information of the motor shaft end under different working conditions and time according to the operating condition parameter information. Thus, during the test, it can effectively simulate the environmental conditions of the propulsion motor and the load conditions borne by the propulsion motor shaft end during the airship's stationary flight.

[0094] In one embodiment of the present invention, adjusting the environmental conditions of the environmental test chamber and the load conditions of each component in the ground test device for the high-altitude airship propulsion motor according to the test environment spectrum and the motor shaft end load spectrum includes:

[0095] For any given operating time, the environmental conditions of the environmental test chamber are adjusted to the corresponding ambient temperature, atmospheric pressure, and irradiance based on the operating time; the airflow velocity is adjusted based on the airflow speed, allowing the airflow from the fan in the high-altitude airship propulsion motor ground test device to the first motor under test; the axial force and bending moment are adjusted based on the axial force and bending moment, allowing the axial attraction and bending moment generated by the axial electromagnet in the high-altitude airship propulsion motor ground test device; the radial force is adjusted based on the radial force, allowing the radial attraction generated by the radial electromagnet in the high-altitude airship propulsion motor ground test device; and the torque current generated by the second motor under test in the high-altitude airship propulsion motor ground test device is adjusted based on the torque.

[0096] Specifically, for any given operating time, the following steps are performed: The environmental conditions within the environmental test chamber, including ambient temperature, atmospheric pressure, and irradiance, are set to the corresponding ambient temperature, atmospheric pressure, and irradiance for that operating time within the test environment spectrum. Additionally, based on the airflow velocity during the operating time, the airflow velocity blown by the fan to the first motor under test in the high-altitude airship propulsion motor ground test device is adjusted; based on the axial force and bending moment during the operating time, the axial attraction force and bending moment generated by the axial electromagnet in the high-altitude airship propulsion motor ground test device are adjusted; based on the radial force during the operating time, the radial attraction force generated by the radial electromagnet in the high-altitude airship propulsion motor ground test device is adjusted; and based on the torque during the operating time, the torque current generated by the second motor under test in the high-altitude airship propulsion motor ground test device is adjusted. Alternatively, the static imbalance generated by the eccentric counterweight in the ground test device for the high-altitude airship propulsion motor can be set to be the same as the static imbalance of the propeller, and the moment of inertia of the momentum disk in the ground test device for the high-altitude airship propulsion motor can be the same as the moment of inertia of the propeller when it is running at high altitude.

[0097] The embodiments of the present invention, through the above-described scheme, realize the simulation of the environmental conditions and load conditions borne by the propulsion motor shaft end during the propulsion motor's stationary flight process in a ground-based simulated environment, based on the test environment spectrum and the motor shaft end load spectrum, under environmental conditions such as ambient temperature, atmospheric pressure, and irradiance in the environmental test chamber, as well as the rotational speed of the motor unit and the axial force, radial force, bending moment, and torque borne by the motor shaft end in the ground-based simulated environment.

[0098] Furthermore, such as Figure 3 As shown, Figure 3 The present invention provides a schematic diagram of the structure of a ground test device for a high-altitude airship propulsion motor. The device includes a high-altitude airship propulsion motor assembly under test, comprising a first test motor 21 and a second test motor 22. The first test motor 21 is mounted on a first motor mounting bracket 12, and the second test motor 22 is mounted on a second motor mounting bracket 13. The second test motor 22 operates in torque mode, meaning it is driven to rotate by the second test motor 21, thus generating a drag torque. Furthermore, the output shafts of the first test motor 21 and the second test motor 22 are connected to a momentum disk 3, wherein the moment of inertia of the momentum disk 3 is the same as the moment of inertia of the propeller operating at high altitude.

[0099] Furthermore, the ground test device for the high-altitude airship propulsion motor also includes axial electromagnets and radial electromagnets. Preferably, the number of axial electromagnets and radial electromagnets is set to two. The axial electromagnets include a first axial electromagnet 41 and a second axial electromagnet 42. The first axial electromagnet 41 and the second axial electromagnet 42 are mounted on the axial electromagnet mounting bracket 14. The cross-sections of the first axial electromagnet 41 and the second axial electromagnet 42 are directly opposite the momentum disk 3. An axial current is generated between the first axial electromagnet 41 and the second axial electromagnet 42 and the momentum disk 3. In addition, when the magnetic settings of the first axial electromagnet 41 and the second axial electromagnet 42 are different, a bending moment can be generated; the radial electromagnet includes a first radial electromagnet 43 and a second radial electromagnet 44. The second radial electromagnet 43 is mounted on the tooling base 11, and the second radial electromagnet 44 is mounted on the radial electromagnet mounting support 15. The longitudinal planes of the cross-sections of the first radial electromagnet 43 and the second radial electromagnet 44 are relative to the upper and lower cross-sections of the momentum disk, thereby generating a radial attraction between the first radial electromagnet 43, the second radial electromagnet 44 and the momentum disk.

[0100] The ground test device for the high-altitude airship propulsion motor also includes a fan and an eccentric counterweight 6. The fan includes a first fan 51 and a second fan 52, which are mounted on the axial electromagnet mounting bracket to generate airflow velocity to the first motor under test 21. The eccentric counterweight 6 is used to generate static imbalance, and the static imbalance generated by the eccentric counterweight 6 is the same as the static imbalance of the propeller.

[0101] During the ground test of the high-altitude airship propulsion motor, the high-altitude airship propulsion motor ground test device is placed in an environmental test chamber. Based on the operating condition parameters of the high-altitude airship propulsion motor unit under test, the load spectrum of the motor shaft end of the high-altitude airship propulsion motor ground test device and the test environment spectrum of the environmental test chamber are calculated. When adjusting the load conditions of each component in the high-altitude airship propulsion motor ground test device, for any operating time, the airflow velocity, the rotational speed of the high-altitude airship propulsion motor unit under test, and the axial force, radial force, bending moment, and torque borne by the shaft end of the high-altitude airship propulsion motor unit under test, can be adjusted. This allows for adjustment of the axial attraction between the first axial electromagnet 41 and the second axial electromagnet 42 and the momentum disk 3, so that the resultant force of the corresponding axial attraction of the first axial electromagnet 41 and the second axial electromagnet 42 is adjusted. Similar to the axial force borne by the shaft end under the operating condition, the bending moment between the first axial electromagnet 41 and the second axial electromagnet 42 can be adjusted so that the bending moment is the same as the bending moment borne by the shaft end under the operating condition. In addition, the radial attraction forces generated between the first radial electromagnet 43 and the second radial electromagnet 44 and the momentum disk 3 can be adjusted so that the resultant force of the radial attraction forces corresponding to the first radial electromagnet 43 and the second radial electromagnet 44 is the same as the radial force borne by the shaft end under the operating condition. Furthermore, the airflow velocity blown onto the first test motor 21 can be made consistent with the airflow velocity corresponding to the reference speed under the operating condition by adjusting the flow rate of the first fan 51 and the second fan 52. Additionally, the torque current of the second test motor 22 can be adjusted so that the resistance torque reaches the torque of the first test motor 21 under the operating condition.

[0102] This method achieves the simulation of varying axial and radial forces using electromagnets in the ground test device for the high-altitude airship propulsion motor, airflow using a fan, propeller inertia using a momentum disk, and centrifugal force using an eccentric counterweight. This maximizes the consistency between the load conditions of the two motors in the ground simulation test and those during flight, solving or partially solving the problems of insufficient simulation of the load on the propulsion motor shaft end and the inability to verify whether the propulsion motor can meet flight requirements in existing high-altitude airship propulsion motor testing methods. Furthermore, it allows for the simultaneous testing of both thrust and pressure-bearing motors, effectively improving testing efficiency and saving testing time and costs.

[0103] In another aspect, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to perform the ground test method for the high-altitude airship propulsion motor provided by the methods described above.

[0104] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0105] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0106] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A ground test method for a high-altitude airship propulsion motor, characterized in that, include: Obtain operating condition parameter information of the propulsion motor unit of the high-altitude airship under test; Based on the operating condition parameter information, the motor shaft end load spectrum and the test environment spectrum of the environmental test chamber are calculated. Based on the test environment spectrum and the motor shaft end load spectrum, the environmental conditions of the environmental test chamber and the load conditions of each component in the ground test device for the high-altitude airship propulsion motor are adjusted to conduct a load operation test on the high-altitude airship propulsion motor unit under test and obtain the test results of the high-altitude airship propulsion motor unit under test. The high-altitude airship propulsion motor unit to be tested is installed in the high-altitude airship propulsion motor ground test device, and the high-altitude airship propulsion motor ground test device is placed in the environmental test chamber; The test environment spectrum includes ambient temperature, atmospheric pressure, irradiance, and airflow velocity under different operating conditions and time periods; The motor shaft end load spectrum includes the rotational speed of the high-altitude airship propulsion motor unit under different operating conditions and the axial force, radial force, bending moment and torque borne by the shaft end of the high-altitude airship propulsion motor unit under the test; The high-altitude airship propulsion motor set under test includes a first motor under test and a second motor under test; The step of adjusting the environmental conditions of the environmental test chamber and the load conditions of each component in the ground test device for the high-altitude airship propulsion motor according to the test environment spectrum and the motor shaft end load spectrum includes: For any given operating time, the environmental conditions of the environmental test chamber are adjusted to the ambient temperature, atmospheric pressure, and irradiance corresponding to that operating time. Based on the airflow velocity under the aforementioned operating conditions, the airflow velocity blown by the fan to the first motor under test in the ground test device for the high-altitude airship propulsion motor is adjusted. Based on the axial force and bending moment under the aforementioned working conditions, adjust the axial attraction and bending moment generated by the axial electromagnet in the ground test device for the high-altitude airship propulsion motor. Based on the radial force under the aforementioned operating conditions, adjust the radial attraction force generated by the radial electromagnet in the ground test device for the high-altitude airship propulsion motor. Based on the torque under the aforementioned operating conditions, the torque current generated by the second motor under test in the ground test device for the high-altitude airship propulsion motor is adjusted.

2. The ground test method for high-altitude airship propulsion motor according to claim 1, characterized in that, The operating condition parameter information includes the reference speed under different operating conditions and time, the rated speed of the propulsion motor unit of the high-altitude airship under test, and the speed command transmission frequency. The calculation of the motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device based on the operating condition parameter information includes: Based on the rated speed of the propulsion motor unit of the high-altitude airship under test and the speed command transmission frequency, the adjustment amplitude and adjustment frequency of the propulsion motor unit of the high-altitude airship under test are determined. Based on the reference speed under different operating conditions, the adjustment amplitude, and the adjustment frequency, the speed of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated.

3. The ground test method for high-altitude airship propulsion motor according to claim 2, characterized in that, The operating condition parameter information also includes the propeller's thrust coefficient, working atmospheric density, diameter, weight, gravitational acceleration, and axial and radial acceleration corresponding to different rated speeds; The calculation of the motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device based on the operating condition parameter information includes: Based on the reference speed, the tension coefficient, the working atmospheric density, the diameter, the weight, the axial acceleration, and the preset safety factor under different operating conditions, the axial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated. Based on the reference speed, gravitational acceleration, weight, radial acceleration, and preset safety factor under different operating conditions, the radial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated.

4. The ground test method for high-altitude airship propulsion motor according to claim 3, characterized in that, The operating condition parameter information also includes bending moment coefficient and torque coefficient; The calculation of the motor shaft end load spectrum of the high-altitude airship propulsion motor ground test device based on the operating condition parameter information includes: Based on the reference speed, diameter, tension coefficient, working atmospheric density, bending moment coefficient, and preset safety factor under different operating conditions, the bending moment borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions is calculated. Based on the rotational speed of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time, the working atmospheric density, the diameter, the torque coefficient, and the preset safety factor, the torque borne by the shaft end of the propulsion motor unit of the high-altitude airship under test under different operating conditions and time is calculated.

5. A ground test apparatus for a high-altitude airship propulsion motor using the ground test method for a high-altitude airship propulsion motor as described in any one of claims 1 to 4, characterized in that, include: The propulsion motor unit of the high-altitude airship under test is connected to the momentum disk via its output shaft. An axial electromagnet is mounted on an axial electromagnet mounting bracket and is horizontally aligned with the momentum disk to generate axial attraction and bending moment. A fan, mounted on the axial electromagnet mounting bracket, is used to generate airflow velocity; A radial electromagnet, with its longitudinal plane facing the momentum disk, is used to generate radial attraction. An eccentric counterweight is mounted on the momentum disk to generate static imbalance.

6. The ground test device for high-altitude airship propulsion motor according to claim 5, characterized in that, The axial electromagnet includes a first axial electromagnet and a second axial electromagnet, wherein: The resultant force of the axial forces generated by the first axial electromagnet and the second axial electromagnet is the same as the axial attraction force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test. The bending moment generated by the first axial electromagnet and the second axial electromagnet is the same as the bending moment borne by the shaft end of the propulsion motor unit of the high-altitude airship under test.

7. The ground test device for high-altitude airship propulsion motor according to claim 5, characterized in that, The radial electromagnets include a first radial electromagnet and a second radial electromagnet; the resultant force of the radial attraction generated by the first radial electromagnet and the second radial electromagnet is the same as the radial force borne by the shaft end of the propulsion motor unit of the high-altitude airship under test.

8. The ground test device for high-altitude airship propulsion motor according to claim 5, characterized in that, The wind turbine includes a first wind turbine and a second wind turbine, wherein the airflow velocity blown by the first wind turbine and the second wind turbine onto the first motor under test in the propulsion motor unit of the high-altitude airship under test is the same as the flight speed of the high-altitude airship when it is running at high altitude.

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