Aero-propulsion test mobile platform control method and system

Abstract

The application discloses an aviation power test mobile platform control method and system, an aero-engine is carried on a mobile platform, and the mobile platform is provided with an electric drive system. The method comprises the following steps: firstly, the aero-engine gradually increases output power to maximum output power. Meanwhile, the electric drive system assists the aero-engine to push the mobile platform to reach a test mode test working condition. Then, a judgment method suitable for the test mode is adopted to judge whether the current motion state of the mobile platform can be maintained. If yes, the aero-engine is tested according to the test mode requirement, and meanwhile, an energy recovery module of the electric drive system is started to recover energy, so as to maintain the test working condition and provide additional load for the aero-engine, so as to detect performance data of the aero-engine under the load condition. If not, the electric drive system is controlled to actively compensate for the power difference required by the mobile platform for maintaining the test working condition, so as to test various performance data of the aero-engine under the current test mode.

Description

Technical Field

[0001] This invention relates to the field of internal combustion engine testing technology, and specifically to a control method and system for a mobile platform for aviation power testing. Background Technology

[0002] In the research and development of electric propulsion aero-engine systems, extensive and precise testing on test platforms is necessary to ensure their performance, reliability, and safety. Electric propulsion aero-engine systems have attracted attention due to their advantages such as high efficiency, environmental friendliness, and low noise; however, this system involves complex technological integration. Traditional testing methods have gradually revealed many shortcomings when testing electric propulsion aero-engine systems. On the one hand, electric propulsion aero-engine systems operate in diverse modes, with significant differences in power requirements and load characteristics at different stages. Traditional ground-based testing methods struggle to accurately simulate these complex operating conditions, leading to deviations between test results and actual flight or ground taxiing conditions. On the other hand, the coordinated operation of the electric propulsion system and the aero-engine involves complex energy interaction and power distribution. Traditional testing methods often fail to achieve flexible coordination between the electric drive system and the aero-engine, making it impossible to effectively test the various functional indicators of the electric propulsion aero-engine system under dynamic conditions. This makes it impossible to obtain data on the various complex operating conditions the engine might encounter in actual flight during testing, limiting in-depth research and optimization of electric propulsion aero-engine systems. Summary of the Invention

[0003] To address the shortcomings of existing technologies, this invention proposes a control method and system for a mobile platform for aero-engine testing, enabling efficient and comprehensive testing of electric propulsion aero-engine systems. The specific technical solution is as follows:

[0004] In a first aspect, a control method for a mobile platform for air-to-ground propulsion testing is provided. In a first feasible embodiment of the first aspect, an air-to-ground engine is mounted on the mobile platform, the mobile platform is equipped with an electric drive system, and the electric drive system is equipped with an energy recovery module, including:

[0005] The aero-engine is controlled to gradually increase its output power to the maximum power, and the electric drive system is simultaneously controlled to assist the aero-engine in driving the mobile platform to achieve the test conditions corresponding to the test mode.

[0006] The method for determining the adaptation test mode is used to determine whether the mobile platform can maintain the test conditions;

[0007] In response to the mobile platform's ability to maintain test conditions, the electric drive system switches to a power consumption mode and recovers energy through its own energy recovery module.

[0008] In response to the mobile platform being unable to maintain the test conditions, the electric drive system switches to a power compensation mode to compensate for the power difference required to maintain the test conditions.

[0009] In conjunction with the first possible implementation of the first aspect, in the second possible implementation of the first aspect, when the test mode is a fixed airspeed mode, determining whether the mobile platform can maintain the test condition includes:

[0010] The thrust generated by the aero-engine and the total drag of the mobile platform at a fixed airspeed are obtained.

[0011] Compare the thrust with the total drag force.

[0012] In response to the thrust exceeding the total resistance of travel, the mobile platform is able to maintain the test conditions;

[0013] In response to the thrust being less than the total resistance of travel, the mobile platform cannot maintain the test conditions.

[0014] In conjunction with the second possible implementation of the first aspect, in the third possible implementation of the first aspect, obtaining the total resistance of the mobile platform at a fixed airspeed includes:

[0015] Determine the type of resistance experienced by the mobile platform based on the road conditions at its current location;

[0016] Obtain the influence parameters corresponding to each of the various resistance types, and calculate the driving resistance corresponding to each resistance type using the appropriate resistance algorithm.

[0017] By combining all the calculated travel resistances, the total travel resistance of the mobile platform is calculated.

[0018] In conjunction with the first possible implementation of the first aspect, in the fourth possible implementation of the first aspect, when the test mode is uniform acceleration mode, determining whether the mobile platform can maintain the test condition includes:

[0019] The minimum and maximum accelerations achieved by the mobile platform at different locations on the test track under the drive of the aircraft engine were obtained.

[0020] Compare the acceleration corresponding to the test condition with the minimum and maximum accelerations at the corresponding locations;

[0021] In response to the acceleration being less than the minimum acceleration, the mobile platform is able to maintain the test conditions;

[0022] In response to the acceleration being greater than the maximum acceleration, the mobile platform cannot maintain the test conditions.

[0023] In conjunction with the first possible implementation of the first aspect, in the fifth possible implementation of the first aspect, when the test mode is variable acceleration mode, determining whether the mobile platform can maintain the test conditions includes:

[0024] Obtain the real-time acceleration of the mobile platform and compare the real-time acceleration with the preset variable acceleration;

[0025] In response to the real-time acceleration exceeding the variable acceleration, the mobile platform is able to maintain the test conditions;

[0026] In response to the real-time acceleration being less than the variable acceleration, the mobile platform cannot maintain the test conditions.

[0027] In conjunction with the first possible implementation of the first aspect, in the sixth possible implementation of the first aspect, compensating for the power difference required to maintain the test condition includes:

[0028] The system acquires the various detection parameters corresponding to the test mode in real time, and uses a power algorithm adapted to the test mode to calculate the required power to maintain the test conditions.

[0029] The power difference is calculated by combining the real-time power output of the aero-engine with the required power, and the electric drive system is controlled to actively compensate for the power difference.

[0030] In conjunction with the first possible implementation of the first aspect, in the seventh possible implementation of the first aspect, the electric drive system is started using a variable frequency speed control method.

[0031] Secondly, a control system for a mobile platform for air-to-ground propulsion testing is provided. An air-to-ground engine is mounted on the mobile platform, which is equipped with an electric drive system. The electric drive system includes an energy recovery module, comprising:

[0032] The auxiliary module is configured to control the aero-engine to gradually increase its output power to the maximum power, and to control the electric drive system to assist the aero-engine in driving the mobile platform to achieve the test conditions corresponding to the test mode.

[0033] The maintenance module is configured to use an adaptive test mode judgment method to determine whether the mobile platform can maintain the test conditions;

[0034] In response to the mobile platform's ability to maintain test conditions, the electric drive system switches to a power consumption mode and recovers energy through its own energy recovery module.

[0035] In response to the mobile platform being unable to maintain the test conditions, the electric drive system switches to a power compensation mode to compensate for the power difference required to maintain the test conditions.

[0036] Beneficial Effects: The control method and system for the mobile platform of the aero-engine test of this invention, through the set electric drive system, can provide auxiliary power to assist the aero-engine in driving the mobile platform to quickly reach the test conditions corresponding to the set test mode, so as to conduct corresponding tests on the aero-engine. This improves test efficiency. Moreover, during the test, the corresponding operating parameters can be detected in real time, and a judgment method matching the test mode can be used to detect whether the aero-engine can maintain the test conditions. Based on the judgment result, the electric drive system can be controlled to provide auxiliary power to the aero-engine or to provide additional load to the aero-engine. Through the coordinated and adaptive control of multiple operating conditions, efficient and comprehensive testing of the electric propulsion aero-engine system can be achieved, improving test flexibility and the richness of parameter acquisition to meet more dynamic test requirements. Attached Figure Description

[0037] To more clearly illustrate the specific embodiments of the present invention, the accompanying drawings used in the specific embodiments will be briefly described below. In all the drawings, the elements or parts are not necessarily drawn to scale.

[0038] Figure 1 A flowchart of a control method for an aero-engine test mobile platform provided in an embodiment of the present invention;

[0039] Figure 2 In fixed airspeed mode, it can maintain the stress conditions during the test.

[0040] Figure 3 In fixed airspeed mode, the mobile platform cannot maintain the stress conditions as it did during the test.

[0041] Figure 4 In uniform acceleration mode, the mobile platform cannot maintain the stress conditions as it did during the test.

[0042] Figure 5 In uniform acceleration mode, the mobile platform can maintain the force conditions during the test.

[0043] Figure 6 In variable acceleration mode, the mobile platform can maintain the stress conditions during the test.

[0044] Figure 7 In variable acceleration mode, the mobile platform cannot maintain the stress conditions as it did during the test. Detailed Implementation

[0045] The embodiments of the technical solution of the present invention will now be described in detail with reference to the accompanying drawings. These embodiments are merely illustrative of the technical solution of the present invention and are therefore intended to limit the scope of protection of the present invention.

[0046] It should be understood that in this embodiment, the aircraft engine is an electric propulsion aircraft engine. During testing, the aircraft engine needs to be fixedly mounted on a mobile platform. The mobile platform is equipped with an electric drive system, and the electric drive system is equipped with an energy recovery module, which is the same as the existing electric vehicle energy recovery system.

[0047] like Figure 1 The flowchart shown is a control method for a mobile platform used for air-to-ground propulsion testing. The control method includes:

[0048] Step 1: Control the aero engine to gradually increase the output power to the maximum power, and simultaneously control the electric drive system to assist the aero engine in driving the mobile platform to reach the test conditions corresponding to the test mode.

[0049] Step 2: Use the adaptation test mode judgment method to determine whether the mobile platform can maintain the test conditions;

[0050] In response to the mobile platform's ability to maintain test conditions, the electric drive system switches to a power consumption mode and recovers energy through its own energy recovery module.

[0051] In response to the mobile platform being unable to maintain the test conditions, the electric drive system switches to a power compensation mode to compensate for the power difference required to maintain the test conditions.

[0052] Specifically, firstly, the output power of the aero-engine can be gradually increased until it reaches its maximum output power. Simultaneously, the electric drive system of the mobile platform can be controlled to assist the aero-engine in propelling the mobile platform to the pre-set test conditions as quickly as possible. This shortens the time and distance required for the mobile platform to reach the test conditions, improves test efficiency, and reduces the requirements for the test site.

[0053] When the mobile platform reaches the aforementioned test conditions, a judgment method matching the test mode can be used to determine whether the mobile platform can maintain its current motion state solely relying on the aircraft engine. If it can, the aircraft engine can be tested accordingly, and the electric drive system can be switched to power consumption mode, activating the energy recovery module of the electric drive system to recover excess energy generated by the aircraft engine. In this way, not only can the mobile platform maintain the test conditions corresponding to the current test mode, but additional load can also be provided to the aircraft engine to detect its performance data under load.

[0054] If the current motion state of the mobile platform cannot be maintained, the electric drive system is switched to power compensation mode. The electric drive system actively compensates the power difference required by the mobile platform to maintain the test conditions for the aero-engine, so as to test various performance data of the aero-engine in the current test mode, such as the power output and aerodynamic characteristics of the aero-engine.

[0055] In this embodiment, optionally, when the test mode is fixed airspeed mode, determining whether the mobile platform can maintain the test conditions includes:

[0056] The thrust generated by the aero-engine and the total drag of the mobile platform at a fixed airspeed are obtained.

[0057] Compare the thrust with the total drag force.

[0058] In response to the thrust exceeding the total resistance of travel, the mobile platform is able to maintain the test conditions;

[0059] In response to the thrust being less than the total resistance of travel, the mobile platform cannot maintain the test conditions.

[0060] Specifically, this embodiment includes several different test modes, such as a fixed airspeed mode, a uniform acceleration mode, and a variable acceleration mode. When the test mode is set to fixed airspeed mode, the electric drive system can assist the aircraft engine in quickly propelling the mobile platform to the specified airspeed required by the fixed airspeed mode. When the speed of the mobile platform reaches the specified airspeed, the thrust generated by the aircraft engine and the total drag experienced by the mobile platform at that time can be obtained in real time.

[0061] like Figure 2 As shown, if the thrust exceeds the total drag, the mobile platform can maintain a specified airspeed. At this time, the output power of the aircraft engine and the power required for the mobile platform to maintain the current speed can be obtained. The power difference between the output power and the power required can be calculated. At the same time, the energy recovery module is controlled to recover energy according to the power difference, so that the mobile platform can maintain a specified airspeed and test the various performance data of the aircraft engine at a fixed airspeed.

[0062] like Figure 3 As shown, if the thrust is less than the total drag, the mobile platform cannot maintain the specified airspeed. In this case, it is necessary to calculate the power difference required for the mobile platform to maintain the specified airspeed based on the output power and the required power. The electric drive system is then controlled to actively compensate for the power difference so that the mobile platform can maintain the specified airspeed.

[0063] In this embodiment, optionally, compensating for the power difference required to maintain the test conditions includes:

[0064] The system acquires the various detection parameters corresponding to the test mode in real time, and uses a power algorithm adapted to the test mode to calculate the required power to maintain the test conditions.

[0065] The power difference is calculated by combining the real-time power output of the aero-engine with the required power, and the electric drive system is controlled to actively compensate for the power difference.

[0066] Specifically, different test modes correspond to different test conditions, have different power requirements, and involve different detection parameters. Therefore, when calculating the power required to maintain the test conditions, it is necessary to select the appropriate power calculation algorithm based on the test mode.

[0067] In this embodiment, when the test mode is fixed airspeed mode, the specific calculation formula for the power required for the mobile platform to maintain a specified airspeed is as follows:

[0068] ;

[0069] If the mobile platform is currently climbing an incline, the power required for climbing also needs to be added. The specific calculation formula for the power required for climbing is as follows:

[0070] ;

[0071] in, For the mechanical efficiency of the transmission system, For the overall quality of the mobile platform, It is the acceleration due to gravity. The rolling resistance coefficient, For a specified airspeed, This is the drag coefficient. For the windward area of ​​the mobile platform, The slope.

[0072] In this embodiment, optionally, obtaining the total resistance of the mobile platform at a fixed airspeed includes:

[0073] Determine the type of resistance experienced by the mobile platform based on the road conditions at its current location;

[0074] Obtain the influence parameters corresponding to each of the various resistance types, and calculate the driving resistance corresponding to each resistance type using the appropriate resistance algorithm.

[0075] By combining all the calculated travel resistances, the total travel resistance of the mobile platform is calculated.

[0076] Specifically, firstly, the type of resistance the mobile platform experiences can be determined based on the road conditions of the current location. During movement, the mobile platform must withstand rolling resistance and air resistance. If it is on an uphill section, it will also need to withstand additional climbing resistance.

[0077] Then, based on the influence parameters corresponding to various resistance types, the corresponding resistance algorithms can be used to calculate the driving resistance values ​​corresponding to each type of resistance experienced by the mobile platform. Rolling resistance air resistance and climbing resistance The specific algorithm is as follows:

[0078] ;

[0079] ;

[0080] .

[0081] Finally, by superimposing the driving resistance values ​​corresponding to all types of resistance experienced by the mobile platform, the total driving resistance of the mobile platform can be calculated.

[0082] In this embodiment, optionally, when the test mode is uniform acceleration mode, determining whether the mobile platform can maintain the test condition includes:

[0083] The minimum and maximum accelerations achieved by the mobile platform at different locations on the test track under the drive of the aircraft engine were obtained.

[0084] Compare the acceleration corresponding to the test condition with the minimum and maximum accelerations at the corresponding locations;

[0085] In response to the acceleration being less than the minimum acceleration, the mobile platform is able to maintain the test conditions;

[0086] In response to the acceleration being greater than the maximum acceleration, the mobile platform cannot maintain the test conditions.

[0087] Specifically, since road conditions vary at different locations along the test route, during the uniform acceleration test, the first step is to test the maximum and minimum acceleration that the mobile platform can achieve at different locations under the drive of the aircraft engine. Then, when the electric drive system assists the aircraft engine in driving the mobile platform to reach the test conditions corresponding to the uniform acceleration mode, the maximum and minimum acceleration at the location of the mobile platform can be compared with the acceleration set for the uniform acceleration mode.

[0088] like Figure 4As shown, if the set acceleration is greater than the maximum acceleration, the mobile platform cannot maintain the test condition. At this time, the electric drive system switches to power compensation mode to actively compensate for the power difference between the maximum output power of the aero-engine and the power required for the mobile platform to maintain the acceleration condition, thereby maintaining the acceleration condition of the mobile platform and collecting dynamic parameters such as the speed, vibration, torque, and intake and exhaust flow of the aero-engine under uniform acceleration to analyze the acceleration performance and stability of the aero-engine.

[0089] like Figure 5 As shown, if the set acceleration is less than the minimum acceleration, the mobile platform can maintain the test condition. At this time, the electric drive system switches to power consumption mode and can control the energy recovery module to recover energy and provide additional load to the aircraft engine, thereby enabling the mobile platform to maintain the set acceleration condition.

[0090] In this embodiment, when the test mode is uniform acceleration mode, the specific calculation formula for the power required for the mobile platform to maintain a specified acceleration is as follows:

[0091] ;

[0092] in, This is a quality conversion factor. Real-time acceleration for mobile platforms.

[0093] If the mobile platform is currently climbing an incline, the power required for climbing also needs to be added.

[0094] In this embodiment, optionally, when the test mode is variable acceleration mode, determining whether the mobile platform can maintain the test conditions includes:

[0095] Obtain the real-time acceleration of the mobile platform and compare the real-time acceleration with the preset variable acceleration;

[0096] In response to the real-time acceleration exceeding the variable acceleration, the mobile platform is able to maintain the test conditions;

[0097] In response to the real-time acceleration being less than the variable acceleration, the mobile platform cannot maintain the test conditions.

[0098] Specifically, when the preset test mode is variable acceleration mode, the output power of the aircraft engine can be gradually increased to its maximum output power, and the aircraft engine can be controlled to maintain the maximum output power continuously. At this time, the real-time acceleration of the current mobile platform can be obtained, and the real-time acceleration can be compared with the variable acceleration curve corresponding to the variable acceleration mode.

[0099] like Figure 6As shown, if the real-time acceleration exceeds the variable acceleration corresponding to the current moment in the variable acceleration curve, the mobile platform can maintain the current test conditions. At this time, the electric drive system switches to power consumption mode, which can control the energy recovery module to recover energy and provide additional load to the aircraft engine, thereby enabling the mobile platform to maintain the set variable acceleration.

[0100] like Figure 7 As shown, if the real-time acceleration is less than the variable acceleration corresponding to the current moment in the variable acceleration curve, the mobile platform cannot maintain the current test condition. At this time, the electric drive system switches to power compensation mode to actively compensate for the power difference between the maximum output power of the aero-engine and the power required for the mobile platform to maintain variable acceleration, thus maintaining the variable acceleration condition of the mobile platform.

[0101] In this embodiment, optionally, the electric drive system is started using a variable frequency speed control method. Starting the electric drive system using a variable frequency speed control method allows for smooth adjustment of the rotational speed by changing the power supply frequency, thereby avoiding the large current surge during startup.

[0102] A control system for a mobile platform for air power testing, wherein an air engine is mounted on the mobile platform, the mobile platform is equipped with an electric drive system, and the electric drive system is equipped with an energy recovery module, the control system comprising:

[0103] The auxiliary module is configured to control the aero-engine to gradually increase its output power to the maximum power, and to control the electric drive system to assist the aero-engine in driving the mobile platform to achieve the test conditions corresponding to the test mode.

[0104] The maintenance module is configured to use an adaptive test mode judgment method to determine whether the mobile platform can maintain the test conditions;

[0105] In response to the mobile platform's ability to maintain test conditions, the electric drive system switches to a power consumption mode and recovers energy through its own energy recovery module.

[0106] In response to the mobile platform being unable to maintain the test conditions, the electric drive system switches to a power compensation mode to compensate for the power difference required to maintain the test conditions.

[0107] Specifically, the control system includes an auxiliary module and a maintenance module. In the initial stage of testing, the aero-engine's output power can be gradually increased until it reaches its maximum output power. Simultaneously, the auxiliary module controls the electric drive system of the mobile platform, assisting the aero-engine in propelling the platform to the pre-set test conditions as quickly as possible. This shortens the time and distance required for the platform to reach the test conditions, improves testing efficiency, and reduces the requirements for the test site.

[0108] When the mobile platform reaches the aforementioned test condition, the maintenance module can use a judgment method matching the test mode to determine whether the mobile platform's current motion state can be maintained solely by the aircraft engine. If it can be maintained, the aircraft engine can be tested accordingly, and the electric drive system can be switched to power consumption mode, activating the energy recovery module of the electric drive system to recover excess energy generated by the aircraft engine. In this way, not only can the mobile platform maintain the test condition corresponding to the current test mode, but additional load can also be provided to the aircraft engine to detect its performance data under load.

[0109] If the current motion state of the mobile platform cannot be maintained, the electric drive system is switched to power compensation mode. The electric drive system actively compensates the power difference required by the mobile platform to maintain the test conditions for the aero-engine, so as to test various performance data of the aero-engine in the current test mode, such as the power output and aerodynamic characteristics of the aero-engine.

[0110] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. 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 or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and they should all be covered within the scope of the claims and specification of the present invention.

Claims

1. A control method for a mobile platform for air-to-ground propulsion testing, wherein an air-to-ground engine is mounted on the mobile platform, the mobile platform is equipped with an electric drive system, and the electric drive system is equipped with an energy recovery module, characterized in that, include: The aero-engine is controlled to gradually increase its output power to the maximum power, and the electric drive system is simultaneously controlled to assist the aero-engine in driving the mobile platform to achieve the test conditions corresponding to the test mode. The method for determining the adaptation test mode is used to determine whether the mobile platform can maintain the test conditions; In response to the mobile platform's ability to maintain test conditions, the electric drive system switches to a power consumption mode and recovers energy through the energy recovery module. In response to the mobile platform's inability to maintain the test conditions, the electric drive system switches to a power compensation mode to compensate for the power difference required to maintain the test conditions, including: The system acquires the various detection parameters corresponding to the test mode in real time, and uses a power algorithm adapted to the test mode to calculate the required power to maintain the test conditions. The power difference is calculated by combining the real-time power output of the aero-engine with the required power, and the electric drive system is controlled to actively compensate for the power difference. When the test mode is fixed airspeed mode, the specific calculation formula for the power required to maintain the specified airspeed is as follows: ； in, For the mechanical efficiency of the transmission system, For the overall quality of the mobile platform, It is the acceleration due to gravity. The rolling resistance coefficient, For a specified airspeed, This is the drag coefficient. For the windward area of ​​the mobile platform; When the test mode is uniform acceleration mode, the specific formula for calculating the power required to maintain a specified acceleration is as follows: ； in, This is a quality conversion factor. Real-time acceleration for mobile platforms.

2. The control method for an electrically driven mobile platform for air power testing according to claim 1, characterized in that, When the test mode is fixed airspeed mode, determining whether the mobile platform can maintain the test conditions includes: The thrust generated by the aero-engine and the total drag of the mobile platform at a fixed airspeed are obtained. Compare the thrust with the total drag force. In response to the thrust exceeding the total resistance of travel, the mobile platform is able to maintain the test conditions; In response to the thrust being less than the total resistance of travel, the mobile platform cannot maintain the test conditions.

3. The control method for an electrically driven mobile platform for air power testing according to claim 2, characterized in that, Obtaining the total resistance of the mobile platform at a fixed airspeed includes: The type of resistance experienced by the mobile platform is determined based on the road conditions at the current location. The resistance types include rolling resistance, air resistance, and climbing resistance. Obtain the influence parameters corresponding to each of the various resistance types, and calculate the driving resistance corresponding to each resistance type using the appropriate resistance algorithm. By combining all the calculated travel resistances, the total travel resistance of the mobile platform is calculated.

4. The control method for an electrically driven mobile platform for airborne power testing according to claim 1, characterized in that, When the test mode is uniform acceleration mode, determining whether the mobile platform can maintain the test conditions includes: The minimum and maximum accelerations achieved by the mobile platform at different locations on the test track under the drive of the aircraft engine were obtained. Compare the acceleration corresponding to the test condition with the minimum and maximum accelerations at the corresponding locations; In response to the acceleration being less than the minimum acceleration, the mobile platform is able to maintain the test conditions; In response to the acceleration being greater than the maximum acceleration, the mobile platform cannot maintain the test conditions.

5. The control method for an electrically driven mobile platform for airborne power testing according to claim 1, characterized in that, When the test mode is variable acceleration mode, determine whether the mobile platform can maintain the test conditions, including: Obtain the real-time acceleration of the mobile platform and compare the real-time acceleration with the preset variable acceleration; In response to the real-time acceleration exceeding the variable acceleration, the mobile platform is able to maintain the test conditions; In response to the real-time acceleration being less than the variable acceleration, the mobile platform cannot maintain the test conditions.

6. The control method for an electrically driven mobile platform for air power testing according to claim 1, characterized in that, The electric drive system is started using a variable frequency speed control method.

7. A control system for a mobile platform for air-to-ground propulsion testing, wherein an air-to-ground engine is mounted on the mobile platform, the mobile platform is equipped with an electric drive system, and the electric drive system is equipped with an energy recovery module, characterized in that, include: The auxiliary module is configured to control the aero-engine to gradually increase its output power to the maximum power, and to control the electric drive system to assist the aero-engine in driving the mobile platform to achieve the test conditions corresponding to the test mode. The maintenance module is configured to use an adaptive test mode judgment method to determine whether the mobile platform can maintain the test conditions; In response to the mobile platform's ability to maintain test conditions, the electric drive system switches to a power consumption mode and recovers energy through its own energy recovery module. In response to the mobile platform's inability to maintain the test conditions, the electric drive system switches to a power compensation mode to compensate for the power difference required to maintain the test conditions, including: The system acquires the various detection parameters corresponding to the test mode in real time, and uses a power algorithm adapted to the test mode to calculate the required power to maintain the test conditions. The power difference is calculated by combining the real-time power output of the aero-engine with the required power, and the electric drive system is controlled to actively compensate for the power difference. When the test mode is fixed airspeed mode, the specific calculation formula for the power required to maintain the specified airspeed is as follows: ； in, For the mechanical efficiency of the transmission system, For the overall quality of the mobile platform, It is the acceleration due to gravity. The rolling resistance coefficient, For a specified airspeed, This is the drag coefficient. For the windward area of ​​the mobile platform; When the test mode is uniform acceleration mode, the specific formula for calculating the power required to maintain a specified acceleration is as follows: ； in, This is a quality conversion factor. Real-time acceleration for mobile platforms.

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