A method and system for comprehensive environmental adaptability simulation testing of low-altitude aircraft

Abstract

This invention discloses a comprehensive environmental adaptability simulation test method and system for low-altitude aircraft. Addressing the shortcomings of traditional tests that neglect the latent runaway caused by asymmetric icing, this invention collects basic operating parameters in real time and calculates the real-time equivalent power coefficient of each rotor. Based on this, it calculates the global asymmetric electrical stress index to quantify the degree of imbalance in internal power distribution. Subsequently, it dynamically derives the ultimate trigger threshold by combining hardware limit protection current. When the relative deterioration rate of this index approaches the threshold, gust disturbances are injected into the test cabin. Through this dynamic testing mechanism, this invention can accurately capture the critical point of control margin depletion and induce multi-domain coupled testing, effectively filtering out misjudgments caused by uniform icing and effectively defining the true safety boundary of the aircraft under complex weather conditions.

Description

Technical Field

[0001] This invention relates to the field of environmental reliability testing and evaluation technology for low-altitude aircraft, and more specifically, to a method and system for simulating the comprehensive environmental adaptability of low-altitude aircraft based on dynamic electro-aerodynamic coupling characteristics. Background Technology

[0002] With the development of the low-altitude economy, low-altitude aircraft such as drones are increasingly used in logistics, inspection, and other fields. In actual operation, low-altitude aircraft often face complex environments such as low temperatures, high humidity, and shear winds. Existing third-party laboratories, when conducting environmental adaptability tests, typically treat environmental factors as static background conditions, such as observing whether the aircraft structure ices up in a low-temperature, high-humidity environment, or testing its maximum wind resistance level under constant wind speed.

[0003] Traditional testing methods often overlook a hidden problem: in low-temperature, high-humidity environments such as through clouds or freezing rain, the icing evolution of aircraft rotors often exhibits asymmetry. For perfectly symmetrical, uniform icing, current technology can detect and warn of this by monitoring a decrease in total thrust or a sudden increase in total current; this overall power reduction is a visible fault. However, asymmetric icing poses a significant risk of sudden loss of control under complex weather conditions. This asymmetric aerodynamic degradation causes the flight control system to continuously issue differentiated torque compensation commands, forcing high-frequency current fluctuations in the electronic speed controllers (ESCs). In this state, even if the overall rotor thrust has not yet stalled, the asymmetric electrical stress has already pushed the power distribution system close to the hardware's overcurrent protection limit. If a sudden crosswind occurs at this time, the instantaneous discharge current can easily exceed the limit, causing the aircraft to lose control and crash.

[0004] This invention addresses the specific technical blind spot of internal control margin depletion caused by asymmetric icing. It breaks through the conventional thinking of only observing external physical icing phenomena or only testing the overall thrust reduction. It proposes to map the asymmetric physical icing process of the rotor into high-frequency electrical data. By capturing the critical point of asymmetric electrical stress and triggering dynamic wind field disturbance at this moment, the true safety boundary of the aircraft under the coupling of asymmetric aerodynamic attenuation and external wind disturbance can be tested. Summary of the Invention

[0005] To achieve the above-mentioned objectives, this invention provides a method for simulating and testing the comprehensive environmental adaptability of low-altitude aircraft, comprising: Step S1: The environmental perception and data acquisition module acquires the basic operating parameters of the low-altitude aircraft, including voltage, current, angular velocity, air pressure, temperature, and rotor radius. Step S2: The aero-electric equivalent coefficient real-time calculation module calculates the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft based on the basic operating parameters; Step S3: The global asymmetric electrical stress index analysis module calculates the global asymmetric electrical stress index of the low-altitude aircraft based on the real-time equivalent power coefficient; Step S4: The wind field dynamic disturbance closed-loop control module derives the ultimate trigger threshold based on the global asymmetric electrical stress index. The wind field dynamic disturbance closed-loop control module injects gust disturbances into the test chamber based on the ultimate trigger threshold and the global asymmetric electrical stress index.

[0006] Optionally, in step S2, the calculation of the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft based on the basic operating parameters specifically includes: the aero-electric equivalent coefficient real-time calculation module obtaining the theoretical basic aerodynamic power based on the air pressure, temperature, angular velocity, and rotor radius; the aero-electric equivalent coefficient real-time calculation module obtaining the real-time electrical power based on the voltage and current; and the aero-electric equivalent coefficient real-time calculation module obtaining the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft based on the theoretical basic aerodynamic power and the real-time electrical power.

[0007] Optionally, in step S3, the calculation of the global asymmetric electrical stress index of the low-altitude aircraft based on the real-time equivalent power coefficient specifically includes: the global asymmetric electrical stress index analysis module obtaining the arithmetic mean based on the real-time equivalent power coefficients corresponding to all rotors, and the global asymmetric electrical stress index analysis module obtaining the global asymmetric electrical stress index of the low-altitude aircraft based on the real-time equivalent power coefficients corresponding to each rotor and the arithmetic mean.

[0008] Optionally, in step S4, deriving the ultimate trigger threshold based on the global asymmetric electrical stress index specifically includes: the wind field dynamic disturbance closed-loop control module obtaining the ultimate protection current and the average foundation current corresponding to the low-altitude aircraft; the wind field dynamic disturbance closed-loop control module obtaining the theoretical ultimate electrical stress index based on the ultimate protection current and the average foundation current; and the wind field dynamic disturbance closed-loop control module obtaining the ultimate trigger threshold based on the theoretical ultimate electrical stress index and the pre-stored measured foundation electrical stress index.

[0009] Optionally, the wind field dynamic disturbance closed-loop control module injects gust disturbances into the test chamber based on the limit trigger threshold and the global asymmetric electrical stress index. Specifically, the wind field dynamic disturbance closed-loop control module obtains a relative deterioration rate based on the current global asymmetric electrical stress index and the basic measured electrical stress index. The wind field dynamic disturbance closed-loop control module obtains a trigger product term based on the limit trigger threshold and a preset safety approximation coefficient. When the wind field dynamic disturbance closed-loop control module determines that the relative deterioration rate is greater than or equal to the trigger product term, it sends a command to the wind field generator in the test chamber to inject the gust disturbance.

[0010] Optionally, obtaining the basic operating parameters of the low-altitude aircraft in step S1 specifically includes: the environmental perception and data acquisition module establishing a connection with the sensor through a hardware interface; the environmental perception and data acquisition module acquiring raw analog signals through the sensor; and the environmental perception and data acquisition module performing filtering and noise reduction operations and analog-to-digital conversion operations on the raw analog signals to obtain the basic operating parameters.

[0011] Optionally, after injecting gust disturbances into the test cabin in step S4, a test result output step is also included, specifically including: the wind field dynamic disturbance closed-loop control module acquires the attitude maintenance capability data and electrical protection response data of the low-altitude aircraft during the injection of gust disturbances; the wind field dynamic disturbance closed-loop control module sends the attitude maintenance capability data and the electrical protection response data to the display terminal for display; and the wind field dynamic disturbance closed-loop control module stores the attitude maintenance capability data and the electrical protection response data in a computer-readable storage medium.

[0012] Optionally, the wind farm dynamic disturbance closed-loop control module obtains the theoretical ultimate electrical stress index based on the ultimate protection current and the average foundation current. Specifically, the wind farm dynamic disturbance closed-loop control module acquires the voltage, air pressure, temperature, and average rotational speed collected in real time at the current moment. The wind farm dynamic disturbance closed-loop control module obtains the ultimate equivalent power coefficient based on the voltage, air pressure, temperature, average rotational speed, and the ultimate protection current. The wind farm dynamic disturbance closed-loop control module obtains the basic equivalent power coefficient based on the voltage, air pressure, temperature, average rotational speed, and the average foundation current. The wind farm dynamic disturbance closed-loop control module obtains the theoretical ultimate electrical stress index based on the ultimate equivalent power coefficient and the basic equivalent power coefficient.

[0013] Optionally, the wind field dynamic disturbance closed-loop control module obtains the limit trigger threshold based on the theoretical limit electrical stress index and the pre-stored basic measured electrical stress index. Specifically, the wind field dynamic disturbance closed-loop control module extracts a preset minimum normal number, obtains a sum based on the basic measured electrical stress index and the minimum normal number, and obtains the limit trigger threshold based on the theoretical limit electrical stress index, the basic measured electrical stress index, and the sum.

[0014] Furthermore, the present invention also provides a comprehensive environmental adaptability simulation test system for low-altitude aircraft, applying the comprehensive environmental adaptability simulation test method for low-altitude aircraft as described above. The system includes: The environmental perception and data acquisition module acquires the basic operating parameters of the low-altitude aircraft, including voltage, current, angular velocity, air pressure, temperature, and rotor radius. The aero-electric equivalent coefficient real-time calculation module calculates the real-time equivalent power coefficient of each rotor in the low-altitude aircraft based on the basic operating parameters. The global asymmetric electric stress index analysis module calculates the global asymmetric electric stress index of the low-altitude aircraft based on the real-time equivalent power coefficient. The wind field dynamic disturbance closed-loop control module derives the ultimate trigger threshold based on the global asymmetric electrical stress index. The wind field dynamic disturbance closed-loop control module injects gust disturbances into the test chamber based on the ultimate trigger threshold and the global asymmetric electrical stress index.

[0015] The technical effects of this invention are as follows: This solution, by continuously monitoring the equivalent power coefficient and the global asymmetric electrical stress index, can accurately pinpoint the critical moment when the aircraft's dynamic adjustment margin is nearly exhausted due to asymmetric icing. At this moment, a transverse gust is actively injected, forcing the flight control system to perform instantaneous extreme torque compensation under its original high-load condition. This effectively detects the aircraft's true attitude maintenance capability, power distribution robustness, and extreme survival boundary under the instantaneous coupling of multiple stresses from ice, wind, and electricity, effectively eliminating false safety assessment conclusions obtained from conventional single-factor tests.

[0016] The technical solution of this invention calculates the aero-electric equivalent coefficients of each rotor in real time and further generates a global asymmetric electrical stress index, quantifying and mapping the invisible physical icing evolution process outside the aircraft as an imbalance in the internal power distribution. Based on this overall calculation logic, the system can effectively filter out the overall power reduction caused by completely uniform icing, accurately pinpoint the asymmetric icing problem that truly consumes the torque compensation margin of the flight control system, and significantly improve the ability to target and identify potential hazards in complex environments. Attached Figure Description

[0017] Figure 1 This is a flowchart illustrating a comprehensive environmental adaptability simulation test method for low-altitude aircraft. Detailed Implementation

[0018] The present invention will now be described in detail with reference to the specific embodiments shown in the accompanying drawings. However, these embodiments do not limit the present invention, and any structural, methodological, or functional modifications made by those skilled in the art based on these embodiments are included within the scope of protection of the present invention.

[0019] If the present invention involves orientation (e.g., up, down, left, right, front, back, outside, inside, etc.) when described, then the orientations involved need to be defined.

[0020] The scope of the embodiments described herein includes the entire scope of the claims and all available equivalents thereof. Throughout this document, the terms “first,” “second,” etc., are used only to distinguish one element from another without requiring or implying any actual relationship or order between the elements. Indeed, a first element can also be referred to as a second element, and vice versa. Furthermore, the terms “comprising,” “including,” or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure, apparatus, or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a structure, apparatus, or device. Without further limitations, an element defined by the phrase “comprising one…” does not exclude the presence of other identical elements in the structure, apparatus, or device that includes said element. The various embodiments described herein are presented in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably.

[0021] The terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" used in this document to indicate orientation or positional relationships are based on the orientation or positional relationships shown in the accompanying drawings and are used only for the convenience of describing this document and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention. In the description herein, unless otherwise specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to mechanical or electrical connections, or internal connections between two elements, or direct connections or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms according to the specific circumstances.

[0022] The following is in conjunction with the appendix Figure 1 This application provides a detailed description of a comprehensive environmental adaptability simulation test method for low-altitude aircraft.

[0023] This embodiment provides a comprehensive environmental adaptability simulation test method for low-altitude aircraft, including the following core steps: Step S1: The environmental perception and data acquisition module acquires the basic operating parameters of the low-altitude aircraft, including the bus voltage. Real-time current Real-time angular velocity Atmospheric pressure Ambient temperature and rotor radius .

[0024] Step S2: The aero-electric equivalent coefficient real-time calculation module calculates the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft based on the basic operating parameters. .

[0025] Step S3: The global asymmetric electric stress index analysis module analyzes the real-time equivalent power coefficient. Calculate the global asymmetric electrical stress index of the low-altitude aircraft. .

[0026] Step S4: The wind field dynamic disturbance closed-loop control module controls the wind field dynamic disturbance based on the global asymmetric electric stress index. Derivation of the Limit Trigger Threshold The wind farm dynamic disturbance closed-loop control module controls the wind farm according to the aforementioned limit trigger threshold. and the global asymmetric electric stress index Gusts of wind disturbance were injected into the test chamber.

[0027] As an optional embodiment, for step S1, the environmental perception and data acquisition module establishes a connection with the sensor through a hardware interface, acquires the original analog signal through the sensor, and performs filtering and noise reduction operations and analog-to-digital conversion operations to obtain the basic operating parameters.

[0028] The high-frequency PWM speed control of the motor inside the test chamber generates significant electromagnetic interference. Through coordinated hardware and software filtering and noise reduction, as well as high-precision analog-to-digital conversion, the bus voltage was ensured. Real-time current The purity of basic operating parameters is ensured, avoiding subsequent calculation distortion caused by glitch noise.

[0029] As an optional embodiment, for step S2, the real-time calculation module for the pneumatic-electrical equivalence coefficient is specifically based on the ambient atmospheric pressure. Ambient temperature Real-time angular velocity and rotor radius The theoretical aerodynamic power is obtained based on the bus voltage. and real-time current By obtaining the real-time electrical power, the real-time equivalent power coefficient of each rotor in the low-altitude aircraft can be obtained. .

[0030] The specific calculation formula is as follows: in is a known gas constant for air.

[0031] Specifically, real-time equivalent power factor In the calculation formula: denominator The real-time air density inside the cabin was accurately derived based on the ideal gas law. ; Convert angular velocity to rotational speed ; Convert rotor radius to rotor diameter Therefore, the denominator as a whole This represents the theoretical aerodynamic power required for a single rotor to maintain aerodynamic balance under the current environment and rotational speed. (Molecular part) This represents the actual electrical power consumed. Real-time equivalent power factor. This restores the aircraft's most realistic energy efficiency ratio. When microscopic asymmetric icing occurs on a local rotor, increasing airfoil drag, the corresponding current for that rotor needs to maintain the same rotational speed. It must be increased so that the corresponding It increases sensitively and proportionally.

[0032] Furthermore, regarding step S3, the global asymmetric electric stress index analysis module specifically analyzes the real-time equivalent power coefficients corresponding to all rotors. Calculate the arithmetic mean Furthermore, based on the real-time equivalent power coefficient corresponding to each rotor... and the arithmetic mean The global asymmetric electrical stress index of the low-altitude aircraft was obtained. The specific mathematical model is as follows: in The total number of rotors of the aircraft. Global asymmetric electrical stress index. The physical meaning is that if an aircraft experiences completely uniform icing, all rotor blades... Simultaneous rise, The problem remains at a low level; this type of uniform, overt fault is handled by routine total thrust testing. However, asymmetric icing, as a core hidden danger, can cause damage to each rotor. When discrepancies arise, the standard deviation formula acts like a magnifying glass, capturing these discrepancies and directly quantifying the hidden compensatory pressures of the flight control system into observable, independent scalars. .

[0033] In a specific application scenario, based on the dynamic derivation logic of the threshold in step S4, the wind field dynamic disturbance closed-loop control module obtains the limit protection current corresponding to the low-altitude aircraft. and the base average current Thus, the theoretical limiting electric stress index is obtained. And finally, the extreme trigger threshold is calculated. .

[0034] Specifically, the system synchronously acquires the bus voltage collected in real time at the current moment. Atmospheric pressure Ambient temperature and average speed Compare the above real-time parameters with the factory-specified ultimate protection current. Substituting into the aforementioned equivalent power coefficient equation yields the limiting equivalent power coefficient. Similarly, the base average current Substituting the values ​​yields the basic equivalent power coefficient. .

[0035] Subsequently, the following theoretical limit asymmetric state model is constructed to solve for the theoretical limit electric stress exponent. : Based on the aforementioned theoretical extreme values, the system extracts the pre-stored basic measured electrical stress index. and the preset minimal positive number The extreme trigger threshold is calculated. : When executing an action command, the system calculates the current relative deterioration rate and makes a conditional judgment, using the following formula: in, For the set safety approximation coefficient, such as Setting it to 0.9 represents approaching 90% of the dynamic theoretical limit. This occurs when the relative deterioration rate is greater than or equal to the trigger product term. At that time, a command is sent to the wind field generator in the test chamber to inject the gust disturbance instantaneously.

[0036] Although in actual engineering environments, due to factors such as motor manufacturing tolerances, minor differences in rotor dynamic balance, and inherent thermal noise of sensors, the measured electrical stress index of the foundation under healthy conditions may vary. Generally, it is a tiny measured value greater than zero, and will not be absolutely zero; however, under extremely ideal assembly conditions, in a purely digital simulation testing environment, or when limited by the data bit width truncation of the underlying acquisition device, the system's underlying calculation still faces the mathematical risk of the denominator being strictly zero. Therefore, extremely small normal numbers... The introduction of this feature forces a non-zero denominator for calculations under extreme or ideal data input conditions, thereby completely avoiding overflow crashes or system freezes caused by "division by zero" in the control program, and giving the control algorithm high industrial-grade fault tolerance and robustness. This solution substitutes real-time environmental parameters into the hardware current boundary. By performing a reverse calculation, "dynamic adaptation" of the threshold was achieved. This resolved the benchmark distortion caused by temperature and pressure drift in the testing chamber and battery power loss. Simultaneously, in the denominator... The introduction of this method establishes the mathematical baseline for preventing zero-collapse. By injecting crosswinds at the critical moment when asymmetric electrical stress depletes the system's margin, the power supply balance of the aircraft can be precisely disrupted, thereby effectively reproducing crashes caused by multi-domain coupling of ice, wind, and electricity, and avoiding overly optimistic airworthiness assessments.

[0037] As an optional embodiment, after injecting gust disturbance into the test cabin in step S4, the wind field dynamic disturbance closed-loop control module acquires the attitude maintenance capability data and electrical protection response data of the low-altitude aircraft during the injection of gust disturbance, sends the data to the display terminal for display, and stores it in a computer-readable storage medium.

[0038] The following describes a comprehensive environmental adaptability simulation test system for low-altitude aircraft provided in this application, in conjunction with the above-described method embodiments: The system employs the aforementioned method and specifically comprises four entity logic modules: The environmental perception and data acquisition module executes logic to obtain the basic operating parameters of the low-altitude aircraft, including voltage. Current angular velocity air pressure ,temperature and rotor radius ; The aero-electric equivalent coefficient real-time calculation module executes by eliminating environmental density deviations based on the aforementioned basic operating parameters and calculating the real-time equivalent power coefficients for each rotor in the low-altitude aircraft. ; The global asymmetric electric stress index analysis module executes its logic based on the real-time equivalent power coefficient. Using the standard deviation and variance principle, the global asymmetric electrical stress index of this low-altitude aircraft is calculated. ; The wind farm dynamic disturbance closed-loop control module executes its logic based on the global asymmetric electrical stress index. Derivation of the Limit Trigger Threshold And according to the aforementioned limit trigger threshold and the global asymmetric electric stress index Gusts of wind disturbance were injected into the test chamber.

[0039] Based on the same inventive concept, embodiments of this application also provide a computer-readable storage medium and an electronic terminal device. The electronic terminal device includes a general-purpose processor, a memory, a communication bus, and input / output interfaces. The program code for the aforementioned environmental perception and data acquisition module, the real-time calculation module for aero-electrical equivalence coefficients, the global asymmetric electrical stress index analysis module, and the wind field dynamic disturbance closed-loop control module is stored in the memory.

[0040] When the electronic terminal device is powered on, the communication bus is responsible for data transmission. When the program in the memory is executed by the processor, the hardware-level flow of the test logic is realized. The overall flow process can be summarized as follows: first, the extreme values ​​of asymmetric stress are extracted, and then the wind field is dynamically injected to explore the safety boundary. In this way, all the actions of the comprehensive environmental adaptability simulation test disclosed in this invention are fully realized.

[0041] The present invention can also be an apparatus, method, and / or computer program product. A computer program product may include a readable storage medium having computer-readable program instructions loaded thereon for causing a processor to implement various aspects of the present invention.

[0042] Storage media can be tangible devices that hold and store instructions for use by instruction execution devices. Storage media can include, for example, electrical storage devices, magnetic storage devices, optical storage devices, electromagnetic storage devices, semiconductor storage devices, or any suitable combination thereof. More specific examples (a non-exhaustive list) of readable storage media include: portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), static random access memory (SRAM), portable compact disc read-only memory (CD-ROM), digital multifunction disc (DVD), memory sticks, floppy disks, mechanical encoding devices, such as punch cards or recessed protrusions storing instructions thereon, and any suitable combination thereof.

[0043] It should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This way of describing the specification is only for clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

[0044] The detailed descriptions listed above are merely specific descriptions of feasible embodiments of the present invention, and are not intended to limit the scope of protection of the present invention. All equivalent embodiments or modifications made without departing from the spirit of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for simulating and testing the comprehensive environmental adaptability of low-altitude aircraft, characterized in that, include: Step S1: The environmental perception and data acquisition module acquires the basic operating parameters of the low-altitude aircraft, including voltage, current, angular velocity, air pressure, temperature, and rotor radius. Step S2: The aero-electric equivalent coefficient real-time calculation module calculates the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft based on the basic operating parameters; Step S3: The global asymmetric electrical stress index analysis module calculates the global asymmetric electrical stress index of the low-altitude aircraft based on the real-time equivalent power coefficient; Step S4: The wind field dynamic disturbance closed-loop control module derives the ultimate trigger threshold based on the global asymmetric electrical stress index. The wind field dynamic disturbance closed-loop control module injects gust disturbances into the test chamber based on the ultimate trigger threshold and the global asymmetric electrical stress index.

2. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 1, characterized in that, In step S2, the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft is calculated based on the basic operating parameters, specifically as follows: The aero-electric equivalent coefficient real-time calculation module obtains the theoretical aerodynamic power based on the air pressure, temperature, angular velocity, and rotor radius. The aero-electric equivalent coefficient real-time calculation module obtains the real-time electrical power based on the voltage and current. The aero-electric equivalent coefficient real-time calculation module obtains the real-time equivalent power coefficient corresponding to each rotor in the low-altitude aircraft based on the theoretical aerodynamic power and the real-time electrical power.

3. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 1, characterized in that, In step S3, the global asymmetric electrical stress index of the low-altitude aircraft is calculated based on the real-time equivalent power coefficient, specifically as follows: The global asymmetric electric stress index analysis module obtains the arithmetic mean based on the real-time equivalent power coefficients corresponding to all rotors. The global asymmetric electric stress index analysis module obtains the global asymmetric electric stress index of the low-altitude aircraft based on the real-time equivalent power coefficients corresponding to each rotor and the arithmetic mean.

4. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 1, characterized in that, In step S4, the ultimate triggering threshold is derived based on the global asymmetric electrical stress exponent, specifically as follows: The wind field dynamic disturbance closed-loop control module obtains the limit protection current and the average foundation current corresponding to the low-altitude aircraft. The wind field dynamic disturbance closed-loop control module obtains the theoretical limit electrical stress index based on the limit protection current and the average foundation current. The wind field dynamic disturbance closed-loop control module obtains the limit trigger threshold based on the theoretical limit electrical stress index and the pre-stored measured electrical stress index of the foundation.

5. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 4, characterized in that, The wind field dynamic disturbance closed-loop control module injects gust disturbances into the test chamber according to the ultimate trigger threshold and the global asymmetric electrical stress index, specifically as follows: The wind field dynamic disturbance closed-loop control module obtains the relative deterioration rate based on the current global asymmetric electrical stress index and the basic measured electrical stress index. The wind field dynamic disturbance closed-loop control module obtains the trigger product term based on the limit trigger threshold and the preset safety approximation coefficient. When the wind field dynamic disturbance closed-loop control module determines that the relative deterioration rate is greater than or equal to the trigger product term, it sends a command to the wind field generator in the test chamber to inject the gust disturbance.

6. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 1, characterized in that, The basic operating parameters of the low-altitude aircraft obtained in step S1 are as follows: The environmental perception and data acquisition module establishes a connection with the sensor through a hardware interface. The environmental perception and data acquisition module acquires raw analog signals through the sensor. The environmental perception and data acquisition module performs filtering and noise reduction operations and analog-to-digital conversion operations on the raw analog signals to obtain the basic operating parameters.

7. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 1, characterized in that, After injecting gust disturbances into the test chamber in step S4, the step also includes a test result output step, specifically: The wind field dynamic disturbance closed-loop control module acquires the attitude maintenance capability data and electrical protection response data of the low-altitude aircraft during the injection of gust disturbances. The wind field dynamic disturbance closed-loop control module sends the attitude maintenance capability data and the electrical protection response data to the display terminal for display. The wind field dynamic disturbance closed-loop control module stores the attitude maintenance capability data and the electrical protection response data in a computer-readable storage medium.

8. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 4, characterized in that, The wind farm dynamic disturbance closed-loop control module obtains the theoretical ultimate electrical stress index based on the ultimate protection current and the average foundation current, specifically: The wind farm dynamic disturbance closed-loop control module acquires the voltage, air pressure, temperature, and average rotational speed collected in real time at the current moment. Based on the voltage, air pressure, temperature, average rotational speed, and the ultimate protection current, the wind farm dynamic disturbance closed-loop control module obtains the ultimate equivalent power coefficient. Based on the voltage, air pressure, temperature, average rotational speed, and the average base current, the wind farm dynamic disturbance closed-loop control module obtains the basic equivalent power coefficient. Based on the ultimate equivalent power coefficient and the basic equivalent power coefficient, the wind farm dynamic disturbance closed-loop control module obtains the theoretical ultimate electrical stress index.

9. The method for simulating and testing the comprehensive environmental adaptability of a low-altitude aircraft as described in claim 4, characterized in that, The wind farm dynamic disturbance closed-loop control module obtains the ultimate trigger threshold based on the theoretical ultimate electrical stress index and the pre-stored basic measured electrical stress index, specifically as follows: The wind field dynamic disturbance closed-loop control module extracts a preset minimum normal number. The wind field dynamic disturbance closed-loop control module obtains a sum value based on the measured basic electrical stress index and the minimum normal number. The wind field dynamic disturbance closed-loop control module obtains the limit trigger threshold based on the theoretical limit electrical stress index, the measured basic electrical stress index, and the sum value.

10. A comprehensive environmental adaptability simulation test system for low-altitude aircraft, characterized in that, The method for simulating and testing the integrated environmental adaptability of a low-altitude aircraft as described in any one of claims 1 to 9, wherein the system comprises: The environmental perception and data acquisition module acquires the basic operating parameters of the low-altitude aircraft, including voltage, current, angular velocity, air pressure, temperature, and rotor radius. The aero-electric equivalent coefficient real-time calculation module calculates the real-time equivalent power coefficient of each rotor in the low-altitude aircraft based on the basic operating parameters. The global asymmetric electric stress index analysis module calculates the global asymmetric electric stress index of the low-altitude aircraft based on the real-time equivalent power coefficient. The wind field dynamic disturbance closed-loop control module derives the ultimate trigger threshold based on the global asymmetric electrical stress index. The wind field dynamic disturbance closed-loop control module injects gust disturbances into the test chamber based on the ultimate trigger threshold and the global asymmetric electrical stress index.

Images