A method and system for rapid detection of landing overload of high-altitude skid landing gear

Abstract

This invention provides a rapid detection method and system for landing overload of high-altitude skid landing gear, relating to the field of intelligent detection technology. The method includes: acquiring the landing state of the high-altitude skid landing gear during landing, and after simulating and calculating the total landing energy, obtaining the simulated landing state of the high-altitude skid landing gear; determining whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to a preset critical load value for simulated landing of the high-altitude skid landing gear; if so, adjusting the deviation of the landing state of the high-altitude skid landing gear; and ensuring the safe landing of the high-altitude skid landing gear based on the adjustment result. This invention solves the technical problem of insufficient control over overload detection during the landing process of high-altitude skid landing gear in the prior art, which leads to overload during the final landing of the high-altitude skid landing gear. It realizes reasonable and accurate detection of overload during the landing of high-altitude skid landing gear, thereby reducing the situation of landing overload of high-altitude skid landing gear.

Description

Technical Field

[0001] This invention relates to the field of intelligent detection technology, specifically to a rapid detection system for high-altitude skid landing gear landing overload. Background Technology

[0002] With the development of skid landing gear, some helicopters can extend a tubular, ski-like frame from under the fuselage. This frame is called skid landing gear. A helicopter's skid landing gear typically has a pair of cross tubes that connect to a pair of skid tubes with four saddles. The skid tubes usually have a circular cross-section and are made of extruded aluminum or seamless drawn aluminum tubing. The saddle design generally includes a suspension system. The skids are fitted with wear-resistant strips to withstand the friction caused by slight slippage during landing and takeoff. Generally, the landing gear is bolted to the helicopter, unlike other major components that are fixed to the fuselage. The skid design provides the helicopter with a larger landing area, distributing the helicopter's entire weight across the entire skid tube. The internal suspension system of the skid landing gear absorbs the weight impact during landing, allowing the helicopter to land on various types of ground.

[0003] However, the existing technology for high-altitude skid landing gear lacks sufficient control over landing overload detection during landing, resulting in overload issues when the high-altitude skid landing gear finally lands. Summary of the Invention

[0004] This application provides a rapid detection method for landing overload of high-altitude skid landing gear, which addresses the technical problem of insufficient control over landing overload detection during the landing process of high-altitude skid landing gear in the prior art, resulting in overload during the final landing of the high-altitude skid landing gear.

[0005] In view of the above problems, this application provides a method and system for rapid detection of high-altitude skid landing gear landing overload.

[0006] In a first aspect, this application provides a method for rapid detection of landing overload of high-altitude skid landing gear. The method includes: acquiring the landing state of the high-altitude skid landing gear during landing; performing simulation calculations based on the landing state to obtain the total landing energy; obtaining the simulated landing state of the high-altitude skid landing gear based on the total landing energy; obtaining a preset critical load value for simulated landing of the high-altitude skid landing gear; determining whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear; if so, adjusting the deviation of the landing state of the high-altitude skid landing gear, and ensuring safe landing of the high-altitude skid landing gear according to the adjustment result.

[0007] Secondly, this application provides a rapid detection system for landing overload of high-altitude skid landing gear. The system includes: a landing state acquisition module for acquiring the landing state of the high-altitude skid landing gear during landing; a simulation calculation module for performing simulation calculations based on the landing state to obtain the total landing energy; a simulated landing state acquisition module for obtaining the simulated landing state of the high-altitude skid landing gear based on the total landing energy; a critical load value acquisition module for obtaining a preset critical load value for simulated landing of the high-altitude skid landing gear; a judgment module for judging whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value; and a deviation adjustment module for adjusting the landing state of the high-altitude skid landing gear if the condition is met, and ensuring safe landing of the high-altitude skid landing gear based on the adjustment result.

[0008] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0009] This application provides a rapid detection method for landing overload of high-altitude skid landing gear, which relates to the field of intelligent detection technology. It solves the technical problem that the existing technology lacks sufficient control over landing overload detection during the landing process of high-altitude skid landing gear, resulting in overload during landing. The method realizes reasonable and accurate detection of overload during landing of high-altitude skid landing gear, thereby reducing the situation of landing overload of high-altitude skid landing gear. Attached Figure Description

[0010] Figure 1 This application provides a schematic flowchart of a rapid detection method for high-altitude skid landing gear landing overload.

[0011] Figure 2 This application provides a schematic diagram of a high-altitude skid landing gear landing overload rapid detection system.

[0012] Explanation of reference numerals in the attached diagram: Landing status acquisition module 1, Simulation verification module 2, Simulated landing status acquisition module 3, Critical load value acquisition module 4, Judgment module 5, Deviation adjustment module 6. Detailed Implementation

[0013] This application provides a rapid detection method for landing overload of high-altitude skid landing gear, which solves the technical problem of insufficient control over landing overload detection during the landing process of high-altitude skid landing gear in the prior art, resulting in overload during the final landing of the high-altitude skid landing gear.

[0014] Example 1

[0015] like Figure 1 As shown in the figure, this application provides a method for rapid detection of landing overload of high-altitude skid landing gear, the method comprising:

[0016] Step S100: Obtain the landing status of the high-altitude skid landing gear during landing;

[0017] Specifically, the high-altitude skid landing gear landing overload rapid detection method provided in this application embodiment is applied to a high-altitude skid landing gear landing overload rapid detection system. The system is communicatively connected to a sensor, which is used to collect high-altitude skid landing gear landing parameters.

[0018] Because high-altitude skid landing gear may experience overload during landing, it is necessary to acquire the aircraft's center of gravity information during landing using a balancer and the aircraft's landing speed information using a speed sensor. Furthermore, based on the aircraft's center of gravity and landing speed during landing, the aircraft's landing attitude data is determined and extracted. Finally, the aircraft's landing attitude data is added to the landing status data of the high-altitude skid landing gear, providing an important reference for ensuring the safe landing of the high-altitude skid landing gear in the future.

[0019] Step S200: Perform simulation calculations based on the landing state to obtain the total landing energy;

[0020] Specifically, in order to analyze the landing performance of skid landing gear in advance, a modal analysis platform was used to establish a landing simulation model of skid landing gear, and landing performance simulation calculations were performed to obtain the kinetic energy and potential energy of the aircraft before touchdown, as well as the energy absorbed by the landing gear. Based on the skid landing gear drop test, the landing performance parameters of the landing gear were measured. By comparing the simulation analysis results with the experimental measured data, the feasibility of the landing gear landing performance analysis method based on the analysis platform was verified in engineering. At the same time, the total energy of the aircraft during landing was obtained by combining simulation calculations with experimental results, providing a reference for ensuring the safe landing of high-altitude skid landing gear.

[0021] Step S300: Based on the total landing energy, obtain the simulated landing state of the high-attitude skid landing gear;

[0022] Specifically, during the landing of a high-altitude skid landing gear, to absorb excess energy generated during severe or partial impact landings, the shock absorbers in the high-altitude skid landing gear prevent their pistons from fully bottoming out, even in the compression position. The reserved air volume (assumed to be 10% of the displacement) allows the shock absorber struts to travel an additional stroke under a predetermined load, thereby absorbing excess energy through work and obtaining the high-altitude skid landing gear load-stroke curve. The total landing energy obtained through simulation is then converted to obtain the objective function corresponding to the high-altitude skid landing gear load-stroke curve. Based on theoretical calculations and QAR data, the characteristic curve of the dual-chamber landing gear corresponding to the load-stroke curve is derived. Finally, based on the obtained objective function and the obtained dual-chamber landing gear characteristic curve, the landing state of the high-altitude skid landing gear is simulated, thereby generating a simulated landing state of the high-altitude skid landing gear, ensuring a safe landing for the high-altitude skid landing gear.

[0023] Step S400: Obtain the preset high-attitude skid landing gear simulated landing critical load value;

[0024] Specifically, to quickly detect whether the high-altitude skid landing gear is overloaded during landing, a preset value needs to be set as a reference standard. First, based on a BP neural network, the objective function calculated above and the characteristic curve of the dual-chamber landing gear are used as input training data to train the simulated landing load model of the high-altitude skid landing gear. Further, the simulated landing load model of the high-altitude skid landing gear is iteratively trained based on the objective function and the characteristic curve of the dual-chamber landing gear. When the simulated landing load error parameter of the high-altitude skid landing gear meets the preset requirements for a preset number of consecutive times, it is considered that the simulated landing load model of the high-altitude skid landing gear has converged. Finally, the objective function and the characteristic curve of the dual-chamber landing gear are input into the converged simulated landing load model of the high-altitude skid landing gear, thereby outputting the preset critical load value for simulated landing of the high-altitude skid landing gear, laying a solid foundation for the subsequent safe landing of the high-altitude skid landing gear.

[0025] Step S500: Determine whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear;

[0026] Specifically, during the landing process of the high-altitude skid landing gear, a stability analysis of the simulated landing state is performed. Based on the results of the stability analysis, the simulated landing state of the high-altitude skid landing gear is judged to determine whether it is greater than or equal to a preset critical load value for simulated landing. This allows for the identification of aircraft landing with a load value greater than or equal to the preset critical load value. Simultaneously, feature analysis is performed on the high-altitude skid landing gear data to obtain overload information for the simulated landing state of the high-altitude skid landing gear, which plays a limiting role in achieving safe landing of the high-altitude skid landing gear.

[0027] Step S600: If yes, then the landing state of the high-altitude skid landing gear is adjusted to ensure safe landing of the high-altitude skid landing gear according to the adjustment result.

[0028] Specifically, the system first determines whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing. When the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value, it is considered that the landing state of the high-altitude skid landing gear is in an overload state. Based on the current overload state, the high-altitude skid landing gear is adjusted for overload deviation. Based on the current overload situation, the center of gravity and speed of the aircraft are also adjusted for overload deviation. The results of the deviation adjustment are used to make appropriate adjustments to the current high-altitude skid landing gear. This achieves reasonable and accurate detection of overload during landing of the high-altitude skid landing gear, thereby reducing the overload situation of the high-altitude skid landing gear.

[0029] Furthermore, step S100 of this application also includes:

[0030] Step S110: Obtain the aircraft's center of gravity information during landing;

[0031] Step S120: Obtain aircraft landing speed information through sensors;

[0032] Step S130: Determine the landing attitude data of the aircraft based on the aircraft's center of gravity and landing speed;

[0033] Step S140: Add the aircraft landing attitude data to the landing state when the high-attitude skid landing gear lands.

[0034] Specifically, the X and Y axis center of gravity positions of the helicopter are calculated based on the principle of torque balance. Then, the Z axis center of gravity position is calculated by measuring the tilt angle using vertical suspension. The rotational inertia of the helicopter about the X and Y axes is measured and calculated. The Z-axis rotational inertia is measured using a scaled-down helicopter model. Three small balls are placed in the model to adjust the helicopter model's center of gravity to the experimental measurement position. The rotational inertia of the X and Y axes matches the experimental measurement data, thus obtaining the value of the Z-axis rotational inertia and acquiring the helicopter's center of gravity information. Furthermore, the current helicopter speed is monitored using a speed sensor. Based on the aircraft's center of gravity and landing speed, the landing attitude data is determined, and corresponding control is applied to the aircraft's center of gravity and landing speed based on the helicopter's landing attitude. The landing of a high-skid landing gear must be determined based on specific factors such as the size of the landing area, atmospheric conditions, the height of surrounding obstacles, and the takeoff weight. The aircraft's landing attitude can be corrected based on the obtained center of gravity and landing speed to avoid overload during high-skid landing gear landings. The aircraft's landing attitude includes normal vertical landing, vertical landing over obstacles, runway landing, and gliding landing with rotor rotation. Finally, the aircraft's landing attitude data is added to the landing status of the high-skid landing gear as part of the landing status output, which has a profound impact on the subsequent safe landing of the high-skid landing gear.

[0035] Furthermore, step S200 of this application also includes:

[0036] Step S210: Obtain the kinetic energy of the aircraft before it touches down;

[0037] Step S220: Obtain the potential energy of the aircraft before it touches down;

[0038] Step S230: Calculate the kinetic energy of the aircraft before touchdown, the potential energy of the aircraft before touchdown, and obtain the total energy of the aircraft upon landing.

[0039] Specifically, according to Where m is the mass of the aircraft, v is the vertical velocity of the aircraft, the kinetic energy of the aircraft before touchdown is obtained, and then the potential energy of the aircraft before touchdown is obtained according to the formula mgh, where m is the mass of the aircraft, g is the gravitational acceleration of the aircraft, and h is the height of the aircraft above the horizontal plane.

[0040] Furthermore, the total energy (E) of an aircraft during landing consists of kinetic energy and potential energy, which can be expressed by the following expression:

[0041]

[0042] Where W is the aircraft weight, V is the descent speed (descent rate), g is the gravitational acceleration, L is the wing lift, St is the tire compression distance, and S is the shock absorber stroke. By substituting the kinetic energy and potential energy of the aircraft before touchdown into the above formula, the total energy of the aircraft during landing can be calculated, thus providing an important basis for the safe landing of high-attitude skid landing gear in the future.

[0043] Furthermore, step S300 of this application also includes:

[0044] Step S310: Obtain the load-stroke curve of the high-altitude skid landing gear;

[0045] Step S320: Convert the total landing energy to obtain the objective function corresponding to the load stroke curve of the high-attitude skid landing gear;

[0046] Step S330: Derive the dual-chamber landing gear characteristic curve based on the load-stroke curve;

[0047] Step S340: Based on the objective function and the characteristic curve of the dual-chamber landing gear, generate the simulated landing state of the high-altitude skid landing gear.

[0048] Specifically, to absorb excess energy generated during severe or partial impact landings, the pistons in the high-altitude skid landing gear are not fully bottomed out, even in the compression position. The reserved air volume (assumed to be 10% of displacement) allows the shock struts to travel an additional stroke under a predetermined load, thus absorbing excess energy by doing work. The energy absorbed by the shock struts is obtained by integrating the area under the load-stroke curve during their stroke, which correlates the magnitude of the applied ground load with the distance traveled.

[0049] Furthermore, based on the aircraft landing energy conversion formula, the total landing energy is converted into the following formula:

[0050]

[0051] F(x) is the function corresponding to the landing gear (including shock absorber struts and tires) load-stroke curve, L is the wing lift, d is the landing gear compression stroke, m is the aircraft mass, v is the aircraft vertical velocity (downward is positive, unit is m / s), and W is the aircraft weight. Thus, the objective function corresponding to the high-altitude skid landing gear load-stroke curve is obtained. Further calculations are performed based on theoretical calculations and QAR data. This QAR data is important flight data for flights and is a mirror image of the airborne black box. It is often used for post-flight technical analysis, engine health analysis, flight safety incident investigation, etc. It is an important data warehouse in flight quality analysis, operational quality analysis, and aircraft health management. Then, the characteristic curve of the dual-chamber landing gear is derived from the load-stroke curve to simulate the current landing state of the high-altitude skid landing gear, so as to ensure the safety of high-altitude skid landing gear landing.

[0052] Furthermore, step S400 of this application also includes:

[0053] Step S410: Using the objective function and the characteristic curve of the dual-chamber landing gear as input training data, train the high-attitude skid landing gear simulation landing load model based on the BP neural network;

[0054] Step S420: Iteratively train the high-altitude skid landing gear simulated landing load model according to the objective function and the characteristic curve of the dual-chamber landing gear. When the high-altitude skid landing gear simulated landing load error parameters meet the preset requirements for a preset number of consecutive times, it is considered that the high-altitude skid landing gear simulated landing load model has converged.

[0055] Step S430: Input the objective function and the characteristic curve of the dual-chamber landing gear into the converged high-altitude skid landing gear simulated landing load model to obtain the preset high-altitude skid landing gear simulated landing critical load value.

[0056] Specifically, based on a BP neural network, the objective function and the characteristic curve of the dual-chamber landing gear are used as input training data to simulate the landing load model of the high-altitude skid landing gear. The high-altitude skid landing gear simulated landing load model is a BP neural network model in machine learning that can continuously perform self-iterative optimization. The high-altitude skid landing gear simulated landing load model is trained through training datasets and supervised datasets. Each set of training data in the training dataset includes the objective function and the characteristic curve of the dual-chamber landing gear; the supervised dataset is the supervised data that corresponds one-to-one with the training dataset.

[0057] Furthermore, the construction process of the high-altitude skid landing gear simulated landing load model is as follows: each set of training data in the training dataset is input into the high-altitude skid landing gear simulated landing load model. The output of the high-altitude skid landing gear simulated landing load model is adjusted by the supervision data corresponding to this set of training data. When the output result of the high-altitude skid landing gear simulated landing load model is consistent with the supervision data, the training of the current set ends. The training of all training data in the training dataset is completed, and the training of the high-altitude skid landing gear simulated landing load model is completed.

[0058] To ensure the accuracy of the high-altitude skid landing gear simulated landing load model, the accuracy of the output results of the high-altitude skid landing gear simulated landing load model can be evaluated by using the load data of the high-altitude skid landing gear. For example, the test accuracy can be set to 85%. When the test accuracy meets 85%, the preset high-altitude skid landing gear simulated landing critical load value is obtained.

[0059] The high-altitude skid landing gear simulated landing load error parameters are used to iteratively train the high-altitude skid landing gear simulated landing load model. When the high-altitude skid landing gear simulated landing load error parameters meet a preset requirement for a predetermined number of consecutive iterations, the number of iterations for training the high-altitude skid landing gear simulated landing load model is limited. For example, if the number of iterations is limited to 10, then when the high-altitude skid landing gear simulated landing load error parameters meet the preset requirement for training the high-altitude skid landing gear simulated landing load model... After the landing gear simulation landing load model is iterated and trained 10 times, if the current high-altitude skid landing gear simulation landing load error parameters meet the preset requirements, it is considered that the high-altitude skid landing gear simulation landing load model has converged. Finally, the objective function and the dual-chamber landing gear characteristic curve are input into the converged high-altitude skid landing gear simulation landing load model to obtain the preset high-altitude skid landing gear simulation landing critical load value, thereby achieving a more accurate technical effect of safe landing of the high-altitude skid landing gear.

[0060] Furthermore, step S500 of this application also includes:

[0061] Step S510: Perform stability analysis on the simulated landing state of the high-altitude skid landing gear to obtain the landing stability analysis results;

[0062] Step S520: Based on the landing stability analysis results, a landing body with a value greater than or equal to the preset high-attitude skid landing gear simulated landing critical load value is obtained;

[0063] Step S530: Perform feature analysis on the high-altitude skid landing gear data corresponding to the identified landing body to obtain overload information of the simulated landing state of the high-altitude skid landing gear.

[0064] Specifically, a stability analysis of the landing state is performed on the simulated landing state of the high-altitude skid landing gear obtained through the total landing energy. This stability analysis refers to the helicopter's ability to withstand external geological disturbances during landing. The results of this stability analysis are then evaluated to determine if they are greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear. If the result is greater than or equal to this preset critical load value, it is considered that the current high-altitude skid landing gear landing state is stable. If the skid landing gear lands, a landing overload will occur. The landing stability analysis result is greater than or equal to the preset critical landing load value of the high-altitude skid landing gear. The landing body corresponding to this is the helicopter, which is then marked. The high-altitude skid landing gear data corresponding to the marked landing body is then used to analyze different characteristics such as lateral span, longitudinal span, and stopping angle. Based on this, the overload information of the high-altitude skid landing gear in the simulated landing state is obtained. This achieves the technical effect of providing an important basis for the safe landing of the high-altitude skid landing gear in the later stage.

[0065] Example 2

[0066] Based on the same inventive concept as the high-altitude skid landing gear landing overload rapid detection method in the foregoing embodiments, such as Figure 2 As shown, this application provides a rapid detection system for high-altitude skid landing gear landing overload, the system comprising:

[0067] Landing status acquisition module 1, the landing status acquisition module 1 is used to acquire the landing status when the high-attitude skid landing gear lands;

[0068] Simulation verification module 2 is used to perform simulation verification based on the landing state to obtain the total landing energy;

[0069] The simulated landing state acquisition module 3 is used to obtain the simulated landing state of the high-attitude skid landing gear based on the total landing energy.

[0070] Critical load value acquisition module 4, which is used to obtain a preset critical load value for simulated landing of high-inclination skid landing gear;

[0071] Judgment module 5, the judgment module 5 is used to determine whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear;

[0072] Deviation adjustment module 6 is used to adjust the landing state of the high-altitude skid landing gear if the condition is met, and to ensure the safe landing of the high-altitude skid landing gear based on the adjustment result.

[0073] Furthermore, the system also includes:

[0074] Center of gravity module, used to obtain the aircraft's center of gravity information during landing;

[0075] The speed module is used to obtain aircraft landing speed information through sensors;

[0076] The first judgment module is used to judge the landing attitude data of the aircraft based on the center of gravity of the aircraft and the landing speed of the aircraft.

[0077] The addition module is used to add the aircraft landing attitude data to the landing state when the high-attitude skid landing gear lands.

[0078] Furthermore, the system also includes:

[0079] The kinetic energy module is used to obtain the kinetic energy of the aircraft before it touches down.

[0080] Potential energy module, used to obtain the potential energy of the aircraft before it touches down;

[0081] The calculation module is used to calculate the kinetic energy of the aircraft before touchdown, the potential energy of the aircraft before touchdown, and to obtain the total energy of the aircraft upon landing.

[0082] Furthermore, the system also includes:

[0083] The first curve module is used to obtain the load-stroke curve of the high-altitude skid landing gear.

[0084] The objective function module is used to convert the total landing energy into an objective function corresponding to the load stroke curve of the high-attitude skid landing gear.

[0085] The second curve module is used to derive the dual-chamber landing gear characteristic curve based on the load stroke curve.

[0086] The simulated landing state generation module is used to generate the simulated landing state of the high-attitude skid landing gear based on the objective function and the characteristic curve of the dual-chamber landing gear.

[0087] Furthermore, the system also includes:

[0088] The model training module is used to train a high-attitude skid landing gear simulation landing load model based on a BP neural network, using the objective function and the characteristic curve of the dual-chamber landing gear as input training data.

[0089] The model convergence module is used to iteratively train the high-altitude skid landing gear simulated landing load model based on the objective function and the characteristic curve of the dual-chamber landing gear. When the high-altitude skid landing gear simulated landing load error parameters meet the preset requirements for a preset number of consecutive times, it is considered that the high-altitude skid landing gear simulated landing load model has converged.

[0090] The input module is used to input the objective function and the characteristic curve of the dual-chamber landing gear into the converged high-altitude skid landing gear simulated landing load model to obtain the preset high-altitude skid landing gear simulated landing critical load value.

[0091] Furthermore, the system also includes:

[0092] The stability analysis module is used to perform stability analysis on the simulated landing state of the high-attitude skid landing gear and obtain the landing stability analysis results.

[0093] The landing body identification module is used to determine, based on the landing stability analysis results, a landing body identification module that is greater than or equal to the preset high-attitude skid landing gear simulated landing critical load value.

[0094] The feature analysis module is used to perform feature analysis on the high-altitude skid landing gear data corresponding to the identified landing body to obtain overload information of the high-altitude skid landing gear in the simulated landing state.

[0095] Through the foregoing detailed description of a rapid detection method for high-altitude skid landing gear landing overload, those skilled in the art can clearly understand the rapid detection method and system for high-altitude skid landing gear landing overload in this embodiment. As for the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and relevant parts can be referred to in the method section.

[0096] The above description of the disclosed embodiments enables those skilled in the art to make or use this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A rapid detection method for landing overload of high-altitude skid landing gear, characterized in that, The method includes: Acquire the landing status during high-altitude skid landing gear landing; Based on the landing state, a simulation calculation was performed to obtain the total landing energy. Based on the total landing energy, the simulated landing state of the high-attitude skid landing gear is obtained; Obtain the preset critical landing load value for high-altitude skid landing gear; Determine whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear; If so, the landing state of the high-altitude skid landing gear is adjusted to ensure a safe landing.

2. The method as described in claim 1, characterized in that, The acquisition of the landing state during high-altitude skid landing gear landing includes: Obtain aircraft center of gravity information during landing; The aircraft's landing speed information is obtained through sensors; The landing attitude data of the aircraft is determined based on the aircraft's center of gravity and landing speed. The aircraft landing attitude data is added to the landing status when the high-altitude skid landing gear lands.

3. The method as described in claim 1, characterized in that, The obtained total landing energy includes: To obtain the kinetic energy before the aircraft touches down; To obtain the potential energy of the aircraft before it touches down; Calculate the kinetic energy and potential energy of the aircraft before touchdown, and obtain the total energy of the aircraft upon landing.

4. The method as described in claim 1, characterized in that, The process of obtaining the simulated landing state of the high-altitude skid landing gear includes: Obtain the load-stroke curve of the high-altitude skid landing gear; The total landing energy is converted to obtain the objective function corresponding to the load stroke curve of the high-attitude skid landing gear. Then, based on the load-stroke curve, the characteristic curve of the dual-chamber landing gear is derived; Based on the objective function and the characteristic curve of the dual-chamber landing gear, the simulated landing state of the high-altitude skid landing gear is generated.

5. The method as described in claim 1, characterized in that, The process of obtaining the preset high-altitude skid landing gear simulated landing critical load value includes: Using the objective function and the characteristic curve of the dual-chamber landing gear as input training data, a high-attitude skid landing gear simulation landing load model is trained based on a BP neural network. The high-altitude skid landing gear simulated landing load model is iteratively trained based on the objective function and the characteristic curve of the dual-chamber landing gear. When the high-altitude skid landing gear simulated landing load error parameters meet the preset requirements for a preset number of consecutive times, the high-altitude skid landing gear simulated landing load model is considered to have converged. The objective function and the characteristic curve of the dual-chamber landing gear are input into the converged high-altitude skid landing gear simulated landing load model to obtain the preset high-altitude skid landing gear simulated landing critical load value.

6. The method as described in claim 1, characterized in that, The step of determining whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear includes: Stability analysis was performed on the simulated landing state of the high-altitude skid landing gear to obtain landing stability analysis results; Based on the landing stability analysis results, a landing body with a value greater than or equal to the preset high-attitude skid landing gear simulated landing critical load value is identified. By performing feature analysis on the high-altitude skid landing gear data corresponding to the identified landing body, overload information of the high-altitude skid landing gear in simulated landing state is obtained.

7. A rapid detection system for high-altitude skid landing gear landing overload, characterized in that, The system includes: A landing status acquisition module, which is used to acquire the landing status when the high-inclination skid landing gear lands; A simulation verification module is used to perform simulation verification based on the landing state to obtain the total landing energy. A simulated landing state acquisition module is used to obtain the simulated landing state of the high-attitude skid landing gear based on the total landing energy. A critical load value acquisition module is used to obtain a preset critical load value for simulated landing of a high-inclination skid landing gear. The judgment module is used to determine whether the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear. The deviation adjustment module is used to adjust the landing state of the high-altitude skid landing gear if the simulated landing state of the high-altitude skid landing gear is greater than or equal to the preset critical load value for simulated landing of the high-altitude skid landing gear, and to ensure the safe landing of the high-altitude skid landing gear based on the adjustment result.

Images