Longitudinal aerodynamic parameter identification and calculation method in closed-loop state and large angle-of-attack range

By using flight simulation and genetic algorithms to optimize longitudinal aerodynamic parameters in a closed-loop state of the UAV, the problem of accuracy in identifying longitudinal aerodynamic characteristics in a large angle of attack range was solved, and efficient aerodynamic parameter identification and model applicability improvement were achieved for different types of UAVs.

CN121835199APending Publication Date: 2026-04-10XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Patent Information

Application Number
CN202512054082.9
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-12-31
Publication Date
2026-04-10

AI Technical Summary

Technical Problem

Existing technologies make it difficult to accurately identify longitudinal aerodynamic characteristics within a large angle-of-attack range using simulation methods under closed-loop control of unmanned aerial vehicles (UAVs).

Method used

A flight simulation and optimization calculation method was adopted. The longitudinal aerodynamic parameters were optimized by genetic algorithm. Combined with flight test data, the angle of attack range was divided and the optimal aerodynamic parameters were identified in each sub-range. A complete flight simulation model was constructed to verify the accuracy of the model.

Benefits of technology

It achieves accurate identification of longitudinal aerodynamic parameters over a wide angle of attack range, improving the model's applicability and parameter identification efficiency, and is suitable for different types of UAVs.

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Abstract

The invention belongs to the technical field of unmanned aerial vehicle aircraft design, and particularly relates to a longitudinal aerodynamic parameter identification calculation method in a closed-loop state and a large angle-of-attack range, and the method comprises the steps: building a flight simulation model; performing aerodynamic characteristic simulation based on a flight simulation model to obtain an aerodynamic load value, comparing the aerodynamic load value with data tested in an actual flight experiment, and calculating and minimizing an error sum of squares; dividing the whole angle-of-attack range into a plurality of sub-intervals, respectively obtaining the optimal aerodynamic parameters of each sub-interval based on the minimum sum of squares of errors, inputting each optimal aerodynamic parameter into the flight simulation model, and carrying out model accuracy verification; and drawing an aerodynamic characteristic curve according to each optimal aerodynamic parameter, and verifying the applicability of the flight simulation model. The method has universality and is suitable for longitudinal aerodynamic coefficient parameter identification of different types of unmanned aerial vehicles, the parameter identification efficiency is improved, and meanwhile the applicability of the model under the complex flight working condition is enhanced.
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