Efficient balancing method for flight kinetic model of fixed-wing aircraft

Abstract

The invention belongs to the technical field of aircraft design, and particularly relates to an efficient fixed-wing aircraft flight dynamics model balancing method, which comprises the following steps of: giving balancing calculation precision according to design calculation requirements, comparing a calculation value with given precision in each calculation step during balancing calculation, ifthe calculation value meets a precision requirement, ending balancing calculation, and if the calculation value meets the precision requirement, finishing balancing calculation; taking the attack angle, the elevator deflection angle and the accelerator opening degree calculated in the step as balancing results; and if the calculation value does not meet the precision requirement, continuing iterative calculation until the precision requirement is met or the given state point is judged to be located outside the flight envelope in the calculation process. The method has the characteristics of global fast convergence, low requirement on an initial value, simple algorithm and easiness in mastering and program implementation. Complex calculation of dynamics and kinematics equations is not needed in the calculation process, the iterative calculation amount is reduced, and the balancing efficiency is improved. All parameters in balancing calculation are calculated in a dimensionless form, sothat the accuracy of a balancing result is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and in particular relates to an efficient method for trimming a flight dynamics model of a fixed-wing aircraft. Background technique [0002] In the field of aircraft overall performance design and flight control law design, the trimming of flight dynamics model is the basis of each design content, and the correctness of trimming results and the accuracy of trimming have an important impact on aircraft design. [0003] For fixed-wing aircraft, the overall performance design of the aircraft, such as the design or calculation of the flight envelope, cruising altitude, range, flight time, and mission planning, is based on the trim calculation of the dynamic model; In the process of control law design, tasks such as cruise performance analysis, stability analysis, control structure design, control parameter tuning, time-frequency domain analysis, and robustness analysis are closely related to...

AI Technical Summary

Problems solved by technology

The advantage of genetic algorithm is that it has global convergence characteristics, strong group search ability, and fast initial optimization speed, but genetic algorithm still has the defects of slow subsequent optimization speed and low precision.

[0007] Combining the advantages of Newton's method and genetic algorithm, some scholars have studied a hybrid genetic algorithm with global fast convergence characteristics. This algorithm realizes the combination of the advantages of traditional numerical calculation methods and modern intelligent calculation methods, but still cannot avoid complex The solution process of nonlinear equations, and in practical applications, practitioners in the field of aircraft design are required to master certain modern intelligent calculation methods. The combination of the two algorithms makes the algorithm complex and difficult to understand and program.

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