A dynamic analysis method for UAV flexible flight considering complex wind field

A technology of flight dynamics and analysis methods, applied in computer-aided design, instrumentation, design optimization/simulation, etc., can solve problems such as unstable motion modes, low rigid body free flutter velocity, structural damage, etc., and achieve important application value Effect

Active Publication Date: 2022-05-20
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

Due to the large wingspan of ultra-long-endurance drones, a large number of lightweight structures need to be used. This type of design leads to a sharp increase in the flexibility of the aircraft, which is prone to rigid and elastic coupling, resulting in structural damage or stalling. Not only In this way, when the natural frequency of the UAV flexible structure is very low, the rigid motion will lead to an unstable motion mode or a lower free vibration velocity of the rigid body, which will have an adverse effect on the scheme design

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  • A dynamic analysis method for UAV flexible flight considering complex wind field
  • A dynamic analysis method for UAV flexible flight considering complex wind field
  • A dynamic analysis method for UAV flexible flight considering complex wind field

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Embodiment Construction

[0021] The following combined with the accompanying drawings and embodiments of the UAV flexible flight dynamics analysis method considering the complex wind field is further detailed. Flowchart as shown Figure 1 shown, including the following steps:

[0022] (1) Using the average shaft system theory, the flight dynamics equation of the UAV is established, and the equation is leveled under the assumption of small disturbance;

[0023] In step (1), using the average shaft system theory, the UAV flight dynamic equation is established, which can be obtained from the previous aerodynamic derivatives, and the coupling degree of the longitudinal and horizontal directions of the aircraft is not high, and the coupling term is removed, and the differential equation is linearized at the same time, and the small perturbation linear equation can be obtained;

[0024] (2) Based on the mode truncation method, the equation of elastic motion of the wing under modal coordinates is established;

[...

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Abstract

The invention discloses a flexible flight dynamics analysis method for unmanned aerial vehicles considering complex wind fields. The average shaft system theory is used to establish the unmanned aerial vehicle flight dynamics equation, and the equation is trimmed under the assumption of small disturbances. State truncation method, establish the elastic motion equation of the wing under the modal coordinates, use the second-order system to simulate the reaction process of the steering gear, convert the transfer function of the above steering gear model into the form of state space, and convert the flight dynamics of the state space form The wind gust response of the UAV can be obtained by coupling the scientific model, the atmospheric model, and the steering gear model.

Description

Technical field [0001] The present invention belongs to the field of UAV technology, specifically involving a UAV flexible flight dynamics analysis method considering a complex wind field, which may be used to consider the study of uAV flexible flight dynamics analysis methods for complex wind fields. Background [0002] Unmanned aerial vehicles are an indispensable and important weapon in modern high-tech warfare, a powerful tool for winning wars and performing major tasks, and have developed into a hot spot for the development of various military powers. In civilian areas such as disaster monitoring and emergency response, remote sensing of the earth, drones are playing an important role. In recent years, long-range UAV and new energy ultra-long-term UAV have become hot spots in research. When the UAV is flying in the air, especially through the air over the complex terrain environment such as mountainous areas or in the harsh weather conditions, it often encounters various ser...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/28G06F113/08G06F119/14
CPCG06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 李道春赵仕伟谭溥学申童阚梓邵浩原姚卓尔向锦武
Owner BEIHANG UNIV
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