Posture simulation system and method for rotary wing unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicle simulation / testing devices, and discloses a posture simulation system and method for a rotary wing unmanned aerial vehicle. Theposture simulation system is provided with a rotation inner ring, and the rotation inner ring is connected with a supporting device through a bolt; the rotation inner ring is positioned in a rotationouter ring; the rotation inner ring and the rotation outer ring form a bearing-similar structure and can relatively rotate; the rotation outer ring and a rotating device base are connected through a bolt; V-shaped pulleys are fixed to the rotating device base through fixed set screws; and the V-shaped pulleys are fixed to the upper and lower sides of a guide rail seat and are used for clamping theguide rail seat. According to the posture simulation system, simulation of three degrees of freedom of the rotary wing unmanned aerial vehicle can be achieved, rotation centers of the three degrees of freedom coincide with one another, and simulation of yawing, pitching and overturning flying postures of the unmanned aerial vehicle is achieved; and simulation of motion of the three degrees of freedom is achieved through three rotating devices, the three rotating devices adopt bearings, additional friction force of the rotating devices is quite small, and a better simulation effect is achieved.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicle simulation / testing devices, and in particular relates to a system and method for attitude simulation of a rotor unmanned aerial vehicle. Background technique [0002] At present, the existing technologies commonly used in the industry are as follows: [0003] The development of domestic ground debugging equipment for UAVs is insufficient. The size of the frame of the existing external frame device limits the size of the measured object. If the frame size is increased when the frame thickness is the same, the frame length will It will reduce the strength and rigidity of the frame; this will reduce the stability of the structure, and the aircraft may vibrate up and down after running on the device, resulting in distortion of the measurement structure. However, increasing the strength of the frame by introducing a reinforced structure will increase the weight of the entire test equip...

AI Technical Summary

Problems solved by technology

[0005] (1) The scope of the test object, the strength of the frame, and the influence on the dynamics of the UAV are mutually restricted. The rotation centers of the three degrees of freedom of the device do not coincide, and the relative position of the aircraft cannot be adjusted so that the center of mass of the aircraft coincides with the rotation center of the device.

[0006] (2) The size of the frame of the existing external frame device limits the size of the object to be measured. Increasing the size of the frame will reduce the strength and stiffness of the frame. The influence of

[0007] The difficulty and significance of solving the above technical problems: To solve the above problems, the outer frame design must be abandoned first, which can solve the problem of accurate measurement of the flight performance of large-scale aircraft, and at the same time take into account the detection of flight data, so that the angle sensor needs to be synchronized with the equipment. shaft installation, it is difficult to solve the problem of placement of sensors for monitoring various flight data, which greatly increases the difficulty of structural design

And in order to obtain real flight data, the center of mass of the aircraft, the center of mass of the equipment and the center of rotation of the equipment must be coincident, which further increases the difficulty of structural design

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