Rotor wing unmanned aerial vehicle attitude control testing system and method and unmanned aerial vehicle

Abstract

The invention belongs to the field of unmanned aerial vehicle simulating / testing devices and discloses a rotor wing unmanned aerial vehicle attitude control testing system and method and an unmanned aerial vehicle. A lifting plate is arranged and is connected with a lifting rod through a bolt; the lifting rod is connected with a rotating plate through a locking ring; the rotating plate is fixed ona rotating arm through the bolt; the rotating arm is connected with a sliding rail through a bearing; a sliding rail structure is arranged at the bottom of a guide rail seat; the guide rail seat is connected with a rotating device base through a V groove bearing; eight V groove bearings are fixed on the rotating device base through the bolts; eccentric bearings and floating bearings are embeddedin the V groove bearings; a rotation outer ring is fixedly connected with the rotating device base; and a rotation inner ring is fixed in the rotation outer ring and is fixed on a support device through the bolt. The rotor wing unmanned aerial vehicle attitude control testing system has small limitation on the size of a tested target, can adjust the location of the center of mass of the unmanned aerial vehicle, is more smooth in rotation and higher in simulated effect; and the rotating device is small in size and high in strength and rigidity, can bear larger load and is small in deformation.

Description

technical field [0001] The invention belongs to the field of unmanned aerial vehicle simulation / testing devices, and in particular relates to a rotor unmanned aerial vehicle attitude control testing system and method, and an unmanned aerial vehicle. Background technique [0002] At present, the existing technologies commonly used in the industry are as follows: the development of domestic ground debugging equipment for drones is insufficient, and there are only a handful of patents declared. Existing devices with external frames, such as the patent "A UAV Debugging Platform", patent number CN107063235A, the size of the frame limits the size of the measured object, and increasing the size of the frame will reduce the strength and stiffness of the frame. The influence of the frame on the dynamics of the UAV will be increased by introducing a strengthening structure. The scope of the test object, the strength of the frame, and the influence on the dynamics of the UAV are mutua...

AI Technical Summary

Problems solved by technology

Increasing the test range, such as increasing the size of the drone, will inevitably lead to an increase in the size of the outer frame, which will affect the measurement results of the mechanical properties of the drone; in other words, to obtain accurate measurement results of the mechanical properties of the drone, it is impossible to increase Border strength, so that large-sized drones cannot be measured, then reduce the range of test objects

[0006] (3) The existing equipment does not have a device for adjusting the center of mass, so it is impossible to adjust the center of mass of the device so that it coincides with the center of mass of the aircraft. This is equivalent to the uneven increase of the weight of the aircraft, which is equivalent to moving up or down the center of mass of the aircraft. When the aircraft attitude changes, More power is required, so it is impossible to perfectly simulate the flight attitude of the drone, resulting in test distortion

[0007] (4) The existing device is limited by the structure

[0009] To solve the above problems, we must first abandon the outer frame design, 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 installed coaxially with the device to monitor the sensors of each flight data It is difficult to solve the placement problem, 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

Images