Flight parameter measurement system for small-size bypass aircraft

Abstract

The invention discloses a flight parameter measurement system for a small-size bypass aircraft, which can achieve the purpose of enhancing the measurement convenience and the accuracy of measured data. The flight parameter measurement system for the small-size bypass aircraft comprises a test platform seat, a linear guide rail, a torque sensor, a universal joint coupler, five stretch-press measuring devices, the small-size bypass aircraft, a work table, two knuckle bearings, a hinge, a sliding bearing, an optical axis supporting seat, two axial spacing rings, a fixed axis, an optical axis and three steel poles. In the invention, a sensor is orthogonally arranged according to a coordinate system of a machine body, the torque sensor is arranged along the axis direction of the horizontal machine body, a stretch-press sensor is arranged by adopting the knuckle bearing and the hinge, the torque sensor is connected with the small-size bypass aircraft through the universal joint coupler, and the stretch-press sensor is connected with the small-size bypass aircraft through the knuckle bearing, and therefore, the measurement of the quality, the mass center position, the engine thrust, the pitching moment, the rolling moment and the yawing moment of the small-size bypass aircraft is realized.

Description

technical field [0001] The invention belongs to the field of measurement system design, and in particular relates to a flight parameter measurement system for a small ducted aircraft. Background technique [0002] At present, small ducted aircraft is becoming one of the key objects of UAV research at home and abroad. The structure and control system design of the aircraft depend on its aerodynamic parameters. When it is necessary to measure the aerodynamic parameters of the aircraft, the traditional method is to use sensors to measure each part of the small ducted aircraft and obtain the measurement data. Therefore, there will be large errors when performing integrated calculations on these individually measured data, which will lead to unreasonable design of the overall machine structure and control system. In addition, since the small ducted aircraft is a statically unstable system, it is impossible to manually control the flight of this type of aircraft, and it is diffic...

AI Technical Summary

Problems solved by technology

When it is necessary to measure the aerodynamic parameters of the aircraft, the traditional method is to use sensors to measure each part of the small ducted aircraft and obtain the measurement data. Therefore, there will be a large error when the integrated calculation of these individually measured data will lead to unreasonable design of the whole machine structure and control system

In addition, since the small ducted aircraft is a statically unstable system, it is impossible to manually control the flight of this type of aircraft, and it is difficult to directly obtain the flight parameters, so the aerodynamic parameters of the aircraft cannot be calculated by the commonly used parameter identification method

[0003] At present, there is no measurement system that can simultaneously measure the mass and the position of the center of mass, the thrust of the engine, the pitching moment, the rolling moment and the yaw moment of the small ducted aircraft.

Images