Control system for model oscillation test under wind tunnel rotational flow field

Abstract

The invention discloses a control system for a model oscillation test under a wind tunnel rotational flow field. The system comprises a remote computer, a system general control computer and an acquisition system, and further comprises a brake energy absorption module, an oscillation starting point sensing module, a driving power output module, a CANopen bus module, a driving control unit, an encoding signal input module, an auxiliary unit, a trigger signal conditioning module, a trigger signal output module and a real-time position output module. The oscillation starting point sensing modulesenses a zero signal of a rotating shaft by adopting an optocoupler and transmits the signal to the driving control unit, so that an oscillation shaft motor is activated to start the oscillation shaftto oscillate, and the oscillation shaft can start oscillating at a zero phase of the rotating shaft when a rotating shaft motor rotates at different rotation frequencies. The driving control unit sends an acquired trigger signal. The auxiliary unit triggers the acquisition system to acquire a scale signal according to a set parameter. According to the control system for the model oscillation testunder the wind tunnel rotational flow field, an establishment of the rotational flow field and a sine oscillation movement are realized, and the system is high in reliability and stability.

Description

technical field [0001] The invention relates to a control system for model oscillation tests under the swirling flow field of a wind tunnel. Background technique [0002] When the aircraft exceeds the stall angle of attack, it is easy to enter a complicated and dangerous spin flight state, which seriously endangers the flight safety of the aircraft. At present, the equipment for researching the aircraft spin mainly simulates the flight situation of the aircraft in the spin state through the belt model test, and analyzes and studies the relevant test data to obtain the necessary information for the aircraft safety design. The control drive system generally uses a traditional inverter motor system to simulate the flight attitude of the aircraft tail spin by changing the rotation frequency and positioning angle, and obtain aerodynamic data through the acquisition system. The sinusoidal oscillating motion is an important content in the study of aircraft spin, and the oscillatin...

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Problems solved by technology

[0003] The purpose of the present invention is to provide a control system for model oscillation tests under the rotating flow field in a wind tunnel, which solves the phase relationship between the oscillation axis and the rotation axis when the oscillation axis starts sinusoidal motion in the dynamic test, and the positive zero-crossing movement of the model sinusoidal oscillation The problem of the determination and acquisition of the trigger acquisition point and the synchronization of the aerodynamic data acquisition and the output position signal of the control system

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