Synchronous control method of motion of combined supporting mechanism of wind tunnel

Abstract

The invention discloses a synchronous control method of the motion of a combined supporting mechanism of a wind tunnel. First, a tail supporting mechanism is identified as an active control object, and a stripe hanging supporting mechanism is identified as a follow-up control object; second, the characteristics including dynamic response time difference, motion speed and the like of the two independent supporting mechanisms in the combined supporting mechanism are tested and data of the characteristics are recorded; finally, the effect that the auxiliary supporting mechanism follows the main supporting mechanism in real time is achieved through sequential control of instructions, and corresponding safety strategies are adopted to cope with risks likely to exist in the process of a test, so that the test suffers no risk at all. The synchronous control method has the advantages that through the synchronous control over the two independent supporting mechanisms, combination supporting of an aircraft model is achieved, and a new test technology is provided for an aerodynamic test of the aircraft model in the wind tunnel; the method is good in operability, strong in engineering adaptability and high in safety and can meet special requirements in the technical field of wind tunnel supporting interference tests, greatly save equipment development expenditure and shorten the development period.

Description

technical field [0001] The invention relates to aircraft wind tunnel test technology, in particular to a synchronous control method for the movement of a wind tunnel combined support mechanism. Background technique [0002] The tail support method is one of the most commonly used and mature support methods in aircraft wind tunnel tests. Under this support method, tests such as conventional force measurement, full-machine pressure measurement and component force measurement can be carried out. When the aircraft conducts wind tunnel simulation tests , the tail support mechanism will cause greater interference to the tail flow field of the aircraft, which will affect the aerodynamic characteristics of the aircraft and cannot provide accurate aerodynamic data. Under the above factors, a set of model attitude control mechanism based on the strip suspension support was developed in combination with the requirements of the model test. Under this support mode, the aerodynamic charac...

AI Technical Summary

Problems solved by technology

The core of the research work is to require the two sets of supporting mechanisms to achieve strict synchronous control, otherwise the normal progress of the interference test cannot be guaranteed, and it may even cause serious damage to the supporting mechanism, aircraft model and wind tunnel body