Wind tunnel Force testing method and system of rotary missile with rudder control

Abstract

The invention relates to a wind tunnel force testing method and system of a rotary missile with rudder control. (1), a to-be-tested rotary missile integrated model with a rudder control system is fixedly connected with a support system through a balance and placed in a wind tunnel flow field; (2), a testing Mach number is preset, the wind tunnel is started to blow, after the flow field is stable,the support system is rotated, thus the integrated model reaches a required testing attack angel, and a motor is controlled to rotate according to a preset present testing rotate speed; (3), a presentrotate speed of a model rotary body is acquired in real time, a rotate speed control signal is sent to the motor to achieve closed-loop control, and the present rotate speed of the model rotary bodyacquired in real time is in a preset error range; and (4), a present rudder surface deflection law signal is determined by the rudder control system according to a given signal law combined with the real-time acquired the present rotate speed of the model rotary body, and dynamic deflection control of a rudder surface is achieved; and aerodynamic data measured by the balance and the present rotatespeed of the model rotary body are collected in real time, and force testing under the present Mach number, the present attack angle and the present testing rotate speed is completed.

Description

technical field [0001] The invention relates to a test method for force measurement in a wind tunnel with rudder control of a rotating missile, which belongs to the field of test aerodynamics. Background technique [0002] Among the short-range / terminal defensive missile weapons, the rotary missile is favored because of its simple control system, high guidance accuracy, and excellent cost performance, and is the preferred solution for this type of missile. Rotary flight can simplify the control system of the missile, and use one control channel to realize the control in both directions of pitch and yaw; it can reduce the adverse effects of asymmetric factors such as thrust eccentricity, mass eccentricity, and aerodynamic eccentricity on flight performance. With the canard layout rotating missile, the canard vortex and missile body vortex are entwined with each other due to the rotational motion of the missile body. Affected by the rotational motion, the flow has a strong uns...

AI Technical Summary

Problems solved by technology

At present, the canard rudder is mechanically deflected in the wind tunnel, and the obtained constant aerodynamic force of the rotating missile under the fixed rudder deflection angle or the data measured by the fixed rudder surface only for the missile body rotation are not enough to develop an accurate dynamic aerodynamic model. For flight simulation of missiles, the dynamic aerodynamic forces of complex fuselage rotation cannot be modeled with a simple linear system; meanwhile, aerodynamic surfaces such as wings and canards may have a large correlation with the rotation rate

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