Development Of Heave And Flat Moving Derivative Test Device

Aircraft is an important reference to measure the military and national defense strength of a country.With the development of science and technology,the design requirements for aircraft are becoming higher and higher.Dynamic derivative is an essential original data for aircraft design,and dynamic derivative test device directly affects the accuracy of aerodynamic dynamic derivative data.By studying the previous dynamic derivative test devices,it is found that most of the existing dynamic derivative test devices make the forced model produce single-dof pitch,yaw and roll vibration,or any two kinds of coupled vibration and three-dof coupled vibration,and few of the test devices specially study heave and flat moving derivatives.In addition,the existing test devices for studying heave and flat moving derivative have disadvantages such as low automation,low frequency and small amplitude.Therefore,it is of great importance to develop a test device for heave and flat moving derivative with high automation,high frequency and large amplitude.This paper carries out in-depth research on the development of heave flat moving derivative test device,and the specific contents are as follows:1.According to the research status of dynamic derivatives in China,some advanced indicators are proposed.Based on these indicators,the overall scheme of the test device for the heave flat moving derivative is designed,including three modules: linear oscillation,angle of attack control and Y displacement compensation.In the linear oscillation module,by comparing the advantages and disadvantages of the previous oscillation mechanism,the linear motor is selected as the mechanism to realize heave oscillation and flat moving oscillation.In the angle of attack control module,the reverse crank slider mechanism is adopted as the mechanism to realize the change of angle of attack.2.The mechanical system of heave flat moving derivative test device is designed in detail.Firstly,the stress analysis and selection calculation of key components are carried out in detail.Finally,the device is simulated,including modal analysis,blocking analysis and statics analysis of key components.The results show that the natural frequency of the device is greater than 14 Hz,the blocking degree is less than 6%,and the safety factors of the key parts are greater than 2.5,which meet the design requirements.3.The motion control system framework is built based on modular design,and the control system is designed based on the control principle of "host computer-motion controller-motor driver".The host layer is composed of host computer equipment and process CPU,and the field layer is composed of motor drive system SINAMICS S120 and operation panel.The control system design realizes the function hierarchy and structure modularization in software and hardware,and has the ability of function expansion.4.Based on the mechanical system and control system designed above,the manufacturing of heave flat moving derivative test device is completed,and the ground debugging is carried out.The debugging results show that the device meets all the design indicators,the device can force aircraft model 2 Hz frequency corresponding to 200 mm of simple harmonic oscillation amplitude,angle of attack range-10 ° ～ 90 °,The center of mass of the aircraft model is always 2600 mm away from the base seat.The feasibility of measuring heave and derivative of horizontal movement in wind tunnel is verified.