Scale measuring device for pitching dynamic derivative experiment

Abstract

The invention provides a scale measuring device for a pitching dynamic derivative experiment. An electric motor is arranged in a motor support rod; a motor output shaft is connected with a transmission shaft via a speed reducer and a shaft coupling; the transmission shaft is rotationally connected with a scale support rod; the rear end of the scale support rod is fixedly connected with the front end of the motor support rod; the front end of the transmission shaft is provided with an eccentric wheel which is provided with a lug; the lug is inserted into a sliding chute of a slide block; upper and lower cross springs of a cross spring scale have a crisscross structure respectively, and the front and rear ends thereof are fixedly connected with a scale frame via a front seat; and central positions of the upper and lower cross springs are provided with supporting cylinders. The scale measuring device for the pitching dynamic derivative experiment is a novel pitching dynamic derivative scale device. A pitching direct derivative of an aerial craft and a rolling crossover derivative induced by yaw oscillation can be measured under a big attack angle by designing a special vibrating mechanism, the cross spring scale and a pitching five-component scale structure. The scale measuring device for the pitching dynamic derivative experiment can meet the requirement of a wind tunnel trial.

Description

Technical field [0001] The invention relates to a balance measuring device, in particular to a balance measuring device used for pitch dynamic derivative experiments capable of measuring the direct derivative of pitch and the roll cross derivative induced by yaw vibration of an aircraft. Background technique [0002] The dynamic stability derivative is abbreviated as the dynamic derivative, which is the time change rate of the aircraft's six aerodynamic coefficients (that is, the three forces and three moment coefficients in the three-dimensional rectangular coordinate system) to the aircraft attitude parameters (p, q, r, α, β, dV) / dt) derivative. Dynamic derivative is an indispensable primitive aerodynamic parameter in aircraft guidance system, control system and dynamic quality analysis. Especially for space shuttles, spaceships, and advanced performance military fighters, they all fly at high angles of attack, and there are usually phenomena such as air flow separation, vort...

AI Technical Summary

Problems solved by technology

Flying at a high angle of attack, the aerodynamic load of the aircraft is relatively large. The cross spring balance in the current pitching dyn

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