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To lower the labor intensity, reduce energy consumption, improve efficiency, increase the service life of the pumping unit and achieve automatic adjustment of pumping unit, based on the CYJ10-4.2-53 HF type pumping unit, this paper completes the structure and parameter design of the crank automatic balance device. The key transmission part screw is selected and checked based on the fourth strength theory. ANSYS Workbench is used to analyze the finite element strength. It is concluded that the theoretical check is basically as the same as the simulation result, the theoretical calculation is feasible, and the overall structure meets the strength requirements.Finally, the pumping unit is tested in the field, the instrument measured its balance meets the requirements, the energy saving effect is satisfactory, and it has a certain promotion and application prospects.

longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model are investigated in a low speed wind tunnel. Normal force measuring experiment is conducted to gain the longitudinal aerodynamic characteristics and yaw control characteristics, and the PIV test is also conducted to investigate the flow mechanism of the low aspect ratio flying wing. The results indicate that the leading-edge separation vortex appears on the wing's spine surface when the attack angle is at 6 degree. The vortex intensity increases and the vortex core shifts to the symmetric plane of flying wing with the increase of attack angle. Increasing the attack angle further, the vortex core becomes unsteady and begins to oscillate, finally break entirely. The broken position shifts from the ending edge to the leading edge. Yaw control characteristics of low aspect ratio flying wing is also studied in this paper. The results indicate that the flying wing is static stabile at the test attack angle. When the attack angle is less than 6 degree, it is controllable in yaw direction. And when attack angle is more than 6 degree, the yaw control ability decreases because the control surface may lays in the wake region of broken leading-edge vortex. [ABSTRACT FROM AUTHOR]