弹性飞机跨声速机动载荷计算方法

doi:10.7527/S1000-6893.2016.0070

Abstract

Abstract:

Based on the overset field-panel method for computing unsteady aerodynamics in transonic flows, the calculation approach of maneuver load for flexible aircraft in transonic flows is developed, for the purpose of providing expedient and accurate critical loads for the design in structural strength of modern aircraft. The LANN wing in pitch mode about 62% root chord at Mach number 0.822 is solved to validate the unsteady pressure coefficient with the experimental data, and excellent agreement shows the capability of the overset field-panel method in predicting the shock location and strength. State space model for analyzing maneuver loads is generated through rational aerodynamic approximations, then the transient load analysis of a transport aircraft in pitching is conducted to investigate the response of the airframe states and loads acting on the components of the aircraft. The results indicate that the peak loads acting on the wing and horizontal tail decrease by 5.1% and 10.6% respectively, while one on the elevator increases by 16.2%, due to the structural deformation. Therefore, the effect of structural deformation on loads must be considered in the design concerning structural strength of modern aircraft.

Key words: maneuver load, unsteady aerodynamics, aerodynamic influence coefficient matrix, transonic, oveset field-panel method

CLC Number:

V211.47

ZHANG Hui, LI Jie. Maneuver load analysis for flexible aircraft in transonic flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(11): 3236-3248.

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Maneuver load analysis for flexible aircraft in transonic flow

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