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带滑流的全机测压实验技术螺旋桨仍然是中、小型民用飞机的主要动力。国内外螺旋桨飞机强度计算用的气动载荷,多用无螺旋桨滑流时的试验结果,或略加以滑流修正的结果。与飞机的实际受载情况相差较远,只有获得有滑流的全机压力分布,才能提供带螺旋桨动力的准确气动载荷。航空航天部627所与西安飞机工业公司共同进行了在风洞中模拟螺旋桨工作状态下的全机测压实验。试验了整个前进比范围内模拟工作状态,提出“螺旋桨转速补偿修正法”和“速压控制偏差修正法”,对不同大气参数下螺旋桨参数的修正,保证实验拉力系数恒定,提高模拟状态的准确度。在模型设计中,考虑到尽量减小模型支架对机身和尾翼的干扰,采用尾部支撑技术,避免了常规的腹撑支架对压力分布的严重影响,使支撑对模型绕流的干扰最小。在对复杂的测压管路的安排,电子扫描模块、强弱电路
Full-scale pressure measurement experiment with slipstream Propeller is still the main power of medium and small commercial aircraft. The aerodynamic loads for the calculation of the strength of the propeller aircraft both at home and abroad are multiplied by the test results when there is no propeller slip flow, or the result slightly corrected by the slip slip. And the actual load situation with the aircraft a long way to go, only to have slipstream of the whole pressure distribution, in order to provide propeller-powered accurate aerodynamic load. The 627 Institute of Aeronautics and Astronautics, in conjunction with Xi’an Aircraft Industrial Co., conducted a full-scale pressure measurement experiment in a wind tunnel simulating propeller operation. Experiments were carried out to simulate the working conditions in the entire forward ratio range. Proposed Propeller Rotation Speed Compensation Correction Method and Speed Pressure Control Deviation Correction Method were used to correct the propeller parameters under different atmospheric parameters to ensure that the experimental tension coefficient was constant and the simulation accuracy was improved degree. In the model design, taking into account minimizing the interference of the model support to the fuselage and the tail, the tail support technology is adopted to avoid the serious influence of the conventional brace on the pressure distribution and to minimize the interference of the support on the flow around the model. Arrangements for complex pressure measurement lines, electronic scanning modules, strong and weak circuits