2.4米跨声速风洞推力矢量试验技术

The thrust vectoring experiment technique in the 2.4m×2.4m transonic wind tunnel

针对先进战斗机推力矢量高速试验需求,研制了可用于校准通气不传力系统对推力天平性能影响的装置和基于数字流量阀的喷流质量流量闭环测控系统,在2.4m跨声速风洞建立了通气叶片支撑、金属波纹管通气不传力系统实现喷流供气转换、三台天平内置的双发战斗机推力矢量试验平台,实现了飞机气动力和两尾喷管转向喷流推进特性同时分别测量。系统调试和模型风洞试验表明：试验系统运行稳定、可靠,质量流量测控精度优于0.5%;全机气动力及两个喷管矢量喷流推进特性规律合理,重复性精度达到国军标常规测力合格指标;建立的试验技术系统可用于来流马赫数0.3~1.2、迎角-10＂~60＂、喷管偏角-20＂~20＂、喷流总质量流量0~3kg/s的双发战斗机推力矢量试验。

In order to meet the requirement for the testing of the advanced aircrafts＇ thrust vectoring techniques in high speed wind tunnel,a device for the flexible metal bellow system＇s calibration of the performance impact on thrust vectoring balance and the corresponding high precision flow close-loop measurement and control system based on the digital flow valve are developed.A test platform for a twin-engine aircraft thrust vectoring,including the supply lamina support,the flexible metal bellow for realizing the jet air supply and three balances system,is established.Separate measurement of both aerodynamic characteristics and propulsion characteristics is achieved simultaneously.The system adjustment and the results of model tests demonstrate that,the experimental equipment and the overall system operate accurately and steadily,the precision of jet mass flow measurement is better than 0.5%.The experimental results of aerodynamic characteristics and propulsion characteristics obtained in the research are normative and reasonable,and the precision of repeatability tests is up to the standard of GJB.The experimental skills obtained in the research can satisfy the twin-engine aircraft requirement,and the test condition is within the margin of Mach number of 0.3~1.2,angle of attack of-10°~60°,nozzle thrust vector angle of-20°~20°,jet mass flow 0~3kg/s.