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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。
According to the demand of high-speed thrust test of advanced fighter, a device that can be used to calibrate the performance of thrust non-transmission system on thrust balance and a closed flow measurement and control system of mass flow based on digital flow valve were developed. Ventilation was established at 2.4 m transonic wind tunnel Blade support, metal bellows ventilation system to achieve non-jet air supply and jet conversion, three balance built-in double-fighter thrust vector test platform to achieve the aircraft aerodynamic and two nozzle jet steering thrust characteristics were measured at the same time. The system debugging and model wind tunnel tests show that the test system is stable and reliable, and the accuracy of mass flow measurement and control is better than 0.5%. The aerodynamic characteristics of the whole machine and the jet flow characteristics of two nozzle vector jets are reasonable and the repeatability accuracy reaches the standard The test technology system established can be used for Mach-flow Mach number 0.3 ~ 1.2, Angle of attack -10 “~ 60”, nozzle deflection angle -20 “~ 20”, total jet flow rate 0 ~ 3kg / s twin-engine fighter thrust vector test.