摘要:
介绍了中国航天空气动力技术研究院FD-09低速风洞利用YF-16标模作为研究对象开发的一种推力矢量试验系统,系统利用中压气源提供的最大2.0 MP a压缩空气,通过通气管路和推力矢量管道由模型尾喷管排出,用于模拟飞机喷流对全机气动特性的影响。推力矢量试验系统充分利用现有的大迎角机构预弯支杆作为模型支撑装置和引气管路,使同一次车次的试验迎角范围能够达到-6°~90°,同时极大降低管路压力损失,使得喷口最大落压比NPR超过5,并且能够实现模型腹部支撑和背部支撑两种形式的相互转换。试验采用六分量常规测力天平和推力矢量传感器以及总压传感器等,测量得到了推力矢量喷流对全机气动性能的影响以及喷管的气动性能。主要介绍整个系统布局、推力矢量管路的优化设计、测试设备以及两套喷管的典型试验结果。推力矢量试验系统在经过支撑干扰修正、喷流状态下传感器校准、压力管路化等方面做进一步的深入研究之后,将形成试验能力。
Abstract:
A vectoring thrust test system for YF-1 6 standard model has been developed by FD-09 low-speed wind tunnel laboratory of China Academy of Aerospace Aerodynamics (CAAA).The maximum 2 .0 MPa compressed air flow through vectoring thrust pipe and j etted from nozzle can be generated to simulate the influence of the vectoring thrust j et on the aerody-namic characteristics of the whole plane.The system takes the full advantage of the existing high angle of attack device to achieve convenient conversion between the ventral and the dorsal air-sup-ply.The range of angle of attack can be adjusted from-6 degree to 90 degree,and the maximum Nozzle Pressure Ratio (NPR)is more than 5 .In tests an ordinary balance,a vectoring thrust force measurement sensor and other instruments are applied to obtain the influence of the j et flow on the aerodynamic characteristics of the whole plane and the nozzle aerodynamic performance. This paper describes the vectoring thrust test system design,the instruments and devices employed,and the typical results obtained.The system can be used for proj ect tests after making further improvements in sting interference correcting;sensor calibration in jetting status and pipe optimization design.
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