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要解决先进飞行器的气动/运动非线性耦合问题,就需要建立气动/飞行力学一体化的虚拟飞行试验平台,用于获取飞行器机动飞行过程中的非定常气动力特性,弄清气动/运动非线性耦合机理。2.4m×2.4m跨声速风洞(以下简称2.4m风洞)虚拟飞行试验天平研制技术是虚拟飞行试验机理性研究的关键技术之一。由于试验模型为两段的细长结构,天平设计空间受到限制,并且载荷极不匹配。风洞试验研究要求天平不仅要实现分段模型气动力的测量,还要实现两段模型的同步小摩擦滚转运动,传统天平无法满足试验要求。新设计的天平采用一种带有轴承和心轴的环式“双天平”新结构,较好解决了载荷匹配问题以及测量与运动之间的矛盾。天平设计利用有限元软件ANSYS进行应变和应力分析与优化,并设计了耦合式电桥。天平静校和风洞试验数据表明,该天平满足风洞虚拟飞行试验机理性研究的要求。
To solve the aerodynamic / kinematic nonlinear coupling problem of advanced aerocraft, an aerodynamic / flight mechanics integrated virtual flight test platform needs to be established to acquire the unsteady aerodynamic characteristics of the aircraft during maneuver flight and to ascertain the aerodynamic / kinematic nonlinearity Coupling mechanism. 2.4m × 2.4m transonic wind tunnel (hereinafter referred to as 2.4m wind tunnel) Virtual flight test balance research technology is one of the key technologies for the study of the mechanism of virtual flight test. Because the test model is a two-stage, slender structure, the balance of the balance is limited and the loads do not match. The wind tunnel test requires that the balance should not only measure the aerodynamic force of the staged model, but also realize the synchronous small-friction roll motion of the two models. The traditional balance can not meet the test requirements. The newly designed balance uses a new “double balance” structure with bearings and spindles to better solve the problem of load matching and the contradiction between measurement and movement. Balance design using finite element software ANSYS strain and stress analysis and optimization, and design of the coupling bridge. Balance Calm and wind tunnel test data show that the balance to meet the requirements of the wind tunnel virtual flight test mechanism of research.