面对称高超声速飞行器横向多频扰流控制响应特性研究

To increase the lift-drag-ratio, hypersonic aircrafts incline to adopt plane-symmetry aerodynamic layout, realization of accurate and effective goal of plane-symmetry hypersonic aircraft requires solution of weakness of lateral stability. According to the study of applicant, during the wind-tunnel tests, the oscillations of the model present a certain multi-frequency and periodical characteristics. The spectrum analysis of roll vibration data under several different flow conditions show: they share three main vibration frequencies apart from the mechanical vibration frequency, which may be the core reason for the nonlinearity of aerodynamic force and the weakness of lateral stability of aircraft. Improvement of lateral stability, needs removal of multi-frequency disturbances or reduction of width of frequency bands. Correlative study show, forebody flow control of hypersonic aircrafts can change the flow structure from the origin. The task aims at studying effective aerodynamic methods to remove multi-frequency disturbances or reduce the width of frequency bands. The aerodynamic methods attempt to control the lateral non-symmetry flow of forebody by the small modification of forebody aerodynamic layout.The presented technique can effectively improve the lateral stability of plane-symmetry hypersonic aircraft, and can be used for the aerodynamic configuration design of this kind of aircrafts.

为了提高升阻比，高超声速飞行器多采用面对称布局，但横侧向稳定性差是面对称高超声速飞行器研制面临的主要瓶颈之一。根据以往的研究，高超声速面对称飞行器的横向流场具有多频率的扰动特征，这可能是横向气动力出现非线性和飞行器横向稳定性弱的根本原因，为改善横向稳定性，需要消除多频扰动或减小多频效应的谱宽。研究表明，对于高超声速飞行器,前体流动控制能从源头改变流场结构，控制效率高。本课题旨在通过风洞试验深入研究有效的消除多频扰动或减小多频效应谱宽，改善横侧向稳定性的气动干预方法。设计通过前体布局微调，控制面对称高超声速飞行器前体横向不对称扰流，从飞行器流场源头上消除多频扰动的致因。利用本方法可以有效改善面对称高超声速飞行器的横侧向稳定性，为该类飞行器的气动设计提供借鉴。

为了提高升阻比，高超声速飞行器多采用面对称布局，但横侧向稳定性差是面对称高超声速飞行器研制面临的主要瓶颈之一。根据以往的研究，高超声速面对称飞行器的横向流场具有多频率的扰动特征，这可能是横向气动力出现非线性和飞行器横向稳定性弱的根本原因，为改善横向稳定性，需要消除多频扰动或减小多频效应的谱宽。研究表明，对于高超声速飞行器,前体流动控制能从源头改变流场结构，控制效率高。本课题通过CFD方法研究有效地消除多频扰动或减小多频效应谱宽，改善横侧向稳定性的气动干预方法。设计通过前体布局微调，控制面对称高超声速飞行器前体横向不对称扰流，从飞行器流场源头上消除多频扰动的致因。利用本方法可以有效改善面对称高超声速飞行器的横侧向稳定性，为该类飞行器的气动和稳定性设计提供借鉴。