A Multi-Disciplinary Designing Method Considering Controllability for High Speed Flight Vehicle
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摘要: 高速面对称飞行器大空域、宽速域和大攻角变化范围的飞行特点，导致失稳模式多、稳定性差、通道耦合严重、姿控难度大等系列问题，为飞行器的总体设计带来了很大挑战.文章针对高速面对称飞行器抗失控设计难题，基于耦合稳定性与可控特性理论研究，综合考虑总体多专业设计约束，发展了飞行器总体抗失控设计方法.通过该方法，可以获得多专业参数对总体性能与稳定特性的影响规律，进而对飞行器的总体性能、稳定性与可控性进行综合优化设计.Abstract: The plane-symmetric configuration has been widely used for new flight vehicles to achieve a wide-velocity-range and large-space flight. However, large flight amplitude and speed arrange result in poor stability and uncontrollable flight. In this paper, the lateral-directional coupling was comprehensively considered in the flight vehicle design, and a multidisciplinary designing method was presented. By the aid of this designing method, a quantitative study of the design parameters for the stability and performance parameters can be conducted, which can further support optimization of the overall design.
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表 1 设计参数表
Table 1. Designing parameters
symbols parameters rhead head radius swangle sweep angle of fuselage bhigh height of fuselage bodyup height of upside fuselage bodyside width of fuselage Tailx axial position of tail Tail1 height of tail Tail2 length of tail tip Tail3 length of tail root Tail4 length of rudder tip Tail5 length of rudder root TailSwAgl sweep angle of tail BF1 length of flap inside edge BF2 length of flap outside edge BF3 width of flap IX inertia X IXY inertia XY IY inertia Y IZ inertia Z Xcg X center of mass Ycg Y center of mass 
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