CAJ | 학술논문

随着新一代高超飞行器性能的要求越来越高，飞行性能提高和可操纵性下降之间矛盾问题凸显出来，传统的三通道静稳定设计判据，所能提供的设计区域非常狭窄，以往通过牺牲飞行性能确保操作性的做法已经不可取。为此需要探索新型的气动布局设计准则，扩宽可用设计区域，为设计高性能的飞行器创造条件。国外的经验表明，将横航向作为一个整体设计是一种可行的设计思路，Cnβ-dyn 和 LCDP 参数对飞行器的横航向的开环和闭环模态特性能够进行可靠的划分，采用上述参数的组合可以作为先进气动布局的设计判据。在本文中，通过上诉组合参数极性划分了不同区域，以某一典型飞行器作为研究对象，开展了不同区域的开环模态特性，并采用根轨迹法，研究偏航角速率、滚转角速率和侧滑角反馈信号分别单独作用于航向通道和横向通道的6种闭环响应特性。研究结果显示，飞行器的可操作性和不同信号的闭环反馈特性同划分区域是紧密相关的。这种区域划分可以为高性能飞行器的设计提供一种设计方向性的指导。
수착신일대고초비행기성능적요구월래월고，비행성능제고화가조종성하강지간모순문제철현출래，전통적삼통도정은정설계판거，소능제공적설계구역비상협착，이왕통과희생비행성능학보조작성적주법이경불가취。위차수요탐색신형적기동포국설계준칙，확관가용설계구역，위설계고성능적비행기창조조건。국외적경험표명，장횡항향작위일개정체설계시일충가행적설계사로，Cnβ-dyn 화 LCDP 삼수대비행기적횡항향적개배화폐배모태특성능구진행가고적화분，채용상술삼수적조합가이작위선진기동포국적설계판거。재본문중，통과상소조합삼수겁성화분료불동구역，이모일전형비행기작위연구대상，개전료불동구역적개배모태특성，병채용근궤적법，연구편항각속솔、곤전각속솔화측활각반궤신호분별단독작용우항향통도화횡향통도적6충폐배향응특성。연구결과현시，비행기적가조작성화불동신호적폐배반궤특성동화분구역시긴밀상관적。저충구역화분가이위고성능비행기적설계제공일충설계방향성적지도。
The contradiction between the higher performance and the humble controllability becomes more and more serious as higher and higher flight performance is required,the tradition-al three-axis static stability principle is not appropriate to the configuration design for new gener-ation hypersonic vehicle,whose flight performance requirement will exasperate the control per-formance.It is necessary to explore a new configuration design principle,which expands the a-vailable design space and creates possibilities for higher performance hypersonic vehicle.In the new method,the lateral and directional performance is dealt with as a unity.From the overseas experience,Cnβ-dyn (Dynamic Directional Stability Parameter)and LCDP (Lateral Control Depar-ture Parameter)can be used to classify the open-loop and close-loop lateral-directional model characteristic well and truly,which can be adopted as the advanced criterion for aerodynamic con-figuration design.According to the combination of Cnβ-dyn and LCDP ,three typical states of a cer-tain hypersonic vehicle are research objects,and open-loop mode characteristic and close-loop mode characteristic for six kinds of feedback performance are investigated with root locus method in this paper.Elementary result shows the controllability and close-loop feedback characteristic are closely connected with different areas divided by these two combination parameters,and Cnβ-dyn and LCDP parameter can be used as the aerodynamic configuration design criterion.