基于变头锥概念的新型高超声速飞行器力矩特性分析研究  

Analysis and Study on Moment Characteristics of a Novel Hypersonic Vehicle Based on Variable Cone Concept

作　　者：俞宗汉 李伟 刘航 孟凡硕 孟鑫 孙佳鑫 何国忠 YU Zonghan;LI Wei;LIU Hang;MENG Fanshuo;MENG Xin;SUN Jiaxin;HE Guozhong(School of Mechanical and Material Engineering,North China University of Technology,Beijing 100144,China;Sichuan Aerospace Zhongtian Power Equipment Co.,Ltd.,Chengdu 610100,China)

机构地区：[1]北方工业大学机械与材料工程学院,北京100144 [2]四川航天中天动力装备有限责任公司,成都610100

出　　处：《北方工业大学学报》2024年第5期76-88,共13页Journal of North China University of Technology

基　　金：国家自然科学基金青年项目(12002162);北方工业大学毓秀创新项目(2024NCUTYXCX106)。

摘　　要：本研究深入探讨了高超声速飞行器变头锥设计原理及其气动性能,提出了一种新颖的多级变头锥设计方法。该方法基于一级变头锥设计,各级头锥的尺寸参数与造型保持不变。通过GoCart软件的数值模拟,详细分析了一至五级变头锥在15°偏转角和0°至10°攻角下的气动性能。研究结果显示:与舵相比,多级变头锥在升阻比上最高提升了4.53%,在俯仰力矩上优化了12.80%,显著增强了飞行器的稳定性和高机动性,实现了变头锥对舵的取代,在飞行中可以通过头锥的变形去完成舵所能表现的性能。具体而言,五级变头锥相较于一级变头锥,升阻比提升了33.30%,阻力降低了20.80%,而一级变头锥的投影面积相对变化量较五级多了0.10%。同时,随着变头锥级数的增加,较小变形量即可实现较大的头锥角度变动,而且升阻比增加,阻力相应减少。五级变头锥与三级在升阻比上的差距仅为3.06%,综合考虑升阻比的衰减、力矩系数的增益、结构复杂度及工程实践需求后,本研究最终确定三级变头锥为最佳设计方案。This research thoroughly examines the design principles and aerodynamic attributes of variable nose cones employed in hypersonic vehicles,introducing an innovative multi-stage design approach.This methodology,grounded in the principles of single-stage variable nose cone design,ensures uniformity in dimensional parameters and configurations across its various stages.Leveraging numerical simulations facilitated by GoCart software,a rigorous analysis is conducted to assess the aerodynamic efficacy of variable nose cones spanning from one to five stages,under conditions of a 15°yaw angle and angles of attack ranging from 0°to 10°.The outcomes demonstrate that,when compared to traditional control surfaces,the multi-stage variable nose cone design attains a peak improvement of 4.53%in the lift-to-drag ratio and a 12.80%optimization in pitching moment,significantly bolstering the aircraft's stability and high maneuverability.This achievement underscores the successful substitution of control surfaces with the variable nose cone,which,through morphing capabilities,replicates the performance previously reliant on control surfaces.Notably,the five-stage variant surpasses the single-stage design by enhancing the lift-to-drag ratio by 33.30%and reducing drag by 20.80%,despite the latter exhibiting a marginally higher(0.10%)relative change in projected area.Moreover,as the number of stages in the variable nose cone escalates,substantial alterations in nose cone angles can be achieved with minimal deformation,concomitant with an increase in the lift-to-drag ratio and a corresponding decrease in drag.Notably,the marginal difference in lift-to-drag ratio between the five-stage and three-stage designs is a mere 3.06%.Upon weighing factors such as the attenuation of lift-to-drag ratio,enhancements in moment coefficient,structural intricacy,and engineering feasibility,the threestage variable nose cone is ultimately adjudged as the optimal design configuration.

关 键 词：高超声速 变头锥 GoCart 数值模拟 高机动性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]