一种翼身融合布局飞行器的偏离特性分析

付军泉; 史志伟; 陈杰; 周梦贝; 吴大卫; 潘立军

doi:10.11729/syltlx20190110

一种翼身融合布局飞行器的偏离特性分析

doi: 10.11729/syltlx20190110

1.
南京航空航天大学航空学院非定常空气动力学与流动控制工信部重点实验室, 南京 210016
2.
中国商飞上海飞机设计研究院, 上海 201210

基金项目:

国家自然科学基金 12072155

江苏省研究生科研与实践创新计划项目 KYCX18_0250

详细信息

作者简介:
付军泉(1993-), 男, 江西抚州人, 博士研究生。研究方向:飞行器飞行力学与控制, 流体力学。通信地址:江苏省南京市秦淮区御道街29号南京航空航天大学航空学院非定常空气动力学与流动控制工信部重点实验室(210016)。E-mail:fujquan@nuaa.edu.cn

通讯作者:
史志伟, E-mail: szwam@nuaa.edu.cn

中图分类号: V212.12
计量
- 文章访问数: 516
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- PDF下载量: 32
- 被引次数: 0
出版历程
- 收稿日期: 2019-09-10
- 修回日期: 2019-11-11
- 刊出日期: 2020-12-25

Departure characteristics of blended-wing-body aircraft

1.
Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
COMAC Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

摘要

摘要: 为研究某翼身融合布局飞行器的偏离特性，在南京航空航天大学回流式低湍流度开口风洞中进行了飞机模型的大迎角静态测力试验。通过对试验结果的充分挖掘，利用横航向静稳定性判据、侧滑偏离判据、横向控制偏离参数以及Weissman组合判据进行分析，获得了飞机的大致初始偏离迎角和偏离区域，并对飞机的尾旋敏感区进行了预测。同时，利用风洞虚拟飞行试验技术进行三自由度释放验证。结果表明：该翼身融合布局飞行器的横向静稳定性较差，在很小的迎角下就可能出现非指令滚转运动，这也是造成偏离发散的主要原因；而虚拟飞行试验对偏离现象有较好的复现，与通过稳定性判据得到的偏离特性具有较好的对应关系，验证了虚拟飞行试验在偏离特性研究上的可靠性。
- 翼身融合 /
- 偏离特性 /
- 虚拟飞行试验 /
- 稳定性判据
Abstract: Static force measurements of blended-wing-body aircraft at high angles of attack were carried out in the 1 m low speed wind tunnel of Nanjing University of Aeronautics and Astronautics. By fully mining and analyzing the experimental results, the approximate initial departure angle of attack and departure region of BWB aircraft are obtained by using multiple criteria, including the static stability derivative, the dynamic directional stability parameter, the lateral control departure parameter and the Weissman chart. Besides, the spin sensitive region of BWB aircraft is predicted. At the same time, the departure is simulated by the virtual flight test in wind tunnel. The results show that the lateral stability of BWB aircraft is poor, and the non-command roll motion may occur at a very small angle of attack, which is also the main reason for the divergence of the departure. And the departure characteristics obtained from the virtual flight test and these stability criteria are in good consistency, which verifies the reliability of the virtual flight test in departure characteristics research.
- blended-wing-body /
- departure characteristics /
- virtual flight test /
- stability criterion

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图 1 试验模型安装图

Figure 1. Installation of the experimental model

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图 2 虚拟飞行试验模型

Figure 2. The virtual flight test model

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图 3 虚拟飞行试验模型三视图

Figure 3. Three views of the virtual flight test model

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图 4 三自由度机构

Figure 4. 3 degree of freedom rig

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图 5 横航向力矩系数曲线

Figure 5. Roll and yaw moment coefficient curves

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图 6 横航向稳定性导数

Figure 6. Directional and lateral stability derivatives

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图 7 动态航向稳定参数C_{nβ, dyn}

Figure 7. Dynamic directional stability parameter

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图 8 操纵导数

Figure 8. Control derivative

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图 9 横向控制偏离参数LCDP

Figure 9. Lateral control departure parameter

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图 10 WEISSMAN组合判据结果

Figure 10. Weissman chart

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图 11 姿态角随时间的变化曲线

Figure 11. Attitude angle curve

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表 1 试验模型几何参数

Table 1. Geometric parameters of the test model

几何参数	参数
参考面积S	0.067 m²
参考展长L	0.7 m
平均气动弦长c	0.1 m
对称面机翼弦长	0.385 m
重心与机头距离	0.2 m
后掠角	40°

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表 2 虚拟飞行试验模型几何参数

Table 2. Geometric parameters of the virtual flight test model

几何参数	参数
参考面积S	0.25 m²
参考展长L	1.4 m
模型重量	5.5 kg
横向转动惯量I_x	0.279 kg/m³
纵向转动惯量I_y	0.486 kg/m³
航向转动惯量I_z	0.194 kg/m³

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表 3 不同判据偏离迎角预测结果

Table 3. Prediction results of different criteria

稳定性判据	失稳迎角范围
C_lβ	5°＜α＜37°
C_nβ	28°＜α＜38°
C_{nβ, dyn}	16°＜α＜37°
LCDP	16°＜α＜30°、α＞36°
Weissman组合判据	α＞16°

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