基于被动二次流的射流偏转比例控制

doi:10.7527/S1000-6893.2014.0116

流体力学与飞行力学

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基于被动二次流的射流偏转比例控制

曹永飞¹, 顾蕴松¹, 程克明¹, 肖中云², 陈作斌², 何开锋²

1. 南京航空航天大学航空宇航学院, 南京 210016;
2. 中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

收稿日期:2014-03-31 修回日期:2014-06-09 出版日期:2015-03-15 发布日期:2015-03-31
通讯作者: 顾蕴松男, 博士, 教授, 博士生导师。主要研究方向: 实验空气动力学, 流动测量及流动控制。Tel: 025-84896361 E-mail: yunsongg@nuaa.edu.cn E-mail:yunsongg@nuaa.edu.cn
作者简介:曹永飞男, 博士研究生。主要研究方向: 实验空气动力学, 流动测量及流动控制, 推力矢量控制。E-mail: cyffb1@163.com
基金资助:
江苏省普通高校研究生科研创新计划资助项目(CXLX13_131);中央高校基本科研业务费专项资金资助;江苏高校优势学科建设工程资助项目

Proportional control of jet deflection with passive secondary flow

CAO Yongfei¹, GU Yunsong¹, CHENG Keming¹, XIAO Zhongyun², CHEN Zuobin², HE Kaifeng²

1. .College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2014-03-31 Revised:2014-06-09 Online:2015-03-15 Published:2015-03-31
Supported by:
Funding of Jiangsu Innovation Program for Graduate Education (CXLX13_131); Fundamental Research Funds for the Central Universities; Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions(PAPD)

摘要/Abstract

摘要：

射流偏转比例控制一直是流体式推力矢量(FTV)技术所追求的目标之一。本文研制了一种二元流体式推力矢量喷管,采用能量消耗极小的被动二次流与Conada壁面相结合的方式对低速主射流进行矢量偏转控制,通过改变喷管控制缝入口面积实现了主射流偏转的连续比例控制。对低速主射流两侧控制缝压力和射流偏转角进行测量,获得了主射流偏转角随两侧控制缝压力差系数变化的控制规律曲线。结果表明:低速主射流最大偏转角达到19°,在偏转范围内控制曲线分为敏感区和迟钝区。敏感区的控制曲线近似线性,斜率较大,范围约为±15°;而迟钝区的控制曲线斜率较小,在两侧15°~19°的范围内。该结果证实了主射流两侧的压力差是造成其偏转的直接原因。

关键词: 流体式推力矢量, 推力矢量喷管, 二次流, 流动控制, 比例控制, Coanda效应

Abstract:

The proportional control of jet deflection is always one of the goals of fluidic thrust vectoring (FTV) technology. A two-dimensional new fluidic thrust vectoring nozzle is designed and manufactured. Thrust vector control of the low-speed primary jet is investigated using passive secondary flow and Conada wall surfaces, which has ultra-low energy consumption. The primary jet can be continuously and proportionally vectored by changing the area of entrance of nozzle control slot. The pressure of control slots on both sides and deflection angle of the primary jet are measured; the control curve of the primary jet deflection angle versus the coefficient of pressure difference between control slots is obtained. The results show that the maximum deflection angle of the low-speed primary jet is up to 19°; the control curve is divided into sensitive zone and inert zone in the deflection range. The control curve of sensitive zone is approximately linear with steep slope, within a range of ±15°; while the inert zones are from -19° to -15° and from +15° to +19°, where the control curve slope is gentle. The experimental results demonstrate that the pressure difference between both sides of the primary jet is the direct cause of jet deflection.

Key words: fluidic thrust vectoring, thrust vector nozzle, secondary flow, flow control, proportional control, Coanda effect

中图分类号:

V211.71

曹永飞, 顾蕴松, 程克明, 肖中云, 陈作斌, 何开锋. 基于被动二次流的射流偏转比例控制[J]. 航空学报, 2015, 36(3): 757-763.

CAO Yongfei, GU Yunsong, CHENG Keming, XIAO Zhongyun, CHEN Zuobin, HE Kaifeng. Proportional control of jet deflection with passive secondary flow[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(3): 757-763.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于被动二次流的射流偏转比例控制

Proportional control of jet deflection with passive secondary flow

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