Research on multi-axis vector control characteristics of supersonic axisymmetric fluidic thrust vectoring nozzle
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摘要:
无源流体推力矢量技术无须二次流控制气源、结构简单且隐身性好，已成为飞行器矢量控制领域的前沿研究热点。基于无源流体推力矢量技术设计了一种周向均布6个被动二次流通道的超声速轴对称气动推力矢量喷管，通过控制被动二次流通道的启闭组合，构建了两种射流偏转控制策略。采用纹影流动显示技术与空气桥测力技术，研究了喷管在落压比为3.5～5.0范围内的射流偏转控制特性与推力矢量性能。研究结果表明：喷管成功实现了全周向12个方向的推力矢量控制，在主控与次控方向上的最大推力矢量角均可达9.8°，主控方向线性度最高为89.58%，次控方向线性度最高为97.28%，喷管推力矢量效率最高可达13.45°/%。相关结果为无源流体推力矢量技术在导弹、火箭等需要多轴控制力矩平台的进一步工程应用提供实验依据与设计参考。
Abstract:Passive fluidic thrust vectoring technology has emerged as a frontier research hotspot in aircraft thrust vector control due to its advantages of requiring no external gas source, simple structure, and low observability. A supersonic axisymmetric fluidic thrust vectoring nozzle with six passive circumferentially uniform secondary flow channels was designed. By controlling the on/off combinations of these secondary flow channels, two control strategies were established. Utilizing schlieren flow visualization and air-bridge balance force measurement techniques, the jet deflection characteristics and thrust vectoring performance of the nozzle within the nozzle pressure ratio (NPR) range of 3.5 to 5.0 were systematically investigated. Experimental results demonstrated that the nozzle successfully achieved vector control in 12 circumferential directions, with maximum thrust vector angles reaching 9.8° in both the primary and secondary control directions. The highest linearity was 89.58% in the primary control direction and 97.28% in the secondary control direction. The maximum thrust vectoring efficiency of the nozzle reached 13.45°/%. This research could provide experimental evidence and design references for further engineering application of passive fluidic thrust vectoring technology in platforms requiring multi-axis control moments, such as missiles and rockets.
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图 1 轴对称气动矢量喷管结构示意图
Figure 1. Schematic diagram of axisymmetric fluidic thrust vectoring nozzle structure
图 2 轴对称气动矢量喷管剖面图
Figure 2. Cross-sectional view of axisymmetric fluidic thrust vectoring nozzle
图 3 基于纹影技术的喷管流动显示实验平台
Figure 3. Schlieren-based nozzle flow visualization test platform
图 4 基于空气桥测力技术的喷管推力矢量实验平台
Figure 4. Nozzle thrust vectoring test platform based on air-bridge force measurement technique
图 5 轴对称气动矢量喷管建模图
Figure 5. Modeling diagram of axisymmetric fluidic thrust vectoring nozzle
图 7 主控方向控制策略示意图
Figure 7. Schematic diagram of primary control direction control strategy
图 8 次控方向控制策略示意图
Figure 8. Schematic diagram of secondary control direction control strategy
图 9 全周向矢量控制方向示意图
Figure 9. Schematic diagram of circumferential vector control directions
图 10 主控方向喷管纹影结果
Figure 10. Primary control direction nozzle jet deflection schlieren result
图 11 主控方向力矢量角控制曲线
Figure 11. Control curve of thrust vector angle for primary control direction
图 13 次控方向力矢量角控制曲线
Figure 13. Control curve of thrust vector angle for secondary control direction
图 14 喷管多轴推力矢量效果（RNPR为3.5）
Figure 14. Multi-axis thrust vectoring effect of the nozzle（RNPR is 3.5）
图 18 轴对称气动推力矢量喷管推力效率曲线
Figure 18. Axisymmetric fluidic thrust vectoring nozzle vectoring efficiency curve
表 1 喷管结构参数表
Table 1. Table of the nozzle structure parameter
参数 数值 主喷流喷管入口高度Din/mm 50 主喷流喷管喉道高度D/mm 10 喷管出口高度Dout/mm 20.4 Coanda扩张壁面长度Lc/mm 20 壁面扩张角θ/（°） 10 被动二次流通道直径D1/mm 6 被动二次流通道与喷管喉道间距L2/mm 11.1 被动二次流控制孔直径Dsec/mm 2 
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表 2 空气桥系统参数表
Table 2. Table of the air-bridge force measurement system parameter
参数 数值 精度/% FX/N 150 0.5 FY/N 250 0.5 FZ/N 100 0.5 MX/（N·m） 12 0.3 MY/（N·m） 30 0.3 MZ/（N·m） 15 0.3 流量q/（g/s） 500
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表 3 主控方向控制输入表
Table 3. Table of primary control direction control inputs
控制输入K/% 被动二次流通道关闭个数n 0 6 33 1 67 3 100 5
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表 4 次控方向控制输入表
Table 4. Table of secondary control direction control inputs
控制输入K/% 被动二次流通道关闭个数n 0 6 50 2 100 4
下载: 导出CSV
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