Development and flight testing of a fluidic thrust vectoring demonstrator

CAO Yongfei; GU Yunsong; HAN Jiexing

doi:10.7638/kqdlxxb-2017.0202

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Development and flight testing of a fluidic thrust vectoring demonstrator

更新时间：2026-05-28

- Development and flight testing of a fluidic thrust vectoring demonstrator
- Vol. 37, Issue 4, Pages: 593-599(2019)
- 作者机构：
  
  1. 中国航空工业空气动力研究院,沈阳,110034
  2. 南京航空航天大学航空宇航学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0202
  CLC： V211.7
- Published：2019
- 稿件说明：
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曹永飞, 顾蕴松, 韩杰星. 流体推力矢量技术验证机研制及飞行试验研究[J]. 空气动力学学报, 2019, 37(4): 593-599.

CAO Yongfei, GU Yunsong, HAN Jiexing. Development and flight testing of a fluidic thrust vectoring demonstrator[J]. 2019, 37(4): 593-599.
曹永飞, 顾蕴松, 韩杰星. 流体推力矢量技术验证机研制及飞行试验研究[J]. 空气动力学学报, 2019, 37(4): 593-599. DOI： 10.7638/kqdlxxb-2017.0202.

CAO Yongfei, GU Yunsong, HAN Jiexing. Development and flight testing of a fluidic thrust vectoring demonstrator[J]. 2019, 37(4): 593-599. DOI： 10.7638/kqdlxxb-2017.0202.

摘要

为验证被动二次流推力矢量技术的有效性，评估其飞行控制能力，研制了一架基于被动二次流推力矢量动力装置的验证机模型并开展了飞行试验研究。以完成筋斗机动动作的时间和半径作为流体推力矢量控制性能的评估参数。采用微型航姿传感器记录了验证机模型在有无流体矢量作用时完成筋斗动作的俯仰角和俯仰角速度数据，并通过无线数据传输装置传回地面加以储存和分析。飞行试验结果显示，在使用流体矢量情况下，验证机完成筋斗机动动作的半径由单独舵面控制时的约9倍机身长度减小为2倍机身长度、平均时间由4.93 s降为2.28 s、最大俯仰角速度的均值由114.5°/s提高到了270.3°/s。该结果证实了被动二次流推力矢量技术在急剧飞行状态下能够发挥作用，且具有较强的姿态控制效能。

Abstract

A demonstrator model based on passive secondary flow thrust vector power device was developed and the flight test was carried out

in order to verify the effectiveness of the passive secondary flow thrust vectoring technique and to evaluate its ability to change the attitude. The maneuvering time and radius of the loop maneuver were chosen as evaluation parameters of fluidic thrust vectoring control performance. The pitch angle and pitch rate data of the demonstrator model completed loop maneuver with and without vectors were recorded by micro-attitude sensors

and the data were sent back to the ground through the wireless data transmission device to store and analyze. The results show that

after employing the fluidic vectoring

the radius of the loop maneuver is reduced from 9 times the length of the fuselage to 2 times

the average time is reduced from 4.93s to 2.28s

and the mean value of maximum pitch rate is increased from 114.5°/s to 270.3°/s

compared with only rudder control. The results confirm that the passive secondary flow thrust vectoring technique can work in the rapid flight state and has a strong attitude control efficiency.

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references

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