Flight dynamics characteristics of miniature unmanned ducted vehicle

ZHAO Hong; LI Jian-bo; CUI Zhao

doi:10.13224/j.cnki.jasp.2014.07.027

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Flight dynamics characteristics of miniature unmanned ducted vehicle

更新时间：2026-07-07

- Flight dynamics characteristics of miniature unmanned ducted vehicle
- Issue 7, (2014)
- 作者机构：
  
  南京航空航天大学航空宇航学院直升机旋翼动力学国家级重点实验室,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.07.027
  CLC：
- Published：2014
- 稿件说明：
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赵洪, 李建波, 崔钊. 小型无人涵道飞行器飞行动力学特性[J]. 航空动力学报, 2014, (7): 1721-1728. doi: 10.13224/j.cnki.jasp.2014.07.027

ZHAO Hong, LI Jian-bo, CUI Zhao. Flight dynamics characteristics of miniature unmanned ducted vehicle[J]. 2014, (7).
赵洪, 李建波, 崔钊. 小型无人涵道飞行器飞行动力学特性[J]. 航空动力学报, 2014, (7): 1721-1728. doi: 10.13224/j.cnki.jasp.2014.07.027 DOI：

ZHAO Hong, LI Jian-bo, CUI Zhao. Flight dynamics characteristics of miniature unmanned ducted vehicle[J]. 2014, (7). DOI： 10.13224/j.cnki.jasp.2014.07.027.

摘要

为了研究无人涵道飞行器的配平特性与稳定性，首先进行了全尺寸涵道螺旋桨风洞吹风试验，分析了涵道螺旋桨的气动特性并建立了涵道螺旋桨的气动模型，在此基础上建立了无人涵道飞行器的飞行动力学数学模型，对无人涵道飞行器进行了配平特性与稳定性分析.结果表明：前飞速度与迎角对涵道螺旋桨气动特性影响很大，导致无人涵道飞行器在不同前飞速度下稳定性与操纵性变化较大.在悬停及小前飞速度下，无人涵道飞行器是一种类似倒立摆的不稳定体，而且气动阻尼较小，无人涵道飞行器的速度与姿态角发散很快，倍幅时间约为0.5 s；在大前飞速度下，无人涵道飞行器的气动阻尼增加，飞行稳定性改善，但出现了纵向反操纵现象，增加了无人涵道飞行器的飞行控制难度.

Abstract

To investigate the flight characteristics of unmanned ducted vehicle

a full-scale ducted propeller wind tunnel test was conducted to build the aerodynamic model and analyze the aerodynamic characteristics of ducted propeller. On these foundations

the flight dynamic mathematical model of the vehicle was established to investigate the characteristics trimming and stability of unmanned ducted vehicle.The results indicate that the aerodynamic characteristics of the ducted-propeller are strongly influenced by the forward speed and attitude angle

leading to significant variations in stability and maneuverability of the unmanned ducted vehicle at different forward speeds. This unmanned ducted vehicle is an unstable body similar to inverted pendulum in hover and low forward speed. The aerodynamic damping is small

while the speed and attitude angle diverge quickly

with double amplitude in 0.5 s. The flight stability is improved due to the increase of aerodynamic damping at high forward speed. The reverse control brings difficulties to flight control the unmanned ducted vehicle.

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