Investigation of control strategy for quad⁃tilt⁃rotor aircraft in helicopter mode

Pan ZHOU; Renliang CHEN; Zhiming YU

doi:10.13224/j.cnki.jasp.20200384

Chinese

您当前的位置：

首页 >

文章列表页 >

Investigation of control strategy for quad⁃tilt⁃rotor aircraft in helicopter mode

Aerothermodynamics and Aeroengine Design | 更新时间：2025-04-07

- Investigation of control strategy for quad⁃tilt⁃rotor aircraft in helicopter mode
- Journal of Aerospace Power Vol. 36, Issue 10, Pages: 2036-2051(2021)
- 作者机构：
  
  南京航空航天大学航空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.20200384
  CLC：
- 稿件说明：
移动端阅览
Pan ZHOU, Renliang CHEN, Zhiming YU. Investigation of control strategy for quad⁃tilt⁃rotor aircraft in helicopter mode[J]. Journal of Aerospace Power, 2021, 36(10): 2036-2051.
DOI：

Pan ZHOU, Renliang CHEN, Zhiming YU. Investigation of control strategy for quad⁃tilt⁃rotor aircraft in helicopter mode[J]. Journal of Aerospace Power, 2021, 36(10): 2036-2051. DOI： 10.13224/j.cnki.jasp.20200384.

摘要

由于倾转四旋翼飞行器具有特殊的构型，针对直升机模式下的操纵策略，建立了样机的非线性飞行动力学模型并结合试验数据进行了验证，提出了适用于直升机模式的四种操纵方式，对比了不同操纵方式相应的配平值、操纵功效及操纵耦合，随后确定了一组相对合理的操纵方式，解决了倾转四旋翼飞行器在直升机模式下操纵冗余的问题。分析了重心位置对所确定操纵方式的配平特性和操纵功效的影响。结果表明：纵横向通道下总距差动引起的操纵功效比周期变距联动大得多；偏航通道下周期变距差动引起的操纵功效大于总距差动，横向周期变距差动引起的交叉耦合小于纵向周期变距差动；正常重心位置所得到的配平量和交叉耦合最小。

Abstract

Quad⁃tilt⁃rotor aircraft is a vehicle of particular configuration.For its strategy of the helicopter mode，a nonlinear flight dynamic model was established for a prototype，and some relevant test were carried out.Four control strategies were proposed，and a relatively reasonable control strategy was determined by comparing the trim values，control efficiency and cross coupling.The control redundant problem of quad⁃tilt⁃rotor aircraft in helicopter mode was solved under the strategy.At last，the influence of the center of gravity location on trim characteristics and control efficiency was analyzed.The results showed that the main control efficiency of longitudinal and lateral channel obtained by collective differential was much greater than by linkage of cyclic pitch.The main control efficiency of yaw channel obtained by cyclic pitch differential was greater than by collective differential.The cross coupling of yaw channel obtained by lateral cyclic pitch differential was less than longitudinal cyclic pitch differential.The values of trimming and cross coupling were the minimum at the normal position of center of gravity.

关键词

Keywords

references

陈恒 , 左晓阳 , 张玉琢 . 倾转旋翼飞机技术发展研究 [J]. 飞行力学 , 2007 , 25 （ 1 ）: 5 ⁃ 8 .

CHEN Heng , ZUO Xiaoyang , ZHANG Yuzhuo . Tilt⁃rotor aircraft key technology developing research [J]. Flight Dynamics , 2007 , 25 （ 1 ）: 5 ⁃ 8 . （in Chinese）

薛蒙 , 孙强 . 倾转旋翼机军事需求与关键技术分析 [J]. 直升机技术 , 2020 （ 1 ）: 47 ⁃ 49，27 .

XUE Meng , SUN Qiang . Tiltrotor military requirement and critical technology analysis [J]. Helicopter Technique , 2020 （ 1 ）: 47 ⁃ 49，27 . （in Chinese）

BRAGANCA E . The V⁃22 osprey:from trouble past to viable and flexible option [J]. Joint Force Quarterly , 2012 , 66 : 80 ⁃ 84 .

KING D W . A system engineering approach to carefree maneuvering in the BA609 [R]. Grapevine,US : American Helicopter Society , 2005 .

SNYDER D E . The quad tiltrotor:its beginning and evolution [R]. Arlington,US : International Powered Lift Conference , 2000 .

RADHAKRISHMAN A , SCHMITZ F H . Quad tilt rotor aerodynamics in ground effect [R]. Toronto,Canda : AIAA Applied Aerodynamics Conference , 2006 .

RADHAKRISHMAN A . An experimental investigation of ground effecton a quad tilt rotor in hover and low speed forward flight [D]. College Park,US : University of Maryland , 2006 .

YEO H , JOHNSON W . Performance and design investigation of heavy lift tilt⁃rotor with aerodynamic interference effects [J]. Journal of Aircraft , 2009 , 46 （ 4 ）: 1231 ⁃ 1239 .

潘浙平 . 倾转四旋翼飞行器倾转过渡走廊计算方法研究 [D]. 南京 : 南京航空航天大学 , 2019 .

PAN Zheping . Investigation on conversion corridor analysis method of quad tilt rotor aircraft [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2019 . （in Chinese）

周攀 , 陈仁良 , 俞志明 . 倾转四旋翼飞行器直升机模式操稳特性分析 [J]. 西北工业大学学报 , 2021 , 39 （ 3 ）: 675 ⁃ 684 .

ZHOU Pan , CHEN Renliang , YU Zhiming . Analysis on controllability and stability of quad⁃tilt⁃rotor aircraft in helicopter mode [J]. Journal of Northwestern Polytechnical University , 2021 , 39 （ 3 ）: 675 ⁃ 684 . （in Chinese）

俞志明 , 陈仁良 , 孔卫红 . 倾转四旋翼飞行器倾转过渡走廊分析方法研究 [J]. 北京航空航天大学学报 , 2020 , 46 （ 11 ）: 2106 ⁃ 2113 .

YU Zhiming , CHEN Renling , KONG Weihong . Investigation on analysis methed for conversion corridor of quad tilt rotor aircraft [J]. Journal of Beijing University of Aeronautics and Astronautics , 2020 , 46 （ 11 ）: 2106 ⁃ 2113 . （in Chinese）

WANG Z G , ZU R , DUAN D Y , et al . Tuning of ADRC for QTR in transition process based on NBPO hybrid algorithm [J]. IEEE Access , 2019 （ 7 ）: 177219 ⁃ 177240 .

蒋海辉 . 倾转四旋翼飞行器操纵策略研究 [D]. 南京 : 南京航空航天大学 , 2019 , 35 ⁃ 50 .

JIANG Haihui . Manipulation stategy for quad tilt rotor aircraft [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2019 , 35 ⁃ 50 . （in Chinese）

严旭飞 , 陈仁良 . 倾转旋翼机动态倾转过渡过程的操纵策略优化 [J]. 航空学报 , 2017 , 38 （ 7 ）: 520865.1 ⁃ 520865.11 .

YAN Xufei , CHEN Renliang . Control strategy optimization of dynamic conversion procedure of tilt⁃rotor aircraft [J]. Acta Aeronautica et Asastronatica Sinca , 2017 , 38 （ 7 ）: 520865.1 ⁃ 520865.11 . （in Chinese）

曹芸芸 , 陈仁良 . 倾转旋翼飞行器的操纵策略和配平方法 [J]. 南京航空航天大学学报 , 2009 , 41 （ 1 ）: 6 ⁃ 10 .

CAO Yunyun , CHEN Renliang . Control strategy for tilt⁃rotor aircraft trimming in steady level flight [J]. Journal of Nanjing University of Aeronautics and Astronautics , 2009 , 41 （ 1 ）: 6 ⁃ 10 . （in Chinese）

夏青元 , 徐锦法 , 金开保 . 倾转旋翼飞行器的建模和操纵分配策略 [J]. 航空动力学报 , 2013 , 28 （ 9 ）: 2016 ⁃ 2028 .

XIA Qingyuan , XU Jinfa , JIN Kaibao . Tilt⁃rotor aircraft modeling and its manipulation assignment strategy [J]. Journal of Aerospace Power , 2013 , 28 （ 9 ）: 2016 ⁃ 2028 . （in Chinese）

余新 , 陈仁良 . 基于增益调度与光滑切换的倾转旋翼机的最优控制 [J]. 北京航空航天大学学报 , 2021 , 47 （ 6 ）: 1186 ⁃ 1198 .

YU Xin , CHEN Renliang . Optimal control of tilt rotor aircraft based on gain⁃scheduling and smooth⁃switching [J]. Journal of Beijing University of Aeronautics and Astronautics , 2021 , 47 （ 6 ）: 1186 ⁃ 1198 . （in Chinese）

TALBOT P D , TINLING B E , DECKER W A . A mathematical model of a single main rotor helicopter for piloted simulation [R]. San Jose,US : NASA Technical Memorandum 84281 , 1982 .

曹芸芸 . 倾转旋翼飞行器飞行动力学数学建模方法研究 [D]. 南京 : 南京航空航天大学 , 2012 .

CAO Yunyun . Research on mathematical modeling method for tilt rotor aircraft flight dynamics [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2012 . （in Chinese）

FERGUSON S W . A mathematical model for real time flight simulation of a generic tilt⁃rotor aircraft [R]. NASA CR⁃166536 , 1988 .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Control strategy for compound coaxial helicopter under conversion mode

Development overview and key technologies of high speed hybrid helicopter with single main rotor

Rotor aerodynamic characteristics analysis and helicopter trimming

Analytical method of rotor aerodynamic characteristics by coupling a high-efficiency trim strategy

Helicopter performance improvement by rotor morphing technologies

Related Author

WANG Qiang

CHEN Ming

XU Guan-feng

WANG Liangquan

ZHU Qinghua

HE Long

XU Dongxia

HUANG Mingqi

Related Institution

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics

Army Aviation Research Institute, the Headquarters of General Staff, the Chinese People's Liberation Army

Rotor Aerodynamics Key Laboratory,Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics

中国人民解放军陆军航空兵研究所总体论证室

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰