检索结果-南通市图书馆

Study on the lift and propulsive force shares to improve the flight performance of a compound helicopter

Chinese Journal of Aeronautics 2022年第1期35卷 365-375页

作者： Kelong YANG Dong HAN Qipeng SHI Key Laboratory of Science and Technology on Rotorcraft Aeromechanics College of Aerospace EngineeringNanjing University of Aeronautics and AstronauticsNanjing 210016China

To investigate the effects of lift and propulsive force shares on flight performance,a compound helicopter model is *** model consists of a helicopter model,a wing model and a propeller *** a low speed of 100 km/h,the Lift-to-Drag ratio(L/D)of the compound helicopter is improved when the wing provides 20.2%of the take-off *** high speeds,the L/D can be improved when the propeller provides the total propulsive *** the main rotor speed increases the wing lift share,however,the maximum L/D increases first and then *** maximum L/D increases with decreasing the blade twist of the main *** the blade twist from-16°to-8°increases the maximum L/D by 2.3%,and the wing lift share is increased from 65.0%to 74.7%.When the main rotor torque is balanced by the rudder,the maximum L/D is increased by 2.2%without changing the wing lift *** wing should provide more lift as increasing the take-off weight,which reduces the induced power of the main rotor and increases the L/*** increasing the take-off weight from 9500 kg to 11000 kg,the maximum L/D is increased by 6.5%,and the wing lift share is increased from 74.7%to 80.2%.

关键词： compound helicopter Flight performance Lift share Lift-to-Drag ratio Propeller Propulsive force share Wing

来源：

维普期刊数据库

同方期刊数据库评论

在线全文

学校读者我要写书评

暂无评论

Performance Analysis of Slowed Rotor compound helicopter

引用

Transactions of Nanjing University of Aeronautics and Astronautics 2020年第S1期37卷 9-17页

作者： SHAH Suman HAN Dong YANG Kelong College of Aerospace Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China

The performance of slowed-rotor compound aircraft,particularly at high-speed flight condition,is *** forward flight performance calculation model of the composite helicopter is established,and the appropriate wing and propeller parameters are *** predicted performance of isolated propeller,wing and rotor combination is *** kinds of tip speed and a range of load share setting are *** bearing 80%of the thrust with wing sharing lift is found to be the best condition to have better performance and the maximum L/D for maximum forward *** rotor,propeller,and wing performance are examined for sea level,1000 m,and 2000 m cruise ***,propeller,and wing power are found to be largely from profile drag,except at low speed where the wing is near *** elevation offloads lift from the rotor to the wing,dropping the total power required and increasing the maximum speed limit over 400 km/h.

关键词： compound helicopter wing propeller flight performance lift distribution thrust distribution

来源：

维普期刊数据库

同方期刊数据库评论

在线全文

学校读者我要写书评

暂无评论

Research on Trim Control of compound High Speed helicopter

引用

Transactions of Nanjing University of Aeronautics and Astronautics 2019年第3期36卷 449-458页

作者： YU Zhiming KONG Weihong CHEN Renliang National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics Nanjing University of Aeronautics and Astronautics

An investigation is conducted on optimizing the control allocation for trimmed flight on the compound *** compound helicopter features a single main rotor,a vectored thrust ducted propeller(VTDP)and lifting *** to the redundant controls for thrust,elevator deflection,and differential and symmetric flap deflection,there is a wide range of trim solutions in forward flight for compound helicopter.A method is developed to calculate optimal trim ***,aerodynamics models for deferent subsystems of the compound helicopter are conducted,which consider the mutual interaction of each ***,a flight dynamics model is developed based on which the method of trim optimization is ***,the method is demonstrated using a compound helicopter UH 60L/*** trim optimization of flight conditions from hover to 370 km/h is conducted using the optimization *** controls,fuselage attitudes as well as the allocation of lift and thrust along with the flight speed are obtained.

关键词： compound helicopter trim control optimization

来源：

维普期刊数据库

同方期刊数据库评论

在线全文

学校读者我要写书评

暂无评论

欢迎您,

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

在线全文

在线全文

在线全文

请选择保存的检索档案：

请选择收藏分类：

通借通还

欢迎您,

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

在线全文

在线全文

在线全文

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：