复合式直升机过渡飞行功率特性

曹飞; 陈铭; 田力; 邓阳平

doi:10.13224/j.cnki.jasp.2016.02.021

复合式直升机过渡飞行功率特性

doi: 10.13224/j.cnki.jasp.2016.02.021

1. 北京航空航天大学航空科学与工程学院, 北京 100191;
2. 西北工业大学航空学院, 西安 710072

详细信息

作者简介:
曹飞(1987-),男,北京人,博士生,主要从事直升机总体设计和飞行动力学研究.

中图分类号: V275
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- 被引次数: 0
出版历程
- 收稿日期: 2015-03-19
- 刊出日期: 2016-02-28

Power characteristics of the compound helicopter in transition flight mode

1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 为研究复合式直升机其特殊飞行方式下的动力系统功率分配问题,建立了由气动部件和机械传动部件数学模型组成的复合式直升机性能综合计算模型.通过对其飞行条件进行约束,建立了该种飞行器的过渡飞行边界,并对边界内不同过渡路线下的功率进行计算,分析了气动部件和传动部件对复合式直升机过渡飞行过程中的功率影响,并通过地面试验模拟该飞行方式下的功率使用状况对计算模型进行数据验证,结果表明虽然计算值与试验值存在6%的误差,但比传统性能计算方法精度提高了4%.通过该方法可建立一种更为有效的复合式直升机性能计算方法.
- 复合式直升机 /
- 动力系统 /
- 功率分配 /
- 数学模型 /
- 功率损耗
Abstract: To study the power and transmission system's power division of compound helicopter in its particular flight style, a comprehensive performance calculation model that consists of the mathematical model combining the aerodynamics parts and mechanical drive system parts was established. By limiting the flight conditions, the compound helicopter's transition flight border was established. After calculating the power of different routes in the transition flight border, what impact the aerodynamics parts and mechanical drive system parts had on the compound helicopter during the transition flight was analyzed. By a ground test simulating power division in that flight style, the date validation for mathematical model was made. Although there is error of 6% between the computing result and the experimental result, the accuracy has been improved 4% compared with the traditional calculation method. According to this method, it's possible to establish a more effective compound helicopter performance calculation method.
- compound helicopter /
- power system /
- power division /
- mathematical model /
- power loss

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