直升机旋翼桨叶防/除冰系统防护范围研究

常士楠; 刘达经; 袁修干

直升机旋翼桨叶防/除冰系统防护范围研究

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
中国直升机设计研究所, 景德镇 333001

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出版历程
- 收稿日期: 2006-03-09
- 修回日期: 2006-05-18
- 刊出日期: 2007-03-28

Research on protected range of the anti-icing/deicing system for helicopter rotor

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
China Helicopter Research and Development Institute, Jingdezhen 333001, China

摘要

摘要: 直升机主旋翼桨叶在结冰气象条件下有结冰的危险, 为了满足直升机全天候仪表飞行的要求, 必须对桨叶采取结冰防护.本文针对某翼型直升机桨叶, 通过分析表面各项热流, 计算表面温度为零时极限结冰状态的临界速度, 确定了桨叶展向结冰防护范围为沿展向从翼根到翼尖0～95%;采用分析水滴在气流场中运动的拉格朗日法计算水滴撞击特性, 确定桨叶弦向结冰防护范围为上表面12%, 下表面33%.在此基础上对桨叶表面加热形式和结构进行设计, 可为直升机旋翼桨叶防/除冰系统设计奠定基础, 此研究具有重要的实用价值.
- 航空、航天推进系统 /
- 直升机旋翼 /
- 防/除冰系统 /
- 水滴撞击特性 /
- 桨叶
Abstract: Under icing conditions,helicopter rotor is prone to icing.The rotor icing menaces the safety of the helicopter seriously,so the blade must be protected from icing.Through the analysis of external heat fluxes,the critical velocity was calculated for a given blade at ultimate state of icing when surface temperature was 0℃.The protected range along spanwise was then determined to be 0～95% form blade root to tip.By calculating the droplet impinging characteristic, the protected range along chordwise form the leading edge was then determined to be 12% along the upper surface and 33% along the lower surface.On the basis of the results,the configuration and structure of the heating system for a rotor blade can be designed.
- aerospace propulsion system /
- helicopter rotor /
- anti-icing/deicing system /
- water droplet impingement /
- rotor blade

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参考文献(9)

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