The present invention relates to an acoustic panel for an aircraft nacelle air intake, to an aircraft propulsion unit equipped with such an acoustic panel for a nacelle air intake, and to an aircraftcomprising such a propulsion unit. The acoustic panel comprises a resistive skin 1 perforated by noise absorption holes 10 and a core 2 against which the resistive skin extends, characterized in thatthe resistive skin 1 has a smooth visible face 11 and a castellated rear face 12 with alternating ribs 14 and grooves 13. The noise absorption holes 10 are formed exclusively in the grooves 13, i.e.,in a zone where the skin is less thick, which enables the holes to have a diameter that is both greater than the thickness of the skin and small enough not to have any impact on drag. The mechanical strength of the resistive skin provided by the ribs ensures that the lesser thickness of the resistive skin in the grooves does not render the resistive skin overly flexible.
本发明涉及用于飞行器短舱进气口的声学面板,还涉及短舱进气口配有这种声学面板的飞行器推进单元和包括这种推进单元的飞行器,声学面板包括被噪声吸收孔(10)穿孔的抵抗性蒙皮(1)和抵抗性蒙皮(1)抵靠其延伸的芯部(2),其特征在于,抵抗性蒙皮(1)具有光滑的可见面(11)和带有交替的肋(14)和凹槽(13)的堞形后部面(12),噪声吸收孔(10)仅在凹槽(13)中即在蒙皮不太厚的区域中形成,这使得孔的直径既大于蒙皮的厚度,又足够小,从而不会对阻力产生任何影响。抵抗性蒙皮在凹槽中的较小厚度不会使得抵抗性蒙皮比现有技术中的蒙皮更柔韧,因为根据本发明的抵抗性蒙皮的机械强度由肋确保。
Acoustic panel for an aircraft nacelle air intake, and associated propulsion unit and aircraft
飞行器短舱进气口的声学面板、相关的推进单元及飞行器
2021-03-12
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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