The invention provides an air inlet channel boundary layer separation and elimination device and an aircraft. The boundary layer separation and elimination device comprises a fuselage bottom plate, anair inlet channel front body compression plate, a lip cover plate, a bulge assembly and a driving device, wherein the machine body bottom plate is arranged in the air inlet channel, the air inlet channel front body compression plate extends from an air inlet of the air inlet channel to the machine body bottom plate and is connected with the end, close to the air inlet, of the machine body bottomplate, the lip cover plate is arranged below the machine body bottom plate, an air inlet channel is formed by the lip cover plate and the machine body bottom plate, the bulge assembly comprises a bulge which is arranged in the air inlet channel, and is used for receiving incident lip cover shock waves, the driving device is arranged on the machine body bottom plate and is used for driving the bulge to do the reciprocating motion in the air inlet channel in the axial direction. By the adoption of the device, technical problems that in the prior art, a boundary layer separation and elimination device is large in additional resistance, complex in structure and small in effective working interval, and cannot meet the wide-speed-domain working requirement are solved.
本发明提供了一种进气道边界层分离消除装置及飞行器,该边界层分离消除装置包括机身底板、进气道前体压缩板、唇罩板、鼓包组件和驱动装置。机身底板设置在进气道内,进气道前体压缩板由进气道的进气口向机身底板处延伸,且与机身底板靠近进气口的一端相连接,唇罩板设置在机身底板的下方,与机身底板构成进气通道,鼓包组件包括鼓包,鼓包设置在进气通道内,用于接收入射的唇罩激波,驱动装置设置在机身底板上,用于驱动鼓包在进气通道内沿轴向往复运动。应用本发明的技术方案,以解决现有技术中边界层分离消除装置附加阻力大、结构复杂、有效工作区间小、无法满足宽速域工作需求的技术问题。
Air inlet boundary layer separation and elimination device and aircraft
一种进气道边界层分离消除装置及飞行器
2021-03-30
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Supersonic-inlet boundary-layer bleed flow
AIAA | 1996
|Hypersonic inlet boundary-layer research.
AIAA | 1966
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