高超声速进气道是高超声速吸气式推进系统的重要组成部分，对实现高超声速飞行起着关键作用。
Scramjet inlet is of great importance in the hypersonic airbreathing propulsion system and plays significant role in the realization of hypersonic flight.
进气系统主要包括空气滤清器、进气道、化油器和进气歧管。一些发动机在进气系统中有增压器。
The intake system mainly includes the air filter, intake ducting, the carburetor, and the intake manifold. Some engines have supercharger in the in take system.
研究开发CA6102型汽油机紊流燃烧系统时，涉及到一些切向进气道设计中的基本问题。
Some fundamental problems in designing the tangential inlet passage are involved when the turbulent combustion system for model CA6102 gasoline engine is researched and developed.
飞机进气道斜板控制系统是一种典型的电液位置伺服系统。
The controller for swash plate of aircraft inlet is a typical hydraulic serve position control system.
理论计算与试验结果证明，采用双进气道可控进气涡流系统是改善大功率柴油机低负荷性能的一个有效途径。
Theoretical and experimental results suggest that the engine performance at low load can be improved with the variable swirl twin inlet port.
论述了飞机进气道可变几何形状控制系统的鲁棒设计方法和系统的综合试验。
A Robust design approach and integrated test procedure of the aircraft variable geometry inlet control system are discussed.
论述了飞机进气道可变几何形状控制系统的鲁棒设计方法和系统的综合试验。
A Robust design approach and integrated test procedure of the aircraft variable geometry inlet control system are discussed.
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