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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >DEVELOPMENT OF SCRAMJET ENGINE AIR INTAKE COWL OPENING MECHANISM WITH DAMPED PYRO ACTUATOR AND ITS FLIGHT PERFORMANCE
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DEVELOPMENT OF SCRAMJET ENGINE AIR INTAKE COWL OPENING MECHANISM WITH DAMPED PYRO ACTUATOR AND ITS FLIGHT PERFORMANCE

机译:阻尼高温致动器对SCRAMJET发动机进气口打开机制的研究及其飞行性能

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摘要

The intake of the sc ramjet engines is kept normally closed by the cowl,which is to be opened when scramjet test conditions are reached.Air Intake cowl opening mechanism is designed for this purpose which should not have any protrusions in the flow field as well as provide high initial torque.The mechanism consists o f a coupling o f slider crank mechanism and twin four bar linkage actuated by integrating a pyro actuator with hydraulic damper.This paper describes the configuration,challenges,design and development aspects of air intake cowl opening mechanism,designed and flown in ISRO fs scramjet demonstration flight.An extensive mathematical model is developed inculcating the kinetics and kinematics of the mechanism,damper characteristics and actuator profile for simulating the flight conditions.Qualification test results are used to fine tune the mathematical model which is used for prediction o f flight performance parameters.The flight performance analysis demonstrates that the intended objective is precisely achieved.
机译:冲压冲压发动机的进气口通常由前围板保持关闭,在达到冲压试验条件时应将其打开。为此,设计了进气前围板开启机构,该机构在流场中不应有任何突起,并且该机构由一个滑块曲柄机构和一个双四连杆机构组成的联轴器组成,该双四连杆机构通过将一个火力致动器与液压阻尼器集成而致动。本文介绍了进气罩打开机构的结构,面临的挑战,设计和开发方面,在ISRO fs超燃冲压发动机示范飞行中飞行。开发了广泛的数学模型,其中包括用于模拟飞行条件的机构的动力学和运动学,阻尼特性和执行器轮廓。使用合格测试结果来微调用于预测的数学模型飞行性能参数。飞行性能分析表明最终目标得以实现。

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