摘要
舰载机依靠蒸汽弹射器输出的弹射力推动其达到起飞速度,因此控制弹射力的输出尤为重要,为了分析研究蒸汽弹射器对弹射力输出的控制,本文阐明了蒸汽弹射器中控制蒸汽流量的发射阀结构和基本工作原理,提出发射阀中测量杆的位移与流通面积的计算方法,从而求解蒸汽流量,并结合蒸汽弹射器的热力学变化过程进行数学建模。以C13型弹射器为例进行仿真,通过实验数据的对比分析,说明了本文所建模型的可行性和正确性,其仿真结果可为蒸汽弹射器的设计与试验提供有益参考。
The steam catapult exerts launching force on carrier-based aircraft to thrust it achieving its takeoff speed.In order to analyze the controlling process of launching force of steam catapult, the structure and basic principle of launch valve controlling steam flow in the catapult was illustrated, then a method to calculate placement of metering rod and flow area of launch valve was proposed. Combined with the thermodynamic c working the dis- hangea ble process of catapult, a mathematics model was established, and the flow rate of steam was obtained. Based on C13 steam catapult simulations for its thermodynamics was conducted and the feasibility and correctness of mathe- matical model was proved by the comparison between simulation results and experimental data.
出处
《机械科学与技术》
CSCD
北大核心
2013年第7期963-967,共5页
Mechanical Science and Technology for Aerospace Engineering
基金
航空基金项目(2008ZA53006
2006ZD53050)资助
关键词
蒸汽弹射器
蒸汽流量
仿真
分析
aircraft carriers
catapults （ aircraft launchers）
valves
thermodynamics
steam
aircraft
computersimulation
control
design
experiments
mathematical models
velocity
steam catapult
steamflow
simulation
analysis
