摘要
固体发动机地面试验燃气舵测力试验数据与习惯上的单独舵风洞测力试验存在着差异。多舵风洞测力试验表明：当喷流出口静压小于环境压力（＜１．０）燃气舵的气动性能重现了地面试验的结果；（＞１．０），与单独舵的风洞试验结果相接近。分析得出时燃气舵气动性能变差的原因是多舵使超音速喷流受堵，气流分离之故。
There are differences between the measured force data of the jet vanes in the ground test of solid rocket motor and the conventional wind-tunnet test results of onepiece vane.The wing-tunnel measured force tests of multi-vane shown that:when the static pressure of nozzle exit is less than environmental pressure(p<1.0),the aerodynamic performance of jet vane reappears the data of ground test.When p>1.0,it is slmost the same result with the wind-tunnel test of one-piece vane.The analyses show that: When P<1.0,the reason that jet vane performance is not good enough is that the multivane blocks up the supersonic jet flow and the gas flow is separated.
出处
《宇航学报》
EI
CSCD
北大核心
1994年第3期50-54,63,共6页
Journal of Astronautics
关键词
战术导弹
控制面
燃气舵
气动性能
Tactical missile Control surface Jet vane Aerodynamic performance
