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针对超声速串联布局飞行器在稠密大气层内主级与助推级级间分离的运动特性问题,采用运动自由度不受约束的风洞自由飞试验方法,很好地复现助推级和主级分离的动态运动过程,且创新地模拟助推级发动机带有残余推力对主级与助推级分离特性的影响规律。在试验马赫数Ma=2.5,侧滑角β=0°条件下,通过改变初始分离迎角α(0°、5°),研究了分离迎角α对主级与助推级分离后级间相对位置的影响规律。结果表明:初始分离迎角α是影响主级与助推级分离相对位置的关键参数,当初始分离迎角α=5°时,主级与助推级分离后级间相对位置变化较α=0°迅速,适当增加初始分离迎角α更有利于飞行器的级间分离;助推级有/无发动机残余推力对主级与助推级分离后的级间相对位置影响较小,这表明超声速串联布局飞行器在大气层内级间分离的运动特性由主级与助推级所受的气动力主导。
Aiming at the motion characteristics of the supersonic tandem layout aircraft in separating the main stage and the boosting stage in the dense atmosphere, the wind tunnel free-flying test method with unrestricted freedom of movement is adopted to reproduce the boost stage and main stage separation well The dynamic law of motion of the main stage and the boosting stage is simulated innovatively to simulate the influence of the residual thrust of the boosted engine. Under the condition of Ma = 2.5 and β = 0 °, the attack angle α (0 °, 5 °) of the initial separation was changed, The relative position of the law of influence. The results show that the initial separation angle of attack α is the key parameter that affects the relative position between the main stage and the boost stage. When the initial separation angle of attack α = 5 °, the relative position between the main stage and the boost stage is α = 0 ° quickly and appropriate increase of the initial separation angle of attack α is more conducive to the aircraft’s interstage separation; booster stage with / without engine residual thrust on the main stage and boost stage separated interstage relative position less affected, indicating supersonic The kinematics of tandem layout aircraft in the interplanetary stage are dominated by the aerodynamic forces experienced by the main stage and the boosters.