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发动机喷管外露于火箭尾部是常见情形,但在火箭气动设计过程中却经常不予考虑。利用数值计算方法,研究喷管外露部分对火箭气动静稳定及控制特性的影响。计算结果表明:在超声速Ma=2~12、攻角30°范围内,外露喷管对火箭气动静稳定性有1%~2%的增加,且气动控制效率明显,喷管±3°摆角产生的气动控制力矩约为头部空气舵±20°摆角的1~2倍。因此,对于确实存在喷管外露的火箭,在气动特性设计过程中需充分考虑喷管对静稳定性的影响,甚至可以考虑将喷管作为气动控制面,用于火箭无动力滑行段的姿态控制。
Exposed to the rear of the rocket engine nozzle is a common situation, but in the rocket aerodynamic design is often not considered. Numerical calculation method is used to study the effect of the exposed part of nozzle on aerostatic and static control of rocket. The calculated results show that the aerodynamic stability of the nozzle increases by 1% ~ 2% and the aerodynamic control efficiency is obviously increased when the ultrasonic velocity Ma = 2 ~ 12 and the angle of attack 30 °, and the nozzle angle ± 3 ° The resulting pneumatic control torque is about 1 ~ 2 times the head air rudder ± 20 ° swing angle. Therefore, for the rocket that does exist the nozzle is exposed, the influence of the nozzle on the static stability must be fully considered in the aerodynamic design process, and even the nozzle can be considered as the pneumatic control surface for the attitude control of the rocket without power sliding section .