摘要
为提高潜艇的快速反应能力 ,必须使潜艇具备导弹变深度发射能力 ,则导弹发射系统就必须提供能量可变的发射动力。根据发射系统内弹道计算模型 ,针对燃气发生器喷喉面积对导弹发射动力的影响进行导弹运动参数、内弹道性能的计算与分析。在发射筒构造诸元和装填条件确定时 ,当燃气发生器喷喉面积在一定范围变化 ,导弹运动加速度、出筒速度以及燃气工质的做功能力发生相应改变。因此提出在喷管内设有一调节锥 ,通过改变调节锥的轴向位置来控制喷喉面积 ,以实现有限度的可调发射动力 ,并给出对应于某发射深度范围的喷喉面积调节范围。研究结果表明 ,通过控制燃气发生器喷喉面积 ,使潜射导弹发射动力得到有效调节 。
The submarine needs to be provided with missile changeable depth launch capacity to advance its own speedy feedback capability. Then the available energy of the missile launch system must be controllable. Based on the interior trajectory calculation model of the launch system, the parameters of missile movement and interior trajectory performance are numerated and analyzed for the influence of gas generator nozzle throat area on launch power. Ascertaining the launch canister construct and the propellant, the certain adjustment of nozzle throat area results in the change of the movement acceleration and exiting speed of missile and gas work medium power. Therefore, the technology for controlling nozzle throat area for the realization of limited and adjustable launch power is put forward. It is shown that nozzle throat area is controlled by changing the axis direction position of modulating taper which is set in nozzle. And the adjustment range of the nozzle throat area corresponding to certain launch depth range is educed. Results indicate that the submarine-based missile launch power is effectively controlled by adjusting gas generator nozzle throat area. Therefore the changeable depth missile launch can be realized in theory.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2004年第3期353-357,共5页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
导弹
发射动力
内弹道
喷喉面积
燃气发生器
missile
launch power
interior trajectory
nozzle throat area
gas generator
