摘要
提出一种新型无杆式气缸导弹弹射装置,可实现小尺寸、长行程、低过载发射。引入真实气体状态方程—RK状态方程,推导真实气体条件下比热力学能、比焓等热力学参数表达式,建立考虑真实气体效应的无杆式气缸弹射装置内弹道模型,获得了导弹弹射过程中热力学参数与导弹运动参数的变化规律。计算结果表明:与"单电磁阀"供气方案相比,采用优化后的"主副电磁阀"供气方案,在弹射结束时,气体质量流量增大52.9%,低压室压强提高14.3%,导弹过载系数提高了41.3%;在最大过载和有效推弹行程不变的条件下,导弹的离轨速度提高15.8%。
In order to achieve a type of new ejection device with low acceleration, long travel-length and small size, a kind of high-pressure pneumatic missile cold ejection device with rod-less cylinder was designed. The real gas state equation-'Redlich-Kwong' equation was used as a theoretical basis. Based on the 'RK' state equation, the mathematical expressions of specific thermodynamic energy and specific enthalpy were deduced and a pneumatic internal ballistics equation was proposed. The variation of thermodynamic and kinematic parameters were obtained in the process of catapult. The results show that the mass flow rate from the high pressure chamber to low pressure chamber raises by 52.9% compared with the single valve scheme. Besides, in the later stage in launching, the pressure in low pressure chamber is increased by 14.3% and the missile overload coefficient is improved by 41.3%. Most of all, the launching speed of missiles is increased by 15.8% with the maximum overload and effective stroke kept constant. © 2017, Editorial Office of Journal of Vibration and Shock. All right reserved.
出处
《振动与冲击》
EI
CSCD
北大核心
2017年第6期122-127,198,共6页
Journal of Vibration and Shock
基金
国防基础科研(B2620110005)
江苏省研究生创新资助计划(KYLX_0328)
