摘要
针对新一代防空导弹高机动作战特点,研究了复杂横向变过载对固体火箭发动机绝热结构工程设计的影响。同时考虑过载值和过载角度的瞬时变化,对发动机绝热层进行网格划分,并对烧蚀厚度进行编程计算,进而按照安全裕度设计准则得到不同位置的绝热层设计厚度。与传统设计结果相比,考虑横向过载的变化可以显著减少了发动机的结构质量,提高了发动机总体性能,绝热质量减小了53.7%,总冲提高了6.84%。
Targeting the high-mobility characteristics of the new generation antiaircraft mis-siles, the influence of the complex transverse variable acceleration trajectory on the engineering design for the solid rocket motor insulation structure was studied. It considered the instantaneous changes of acceleration value and angle,meshed the insulation structure,and calculated its abla-tion thickness by programming,and then the design thickness of the heat insulation layer at differ-ent positions was obtained according to the safety margin design criterion. Compared with tradi-tional design results, considering the change of transverse acceleration significantly reduced the structural mass of the motor,and improved the overall performance;the heat insulation mass of the motor was reduced by 53. 7%,and the total impulse was increased by 6. 84%.
作者
孙迪
李永洲
刘晓伟
甘晓松
SUN Di;LI Yongzhou;LIU Xiaowei;GAN Xiaosong(School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China;Xi'an Institute of Aerospace Propulsion Technology,China Aerospace Science and Technology Corporation,Xi'an 710025,China;School of Aerospace Engineering,Huazhong University of Science and Technology,Wuhan 430074,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2021年第11期2458-2464,共7页
Journal of Aerospace Power
基金
国家自然科学基金(11702205)
博士启动基金(EA202006371)。
关键词
固体火箭发动机
横向变过载
烧蚀
绝热结构
总冲
solid rocket motor
transverse variable acceleration
ablation
insulation structure
total impulse
