摘要
3D打印技术相比于传统的固体推进剂浇注成型方法具有更高的制造灵活性和安全性。对于高固含量(质量分数大于85%)的固体推进剂材料,传统挤出打印方式存在挤出不连续、成型质量差等问题,限制了发动机的整体性能。针对上述问题,基于超声减摩辅助挤出原理设计了双超声振子共振挤出高固含量热固性固体推进剂打印头。重点探究了打印过程中打印温度、挤出压力、喷嘴直径等关键工艺参数对于打印推进剂材料孔隙率的影响。在打印温度为70℃、挤出压力为0.6 MPa、喷嘴直径为φ1.7 mm,打印层高间距比为0.8的最优工艺参数条件组合下,可打印制备固含量为88%、孔隙率为3.46%、打印制造误差被控制在0.4%以内的复杂变燃速热固性固体推进剂药柱结构,同时打印样件的拉伸强度较传统浇注样件提升56%,为复杂高固含量固体推进剂药柱结构的制造提供了一个新思路。
Compared with the traditional solid propellant casting method,3D printing technology possesses higher manufacturing flexibility and safety.For solid propellant materials with high solid content(The mass fraction is greater than 85%),the traditional extrusion printing methods have some problems,such as extrusion discontinuity and poor molding quality,which limit the overall performance of the motor.Aiming at the above problems,a dual ultrasonic vibrator resonance extrusion printhead for high solid content thermoset solid propellant was designed based on the principle of ultrasonic anti-friction assisted extrusion.The effects of key process parameters such as printing temperature,extrusion pressure and nozzle diameter on the porosity of the printed propellant material were investigated.Under the optimal process parameters of printing temperature of 70 ℃,extrusion pressure of 0.6 MPa,nozzle diameter of φ1.7 mm and printing layer height spacing ratio of 0.8,the complex variable burning rate thermosetting solid propellant grain structure with content of 88%,porosity of 3.46% can be printed,printing manufacturing error controlled within 0.4%.At the same time,the tensile strength of the printed sample is improved by 56% than that of the traditional casting sample,which provides a new idea for the manufacture of complex high solid content solid propellant grain structures.
作者
王杰
齐瑶
祁威
肖鸿
王奔
李伟
段玉岗
史佳齐
WANG Jie;QI Yao;QI Wei;XIAO Hong;WANG Ben;LI Wei;DUAN Yugang;SHI Jiaqi(School of Mechanical Engineering,Xi'an Jiaotong University,Xi'an 710049,China;Science and Technology on Aerospace Chemical Power Laboratory,Xiangyang 441003,China;Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China;Xi'an Aerospace Chemical Power Co.Ltd.,Xi'an 710025,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2024年第3期397-404,共8页
Journal of Solid Rocket Technology
基金
装备重大基础研究项目。
关键词
固体推进剂
3D打印
高固含量
超声减摩
solid propellant
3D printing
high solid content
ultrasonic anti-friction
