先进反舰导弹ANL选用冲压发动机为动力

最近,法国宇航公司(Aerospatiale)公布了一种新的轻型反舰导弹ANL的情况.该导弹由法宇航公司与西德MBB公司合作研制,拟采用冲压发动机.法宇航公司建议用液体燃料冲压发动机,就像ASMP战术核导弹上用的液体冲压发动机那样,而MBB则建议用固体火箭-冲压发动机.     

氦气泄漏试验研究与应用

用氦气作飞行全程增压气体在我国尚属新的课题.根据型号要求进行的一系列氦气泄漏试验和使用特性研究表明,氦气的泄漏特性是可掌握的,而且普通的密封结构也能适应.对于常规推进剂火箭,其检漏方法亦不需特殊的仪器设备和手段;使用中可用空气代替氦气进行密性检查,同样能达到系统使用要求.采用全程氦气增压可减轻增压系统重量,使火箭运载能力提高1/9.     

推进剂贮箱出流与夹气

本文概述了贮箱出流夹气的四种基本情况,并根据自己试验研究工作中的观察和体会逐一分析了防止夹气的方法和难易程度,指出减少剩余量的方向和措施。供推进剂贮箱设计者参考。     

两种含铝复合推进剂压强耦合响应的实验对比

基于T型燃烧器双脉冲外部激励的方法,对2种含铝HTPB复合固体推进剂开展对比实验研究,分析比较其压强耦合响应特性的差异。在7 MPa条件下成功地开展了4次试验,获得了2种推进剂在T型燃烧器中的衰减常数和燃面增益常数。结果表明,由于推进剂配方中AP粒径分布存在差异,这2种推进剂的压强耦合响应常数存在差别。其中小粒径AP含量较多的推进剂更易产生不稳定燃烧现象。这一实验现象与发动机真实工作情况的表现是一致的。2种推进剂的凝相燃烧产物在发动机中的行为也表现出较大差异。     

Transient simulation of regression rate on thrust regulation process in hybrid rocket motor

The main goal of this paper is to study the characteristics of regression rate of solid grain during thrust regulation process. For this purpose, an unsteady numerical model of regression rate is established. Gas–solid coupling is considered between the solid grain surface and combustion gas.Dynamic mesh is used to simulate the regression process of the solid fuel surface. Based on this model, numerical simulations on a H2O2/HTPB(hydroxyl-terminated polybutadiene) hybrid motor have been performed in the flow control process. The simulation results show that under the step change of the oxidizer mass flow rate condition, the regression rate cannot reach a stable value instantly because the flow field requires a short time period to adjust. The regression rate increases with the linear gain of oxidizer mass flow rate, and has a higher slope than the relative inlet function of oxidizer flow rate. A shorter regulation time can cause a higher regression rate during regulation process. The results also show that transient calculation can better simulate the instantaneous regression rate in the operation process.     

Storage life of silicone rubber sealing ring used in solid rocket motor

It is urgent to carry out detailed research on storage performance of rubber sealing ring to get the criterion for its storage life. This paper acquires material ageing regularity by theoretical analysis and experimental confirmation. On this condition, failure mode and failure criterion of typical sealing structure is studied, and the failure mechanism is found. Thus by analyzing the stress distribution, the relationship between ageing state and sealing condition is established. Rationalization proposal is put forward and storage life of sealing ring is evaluated. The research mentionedabove has special reference to the design of sealing structures and can provide reference for prolonging their service life.     

基于损伤型本构高过载下装药强度数值仿真方法研究

为了准确反映改性双基推进剂装药在高过载发射条件下的破坏情况,采用基于含累积损伤的非线性粘弹性本构模型,利用ABAQUS有限元软件二次开发的UMAT子程序,对某型火箭弹在过载发射情况下的装药进行了数值研究,分析了装药在高过载条件下的变形行为和力学特性。结果显示,在最大加速度为1.39×104g的高过载下,最大应力发生在装药底部内孔处;装药径向尺寸变化很小,可以忽略发动机壳体对装药外表面的约束而将其视为自由表面。比较了最大应力强度准则和累积损伤准则对装药在加速度冲击和压强端面冲击载荷下破坏的判断,两种判据的结果都表明,装药在高过载冲击载荷下没有被破坏。     

推力室逆置点火瞬时真空舱流场数值与试验研究

针对高空模拟舱内逆向布置的推力室点火瞬时过程中舱内压力的变化规律进行了理论和数值仿真分析,推力室高速气流的动能是推力室短程点火过程中舱内压力大幅上升的主要原因.为保证推力室点火时舱内的真空度,需要在推力室出口配置导流装置将燃气导出真空舱.对单台和4台并联推力室进行点火试验,试验表明：采用燃气导流能够较好保持舱内真空度,是整机多推力室高空模拟试验的新思路.