钝感推进剂配方研究及发展趋势

从钝感黏合剂、钝感增塑剂、钝感高能填料以及新型复合材料等方面综述了国内外钝感固体推进剂配方及钝感方法进展。结果表明,HTPE黏合剂、BDNPF/A增塑剂、FOX-7高能填料以及HMX-TATB核-壳微粒等均可有效降低推进剂感度。今后钝感推进剂的重点研究方向主要为推进剂钝感机理、钝感推进剂能量与感度关系、钝感材料的匹配技术以及影响感度的综合因素等。     

Combustion properties of a low-vulnerability propellant: an experimental and theoretical study using laser ignition

Ignition and combustion characteristics of a low-vulnerability propellant based on RDX are studied experimentally. Ignition is obtained using a laser diode. Experiments are performed in a cylindrical closed-volume reactor for different initial pressures and initial propellant masses under nitrogen and argon surrounding atmospheres. Ignition delays, maximal overpressures, and propagation rates are obtained for different initial pressures and laser powers. Thermodynamic predictions of overpressures are also compared with experimental ones. Finally, ignition probabilities for different laser powers and gaseous atmospheres are investigated using a revised Langlie method.     

纳米碳酸盐催化剂对AP/Al/HTPB推进剂性能的影响

研究了纳米碳酸盐催化剂对AP/Al/HTPB推进剂的燃速压强指数、爆热和力学性能等的影响.结果表明:纳米催化剂对推进剂在高压强(10～18 MPa)和低压强(4～10 MPa)段的燃烧性能的影响差别较大,但压强指数都能降低到0.2以下,均达到平台推进剂水平; 而且随着纳米催化剂含量增多,推进剂的燃烧效率更充分,爆热也有一定程度的增加; 但是,纳米催化剂对推进剂的力学性能、工艺性能却有一定程度的影响.确定了纳米碳酸盐催化剂在推进剂中配比为0.5%～1%之间.     

含Cs盐推进剂燃烧产物导电特性研究

运用热力学平衡常数法,在计算磁流体发电机用推进剂燃烧产物组成和燃温等热力学参数的基础上,通过应用沙赫方程和燃烧产物电导率计算模型,计算了磁流体发动机用含Cs盐复合推进剂燃烧产物的电导率,揭示了电导率随Cs盐、铝含量以及电导率随温度、压力的变化规律.结果表明: 铝含量一定,当Cs盐含量在5%～10%时,燃烧产物电导率达到最大; 燃温越高、燃烧室压力越小,燃烧产物电导率越高.     

基于粒子群算法的可重复使用液体火箭发动机减损优化问题研究

针对可重复使用液体火箭发动机起动过程，研究了系统控制输入序列的变化对以涡轮叶片为代表的关键部件累积损伤的影响。在系统性能变化不大前提下，为使瞬间动态过程中涡轮叶片损伤累积较小。从而提高可重复使用发动机工作寿命和使用次数，将系统性能函数和涡轮叶片累积损伤量设为目标函数，应用粒子群算法对系统控制输入序列进行优化设计。仿真结果表明：1）在系统性能函数值相同情况下，控制输入序列引起的涡轮叶片累积损伤大不相同；2）选择优化后的控制输入序列能够实现发动机高性能条件下，降低涡轮叶片累积损伤的目的。     

不同贮存期固体火箭发动机装药或药柱断裂韧性试验研究

[摘要] 参考金属材料断裂韧性的测试方法，对不同贮存年限的某型固体火箭发动机药柱的断裂韧性凡进行了测试．对试验结果进行比较分析，探讨了不同贮存年限推进剂断裂韧性的变化及规律．     

BAMO-THF复合推进剂能量特性计算与分析

利用最小自由能法研究了以3,3-二叠氮甲基氧丁环(BAMO)与四氢呋喃(THF)共聚醚(PBT)为粘结剂,高氯酸铵(AP)、黑索今(RDX)、铝粉(Al)、二硝酰胺铵(ADN)为固体填料,不同增塑剂条件下推进剂比冲变化规律.理论计算表明: 以2,2-二硝基丙醇缩甲醛与2,2-二硝基丙醇缩乙醛等质量比混合物(A3)、硝化甘油与二乙二醇二硝酸酯等质量比混合物(NG/DEGDN)作增塑剂时,推进剂比冲随RDX含量变化呈抛物线形,固体填料存在最佳添加比; NG/DEGDN增塑体系推进剂比冲高于A3体系.15% ADN取代AP时,由于燃烧产物平均相对分子质量降低,推进剂比冲显著提高.     

喷嘴型面对膏体火箭内弹道的影响

为研究燃面变化对膏体火箭发动机内弹道调节精度的影响,根据膏体火箭发动机的工作原理,分别推导了直圆管喷嘴和锥形扩张喷嘴型面下的膏体推进剂燃面方程,建立了膏体火箭发动机零维内弹道模型,分析了喷嘴型面对发动机内弹道性能的影响,并进行了直圆管喷嘴发动机试验.结果表明,直圆管喷嘴下计算的点火时间比试验结果短,但平衡时间及平衡压强与试验结果基本吻合,喷嘴型面变化对发动机平衡时间影响很大.     

Preparation and Safety of Well-Dispersed RDX Particles Coated with Cured HTPB

HTPB/IPDI (hydroxyl terminated polybutadiene & Isophorone diisocyanate) and TNT (2,4,6-trinitrotoluene) were successively coated on RDX (hexogen) particles by solvent evaporation and aqueous slurry melting, respectively. When HTPB coated on RDX particles cured completely, TNT was removed by solvent dissolution and the well-dispersed RDX particles coated with cured HTPB were obtained successfully. SEM (scanning electron microscopy), TEM (transmission electron microscopy), XPS (X-ray photoelectron spectrometry), and laser granularity measurement were employed to characterize the coated samples, and the mechanical sensitivity and thermal stability were measured and analyzed. Results show that TNT on the outer layer effectively hinders the adhesion among the particles resulting from the curing of inner layer (i.e., HTPB and IPDI). The final coating particles disperse well and their mechanical sensitivity decreases significantly. When the covering amount of HTPB is 2 wt.%, drop height (H₅₀) of RDX increases from 37.2 to 66.5 cm and explosion probability (P) decreases from 92 to 16%. Compared with that of uncoated samples, the activation energy and self-ignition temperature of coated samples do not vary.     

再生式密闭爆发器中液体发射药燃烧规律的实验研究

本文介绍了硝酸羟胺液体发射药在再生式密闭爆发器中的喷射燃烧实验.实验采用固体火药以不同的点火压力启动再生式活塞并点燃液体发射药,同时获得了燃烧室和贮液室内 p—t 曲线.研究结果表明,液体发射药在再生式密闭爆发器中10～15MPa点火压力条件下可靠点燃并稳定燃烧,压力梯度和动态活度曲线与固体火药密闭爆发器中的燃烧规律相似,预示了液体发射药应用于再生式液体火炮的可能性,对液体发射药燃烧性能的进一步研究有一定的参考作用.