鸭式布局探空火箭气动特性实验研究

采用风洞实验的方法对超音速鸭式布局探空火箭气动特性进行了研究。在马赫数为1.5和3.0、攻角为-8°~+10°的实验条件下,分别进行了箭身、鸭舵、固定尾翼、滚转尾翼的火箭模型组拆实验,并对各模型状态下的气动力和气动力矩特性进行了对比。实验表明,各组件(箭身、鸭舵、尾翼)对全箭气动力和气动力矩的贡献各有不同,滚转尾翼状态的滚转舵效明显大于固定尾翼状态并解决了跨音速附近固定尾翼滚转舵效反效的问题,尾翼滚转与否对鸭舵的俯仰舵效影响不大。实验结果对鸭式布局探空火箭的设计具有一定的参考意义。     

单磁的弹丸滚转角测量与系统误差分析

针对高旋弹丸滚转角实时测量的问题,建立一种单磁的弹丸滚转角测量与误差分析方法。在弹丸发射前装订先验弹道的角度信息,通过时间匹配的方法获取实时的俯仰与偏航角数据;并结合地磁测量信息完成弹丸滚转角的实时解算。通过采用6自由度外弹道的蒙特卡洛仿真和多因素修正控制仿真的方法,完成弹丸在无控与修正状态的先验角度散布规律研究。在考虑时间基准误差的情况下,经系统误差建模与仿真得出,单磁的弹丸滚转角测量方法在无控和一次修正后的系统误差1σ下分别为小于2°和10°。仿真结果表明,基于先验角度信息的单磁弹丸滚转角测量方法可行,可以保证无控和一次修正后的滚转角测量精度。     

Nonlinear theory of combustion stability in liquid rocket engine based on chemistry dynamics

Detailed models of combustion instability based on chemistry dynamics are developed. The results show that large activation energy goes against the combustion stability. The heat transfer coefficient between the wall and the combust gas is an important bifurcation parameter for the combustion instability. The acoustics modes of the chamber are in competition and cooperation with each other for limited vibration energy. Thermodynamics criterion of combustion stability can be deduced from the nonlinear thermodynamics. Correlations of the theoretical results and historical experiments indicate that chemical kinetics play a critical role in the combustion instability.     

Investigations of bis(methyltetrazolyl)triazenes as nitrogen-rich ingredients in solid rocket propellants – Synthesis,characterization and properties

The energetic nitrogen-rich compounds 1,3-bis(1-methyltetrazol-5-yl)triaz-1-ene (4) and 1,3-bis(2-methyltetrazol-5-yl)triaz-1-ene (5) were synthesized by diazotation of 1-methyl-5-aminotetrazole (2) and 2-methyl-5-aminotetrazole (3), respectively, by using half an equivalent of sodium nitrite. The reaction of 4 and 5 with diluted ammonia solution yields ammonium bis(1-methyltetrazol-5-yl)triazenate (6) and ammonium bis(2-methyl-tetrazol-5-yl)triazenate (7). Treating of 4 and 5 with aqueous sodium hydroxide solution yields sodium bis(1-methyltetrazol-5-yl)triazenate (8) and sodium bis(2-methyltetrazol-5-yl)triazenate (9) almost quantitative. Compounds 8 and 9 were methylated using methyl iodide and dimethyl sulfate, respectively, originating bis(1-methyltetrazol-5-yl)-3-methyltriaz-1-ene (10) and bis(2-methyltetrazol-5-yl)-3-methyltriaz-1-ene (11). The products 4–11 were characterized by Raman, IR, multinuclear NMR and UV–Vis spectroscopy, mass spectrometry, elemental analysis and differential scanning calorimetry. The structures of the crystalline state of 4 · H₂O, 5, 8 · MeOH, 10 and magnesium bis(2-methyltetrazol-5-yl)triazenate (12) were determined by low temperature single crystal X-ray diffraction. The heats of formation Δ_fH^° of 4–7, 10 and 11 were calculated using energies of combustion Δ_cU^° determined by bomb calorimetry, resulting in strongly endothermic values. With these data and by using calculated (4, 5, 10) as well as measured (6, 7, 11) crystal densities, several detonation parameter (heats of explosion, detonation pressure, detonation velocity, explosion temperature) were calculated by the explo5 software. In addition, the specific impulse of different propellant mixtures of the most promising compound 6 with ammonium dinitramide (ADN) were computed. Furthermore the n-octanol/water partition coefficients of 4, 5, 6 and 7 were determined and the long-term stability of 6 was tested by thermal safety calorimetry. Lastly the sensitivities toward impact and friction as well as electrical discharge were determined by the BAM drophammer, friction tester and a small scale electrical discharge tester.     

某特种动力发动机模拟器设计方法

以某特种动力发动机试车试验及半实物仿真试验为工程应用背景,采用DSP+FPGA主协处理器方案设计了固体火箭发动机模拟器,实现了某特种动力发动机推力与燃气发生器压强的闭环控制输出,以及特种动力发动机伺服系统特性在半实物仿真中的真实模拟。该发动机模拟器参与了多次的发动机试车试验及半实物仿真试验,验证了该发动机模拟器软硬件的稳定性和可靠性。为某型号发动机试验研究建立起了工程实用的硬件平台。     

分段弹侵彻效率的数值模拟研究

 采用ANSYS-AUTODYN数值模拟软件针对撞击速度在1 500~3 500 m/s内的平头分段杆侵彻效应进行研究,分析分段杆的侵彻效率和弹坑形状与分段杆的连接结构、间隔和撞击速度等参数的关系。结果表明,在一定的条件下,分段杆的侵彻效率比连续杆更优越。通过对公开报道的实验工况进行数值模拟,验证了数值模拟结果的有效性,对分段杆的侵彻机理研究及工程结构设计具有指导意义。     

钢筋混凝土靶板在弹丸冲击及爆炸载荷下响应的数值模拟

 采用HJC混凝土损伤本构模型及LS-DYNA的流固耦合算法,分别对钢筋混凝土靶板在弹丸冲击和爆炸载荷作用下的响应进行了有限元数值模拟,其中模拟参数由实验数据拟合重新获取。将模拟结果与实验结果和经验公式进行对比分析,结果表明：数值模拟再现了弹体贯穿靶板过程中的开坑、隧道及漏斗碎裂区,计算得到的弹体弹道极限及残余速度与实验数据吻合较好;此外,数值模拟也很好地再现了炸药爆炸后冲击波的传播过程以及爆炸载荷作用下混凝土的破坏情况,模拟结果与实验现象具有良好的一致性。     

超声速弹丸立靶弹着点定位模型研究

针对常规武器火炮直瞄射击时的弹着点测试问题,提出了一种双圆环形传声器阵列方法。该阵列将若干传感器布设在两个圆环上,并根据超声速弹丸产生的激波传播速度随传播距离增加逐渐递减的规律,对每个传声器阵分别引入一个视速度,建立了双视速度模型。计算机仿真分析表明,采用双圆环形传声器阵列及双视速度模型确定弹丸弹着点坐标,带来的模型误差优于3 mm,对于工程应用而言可以忽略。试验结果表明,双视速度模型明显优于将激波传播速度视为恒定的基本模型和交会模型。     

串联战斗部前级聚能装药和隔爆结构设计与实验研究

 前级聚能装药侵彻技术和两级隔爆技术在串联战斗部的设计研究中占有重要地位。从理论分析、实验研究的手段出发,分析了前级装药的结构设计及前级装药爆炸对后级的影响,设计了两种药型罩结构的聚能装药侵彻混凝土靶实验,以及以多孔铝为隔爆体的隔爆防护实验。实验结果表明,设计的前级装药在混凝土靶上侵彻出了深度为8.2倍、孔径为0.4～0.6倍装药口径的孔洞;所采用的多孔铝隔爆结构有效地防护了二级弹体的破坏。实验效果比较理想。     

单线阵CCD相机立靶测量原理

针对现有双CCD交汇立靶在室内使用时存在的光源复杂的问题,提出一种单线阵CCD相机立靶测量原理.采用一台线阵CCD相机,配合两个小功率半导体扇形一字线状激光器和投影板作为光源,将CCD相机的探测光幕面和激光光源的光幕面调整在同一个面内,当弹丸穿越探测光幕面时,档住了两个激光器投射在投影板上的部分光线,并在投影板上留下对...