为改进高能硝胺发射药的力学性能，制备了含缩水甘油叠氮聚醚（GAP）的单孔管状硝胺发射药，用材料试验机测试其冲击和压缩性能，通过扫描电镜观察其内部形貌，用密闭爆发器分析了其燃烧性能。结果表明，GAP可改善高能硝胺发射药的力学性能，加入质量分数1．5％GAP 时，高能硝胺发射药的低温抗冲强度由基础配方的4．51 kJ／m2提高到5．58 kJ／m2，GAP的加入使固体填料与黏结剂体系界面间的黏接强度提高，脱湿现象减少；随着GAP含量的增加，管状发射药的压强指数（n）相比基础配方增加，爆温（Tv ）及火药力（f）逐渐降低，GAP 质量分数为3．5％时，与基础配方相比，f、Tv 分别降低1．41％、3．69％，n增加0．51％。

To improve the mechanical performance of high energy nitramine gun propellant,the single perforation cylinder propellant containing GAP was prepared.The impact and compression performance of the gun propellant were studied by a material testing machine.The internal morphology of the gun propellant was observed by SEM and the combustion performance was analyzed by a closed bomb test.The results show that the mechanical perform-ance of the high energy nitramine gun propellant can be improved by adding GAP.When the mass fraction of GAP is 1 .5%,the impact strength of high energy nitramine gun propellant at low temperature can be increased from 4 .5 1 kJ/m2 of basic formula to 5.58 kJ/m2 .Adding GAP makes the bonding strength between the interfaces of solid filling and binder system enhance and the dehumidifying phenomenon reduce.With increasing the mass fraction of GAP,in comparison with the basic formula,the burning rate pressure exponent (n)of the perforation cylinder propella

提出了一种新的评价高能发射药动态力学强度的方法,即采用落锤撞击发射药粒,用药粒发生临界损伤时的撞击能和极限抗冲应力来表征发射药的动态力学性能。结果表明,该方法能够定量评价发射药的动态力学强度,并得到太根药、硝胺药、硝基胍药等3种发射药的临界撞击能分别为18.8 J/cm2、14.2 J/cm2、3.8 J/cm2,极限抗冲应力分别为247.2 MPa、214.2 MPa、118.5 MPa。

A new evaluation method of dynamic strength of high energy propellants was proposed. Dynamic mechani-cal property of the propellants is characterized by the critical impact energy and the limit impact stress when the critical damage to the granular propellants by a dropping hammer occurs. Results indicate that the evaluation method can quantita-tively reflect the dynamic mechanical strength of the propellants. The critical impact energy of TEGDN propellant, nitra-mine propellant and nitroguanidine propellant is 18. 8 J/cm2,14. 2 J/cm2 and 3. 8 J/cm2,and the limit impact stress 247. 2 MPa,214. 2 MPa and 118. 5 MPa,respectively.

以粒状高能硝胺发射药为基础药,经过表面钝感、包覆、模压处理,制备颗粒模压发射药。设计底部结构和传火管结构两种点传火结构方案,利用30 mm高压模拟火炮,研究颗粒模压发射药装药的点传火性能。结果表明,与底部结构相比,传火管结构将颗粒模压发射药装药的点火延迟时间缩短15.2%,膛内最大负压差降低8.41 MPa,装药床受到的最大挤压力减小11.93 MPa。传火管结构方案使颗粒模压发射药装药具有良好的点传火性能。

Grain-molded gun propellant was prepared based on nitramine propellant by surface-deterring,surface-coating,and grain-molding. Two ignition schemes including bottom configuration and central core igniter were designed. Results show that compared with the bottom configuration,ignition delay time shortens 15. 2% and the maximum negative pressure difference de-creases 8. 41 MPa of central core igniter,and the maximum extrusion process of the propellant decreases 11. 93 MPa,which indi-cate that central core igniter ignition scheme can bring perfect ignition performance for grain-molded gun propellant charge.

为了研究药型结构对发射药燃速测试结果的影响，以高能硝胺发射药为研究对象，采用密闭爆发器燃烧实验和数据处理的分析方法，研究了4种药型及其不同内孔长径比发射药的燃速特性及其变化规律；采用中止燃烧实验研究了发射药内孔长径比对侵蚀燃烧的影响，并与太根发射药对比研究了燃速特性对侵蚀燃烧的影响关系。结果表明，多孔药的燃速压力指数明显小于单孔药，在内孔长径比相同的条件下，随着发射药内孔数量的增加，正比式燃速系数减小，燃速压力指数减小；在药型相同的条件下，随着内孔长径比增大，发射药侵蚀燃烧现象加剧，正比式燃速系数增大，燃速压力指数减小；燃速较高的发射药，侵蚀燃烧现象对燃速参数测试结果的影响更大。

In order to study the influence of charge structure on the test results of the burning rate of propellants,high-energy nitramine propellants was taken as study obj ect.By using closed bomb fired-test and data-treatment methods,the burning rate of propellants of four type structures and different inner hole aspect ratio of the burning rate and its variation character were researched. Using intermission burning test,the influence of the inner hole aspect ratio of propellant on erosive burning was studied.Compared with TEGN propellant,the influence of the burning rate on erosive burning was investigated.Results show that,the burning rate pressure exponent of multiperforated propellant is significantly less than that of the cylindrical monoperforated grain;under the same inner hole aspect ratio condition,the proportional burning rate coefficient u1 decreases with the increase of inner holes of propellants,and the burning rate pressure exponent n decreases.Under the same charge structure co

针对同心筒结构的共架发射系统，研究多武器共架发射时为保证舰艇和武器安全需解决的发射协调问题，提出了时域协调的方法。首先，给出了时域协调的概念，分析了发射速率、燃气排导、初始飞行弹道交叉、防空导弹发射优先等因素对时域协调的影响；然后，建立了基于发射令控制的发射时序模型、发射时间间隔模型及发射优先级模型；最后，对时域协调方法进行了算例验证。结果表明：通过时域上合理地控制武器发射间隔时间可以保证系统安全，同时最大程度地发挥系统效能。

Aiming at the common-frame launching system with concentric canister launcher ,this paper deals with the problem of common-frame weapon launching coordination and proposes the time coordi-nation method .Firstly ,it defines the concept of time coordination ,and analyzes the effects of launch rate ,combustion gas exhaust ,initial trajectory intersection and anti-air missile launch priority on the time coordination .Then ,according to the time coordination ,models for launch sequence ,launch time spacing and launch priority are established .Finally ,some arithmetic examples are used to verify the method of time coordination .The result indicates that the reasonable control of weapon launching time interval in terms of time coordination can ensure the system safety and display the system effi-ciency to the greatest extent .