Propellants Reactivity Enhancement with Nanothermites

Propellant grains (Vectan A1) were coated with a thin and stable layer (50 μm, 10 wt‐%) of a “green” sulfate‐based nanothermite (Na₂SO₄/Al). This flash composition was used herein as an internal pyrotechnic lighter to accelerate the ignition and the combustion of the propellant. The combustion of the modified propellant, which was tested in one‐end open tubes, propagates four orders of magnitude faster than the one of pristine Vectan A1. This tremendous effect was tuned by varying the proportion of coated Vectan A1 grains from 20 to 100 % in the samples. The percolation threshold is in between 20 and 40 %. Beyond this point, the effect can be improved by increasing the proportion of nanothermite‐coated propellant grains in the charge.     

Kinetics of Bu‐NENA Evaporation from Bu‐NENA/NC Propellant Determined by Isothermal Thermogravimetry

Bu‐NENA (N‐butyl‐N‐nitratoethyl nitramine) base propellants have versatile qualities, such as, higher energy, reduced sensitivity, and enhanced mechanical properties. The evaporation of Bu‐NENA, which takes place in the propellant grains in the course of time, can reduce the physical properties of the propellants, weaken the propellant grains, cause the propellants to crack at stress‐concentrated points, and finally result in unfavorable increases or fluctuations of the burning rate and poor performance of the rocket motor. In this study, the evaporation of Bu‐NENA from a double base propellant was investigated using isothermal thermogravimetry. The results showed that the entire process of Bu‐NENA evaporation complied with the power law of evaporation rate with time. The values of kinetic parameters of Bu‐NENA evaporation were calculated: E _vap=67.68 kJ mol⁻¹ and A _vap=1.57×10⁵ s⁻¹. In comparison, the values of NG (nitroglycerin) evaporation were determined: E _vap=69.68 kJ mol⁻¹ and A _vap=1.33×10⁶ s⁻¹. The value of the activation energy of Bu‐NENA evaporation was close to that of NG, but the pre‐exponential factors differed by an order of magnitude. The evaporation of Bu‐NENA followed zero‐order kinetics at the early stage, and the enthalpy of Bu‐NENA evaporation was calculated to be 69.75 kJ mol⁻¹ according to Langmuir and Clausius‐Clapeyron equations.     

Simulation of the Erosion Burning of a Granular Propellant

For combustion of axisymmetric propellant grains under blowing conditions, a mathematical model is proposed and numerical simulation is performed. The effects of incoming–flow parameters (velocity, pressure, and temperature) and surface dimensions and geometry on grain–burning rate are studied. Physical patterns of flow around burning propellant grains are presented.     

Three‐Dimensional Simulation of Pressure Fluctuation in a Granular Solid Propellant Chamber within an Ignition Stage

The effects of the conditions of the ignition system in the propellant chamber of a gun system using a granular solid propellant are numerically investigated with respect to ignition performance criteria such as the differential pressure generation between the breech and the projectile base. Simulations, in which the length of the primer and the igniter mass are varied, are performed using a solid/gas two‐phase fluid dynamics code for three‐dimensional calculation of gas flow and discrete solid propellant particles. This code simulates the igniter combustion in the primer, the movement of burning solid propellant grains, and the formation of pressure gradients inside the chamber in the ignition process. The differential pressures between the breech and the projectile base measured in experiments are well predicted by the simulations for various igniter conditions. In the process of igniting the solid propellant, the propellant grains are accelerated toward the projectile base by the igniter gas flows from the primer vents. Fixed‐particle simulation is also carried out in order to examine the effects of the movement of the solid propellant grains on the chamber pressure profile. The simulated results reveal that the movement of solid propellant grains causes differential pressure fluctuations, which depend on the discharge from the primer vents and the locations of these vents.     

Effect of Bonding Agent on the Mechanical Properties of GAP High‐Energy Propellant

Three kinds of bonding agent were chosen to improve the mechanical properties of GAP high‐energy composite propellant based on GAP, BuNENA, HMX, AP, and Al. These bonding agents are N,N ′‐bis(2‐hydroxyethyl) dimethylhydantoin and 1,3,5‐trisubstituted isocyanurates (BA1), cyano‐hydroxylated amines (BA2), and hyperbranched polyether with terminal groups substituted by hydroxyl, cyano and ester functional groups (BA3). To study the interaction between bonding agents and oxidizers, the effect of coating by bonding agents on the characteristic absorption peaks of AP and HMX were first studied by infrared spectroscopy. Then the effect of bonding agents on the adhesion work between oxidizers and binder system were determined. The results showed that BA2 has the strongest interaction with AP, whereas BA1 and BA3 have relatively strong interaction with HMX. The AP grain coated by BA2 has the strongest adhesion work to the binder system, and there is not much difference in the values of adhesion work towards binder system of three coated HMX grains. At last the three bonding agents were added to GAP propellant, which has a theoretical specific impulse of 276.03 s. When the three kinds of bonding agent was used alone, the sense of “dewetting” in propellant was relieved but still existed. The combination of BA2 to BA1 or BA3 improved the adhesions between oxidizers and binder system effectively, and the mechanical properties of GAP propellant reached to δ _m=0.69 MPa, ϵ _b=32.7 %.     

LOVA Propellant Aging: Effect of Residual Solvent

An investigation of LOVA propellant aging was performed to identify the cause of stabilization periods in certain propellant lots. Two important observations were made: (1) the level of residual solvent in propellant grains slowly decrease while in storage, and (2) during the drying process and while the grains are in storage, plasticizer “co-migrates” with solvent, resulting in plasticizer accumulation at grain surfaces. It was also observed that while in storage, residual solvent may be oxidized to generate organic acids. Based on these results, it is proposed that stabilization periods result from processes related to migration, evaporation, and oxidation of residual solvent.     

发射装药挤压应力与破碎规律研究

建立了发射药粒在动态载荷下的挤压破碎过程动力学模型并进行了数值计算,基于发射装药挤压破碎试验装置,研制了挤压应力PVDF传感器,并进行了发射装药动态挤压应力试验。数值模拟结果与试验结果吻合较好,验证了数学模型的正确性和新型传感器设计的合理性,说明新型传感器可以用于发射装药挤压破碎试验中对发射装药颗粒间挤压应力的测量。     

胶黏固结发射药的燃烧性能

以变燃速发射药为基体,用含能胶黏剂对其药粒表面微胶化处理,压实固结,制成胶黏固结整体变燃速发射药,解决固结装药的燃烧渐增性问题。将高装填密度和变燃速发射药的燃速渐增特性结合在一起,可有效控制高装填密度发射药的燃气释放。由密闭爆发器实验得出变燃速发射药和胶黏固结药的p-t和L-B曲线,并对两种发射药曲线进行对比分析。结果表明,胶黏固结发射药基本保持变燃速发射药的高燃烧渐增性,具有高装填密度和燃烧再现性。     

Burning Characteristics of Consolidated Gun Propellants

To improve the combustion behaviors of conventional consolidated propellants, consolidated propellants were prepared using porous propellant grains as fast‐burning filler. The porous propellant grains were prepared by supercritical fluid foaming process and exhibited the high burning rate. The multi‐perforated structure of the consolidated propellants was designed and adopted to obtain high burning progressivity. To investigate the burning characteristics of the consolidated propellants, closed vessel and quenched combustion experiments were carried out. The results show that deconsolidation of the consolidated propellants does not occur, and that the consolidated propellants exhibit high burning rates and high burning progressivities. Besides, the results show that the consolidated propellants burn steadily even at low (−40 °C) and high temperatures (50 °C).     

NEPE推进剂热安全性的尺寸效应

为了解NEPE推进剂热安全性的尺寸效应,在不同温度下对不同尺寸的NEPE推进剂药柱进行了热爆炸试验,测得其热爆炸延滞期,并计算得到不同尺寸NEPE推进剂药柱在90、100、110、120℃下的热分解反应速率;通过在药柱内部布置热电偶监测了尺寸为Ф100mm×100mm和Ф150mm×150mm药柱在90℃和100℃环境温度下的内部温度变化。结果表明,当温度高于76.2℃时,NEPE推进剂药柱的尺寸越大,反应速率常数越大;活化能与药柱的比表面积呈线性相关,比表面积越小,活化能越大,当NEPE推进剂药柱的比表面积小于0.02mm-1时,活化能(Ea)为179.3kJ/mol,指前因子(A)为4.62×1019s-1。硝酸酯增塑剂的存在是NEPE推进剂在200℃以下发生热爆炸的主要原因。     

Combustion Characteristics of a Novel Grain‐Binding High Burning Rate Propellant

The novel grain‐binding high burning rate propellant (NGHP) is prepared via a solventless extrusion process of binder and spherical propellant grains. Compared with the traditional grain‐binding porous propellants, NGHP is compact and has no interior micropores. During the combustion of NGHP, there appear honeycomb‐like burning layers, which increase the burning surface and the burning rate of the propellant. The combustion of NGHP is a limited convective combustion process and apt to achieve stable state. The larger the difference between the burning rate of the binder and that of the spherical granular propellants exists, the higher burning rate NGHP has. The smaller the mass ratio of the binder to the spherical granular propellants is, the higher the burning rate of NGHP is. It shows that the addition of 3 wt.‐% composite catalyst (the mixture of lead/copper complex and copper/chrome oxides at a mass ratio of 1 : 1) into NGHP can enhance the burning rate from 48.78 mm⋅s⁻¹ in the absence of catalyst to 56.66 mm⋅s⁻¹ at P=9.81 MPa and decrease the pressure exponent from 0.686 to 0.576 in the pressure range from 9.81 to 19.62 MPa.     

Room temperature cured polyurea-urethane propellant with unique mechanical properties

A polyurea-urethane propellant based on an NCO-terminated prepolymer, a diamine and a triol has been developed. This is a room temperature curing propellant which is case-bondable. This has been standardized at 3-kg level and then scaled upto grains of 300-mm diameter and 2250-mm length weighing 250 kg. This propellant has a tensile strength of about 4 kg/cm² and an elongation of 150 percent. Because of low cost, case bondability and room temperature curability this can be used in large solid boosters.     

Enhancement of Aluminum Reactivity to Achieve High Burn Rate for an End Burning Rocket Motor

Aluminum is used in solid propellants to increase the specific impulse (I _sp). It is desirable to have high propellant loading in any stage as it reduces the structural coefficient and an end burning grain is known to be the one with the highest propellant loading. As aluminum combustion is a slow process, the time available for aluminum combustion in an end burning configuration will be very small at the start of the combustion process. This demands an increase in the reactivity of the aluminum. This study is built on the fact that mechanical activation of aluminum powder with PTFE (poly‐tetra‐flouro‐ethylene) enhances the reactivity of aluminum powder. This study also deals with the use of this activated aluminum powder in conjunction with various other methods to enhance the burn rates of the solid propellant. The temperature sensitivity was also measured. Based on these results, new designs with end burning grains for the third stage of Polar Satellite Launch Vehicle (PSLV) and for the second and third stage of Pegasus launch vehicle have been proposed to increase the payload capacity. With this new design, it is seen that the payload can be increased by 12.7 % and 17.6 % for PSLV and Pegasus, respectively. The novelty of this design is that with no changes to any other hardware of the above two systems the increase in payload can be achieved.     

发射药燃烧转爆轰的试验研究

为研究发射药燃烧转爆轰特性及其影响因素,采用联合国危险分级试验中燃烧转爆轰试验方法对单、双、三基以及不同药型的发射药进行燃烧转爆轰试验。结果表明,在管厚4mm弱约束条件下,只有三基小粒发射药发生爆轰,在管厚9mm强约束条件下,6/7双基药、6/7叠氮发射药、6/7三基药以及三基小粒药发生爆轰。发射药配方中添加硝化甘油(NG)、叠氮硝胺(DA)和黑索金(RDX)以及减小药型尺寸,可增强发射药的燃烧转爆轰能力,同时,提高壳体约束强度更易发生燃烧转爆轰。     

Use of A Shatter Test Vessel to Assess Propellant Safety

At low temperatures,gun propellant grains may become brittle and this can lead to fracture or shatter of the grains during gun firing.Should this event occur then it will result in an increase in the burning surface of the propellant and will give rise to a change in ballistic performance.Also,if the resultant over pressure is sufficient,a breech failure may result.Understanding the propensity of a grain to fracture or shatter is therefore important in determining its safety in use.This document describes a test that may be used to derive knowledge and to quantify the physical behaviour of a gun propellant grain at the low temperatures at which fracture or shatter is most likely to occur.     

环境温度作用下固体火箭发动机药柱的累积损伤规律

应用三维热粘弹性有限元分析方法,计算了固体火箭发动机星型药柱在环境温度载荷作用下的温度场和热应力场。应用线性累积损伤模型,计算了不同环境温度载荷作用下药柱的累积损伤。结果表明,在不同应力水平下,推进剂的累积损伤基本符合线性累积损伤规律。星尖处的应力最大,是发动机药柱容易失效的部位。推进剂在长期热应力作用下的累积损伤不仅由应力决定,时温转换因子也是十分重要的因素。     

端面粘贴包覆火药界面粘结强度研究

包覆火药装药控制燃气生成速率，降低弹性温度系数，提高弹丸初速的效果部分来自于包覆层的作用，对预制包覆层端粘包覆火药，其包覆层的厚度，密度，强度等性能已根据弹道和装药表确控制，包覆层与基药的界面粘结度就决定了包覆层控制燃气生成速率的有效性和可靠性，它是检验端面粘贴包覆火药工艺质量的关键指标，本文采用落锤实实验检包覆火药的界面结强度，研究了粘结工艺条件对端面粘贴包覆火药界面粘结强度的影响，通过实验选择出了合适的粘结剂及粘结工艺条件，制备了界面粘结强度良好的端面粘贴包覆火药。     

Burning rate anomaly of composite propellant grains

In this study, characteristics of the burning rate anomaly in composite propellant grains are investigated. The burning rate anomaly has been known as the “midweb anomaly” or the “hump effect.” This paper describes some results of an experimental study on effects of propellant formulations, casting processes, and viscosity of the propellant slurry on the phenomena. According to some past studies, it has been suggested that the geometry of the “isochrone surface” of the propellant slurry affects the local burning rate. To investigate the effect of the isochrone surface, visualization of the isochrone surface in composite propellant grains is carried out. A relation between the geometry and the local burning rate measured in motor firing tests and strand tests is proposed. As a result, besides the common static characteristics of the burning rate anomaly, i.e., the pressure hump effect and the nonisotropic characteristic of the local burning rate, a peculiar burning rate distribution in connection with the isochrone surface is obtained.     

Stabilizer reactions in cast double base rocket propellants. Part V: Prediction of propellant safe life

Propellant deterioration can be kinetically analysed by both Berthelot's law and Arrhenius' law. Kinetic analysis of the mixed stabilizer para-nitro-N-Methylaniline(pNMA)/2-nitrodiphenylamine (2NDPA) based propellant deterioration at different temperatures, during the time necessary for the complete consumption of the more reactive stabilizer pNMA, which can be taken as a measure of the safe life of these propellant compositions, gave results for both Berthelot's law and the Arrhenius' law which are satisfactory. However, it was found that the predicted safe life for the propellant compositions according to the Arrhenius law was much longer than that obtained from Berthelot's law. Therefore, from the safety point of view, it is preferable to use Berthelot's law analysis to assess the safe life of double base propellant compositions.     

Multi‐Objective Optimization of Interior Ballistic Performance Using NSGA‐II

This paper investigates an interior ballistic design with equal and unequal web thicknesses of seven‐perforation propellant grains using optimization methods. In order to reveal the influence of the web thickness of the propellant grains on the overall interior ballistic performance, burning seven‐perforation propellant grains with both equal and unequal web thickness is modeled. A currently popular evolution algorithm (EA) is used to compare two charge shapes, and to seek which one could achieve the optimal ballistic performance. Complete optimization of the interior ballistic performance is a complex process in view of the conflicting objectives to be achieved and a solution to such problems is sought by converting them into a single composite objective and using many tedious measurements. In this paper, a true multi‐objective optimization of the interior ballistic charging design is carried out by considering three objectives simultaneously. The non‐dominated sorting genetic algorithm version II (NSGA‐II) is used to solve this multi‐objective optimization problem (MOP). In order to check its implementation, both the conventional optimization algorithm‐hill climbing method (HCM) and NSGA‐II are used to solve the same single objective problem. The NSGA‐II used to capture the full Pareto‐optimal front is capable of identifying the trade‐off among the conflicting objectives thereby providing alternative useful designs for a designer. Furthermore, for seven‐perforation propellant grains, the results of using equal web thickness are compared with those of unequal web thickness, and it is shown that the two charge shapes produce no distinct difference in the interior ballistic performance.