Theory of nonsteady propellant combustion. Combustion in the presence of harmonically varying pressure

It is shown that in order to construct a theory of nonsteady propellant combustion it is necessary to know the steady-state dependences of the burning rate u₀ °, surface temperature T_s °, and flame temperature T_F ° on the external parameters and the initial temperature of the propellant. The combustion processes in an unbounded space, when one of the external parameters varies according to a harmonic law, are examined within the framework of such a theory.Translated from Zhumal Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki, No. 5, pp. 60–69, September–October, 1971.     

发射药燃烧热辐射传播规律

采用构建物理数学模型和实验验证的方法,首次提出发射药燃烧热辐射柱体理论模型;利用自由场条件下的单基发射药燃烧热辐射实验,对比分析球体热辐射模型,验证了柱体理论模型能够客观反映发射药燃烧热辐射传播规律。实验表明,自由场条件下4种不同单基发射药药量的燃烧热辐射实验数据与柱体燃烧理论模型相吻合;同时由数据拟合分别得到单基发射药热通量与药量、距离以及热剂量与药量、距离的定量函数关系,可为准确评估单基发射药燃烧热辐射毁伤效应提供相关理论基础。

     

Damage of a high-energy solid propellant and its effects on combustion

In order to improve the safety of high-energy solid propellants, a study is carried out for the effects of damage on the combustion of the NEPE (Nitrate Ester Plasticized Polyether) propellant. The study includes: (1) to introduce damage into the propellants by means of a large-scale drop-weight apparatus; (2) to observe microstructural variations of the propellant with a scanning electron microscope (SEM) and then to characterize the damage with density measurements; (3) to investigate thermal decomposition; (4) to carry out closed-bomb tests. The NEPE propellant can be considered as a viscoelastic material. The matrices of damaged samples are severely degraded, but the particles are not. The results of the thermal decomposition and closed-bomb tests show that the microstructural damage in the propellant affects its decomposition and burn rate.     

An approach formulated in terms of conserved variables for the characterisation of propellant combustion in internal ballistics

A model formulated in terms of conserved variables is proposed for its use in the study of internal ballistic problems of pyrotechnical mixtures and propellants. It is a transient two‐phase flow model adapted from the non‐conservative Gough model. This conversion is mathematically attractive because of the wide range of numerical methods for this kind of systems that may be applied. We propose the use of the AUSM+, AUSM + up and Rusanov schemes as an efficient alternative for this type of two‐phase problem. A splitting technique is applied, which solves the system of equations in several steps. A second‐order approach based on Monotonic Upstream‐Centred Scheme for Conservation Laws (MUSCL) is also used. Some tests are used to validate the code, namely a shock wave test, a contact discontinuity problem and an internal ballistics problem. In this last case, one‐dimensional numerical results are compared with experimental data of 155‐mm gunshots. Copyright © 2015 John Wiley & Sons, Ltd.     

基于光学诊断的某新型含铝推进剂燃烧特性分析

为探究某新型含铝固体推进剂燃烧特性和规律,在模拟固体发动机的高压条件下,采用可调功率激光器结合高速摄影、发射光谱等光学诊断技术对该新型含铝固体推进剂开展了系统的点火及燃烧过程研究。通过对该推进剂的点火延迟、退移速率、燃烧温度以及团聚物颗粒尺寸的定量测量和分析,明确了该推进剂的点火延迟量级;证实此推进剂的退移速率严格遵循Summerfield燃速公式;判断出其最高燃烧温度高于3 300 K,且随压力增大而升高;通过对燃烧过程中发光凝聚相产物面积的量化分析得出推进剂产物中团聚物粒径尺寸受环境参数的影响规律。     

A ballistic compressor-based experiment for the visualization of liquid propellant jet combustion above 100 MPa

 This paper describes the components and operation of an experimental setup for the visualization of liquid propellant (LP) jet combustion at pressures above 100 MPa. The apparatus consists of an in-line ballistic compressor and LP injector. The ballistic compressor, based on a modified 76 mm gun, provides high-pressure (ca. 55 MPa) clear hot gas for the jet ignition. A piston (projectile) is fired toward a test chamber beyond the barrel’s end, and its rebound is arrested in a transition section that seals the test chamber to the barrel. The LP jet is injected once the piston is restrained, and combustion of the jet further elevates the pressure. At a preset pressure, a disc in the piston ruptures and the combustion gas vents sonically into the barrel. If a monopropellant is used, the jet injection-combustion process then resembles liquid rocket combustion but at very high pressures (ca. 140 MPa). This paper discusses the ballistics of the compression and compares experimental results to those predicted by a numerical model of the apparatus. Experimentally, a pressure of 70 MPa was achieved upon a 12.5 volumetric compression factor by firing a 10 kg piston into 1.04 MPa argon using a charge of 75 g of small-grain M1 propellant. Received: 16 December 1996/Accepted: 15 July 1997     

点火具点火射流蚀剥作用对底排药柱燃烧特性的影响

为了研究底排点火具射流蚀剥作用对底排药柱碎块脱落情况及其燃烧性能的影响,采用半密闭爆 发器实验装置模拟底排弹出膛口瞬态卸压工况,借助高速录像记录点火具点火与底排药柱燃烧的序列图像。 建立底排药柱在半密闭爆发器燃烧的数学模型,计算分析了不同碎块脱落质量引起的平均压力、质量流率和 燃烧时间的变化情况。研究结果表明:蚀剥作用发生在点火具点火初期,导致脱落的底排药剂碎块来不及燃 烧;蚀剥作用主要是强点火射流对底排药柱侵蚀与冲击造成的;碎块总量约占底排药柱初始质量的7%~ 9%,严重影响点火和燃烧的一致性。计算结果与实验值吻合较好。     

Numerical modeling of the processes within the combustion chamber of a solid propellant rocket engine during the stabilization of the design operation mode

Comprehensive numerical modeling of the processes occurring in the combustion chamber of a solid propellant rocket engine during the stabilization of the design operation mode is performed. The self-consistent problem considered includes nonstationary operation of an ignition device, warmup and ignition of a solid propellant charge followed by its nonstationary burning, nonstationary threephase homogeneous-heterogeneous flow of the combustion products in the combustion chamber, in the nozzle, and behind the engine nozzle unit, engine depressurization, and nozzle unit plug blowing-out. The results of the calculations are presented.     

Heat transfer in the neighborhood of the critical point or line in the presence of hydrogen blowing and combustion

The results of numerical calculations of the thin viscous shock layer equations are presented. The dependence of the heat exchange on the generalized blowing parameter, which depends on the blown gas flow rate and the Reynolds number, is obtained.Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 3, pp. 144–149, May–June, 1995.     

On the measurement of stress in solid propellant

The problems related to the direct measurement of stresses in solid propellant are identified and reviewed. The piezoresistance phenomenon is discussed and it is shown how this phenomenon can be utilized to measure stresses in elastomers and solid propellant. One version of a piezoresistive stress transducer is used to measure radial stresses in an uncontained thick-walled elastic cylinder which is internally pressurized. A smaller similar version of the piezoresistive stress transducer is employed in a rosette configuration to measure the stress state at five critical locations in a quarter-scale Surveyor solid-propellant motor three times during a four-year storage period. The instrumentation and calibration of these piezoresistive stress transducers are briefly described.     

Stability of the combustion process in elastic combustion chambers

High-frequency instability phenomena in rigid combustion chambers have been studied theoretically in [1–3]. This phenomenon is attributed to the interaction between the combustion processes and combustion-product fluctuations in the chamber. One of the possible mechanisms of formation of high-frequency instability is examined in [3], where the combustion rate is represented in the form of a retarded pressure functional. In this case, the problem is reduced to studying the stability of a certain distributed self-oscillating time-lag system.If the oscillation frequencies of the combustion products are comparable to the natural vibrations of the shell which forms the combustion chamber, then it is natural to expect that the elasticity of the chamber walls will affect the combustion process. Coupled effects of acoustoelastic instability can arise, in whose development the vibrations of the chamber wall play a substantial role. These effects are particularly undesirable from the point of view of the vibrational stability of combustion chambers.In this paper, a theory of high-frequency instability of stationary combustion is developed with allowance for elastic deformations of the combustion chamber walls. The theory is based on the mechanism of vibrational combustion [1–3], according to which the combustion front is assumed to the concentrated, while the velocity jump at the front is expressed through a retarded pressure functional. It is assumed that the combustion product flow is one-dimensional and isentropic and that the chamber is cylindrical. The deformations of the chamber are described via the moment theory of shells. The existence is revealed of additional instability regions produced by the interaction between the elastic vibrations of the chamber walls and the acoustic oscillations of the combustion products. The influence of the relation between the elastic and acoustic frequencies and of the structural damping factor in the combustion chamber walls on the stability of the stationary combustion process is examined. The problem discussed is treated as a mathematical model for more complex asymmetric problems in which the elastic and acoustic frequencies can be of the same order.     

Photothermoelastic analysis of bonded propellant grains

A two-dimensional model of the transversal cross section of a bonded rocket propellant grain was subjected to uniform and steady thermal loading and, alternatively, to mechanically applied uniform radial displacements on the outer boundary. The optimization of perforation contours (attained in previous research programs by applying uniform pressure on the outer boundary of the grain model) was confirmed for both types of thermal loading. The concentration factor at the fillets of the inner contour was determined. An attempt was made to predict the maximum strain in the actual propellant subjected to the same thermal conditions. The material used for the model was a urethane rubber. The thermoelastic properties of the model material were determined.     

固体发射药等离子体点火过程及弹道效应分析

总结了常规火炮点火的现状,分析了固体药电热化学炮（ＳＰＥＴＣ）点火的潜在优势,并对等离子体点火过程中存在的燃速增强机理进行了讨论。作为等离子体点火的弹道效应分析,利用电热增强固体药内弹道、等离子体发生器、脉冲功率源三者的耦合编码,计算了不同点火功率、不同毛细管径对ＳＰＥＴＣ炮弹道性能的影响。     

Thermo-damage-viscoelastic constitutive model of HTPB composite propellant

The main goal of this work is to establish a thermo-damage-viscoelastic model for Hydroxyl-Terminated Polybutadiene (HTPB) composite propellant based on the thermodynamic theory and elastic–viscoelastic correspondence principles. The model will also consider the influence of temperatures. The parameter α which represent the damage evolution rate and the material constants a, b are defined as exponential functions of temperature T, i.e. α(T), a(T) and b(T). Relaxation tests and uniaxial constant rate tensile tests are used to acquire the model parameters, and C(S) curves of different rates under the same temperature states are considered to be overlapped in this paper, while noncoincidence under the different temperature states. Then, uniaxial constant rate tensile tests and multi-step tensile-relaxation tests are used to verify the accuracy of the model. The results show that, the model is highly accurate in describing the mechanical property of HTPB under various loading conditions, but some drawback in describing the relaxation property inside of the HTPB’s nonlinear viscoelastic segments.     

两模块装药点传火过程及药粒散布特性

模块装药点传火过程中药粒堆积形态对膛内起始压力波特性有重要影响,而模块装药点传火过程中药盒破裂后药粒飞散过程决定了药粒最终堆积形态。为此设计了模块装药可视化点传火模拟试验装置,通过高速摄像系统,观测不同初始装填位置的两模块装药点传火、药盒破裂及药粒散布过程。试验结果表明,两模块初始装填位置远离底火端且两药盒装填间距增大时,药室内传火时间变长,两个模块药盒燃烧更充分,模块盒的破裂面增大。点传火试验结束后,药室内模拟药粒散布在以底火侧端面中心为起点的轴向195～500 mm区域。其中,药粒主要分布于药室右侧陡坡状堆积区域。基于试验建立了模块装药点传火过程中药盒破裂后药粒散布的三维非稳态气固两相流模型,并进行了模拟计算。计算得到的最终药粒散布与试验测得结果基本吻合,验证了模型的合理性。