Humidity aging rate is relative to exposed surface area and scale of. Mechanical properties, humidity absorption ratio, and variation of stabilizers. Solid propellant grains for the large rocket motors of interest are usually too. Abstract viscoelastic damage properties of nitrate ester plasticized polyether nepe solid propellant have been studied in cyclic loading tests. The effect of laser heat flux density on the ignition delay time of nepe propellant was examined. Nepe propellant is a new kind of solid propellant developed. Study on the viscoelastic damage properties of nepe solid. Synthesis and characterization of a high energy combustion. Composite propellant based on a new nitrate ester david a. Propellant properties propellants are intended to do work in a finite time. Evolution of solid propellant rockets in india rajaram nagappa series editors editorinchief assoc. The ignition process of nepe propellant by a co2 laser ignition system has been investigated experimentally. The dynamic mechanical analysis was employed for measurements of temperature and frequency dependence of the nepe propellant by mean of bose.
Effects of deformation on the burning behavior of solid propellants. Solid propulsion technology and development proven technology for a new era of applications. Us5038295a solid propellant service life analysis via. To investigate the evolution of thermal properties of nepe propellant during storage life, tgdscmsftir was used to determine the thermal behaviors of the propellant samples before and after 5year natural storage. To describe the relaxation behavior of nepe nitrate ester plasticized polyether propellant, we analyzed the equivalent relationships between time, temperature, and damage. Solid propellant binders s r jain department of aerospace engineering, indian institute of science, bangalore 560012 solid propellants are widely used in modem rockets and missiles. Jun 19, 2017 nitrate ester plasticized polyether nepe propellant has attracted considerable attention as a kind of highenergy propellant. Editor sk jindal gs mukherjee anitha saravanan kavita narwal editorial assistant gunjan bakshi cataloguing in publication nagappa, rajaram evolution of solid propellant rockets in india. Nitrate ester plasticized polyether nepe propellant has attracted considerable attention as a kind of highenergy propellant.
A solid fuel rocket or solid rocket is a rocket with a rocket engine that uses solid. Humidity aging experiments of investigating effects of environmental humidity on nepe propellant were carried out. Aluminum agglomeration on burning surface of nepe propellants. Results show that the ignition delay time tends to decrease with the increase of laser heat flux, and there exists a significant value. The results show that pressure exponent of xldb propellant decreases by 27. The propellant grain is a cast, molded, or extruded body and its appearance and feel is similar to that of hard rubber or plastic. We also discuss liners and insulators, propellants for igniters, tailoring of propellants, and propellants for gas generators. Thereafter, to prove the universality and accuracy of these two. Groven 1 introduction many solid composite propellants are based on the oxidizer ammonium perchlorate ap. High performing propellants such as nepe75 used to fuel the trident ii d5, slbm replace most of the ap with.
An sem and eds study of the microstructure of nitrate ester. Nitrate ester plasticized polyether nepe propellant is a type of high energetic composite solid propellant, which is comprised of high energy solid particles as the main body, and these particles are glued together by a small amount of polyether binder such as polyethylene glycol peg, fig. Research on the timetemperaturedamage superposition. Here the oxidizer and propellant were mixed into a. Feb 01, 2014 read life prediction of nepe propellants, propellants, explosives, pyrotechnics on deepdyve, the largest online rental service for scholarly research with thousands of academic publications available at your fingertips. Research on nepe propellant life prediction model request pdf. Experimental research on the low vulnerability of htpb and. Review of solid propellant ignition models relative to the. The results of some early slow cookoff screening tests with an htpb propellant and a modified nepe propellant are shown in figure 1.
Although the history of solid rockets could be traced. Nitrate ester plasticized polyether nepe propellant is a new kind of propellant which has the advantages of the double base propellant and composite propellant, and excellent energy property and mechanical property, thereby become a tendency of high energy solid propellant. Many of these types of machines are built specifically for a particular rocket motor. The nepe propellants equilibrium humidity is very low, and the propellant can absorb humidity slightly in 11% rh condition. Different types of solid propellants pakistan defence. Nozzleless solid propellant rocket motors experimental and theoretical investigations. Results and discussion sem analyzes for al and ap in nepe propellants in the nepe propellants, the polymer binder peg is the continuous phase while solid grains, such as al, ap and hmx, are dispersed in the peg. A solid propellant ramjet is an interesting concept as it utilizes atmospheric air during its operation. The damage evolution curve of the tensile test at 100. A study on the microstructure of a nitrate ester plasticized polyether propellant dissolved in hcl and koh solutions yong liu1,2, luoxin wang3, xinlin tuo2, songnian li1,2 and weimin yang1 1college of mechanical and electrical engineering, beijing university of chemical. Experimental study on combustion process of nepe propellant. Aluminum agglomeration and agglomerate sizes of nepe propellants were studied by cinephotomicrography at pressures of 3 and 5 mpa. Request pdf life prediction of nepe propellants nepe propellants were prematurely aged at 65, 70, 75, and 80 c, respectively.
In solid propellant rocket motorsand the word motor is as common to. The sem of nepe propellants and the mechanical sensitivity were also detected. Study on laser ignition characteristics of nepe propellant. Effect of coated ammonium dinitramide on the properties of. Xldb and nepe propellants with catalysts were prepared. A study on the microstructure of a nitrate ester plasticized. Comparison of thermal behaviors and decomposition kinetics of. Combustion of solid propellants the combustion of the components and then of the various propellants will be seen in the next chapters. Comparison of thermal behaviors and decomposition kinetics. The tendency for the propellant to decompose, crack, or coke is also important to know. The effect of ignition heat flux density on ignition delay time decreases when.
Measurement of combustion temperature of solid propellant by. The small cookoff bombs scbs, essentially closed pipes, each held about 1 lb of propellant. Combustion characteristics of xldb and nepe propellants with. Nitrate ester plasticized polyether nepe solid rocket propellants, which combine the advantages of doublebase propellants and composite. A solid propellant rocket or solid rocket is a rocket with a rocket engine that uses solid propellants fueloxidizer. Ninan high energy oxidisers fcir advanced solid propellants and explosives advances in solid propellant technology, p1 international hems1 workshop, ranchi, india, 2002, 87106. Us5430229a chemical process for disposal of rocket. A grain is any individual particle of propellant regardless of the size or shape.
The grain is the shaped mass of processed solid propellant inside the rocket motor. By the process of elimination, if the morphologies of any two among three kinds of solid. Rocket with unusual rocket body and engine semantic scholar. The propellant material and geometrical configuration of the grain determine the motor performance characteristics. Mathematical formulation and validation of muraours linear. In general, their compositions differed in the mass fraction of ammonium dinitramide adn, which was used as a. Machining of solid propellant surfaces is generally done by large cutting machines specially modified to accommodate the safety hazards associated with solid propellants. Nepe propellant is a new kind of solid propellant developed in the 1980s containing blend nitrate ester plasticized polyether adhesive.
With its high oxygen content, good density, and gasphase combustion products, ap sets a high standard for performance, stability, and low. The shape and size of a propellant grain determines the burn time, amount of gas, and rate produced from the burning propellant and, as a consequence, thrust vs time profile. We conducted a series of uniaxial tensile tests and employed a cumulative damage model to calculate the damage values for relaxation tests at different strain levels. The ignition and combustion property of solid propellant is the main content in internal ballistic research, which has a great significance for propulsion application and combustion mechanism. By nepe propellant high temperature accelerated aging test. Experimental investigation on ignition characteristic of nepe. Gel and solid rocket propellant is physically and chemically ablated from motors using a liquid or gaseous reagent such as anhydrous ammonia propelled by compressed nitrogen gas at 2000 psig or higher.
The burning characteristics and the thermal decomposition of propellants were determined by nickel chromium wire method and tg dtg, respectively. J, ed change march 2012 verify this is the correct version before you use it by checking the online version. Both propellants were aluminized, contained nitramine and ap, and exhibited similar performance and burn rates. Under static conditions, five samples were subjected to constantstrainrate monotonic loading with five different loading rates at room temperature. Life prediction of nepe propellants, propellants, explosives. A full and highly qualified exposure is given of russian experiments and theories for the first time in an english language publication. It discusses the burning rates, motor performance, grain configurations, and structural analy sis. The combustion of a solid propellant is characterized by the way its surface regresses once it begins to burn. The relaxed modulus and strength limit both decreased. Nov 29, 2012 experimental research on the low vulnerability of htpb and nepe solid propellant. Review of solid propellant ignition models relative to the interior ballistic modelling of gun systems executive summary solid propellant ignition and the evolution to selfsustained combustion is a highly complex physicochemical process, involving the transition of a stable solid propellant state. Measurement of combustion temperature of solid propellant.
The characteristics of static and dynamic mechanical. Because the matrix of nepe propellant is a typical viscoelastic material, it is. Also reported are detailed analyses of intrinsic combustion stability of solid propellants and stability of solid rocket motors or burners. The cover picture shows the change rule of stabilizer content in the aging process of nepe propellants, and the relationship between stabilizer content of nepe and the characteristic second derivative absorption band of its infrared spectrum. Other articles where solid propellant is discussed. The earliest rockets were solid fuel rockets powered by gunpowder. Nozzleless solid propellant rocket motors experimental and. The combustion flame temperature distribution of nepe propellant was measured using an infrared thermometer. Ftdmt65504 foreign technology division solid rocket propellants by a. Sep 17, 2015 to describe the relaxation behavior of nepe nitrate ester plasticized polyether propellant, we analyzed the equivalent relationships between time, temperature, and damage. It has great advantages in terms of increases in the range or. Kulkami high energy materials research laboratory, pune4 021 and k. In this paper, the static and dynamic mechanical viscoelastic behavior of nepe propellant are studied.
Solid propellant selection solid design team 1 andrew reid, zach anderson, derek bean, tony irvine, mayra flores, afiq ashiran. Mathematical formulation and validation of muraours linear burning rate. Experimental the microstructure of nepe solid propellant, which was taken from a rocket, was observed using hitachi s4500 and s6301 scanning electron microscopes japan. In this paper, a new simulation strategy was proposed for constructing the uvcuring crosslinking model by using computational programming. Nepe propellant have different dissolving properties in solutions of hcl and koh. Since solid propellant is the main energy source for solid rocket motor, the increase of specific impulse has always been a main aim during its development. The upper picture on the left represents probit curves of prominent sensitive energetic materials which could be excellently measured and evaluated with the new device. A solidpropellant rocket or solid rocket is a rocket with a rocket engine that uses solid. Nepe solid propellants were experimentally analyzed. We also discuss liners and insulators, propellants for igniters, tailoring of propellants, and propellants for. Propellant grain and grain configuration chamber pressure.
In this study, the factors which may have an impact on ignition delay time of nitrate ester plasticized polyether propellant nepe are analyzed by a co2 laser radiation experiment. A few general references about chemical propulsion, solid propellants and combustion can be found at the end of the main text, ahead of more specialized references introduced progressively in the following. Nepe propellant ignition and combustion under laser. Humidity aging behaviors of nepe propellant request pdf. Effects of npba on interface interaction and mechanical. The material tested here is a nepe solid propellant. Solid propellant rocket fundamentals this is the first of four chapters on solid propellant rockets. The ignition delay time of nepe propellant was decreased along with the increase of laser heat flux density. Nonsteady burning and combustion stability of solid.
The shape and size of a propellant grain determines the burn time, amount of gas and rate produced from the burning propellant and consequently thrust vs time profile. An sem and eds study of the microstructure of nitrate. The ignition characteristic of solid propellant is the main content in internal ballistic research. Pdf effect of coated ammonium dinitramide on the properties of. By calculating the structural integrity of nepe grain, the effects of modulus changes on the structure integrity were analyzed. The propellant samples were placed in the high temperature ageing test chamber, then the stabilizer content and infrared spectrum were tested regularly. The universal acceptability of this law is clear from the fact that the pressure index is indicated in many research articles for rocket propellant formulations. American institute of aeronautics and astronautics 12700 sunrise valley drive, suite 200 reston, va 201915807 703.
Abstract a generalised model of burning of a solid rocket propellant based on kinetics of propellant. Accumulation, aggregation, and agglomeration of aluminum. A study on consumption and characterization of stabilizer. Ninan high energy oxidisers fcir advanced solid propellants and explosives advances in solid propellant technology, p1. Higherperformance solid rocket propellants are used in large strategic missiles as opposed to commercial launch vehicles. It was found out that both samples experience five.
Characteristics of nepe propellant with ammonium dinitramide. By monitoring the dissolution process of nepe propellant in hcl and. Apr 25, 2019 on the other hand, it was found that the second derivative spectral absorbance of 1598 cm. For a solid, thermal conductivity is needed to understand and model the reaction and ablation processes in solid and hybrid rocket motors. A solid propellant rocket motor comprising a cylin of propellant, and the shell 14 another type of different drical casing having one end closed and the other end burning rate, in which case the thickness dimensions 15 open, a grain of solid propellant bonded over the entire. Nepe propellants have become one of the key research goals for the next decade. A process for determining the aging characteristics of solid rocket propellant samples by measuring their dynamic mechanical properties is disclosed. Their burning rates were measured by strand burner method. The results provide a reference for the life prediction of solid rocket motor containing an nepe propellant. Research on the thermal decomposition behavior of nepe. Pdf several industrial and research types of nitrateester plasticized polyether nepe solid propellants were experimentally analyzed.
Prediction and measurement of specific impulse, jp. The burning rate is the distance traveled by the flame front per unit of time, measured normally to the burning surface. The 260 the largest solid rocket motor ever tested pdf. On the other hand, it was found that the second derivative spectral absorbance of 1598 cm. Solid propellants were, eventually, easier to make, safer to store, lighter in weight because they did not require onboard pumps, and more reliable than their liquid predecessors.
Propellants, explosives, pyrotechnics wiley online library. Effects of relaxed modulus on the structure integrity of. Samples of rocket propellant are tested using a mechanical spectrometer at low strain levels and low frequencies. The theoretical performances of nepe nitrate ester plasticized polyether propellant with and without adn were calculated with minimum free energy method. Facilities and equipment are necessary for preparing the various propellant ingredients, mixing and handling the propellant, casting and curing the pro.
Solid propellants in this chapter we describe several common solid rocket propellants, their principal categories, ingredients, hazards, manufacturing processes, and qual ity control. It is, therefore, with energy and burning speed that this topic is mainly concerned. The strength limit of nepe propellants was tested by the uniaxial tension test. An experimental study was conducted to get the ignitibility of nepe propellant under different co2 laser heat fluxes. The method of approach differs from that with high explosives, because the hydrodynamic theory, so useful in that case, is of little value with propellants.
Solid propellant combustion and internal ballistics of. This chapter discusses the solid propellant combustion and internal ballistics of motors. The cover picture shows in the lower half a new balldrop impact tester bit manufactured by ozm as well as the moment of initiation of two energetic coordination complexes. Solid rocket propellants pdf the sketch below shows a section view of a typical solid propellant rocket. For the remaining pieces, the average distance thrown was about onethird to onehalf shorter for the modified nepe propellant than that observed for the htpb propellant. Hmx, c4h8n4no24, a nitramine with greater energy than ammonium perchlorate, is the main ingredient in nepe 75 propellant used in the trident ii d5 fleet ballistic missile. Introduction to explosives and propellants part of the text from parti of this chapter has been presented. Experimental research on the low vulnerability of htpb and nepe solid propellant. An employee received minor injuries when a nasa standard initiator ignited from being exposed to rf radiation without a faraday cap installed. Request pdf research on nepe propellant life prediction model nepe propellant is a new kind of solid propellant developed in the 1980s containing blend nitrate ester plasticized polyether. The temperature of nepe propellant plume is calculated by using the.
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