Influence of energetic characteristics of double-base propellants on internal-ballistics parameters (original) (raw)

Specific Design Features of Solid Propellant Rocket Motors for Shoulder-Launched Weapon Systems *

Solid propellant rocket motors for Shoulder Launched Infantry Weapon Systems (SLWS) are characterized with a very short burning time, high-pressure combustion and a wide spectrum of design solutions for rocket motor structure. Interior ballistic behaviour of such rocket motors depends on many factors such as design structure, propellant grain shape, propellant grain joint to the rocket motor case, type and location of the igniter, spinning mode and nozzle design. Erosive burning also plays important role due to high combustion gases mass flow rate. Numerical simulation of the igniter combustion gases flow through the hollow of the propellant grain tubes with gas temperature distribution was carried out in this paper. Results confirmed assumptions that igniter interior gas flow affected duration of the pressure rise. A mathematical model approach for prediction of the curve p = f(t) which was included in a model of the corrected propellant grain burning surface for two types of short...

Some Design Features of Solid Propellant Rocket Motors for Shoulder-Launched Weapon Systems

2010

Solid propellant rocket motors for Shoulder Launche d Infantry Weapon Systems (SLWS) are characterized with very short bu rning time, high-pressure combustion and wide spectrum of design solutions fo r rocket motor structure. Interior ballistic behaviour of such rocket motors depends o n many factors as design structure, propellant grain shape, propellant grain joint to t he rocket motor case, type and location of the igniter, spinning mode and nozzle design. Er osive burning also plays important role due to high combustion gases mass flow rate. Numerical simulation of the igniter combustion gases flow through the hollow of the pro pellant grain tubes with gas temperature distribution was carried out in this pa per. Results confirmed an assumptions that igniter interior gases flow affected pressure ris duration. A mathematical model approach for prediction of curve p=f(t) which was i ncluded a model of the corrected propellant grain burning surface for two types of s hort-time rocke...

Prediction of Internal Ballistic Parameters of Solid Propellant Rocket Motors *

A modular computer program named SPPMEF has been developed which is intended for purposes of predicting internal ballistic performances of solid propellant rocket motors. The program consists of the following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motors), GEOM (This module consists of two parts: a part for dimensioning of the propellant grain and a part for regression of burning surface) and ROCKET (This module provides prediction of an average delivered performance, as well as mass flow, pressure, thrust and impulse as functions of burning time). The program is verified with experimental results obtained from standard ballistic rocket test motors and experimental rocket motors. Analysis of results has shown that the established model enables high accuracy in prediction of solid propellant rocket motors features in cases where influence of combustion gases flow on burning rat...

Experimental Determination of Rocket Motor Internal Ballistic Coefficients and Performance Parameters

In solid propellant rocket motor internal ballistic calculation, next coefficients, performance parameters and characteristics are required: specific impulse, discharge coefficient, thrust coefficient and propellant burning rate law. All those RM working parameters can be theoretically or semi-empirically predicted, but depends from rocket motor design and combustion products flow losses; theoretical values can be very unreliable. Correction of theoretical working parameters can be provided using experimental data, although this approach is expensive and requires necessary experimental equipment. By using corrected working parameters in internal ballistic calculation highly precise results can be achieved, and accuracy of this approach is demonstrated in two different examples.

Prediction the Theoretical Interior Ballistic Properties of Solid Propellant Rocket Motors

Process for prediction the interior ballistic properties of solid propellant rocket motors is based on identification and quantitative estimation of idealized performances deviations. Solid propellants combustion and expansion of combustion gases within a rocket motor and nozzle represent a complex problem, which includes influences of chemical reactions, erosive burning, transport phenomena etc. The computer program TCPSP (Thermo-Chemical Properties Solid Propellant), which ensures calculation the equilibrium contents of combustion gases, transport properties of combustion gases and theoretical performances of rocket motors with specified propellant grains, has been developed. Comparative analyses of results from the TCPSP computer code with referring codes Ophelie and CEA have been carried out. A very good agreement has obtained.

Numerical simulation of internal ballistics parameters of solid propellant rocket motors

During the initial phase of design of solid propellant rocket motors it is necessary to iden-tify and quantitatively estimate deviation of internal ballistics parameters of observed rocket motors types from ideal conditions. In an initial stage of the design of real rocket motors there are differences between the rocket motor theoretical performances and actual performances based on testing of standard ballistic motors. Therefore modern numerical methods were used as a potential tool for the analysis of characteristics of combustion and gas flow in solid propellant rocket motors with specific design. Numerical simulations provide analysis of certain physical processes in rocket mo-tors, optimizing and reducing the cost of development of new rocket systems (minimizing number of models and tests). Mathematical and numerical 3D model, based on equations of mass, momentum and ener-gy conservation, describing transport processes in rocket motors, is used. Numerical simu-lation in CFD pac...

Ballistic design of solid propellant rocket motor

The paper presents a new method of preliminary estimation of main rocket and rocket motor parameters based on results of rocket unguided trajectory solution. The analyses are carried out using a model example, providing new informations for designers in the field of rockets.

Design, Manufacture, Test and Internal Ballistic Simulation of a Solid Propellant Motor

This article studies the solid propellant rocket motor internal ballistic simulation with multi-segmented grain and system engineering approach. Once grain is segmented, the alternative cross-burning Surfaces are added to combustion process. This simulation can estimate all motor performance parameters and satisfy thrust considered by mission. Synthesis and integration of all equations, modeling and relations correction in accordance with the proposed method, feasibility and effectiveness of method along with design, manufacture and test of one engineering prototype motor are the main goals of this study. Motor components are; Combustion chamber, grain, burning surface and nozzle. In this study, two main approaches are included; first is preparing a numerical program in accordance with the proposed method and second is technical requirements of production, static testing with data recording and analyzing. Determining all the inputs and outputs, effective interrelated data communication, correct and improve the calculation accuracy, simplicity and high speed calculation are advantages of the program. Finally, a complete prototype motor was manufactured and productive force was measured using a standard static test stand. Thrust force comparison between numerical and test output are show results matching.

Research of influence of nozzle geometry on internal ballistics performances of solid propellant rocket motors using numerical simulations

For tactical rocket motors with more nozzles allocated in a certain spatial distance from the nozzle axis, the products of combustion after the exit from internal cavity of propellant grain do not enter immediately into the nozzle. Products of combustion are reflected of the nozzle wall, swirling flow in front of the nozzle emerges, and only then products of com-bustion enter into convergent-divergent conical nozzles. There is a significant change in velocity vector and pressure redistribution of gas flow in region ahead of the nozzle, which bring about changes in development of pressure in rocket motor and change of internal ballistics parameters, such as total and specific impulse of rocket motor. A better understanding of complexity of gas flow in these cases is possible using numerical simulation. Research was focused to analysis of flow of double base propellant combustion products (without metal particles in rocket motors), and the influence of shape of the channel for passage...

E MISSILE AND ITS PERFORMANCE -AN ANALYSIS: Antitank Guided Missile, Milan-2T, Classification of Missiles, Propellant Design, Designing of Missile Motor Body & NX Application

Transstellar Journals, 2019

This study mainly deals with the design and structural analysis of missile motor body. This is to design three missile motor bodies with different dimensions and analyze them by applying three different materials for the corresponding loads, which act when two types of propellants are used and find the material with less deformation and better load bearing capability. The main aim of this study is structural analysis performed on the antitank guided missile MILAN 2T motor body, which was designed in NX for varying dimensions and thickness of three motor body designs and analyzed in the NX simulation by applying the loads imposed by two different propellants, namely double base and triple base propellants.