EXPERIMENTAL AND NUMERICAL STUDY OF CASTING PROCESS EFFECTS ON SMALL SCALE SOLID ROCKET MOTOR BALLISTIC BEHAVIOR

This paper describes a zero-dimensional model for evaluating the mass flow rate history of a solid rocket motor igniter. Based on the results of an igniter-firing experiment, in which the igniter is the only source of combustion gas and no propellant is ignited, the proposed model can be used to compute the mass flow rate of the igniter. Different species and temperature-dependent properties, such as the specific heat for each species, are considered. The coupling between the flow field variables in the combustion chamber and the heat transfer at the gas-solid interface is computed in a segment way. Calculations are performed for different species and properties, and the errors are discussed. Using the computed igniter mass flow rate as a boundary condition, a two-dimensional calculation is performed for validation purposes. The results are in good agreement with experimental data. The proposed model can be used to provide reasonable boundary conditions for solid rocket motor simulations and to evaluate the performance of igniters. Although derived on the basis of a small-scale solid rocket motor, the model has the potential to be used in large-scale systems.

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Numerical Study on Response Characteristics of Solid Rocket Pintle Motor

Journal of Aerospace Technology and Management ◽

10.5028/jatm.v11.1050 ◽

2019 ◽

Author(s):

Jeevan Sapkota ◽

Yi Hua Xu ◽

Hai Jun Sun

Keyword(s):

Flow Field ◽

Combustion Chamber ◽

Total Pressure ◽

Numerical Study ◽

Rocket Motor ◽

Chamber Pressure ◽

Head Model ◽

Solid Rocket Motor ◽

Rapid Changes ◽

Solid Rocket

Pintle technology is currently a versatile technology used in a solid rocket motor (SRM) to control the desired thrust by changing the nozzle throat area, while effectively controlling the chamber pressure at the same time. The sudden movement of the pintle can induce rapid changes in the flow field and the occurrence of pressure oscillations inside the combustion chamber. The analysis of such rapid changes is essential to design an efficient controllable pintle rocket motor for a better thrust regulation. Two-dimensional axisymmetric models with mesh generation and required boundary condition were designed to analyze the effects of three different pintle head shape models in SRM thrust regulation effect. Dynamic mesh method was used with specific velocity for moving plug/pintle in the numerical analysis of SRM thrust regulation. The effects of different pintle head models on the flow field, combustion chamber pressure, mass-flow rate, thrust and Mach number were investigated. According to the analysis of total pressure response time, the simulation data revealed that circular pintle head model responded faster among three different models. According to the thrust effect, parabolic pintle has the maximum value of thrust and the greatest total pressure recovery coefficient among all pintle head models.

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Numerical study of the unsteady flow in a simulated solid rocket motor

10.2514/6.1993-112 ◽

1993 ◽

Cited By ~ 7

Author(s):

T. SMITH ◽

R. ROACH ◽

G. FLANDRO

Keyword(s):

Unsteady Flow ◽

Numerical Study ◽

Rocket Motor ◽

Solid Rocket Motor ◽

Solid Rocket

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Research on the Performance Detecting System of High-Precision Small-Scale Solid Rocket Motor

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.346.804 ◽

2011 ◽

Vol 346 ◽

pp. 804-811

Author(s):

Qi Cao ◽

Xi Ping Feng ◽

Jie Li ◽

Tao Dong

Keyword(s):

High Precision ◽

Virtual Instrument ◽

Test Performance ◽

Motor Performance ◽

Rocket Motor ◽

Small Scale ◽

Solid Rocket Motor ◽

Parameter Calibration ◽

Test Fixture ◽

Solid Rocket

According to the performance detecting requirements in development and manufacture of solid rocket motor, a test platform had been set up based on flexible test fixture, a measurement & control platform had been built using virtual instrument technology, a set of solid rocket motor ground test performance detecting software including parameter calibration module, data measurement module and data processing module had been developed based on the LabVIEW7.1, and the solid rocket motor performance detecting system was constructed. The application results through testing normative solid rocket motor show that: the system could actualize parameter calibration expediently, experimental data collection and processing rapidly, even reach the measurement precision by 0.3% that required in project and could monitor the working process of solid rocket motor simultaneously, which satisfies high-precision requirement of motor performance detecting.

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Turbulent Flow Characteristics in a Model of a Solid Rocket Motor Chamber with Sidewall Mass Injection and End-Wall Disturbance

Mathematical Problems in Engineering ◽

10.1155/2021/9978102 ◽

2021 ◽

Vol 2021 ◽

pp. 1-17

Author(s):

F. A. Albatati ◽

A. M. Hegab ◽

M. A. Rady ◽

A. A. Abuhabaya ◽

S. M. El-Behery

Keyword(s):

Flow Field ◽

Turbulent Flow ◽

Stokes Equations ◽

Numerical Study ◽

Rocket Motor ◽

Staggered Grid ◽

Computational Time ◽

Solid Rocket Motor ◽

Solid Rocket ◽

End Wall

The present analytical, numerical, and experimental investigations are performed to study the flow field in acoustically simulated solid rocket motor (SRM) chamber geometry. The computational solution is carried out for a high Reynolds number and low Mach number internal flows driven by sidewall mass addition in a long chamber with end-wall disturbances. This kind of flow (transient, weakly viscous, and contains vorticity) have several features in common with a turbulent flow field. The numerical study is performed by solving the unsteady Reynolds-averaged Navier–Stokes equations along with the energy equation using the control volume approach based on a staggered grid system. The v2-f turbulence model has been implemented in the current study. A comparison of the SIMPLE and PISO algorithms showed that both algorithms provide identical results, and the computational time using the PISO algorithm is higher by about 6% than the corresponding value of the SIMPLE algorithm. A fair agreement has been obtained between the numerical, analytical, and experimental results. Moreover, the results showed that the complex turbulent internal flow patterns are induced inside the chamber due to the strong interaction of the sidewall injection with the traveling acoustic waves. Such a complex internal structure is shown to be dependent on the piston frequency and sidewall mass flux. The current study, for the first time, emphasizes the acoustic-fluid dynamics interaction mechanism and the accompanying unsteady rotational fields along with the effect of the generated turbulence on the unsteady vorticity and its impact on the real burning rate.

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Numerical Study of the Effects of Longitudinal Acceleration on Solid Rocket Motor Internal Ballistics

Journal of Fluids Engineering ◽

10.1115/1.2910045 ◽

1992 ◽

Vol 114 (3) ◽

pp. 404-410 ◽

Cited By ~ 23

Author(s):

J. J. Gottlieb ◽

D. R. Greatrix

Keyword(s):

Numerical Study ◽

Equations Of Motion ◽

Rocket Motor ◽

Rate Equations ◽

Solid Rocket Motor ◽

Two Phase ◽

Internal Ballistics ◽

Solid Propellant Rocket ◽

Solid Rocket ◽

The One

The internal ballistics of a solid-propellant rocket motor subjected to both constant and oscillatory longitudinal accelerations are studied. The one-dimensional time-dependent equations of motion governing the unsteady two-phase core flow in the accelerating motor chamber and nozzle are solved numerically by using the random-choice method, along with pressure-dependent and crossflow-dependent burning-rate equations for propellant combustion. A constant forward acceleration produces negligible effects, whereas longitudinal motor vibrations near the natural frequency of waves criss-crossing the length of the motor chamber can produce large but bounded oscillatory motor-chamber pressures.

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