Numerical Modeling and Studies of Ignition Transients in End-Burning-Grain Solid Rocket Motors

Bo-wen, HU; Wang, Bing; Tian, Xiaotao

doi:10.2514/1.b36024

Cited by 10 publications

(8 citation statements)

References 14 publications

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“…One of the main differences from the models used in Ref. [8] is that, in the proposed model, the grain does not combust. Combustion of the grain is beyond the scope of this paper, so no combustion gas from the grain is added to the fluid domain.…”

Section: Validation Of the Modelmentioning

confidence: 88%

“…This value has been used by multiple researchers [6,9] for radiative heat transfer calculations in the port region. As shown by equations (8) and 14, to determine the heat transfer at the gas-solid interface, the interface temperature at the solid side (T w ) is also needed. The heat conduction normal to the surface of the solid is solved numerically using a one-dimensional FVM to obtain the temperature at the solid surface.…”

Section: The Radiative Heat Transfer Coefficient Is Computed Asmentioning

confidence: 99%

“…The main procedure is similar to that described in Ref. [8]. Both the fluid and the solid were modelled.…”

Section: Validation Of the Modelmentioning

confidence: 99%

“…In all the ignition models for SRMs, the mass flow rate (MFR) of the igniter gas is a relevant boundary condition that directly affects the solution of the associated partial differential equations [7]. Hu et al [8] carried out a series of numerical calculations using the commercial software package ANSYS Fluent and discussed the influence of the igniter MFR on the ignition of an SRM. Results show that changes in the igniter MFR history induce substantial internal ballistic changes in the SRM during the ignition.…”

Section: Introductionmentioning

confidence: 99%

“…For a typical SRM, the initial air, igniter gas, and combustion gas from the main propellant may exist simultaneously in the combustion chamber during the ignition process. In many studies, researchers assume that all three species have the same properties as the propellant combustion gas [8,9]. However, at the early stage of the ignition process, the fractions of different species change quickly, leading to large variations in the thermophysical properties of the mixture gas.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors

Bao

Hui

et al. 2019

International Journal of Aerospace Engineering

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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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Section: Validation Of the Modelmentioning

confidence: 88%

Section: The Radiative Heat Transfer Coefficient Is Computed Asmentioning

confidence: 99%

“…The main procedure is similar to that described in Ref. [8]. Both the fluid and the solid were modelled.…”

Section: Validation Of the Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors

Bao

Hui

et al. 2019

International Journal of Aerospace Engineering

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Mechanism of Influence of High‐Speed Self‐Spin on Ignition Transients for a Solid Rocket Motor: a Numerical Simulation

Guan

Sui

et al. 2020

Propellants Explo Pyrotec

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High‐speed self‐spin is one of extreme working conditions that alters ignition internal ballistic performance and can induce ignition abnormalities. To demonstrate the studies on mechanism of interior ballistics as the results of acceleration loads imposed on spinning SRM, the modes of swirl dynamical flow and acceleration‐induced combustion phenomena for igniter and propellant are developed and first taken into account in a new ignition model by user‐defined sources (UDS). To verify the model, the heat transfer, added‐mass and build‐up pressure modes of this ignition model are verified by comparison with static ignition experimental data, second, the swirl flow field mode is validated through comparison between models and by analogy with experimental phenomena, then the numerical model is proved by grid‐independent verification. Dimensionless analysis eliminates diversity in time scales at different periods. The influences of swirl flow, igniter, and propulsion acceleration‐induced combustion on various stages of ignition are studied. It was found that: (1) Time scale in the ignition process of spinning SRM is mainly affected by the igniter‘s sensitivity to rotational acceleration (Aig), whose change is approximately described as an empirical equation based on rotational overload (α) and ignition sensitivity coefficient limit Aig,max; (2) The acceleration effect on propellant combustion is mainly manifested in the pressure peak and the pressure rate, however, it has little effect on the ignition delay; (3) Swirl flow factors are not the main factors affecting the ignition process for small SRMs with small‐contraction nozzles.

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Numerical simulation of the effect of multiple factors on the ignition process of a solid rocket motor

Li,

Liu,

Zhang

et al. 2024

Propellants Explo Pyrotec

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With the continuous development of manned space technology, higher requirements have been proposed for solid rocket motors. The ignition process of solid rocket motors affects the reliability, stability and safety of their operation. The ignition powder, cover opening pressure and grain length‐diameter ratio are the main factors affecting the ignition process. Therefore, the influence of different factors on the ignition process of solid rocket motors is studied with numerical simulations. Based on the finite volume method, the ignition process of a solid rocket motor is modelled and experimentally verified. Then, the pressure and temperature distribution characteristics during the ignition delay, flame propagation and gas filling times are analysed. Finally, the effects of different ignition powders, cover opening pressures and length‐diameter ratios on the ignition process are compared and analysed. The results show that the model has high prediction accuracy. When the ignition powder is 6 g, the maximum combustion temperature of solid rocket motor increases from 2590 K to 2620 K between 0.1 ms and 0.44 ms. Between 0.44 ms and 3.18 ms, intermittent flame propagation and pressure oscillations occur. In the gas filling time, the flow field gradually stabilizes. Increasing the ignition powder mass is beneficial to the ignition process, but the disadvantages of pressure oscillations should be considered. Increasing the cover opening pressure enhances the ignition process, while increasing the length‐diameter ratio increases the ignition pressure building time. The study results provide technical support for the structural design of solid rocket motors.

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Numerical Modeling and Studies of Ignition Transients in End-Burning-Grain Solid Rocket Motors

Cited by 10 publications

References 14 publications

A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors

A Model for Igniter Mass Flow Rate History Evaluation for Solid Rocket Motors

Mechanism of Influence of High‐Speed Self‐Spin on Ignition Transients for a Solid Rocket Motor: a Numerical Simulation

Numerical simulation of the effect of multiple factors on the ignition process of a solid rocket motor

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