Solid rocket motor burn simulation considering complex 3D propellant grain geometries

Mejia, Guilherme; Jachura, Roberta; Gomes, Susane R.; Rocco, Leopoldo; Rocco, José Atílio Fritz Fidel; Iha, Koshun

doi:10.2514/6.2016-5098

Cited by 7 publications

(3 citation statements)

References 7 publications

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“…Experimental research serves as a foundation to test and guide the establishment of theoretical models [2][3][4]. Theoretical research comprises physical model simulations and numerical analysis, which is based on experimental data and basic theory [5][6][7][8]. However, low fault tolerance rate, high cost, drastic changes and unstable of work process have become the biggest obstacles for experiment research.…”

Section: Introductionmentioning

confidence: 99%

Deep learning-based total impulse prediction method in ignition process of solid rocket motor

Yang,

Wang,

Zheng

et al. 2023

International Workshop on Signal Processing and Machine Learning (WSPML 2023)

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Section: Introductionmentioning

confidence: 99%

Deep learning-based total impulse prediction method in ignition process of solid rocket motor

Yang,

Wang,

Zheng

et al. 2023

International Workshop on Signal Processing and Machine Learning (WSPML 2023)

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“…In recent years, with the rapid development of computer technology and 3D printing technology, scholars have used numerical simulation software and 3D printing equipment to carry out numerous in-depth studies on the design of complex propellants. Mejia et al [20] developed an RSIM (a developed tool for SRM burning simulation) tool to simulate the combustion surface displacement curve of complex solid propellant, which is very useful for combustion calculation of grains with complex structure and solid rocket motor design. In terms of 3D-printed solid propellants with complex grains, the Indian Research Institute [4] reported a solid propellant formulation suitable for 3D printing in 2018.…”

Section: Introductionmentioning

confidence: 99%

A Study on Ultra-Low-Pressure Ratio Technology on the Basis of 3D-Printed Propellant for a Solid Rocket Motor

Song,

Ren,

Tang

et al. 2023

Aerospace

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Fused deposition technology (FDM), as an additive manufacturing (AM) technology, holds immense potential in the field of solid grain manufacturing. It can accomplish complex grain shaping with ultra-low-pressure ratios, which are challenging to achieve using conventional grain manufacturing processes. In this work, solid propellants with complex structures were made by using 3D printing. The obtained sample grains of the solid propellants had a complete structure, which conformed to the design model and had no obvious defects. Then, the combustion and mechanical properties of the printed solid propellant were obtained and analyzed. The results show that the composition of the printed solid propellant is more uniform and the performance is better than that of the conventional solid propellant. In addition, by conducting a motor experiment, it was verified that the 3D-printed grains with complex structures have the characteristic of an “ultra-low pressure ratio”. The comparative analysis revealed that the maximum working pressure was reduced by about 19.5%, the bearing load of the shell was reduced, and the mass of the shell and other bearing parts was reduced by 11.5%. The research in this paper shows that 3D-printed solid propellant technology can realize the formation of grains with complex structure, which can directly promote the solid rocket motor to obtain the “ultra-low pressure ratio” characteristic, and greatly improve the performance of solid rocket motors.

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“…And the physical mechanism mainly includes particle aggregation [3], shear flow [4], composition shift [5,6], stress [5,6], heat conduction effects [7], stressinduced grain defect [8], and end motor structure [9], while chemical mechanism mainly contains chemical reaction feature [10], heat flux of gas [11], and flame stretch by the velocity field [12]. In order to prevent the cone problem and interior ballistic instability from affecting the performance and reliability of a grain, the improvement in grain configuration [13], an important means of stabilizing the working pressure is often adopted. It is necessary to judge the feasibility of the modified design and its advantages and disadvantages in contrast with other designs and study the end-burning law.…”

Section: Introductionmentioning

confidence: 99%

Burning Rate Enhancement Analysis of End-Burning Solid Propellant Grains Based on X-Ray Real-Time Radiography

Wei

Tao

Wang³

et al. 2020

International Journal of Aerospace Engineering

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Unexpected pressure rise may occur in the end-burning grain solid rocket motor. It is generally believed that this phenomenon is caused by the nonparallel layer combustion of the burning surface, resulting in the increase of burning rate along the inhibitor. In order to explain the cause of this phenomenon, the experimental investigation on four different end configurations were carried out. Based on the X-ray real-time radiography (RTR) technique, a new method for determining the dynamic burning rate of propellant and obtaining the real-time end-burning profile was developed. From the real-time images of the burning surface, it is found that there was a phenomenon of nonuniform burning surface displacement in the end-burning grain solid rocket motor. Through image processing, the real-time burning rate of grain center line and the real-time cone angle are obtained. Based on the analysis of the real-time burning rate at different positions of the end surface, the end face cone burning process in the motor working process is obtained. The closer to the shell, the higher the burning rate of the propellant. Considering the actual structure of this end-burning grain motor, it is speculated that the main cause of the cone burning of the grain may be due to the heat conduction of the metal wall. By adjusting the initial shape of the grain end surface, the operating pressure of the combustion chamber can be basically unchanged, so as to meet the mission requirements. The results show that the method can measure the burning rate of solid propellant in real time and provide support for the study of nonuniform combustion of solid propellant.

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Solid rocket motor burn simulation considering complex 3D propellant grain geometries

Cited by 7 publications

References 7 publications

Deep learning-based total impulse prediction method in ignition process of solid rocket motor

Deep learning-based total impulse prediction method in ignition process of solid rocket motor

A Study on Ultra-Low-Pressure Ratio Technology on the Basis of 3D-Printed Propellant for a Solid Rocket Motor

Burning Rate Enhancement Analysis of End-Burning Solid Propellant Grains Based on X-Ray Real-Time Radiography

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