Numerical analysis of the hybrid rocket motor with axial injection based on oxidizer flow distribution

Tian, Hui; Jiang, Xianzhu; Zhu, Hao; Yu, Ronghai; Zhang, Yuanjun; Cai, Guobiao

doi:10.1016/j.actaastro.2021.12.025

Cited by 22 publications

(2 citation statements)

References 36 publications

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“…It was obvious that as L * increased, η c showed an apparent decreasing trend. Tian et al [35] proposed that the liquid oxidizer flow distribution had significant effects on the combustion characteristics in the whole operating process. Additionally, the reason for this might have been the diffusion combustion characteristic of HRM.…”

Section: Formula Modelmentioning

confidence: 99%

Experimental Research on Reconstruction Techniques for Instantaneous Regression Rate of Hybrid Rocket Motor with Single-Port Wagon Wheel Fuel Grain

et al. 2023

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This study investigated reconstruction techniques for building the instantaneous fuel regression rate of the hybrid rocket motor (HRM). Specifically, an experiment in a laboratory 500 N-class hybrid rocket motor with single-port wagon wheel fuel grain, operated with hydrogen peroxide (HP) and hydroxyl-terminated polybutadiene (HTPB) based fuel (including Al), was carried out. A piece of post-processing software was developed to reconstruct the instantaneous regression rate and other performance parameters of the HRM during the firing test. The results produced by the reconstruction techniques are in good agreement with experimental data obtained by traditional methods, with a maximum error of less than 5.75%. Moreover, compared with the traditional endpoint method, the reconstruction method had a significant advantage, which could ascertain the sensitivity of the regression rate to changes in the oxidizer mass flux and fit the formula of regression rate in a single firing test. Additionally, digital image processing techniques were employed to determine the axial distribution of the fuel regression rate after the test using computed tomography (CT) scanning. This served to verify the accuracy of the instantaneous reconstruction calculation. The error in the average regression rate between CT scanning and the reconstruction calculation was 1.91%, proving that the CT scanning and pixel statistic method of the calculating regression rate was practical for characterizing the axial distribution of the average regression rate during the firing test. In summary, the main objective of this study was to reconstruct the transient parameters of hybrid rocket motor with single-port wagon wheel fuel grain using reconstruction techniques, and to fit the formula of the regression rate through a single-firing test. Furthermore, this paper proposes a modified reconstruction method that is essential for investigating fuel regression rate during the firing test of HRMs.

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Section: Formula Modelmentioning

confidence: 99%

Experimental Research on Reconstruction Techniques for Instantaneous Regression Rate of Hybrid Rocket Motor with Single-Port Wagon Wheel Fuel Grain

et al. 2023

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“…The propellants in the motor are 98% hydrogen peroxide and hydroxyl-terminated polybutadiene. The flow field structure in the pre-combustion chamber and front half of the fuel grain port is mostly influenced by oxidizer flow distribution, according to a numerical study which is given by Tian H et.al [4]. Structures should be light, for example, key components should be made of composite and alloy materials with a low weight-to-strength ratio.…”

Section: Literature Reviewmentioning

confidence: 99%

Experimental and Computational Investigation of Sounding Solid Rocket Motor

Jadhav¹,

Nag

Bandyopadhyay

et al. 2022

jame

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Experimental sounding rockets are important contributors to aerospace engineering research. However, experimental-sounding rockets are rarely used for student research projects by institutes in India. The unavailability of rocket motors, which require complex machining and explosive propellants, is a major barrier to the use of sounding rockets in student research projects. We ran into this problem while developing a sounding rocket motor for project and learning purposes. The project focuses on designing and constructing a solid rocket motor that researchers can use as the primary propulsion unit in experimental sounding rockets. Initially, basic designs were evaluated, as various concepts of observations of propellant configuration. The accessibility and ease of use of manufacturing and casting of propellants played a significant role in determining the best propellant based on these findings, the theoretical values for combustion chamber parameters were obtained. Also, materials were chosen accordingly, and a fundamental small-scale experimental design was built and extensively tested. This small-scale motor was created by combining all of the analysis and theoretical data.At experimental testing, we got to know the thrust generated is 763.47N and the motor runs for 4.1 sec, the total mass of the propellant is maxed at 1500g which gives us the max mass flow rate of 0.65Kg/sec this is the output for our solid rocket motor.

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Experimental test analysis of a 300 N hybrid rocket engine

Srivastava,

Thakur,

Gupta

et al. 2024

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Numerical analysis of the hybrid rocket motor with axial injection based on oxidizer flow distribution

Cited by 22 publications

References 36 publications

Experimental Research on Reconstruction Techniques for Instantaneous Regression Rate of Hybrid Rocket Motor with Single-Port Wagon Wheel Fuel Grain

Experimental Research on Reconstruction Techniques for Instantaneous Regression Rate of Hybrid Rocket Motor with Single-Port Wagon Wheel Fuel Grain

Experimental and Computational Investigation of Sounding Solid Rocket Motor

Experimental test analysis of a 300 N hybrid rocket engine

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