Combustion Performance Comparison of Propellant Grain for Hybrid Rocket Motors Manufactured by Casting and Fused Deposition Modeling

In this research, a firing test was conducted on a Hybrid Rocket Motor (HRM) that operates using an aluminized solid propellant containing HMX and Hydrogen Peroxide (HP). The instantaneous regression rate of HRM is determined using reconstruction techniques, and the formula of regression rate is fitted by reconstruction techniques and traditional weight-loss method. The utilization of the reconstruction method presents a notable advantage, as it allows for the determination of the regression rate’s sensitivity to variations in oxidizer mass flux. Additionally, this method enables the fitting of the regression rate formula based on data obtained from a single firing test. The average value of regression rate of four times firing test are 0.944, 0.529, 0.595 and 0.486 mm/s. According to the weight-loss method and reconstruction techniques, the coefficients of determination (R2 ) of regression rate formula fitting are 0.8867 and 0.93 respectively, indicating that the accuracy of the fitting is better than that of traditional method. Overall, this paper presents a comparison of traditional weight-loss method and reconstruction techniques for providing a critical preference for the research of regression rate of HRM.

Section: Introductionmentioning

confidence: 99%

Experiment research on regression rate of aluminized solid propellant with HMX using reconstruction techniques

Wei,

Cai,

Tian

et al. 2024

“…Hybrid rocket motor adopts solid and liquid propellants, which has many inherent merits over the conventional hybrid rocket motor systems, including high reliability, high safety, multiple restart and undemanding throttling [1]. It presents extensive applications for both military and commercial [2][3][4][5][6][7]. The thrust of HRM can be controlled easily by the regulation of oxidizer flow rate.…”

Section: Introductionmentioning

confidence: 99%

Experiment research on instantaneous characteristics of variable-thrust hybrid rocket motor by reconstruction techniques

Wei

Cai

Tan

2023

The firing test of variable-thrust Hybrid Rocket Motor (HRM), operated with Hydrogen Peroxide (HP) and Polyethylene (PE), based on closed-loop thrust control, has been carried out in this paper. The experiment research on instantaneous characteristics of HRM is conducted based on reconstruction techniques. A post-processing software has been developed to reconstruct the instantaneous performance parameters during the burning stage of HRM. Meanwhile, the formula of regression rate is fitted by reconstruction results through a single firing test, which is a significant advantage compared with traditional method. The averages of instantaneous parameters calculated by reconstruction techniques accord well with experimental data summarized by traditional consumption weight loss method, and the accuracy of reconstruction calculation is better than 1%. This paper is designed to achieve the reconstruction for instantaneous parameters and research the instantaneous characteristics during the variable-thrust firing test of HRM. The reconstruction techniques have the better accuracy, and also provide a critical method for the research on instantaneous characteristics of hybrid rocket motor.

“…1. Introduction HRM (HRM) adopts solid fuel and liquid oxidizer [1], and therefore it owns numerous advantages, including long-time working capacities, successive thrust regulation, and multiple start characteristics [2][3][4][5]. Owing to these characteristics, HRM has attracted much attention in some fields, such as tactical missiles, sounding rockets, and suborbital vehicles [6].…”

mentioning

confidence: 99%

Transient numerical investigation on thermochemical erosion of C/C nozzles in hybrid rocket motors

Jiang,

Tian,

2024

Nozzle erosion is a vital important issue that impacts the performance of hybrid rocket motors. Serious nozzle erosion may significantly decrease the combustion chamber pressure and thrust, which increases the difficulty in designing flight control systems. This paper aims to reveal erosion mechanism systematically. In this paper, transient numerical simulations of thermochemical erosion in hybrid rocket motors are conducted, and combustion flow and thermochemical erosion are coupled calculated. The numerical computation of combustion flow is based on the chemical reactions of propellants and regression rate model, and that of thermochemical erosion is based on the surface reactions between oxidizing species and carbon. The movement of burning surface and nozzle inner surface is simulated through dynamic mesh method. The hybrid rocket motor adopts 90% hydrogen peroxide and hydroxyl-terminated polybutadiene. Distributions of flow field parameters and fuel regression rate are given. The spatial developing process of nozzle surface is presented, and it is found that the roughness of nozzle profile increases with time. The nozzle wall temperature and wall pressure decline with time. Erosion by different species is calculated. OH and H2O make a major contribution to the nozzle thermochemical erosion, while nozzle erosion contributed by CO2 and O2 are quite low. Time-varying characteristics of the erosion rate are unveiled. At the first 1.5 s, the total erosion rate remains almost constant, and then it reduces over time.