Regression rate and combustion performance investigation of aluminum metallized HTPB/98HP hybrid rocket motor with numerical simulation

Sun, Xiaofeng; Tian, Hui; Yu, Nanjia; Cai, Guobiao

doi:10.1016/j.ast.2015.01.014

Cited by 43 publications

(10 citation statements)

References 22 publications

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“…Sun et al [15] carried out several ground firing tests, which demonstrate that the addition of 10% Magnesium (Mg), 28% Al, and 2% Carbon (C) resulted in a 12% increase in the regression rate of the pure HTPB. Sun et al [16] also demonstrated through steady-state simulations and experiments that the regression rate increased significantly with the increase of Al content, however, there is no significant relationship between the regression rate and the diameter of Al particles, which agrees well with the experimental results carried out by Strand et al [17]. In addition, according to ref.…”

Section: Introductionsupporting

confidence: 75%

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Dynamic Numerical Simulation of Hybrid Rocket Motor with HTPB-Based Fuel with 58% Aluminum Additives

et al. 2022

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The addition of aluminum (Al) to the fuel is an effective way to increase the regression rate of hybrid rocket motors (HRMs). Due to its high regression rate, the impact of the regression of combustion surface on the performance of HRMs cannot be ignored. Therefore, it is significant to establish a dynamic numerical simulation model to predict the performance of HRMs. In this study, the dynamic simulation model was established based on dynamic mesh technology and was verified by a firing test. The results show that the simulation results agree well with the experimental results, and the errors of the average thrust and combustion chamber pressure are 3.4% and 1.4%, respectively. The dynamic simulation shows that with the regression of the combustion surface, the vortex of the pre-combustion chamber is divided into two vortices. The vortex near the front of the grain will increase the regression rate downstream. The results show that the addition of Al can obviously improve the regression rate of HRMs. The fuel containing 58% Al can improve the regression rate by 88.8% compared with the fuel with pure hydroxyl-terminated polybutadiene (HTPB). Moreover, due to the higher combustion temperature and the scouring of metal particles, the ablation rate of the nozzle with carbon ceramic materials reaches 0.16 mm/s. This investigation provides a valuable reference for HRMs design and simulation.

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Section: Introductionsupporting

confidence: 75%

“…In addition, according to ref. [16], the Al particle diameter has a great influence on the vacuum specific impulse and characteristic velocity. The vacuum specific impulse and characteristic velocity decrease with the increase of the Al particle diameter.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Numerical Simulation of Hybrid Rocket Motor with HTPB-Based Fuel with 58% Aluminum Additives

et al. 2022

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“…This scenario creates a large temperature gradient, significantly enhancing the convective heat transfer process. 51,52 This phenomenon, which can also be seen in Figure 10, is facilitated by the thin boundary layer that forms at this position during the thermal boundary layer's initiation. However, as the axial distance increases, the boundary layer becomes thicker and the flame layer gradually moves away from the solid fuel surface, thereby diminishing the convective heat flux and regression rate, which is consistent with the literature.…”

Section: Setupmentioning

confidence: 73%

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Chen,

Fu,

Yang

et al. 2024

Langmuir

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Despite hybrid rocket motors offering distinct advantages over solid or liquid rocket motors, their low regression rate and insufficient combustion efficiency remain significantly unimproved. This study focuses on the effects of the helix lead on the regression rate distribution and combustion efficiency of vat-polymerized fuel grains with a spiral star port for a hybrid rocket. Both experimental and numerical investigations were conducted to study the combustion characteristics and regression rate distribution of three-dimensional (3D) print grains. Spiral star grains with varying helix leads of 60, 90, and 120 mm were fabricated using light-curing 3D printing technology. A 3D simulation model was developed to obtain the temperature distribution, species mass distribution, and combustion efficiency. Furthermore, firing tests were performed on a two-dimensional radial hybrid combustion test stand to measure the regression rate. Digital image processing of computed tomography images was used to determine the regression rate. Simulation results indicated that the spiral star grain port helps to improve the combustion efficiency compared with those seen with round tube and straight star port grains. With an increase in the axial distance, the flame zone gradually shrinks, and the smaller the helix lead, the faster the shrinkage. At a mass flow rate of 1.50 g/s for oxygen, the regression rate of the spiral star grains is significantly higher than that of the straight star grain and the conventional round tubular grains, and the regression rate gradually increases with a decrease in the helix lead. This finding is expected to solve the problem of the low regression rate of solid fuels with spiral star pore-shaped grains prepared by the light-curing 3D printing method.

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“…The aggregate performance of a propulsion system can be defined by the axial thrust produced per unit mass flow rate of propellant consumed, or specific impulse (I sp ). In propulsion system testing and analysis, the thrust and mass flow rate can be measured and compared to ideal performance for a given propellant combination [1][2][3][4][5]. This overall propulsive performance depends on the components of the system, most notably the combustor, which converts the chemical energy in the propellants to thermal energy, and the nozzle, which accelerates and expands the hot combustion product gas to generate jet thrust, effectively converting the thermal energy into kinetic energy.…”

Section: Introductionmentioning

confidence: 99%

Localized characteristic velocity (c*) for rocket combustion analysis based on gas temperature and composition via laser absorption spectroscopy

Bendana

Sanders

Stacy

et al. 2021

Meas. Sci. Technol.

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In this work, a method for experimentally determining a local characteristic velocity, , is presented for purposes of analyzing rocket combustion progress based on in-situ laser absorption spectroscopy measurements of temperature and gas composition. Measuring from spatially-varying thermochemical properties provides an alternative to the classical evaluation, which uses global chamber pressure and mass flow rate measurements. Accordingly, the novel method provides more detailed insight to the underlying mechanisms (multi-phase thermochemistry, diffusive mixing, turbulence, etc) governing combustion performance in the spatial domain. The method is demonstrated on an RP-2/O2 liquid-propellant rocket engine (LRE) and a PMMA/O2 hybrid rocket combustion experiment. Localized results for the LRE are obtained via in-chamber measurements of temperature, CO, and CO2 and are presented over a range of pressures ( 28–83 bar) and mixture ratios (MR = 2.5–5). For the hybrid rocket combustion experiment, one-dimensional tomographic reconstruction techniques are used to spatially-resolve the flow-field thermochemistry and obtain spatially-resolved measurements of temperature, CO, CO2, and H2O. These measurements are compiled to obtain spatially-resolved images of the combustion zone. The results from both experiments are compared to the theoretical expected from chemical equilibrium, providing for a method to assess combustion performance or progress locally within the combustion zone.

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Regression rate and combustion performance investigation of aluminum metallized HTPB/98HP hybrid rocket motor with numerical simulation

Cited by 43 publications

References 22 publications

Dynamic Numerical Simulation of Hybrid Rocket Motor with HTPB-Based Fuel with 58% Aluminum Additives

Dynamic Numerical Simulation of Hybrid Rocket Motor with HTPB-Based Fuel with 58% Aluminum Additives

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Localized characteristic velocity (c*) for rocket combustion analysis based on gas temperature and composition via laser absorption spectroscopy

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