Dynamic characteristics study of regression rate in variable thrust hybrid rocket motor

Tian, Hui; Meng, Xiangyu; Zhu, Hao; Li, Chengen; Yu, Ronghai; Zhang, Yuanjun; Cai, Guobiao

doi:10.1016/j.actaastro.2022.01.006

Cited by 25 publications

(6 citation statements)

References 21 publications

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“…Other successful throttleable hybrids have been reported in ranges of 3:1 [69,70] with soft landing experiments (see Figure 3), roughly 4:1 (from around 700 N) [71], 8.88:1 (from 950 N) [72], 1.66:1 [73], and 10:1 [74,75]. Ruffin et al [76] achieved throttling ratios of 12.6:1 and Bhadran et al [77] throttled down to 5.5:1.…”

Section: Throttlingmentioning

confidence: 92%

“…Finally, it can be argued whether Reynolds-averaged Navier-Stokes approaches (as in the majority of HRE simulations) are ideally suited for the complex wall blowing and pyrolysing phenomena at the fuel surface. Nevertheless, numerical simulations of HREs are improving significantly, be it in the modelling of hydrodynamic instabilities [149,150], swirl injection [138,[152][153][154], shape changing simulations [153][154][155][156][157] (see Figures 7 and 8), complex geometries such as helices [158][159][160], rotated grains [144,161], throttling [72,162], or nozzle erosion [94,163]. Simplified geometries and simulations carried out on the average fuel port diameter are considerably less computationally costly compared to multiple instances of the fuel port progression, with both providing satisfactory representations of the HRE flow field and local regression rates [157,164].…”

Section: Numerical Simulationsmentioning

confidence: 99%

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Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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Section: Throttlingmentioning

confidence: 92%

Section: Numerical Simulationsmentioning

confidence: 99%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…Additionally, HRMs enable precise control of the oxidizer flow, enabling on-demand start−stop functionality and adjustable thrust capabilities. 1,2 Consequently, HRMs have found wide-ranging applications in sub-orbiting spaceships, sounding rockets, and target missiles. 3−5 However, there are limitations hindering the further commercial development of HRMs.…”

Section: ■ Introductionmentioning

confidence: 99%

“…Due to their unique structural advantages, HRMs combine the benefits of both solid and liquid propulsion systems, resulting in high safety performance in the storage and transportation of the oxidizer and fuel. Additionally, HRMs enable precise control of the oxidizer flow, enabling on-demand start–stop functionality and adjustable thrust capabilities. , Consequently, HRMs have found wide-ranging applications in sub-orbiting spaceships, sounding rockets, and target missiles. − However, there are limitations hindering the further commercial development of HRMs. The internal combustion process of the solid–liquid hybrid engine follows a typical diffusion combustion process, where the oxidizer may not effectively combust with the solid fuel.…”

Section: Introductionmentioning

confidence: 99%

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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“…Typical hybrid rocket motors (HRMs) propellants consist of solid fuel and liquid oxidizers [1][2][3][4]. Since the propellants are stored in different phases, respectively, the hybrid rocket motor has obvious advantages compared with solid and liquid rocket motors in terms of simple structure, adjustable thrust, high safety, low cost, and multiple restart capabilities [5][6][7][8]. The advantages make it suitable for missile systems, attitude control motors, small launch vehicles, and space tourism.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2022

Self Cite

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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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Dynamic characteristics study of regression rate in variable thrust hybrid rocket motor

Cited by 25 publications

References 21 publications

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

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

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

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