Experimental study on precise thrust control of hydrogen peroxide and polyethylene hybrid rocket motors

Tan, Guang; Tian, Hui; Jiang, Xianzhu; Chen, Ruikai; Lu, Yudong; Zhang, Yuanjun

doi:10.1016/j.actaastro.2022.04.032

Cited by 13 publications

(12 citation statements)

References 21 publications

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“…Therefore, either the fuel production and general development of HRE needs to reach a more mature stage (with the growing number of successful tests of large engines of numerous hybrid startups hinting at considerable progress), or the engine needs to be actively controlled to match the desired thrust levels. The signal to close the loop can be either the oxidizer mass flow, the chamber pressure, the thrust, or the instantaneous regression rate [60,87,88].…”

Section: Repeatability and Active Controlmentioning

confidence: 99%

“…To couple the oxidizer mass flow to the thrust as feedback, it is often necessary to accurately develop (or test) the relationship between the oxidizer mass flow and the thrust, as well as to ensure that the commanded and actual oxidizer mass flow rate are identical [88]. For this, the internal ballistics are of upmost importance, including information on the regression rate parameters, combustion efficiency, and nozzle erosion [88]. Using thrust as feedback is the most straightforward of these, however, it is difficult to measure in-flight and needs to be estimated using flight mechanics, velocity, acceleration, and angular momentum [60].…”

Section: Repeatability and Active Controlmentioning

confidence: 99%

“…Moreover, the pressure probes typically read the pre-chamber pressure. This could vary from the true chamber pressure due to the diffusion combustion process [88] and motor acoustic resonant frequencies [60]. In all three cases (thrust, chamber pressure, and oxidizer mass flow as feedback), extensive and expensive tuning and debugging of the controller gains through simulations, cold flow tests, and open loop tests are necessary.…”

Section: Repeatability and Active Controlmentioning

confidence: 99%

See 2 more Smart Citations

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: Repeatability and Active Controlmentioning

confidence: 99%

Section: Repeatability and Active Controlmentioning

confidence: 99%

Section: Repeatability and Active Controlmentioning

confidence: 99%

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Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…The variable-thrust firing test is carried out through the thrust closed-loop control by using the thrust as the feedback signal, which is conducted by our research group [15]. Three-stage thrust is designed to verify the instantaneous characteristics of hybrid rocket motor by reconstruction techniques in this test.…”

Section: Experiments Setupmentioning

confidence: 99%

“…The extrusion oxidizer conveying system is shown in Figure 3 [15], which includes high-pressure gas tank, hydrogen peroxide tank, pressure regulator, mass flowmeter, variable area cavitating venturi, filter, solenoid valve, buffer and blowing pipeline. The oxidizer mass flow rate is controlled and regulated by the variable area cavitating venturi.…”

Section: Oxidizer Delivery Systemmentioning

confidence: 99%

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

Wei

Cai

Tan

2023

J. Phys.: Conf. Ser.

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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.

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Research on thermochemical erosion and thermal protection properties of multiple interface nozzles in long-time working hybrid rocket motors

Tian

Jiang

et al. 2023

Acta Astronautica

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Experimental study on precise thrust control of hydrogen peroxide and polyethylene hybrid rocket motors

Cited by 13 publications

References 21 publications

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

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

Research on thermochemical erosion and thermal protection properties of multiple interface nozzles in long-time working hybrid rocket motors

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