Concept and design of the hybrid test-motor for development of a propulsive decelerator of SARA reentry capsule

Andrianov, Artem; Shynkarenko, Olexiy; Bertoldi, Artur Elias De Morais; Barcelos, Manuel Nascimento Dias; Veras, Carlos

doi:10.2514/6.2015-3941

Cited by 5 publications

(5 citation statements)

References 6 publications

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“…The minimal amount of gas required for 16 ignitions of the hybrid rocket motor [1] are m ox = 105 g, and m f = 20.56 g, calculated taking into account the average ignition delay of 1.16 ± 0.48 s measured experimentally.…”

Section: Resultsmentioning

confidence: 99%

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Oxygen–Methane Torch Ignition System for Aerospace Applications

Shynkarenko¹,

Simone²

2020

Aerospace

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A new ignition system, based on a CH4/O2 torch has been developed by the Chemical Propulsion Laboratory of the University of Brasilia. Designed to ignite a hybrid rocket, this device has been improved to be used in testing of solid and liquid ramjet engines under development in our lab. The capability to provide multiple ignitions and to cool-down its combustion chamber walls by using a swirled injection of the oxidizer, along with a very low weight to power ratio, makes this device versatile. The igniter is controlled by a feedback system, developed by our group, which guarantees the possibility of operating in different design conditions enabling, therefore, complete integration with systems of different nature. The main characteristics of the igniter and the design solutions are presented including some considerations about the tests performed to evaluate the quality and performance of the ignition system.

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Section: Resultsmentioning

confidence: 99%

“…A torch ignition system has been developed in the Chemical Propulsion Laboratory (CPL) of the University of Brasilia in the context of a project sponsored by the Brazilian Space Agency (AEB) promoting design and development of a scientific payload (the SARA capsule) [1] powered during the re-entry phase by a hybrid rocket.…”

Section: Introductionmentioning

confidence: 99%

Oxygen–Methane Torch Ignition System for Aerospace Applications

Shynkarenko¹,

Simone²

2020

Aerospace

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“…The pre-combustion chamber of the UnB motor is exchangeable, allowing motor configurations with different chamber lengths. A detailed description of the system can be found in [24,25]. Previous researches have pointed out the strong influence of the oxidizer injection type on the instability of hybrid rockets engines [8][9][10][11][12][13].…”

Section: Methodsmentioning

confidence: 99%

Role of Precombustion Chamber Design in Feed-System Coupled Instabilities of Hybrid Rockets

Lee

Bertoldi

Andrianov

et al. 2020

Journal of Propulsion and Power

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Oxidizer feed-system coupled instabilities have been observed in several liquid and hybrid propellant rocket engines, though, not likely to be catastrophic for the latter. However, severe pressure oscillation in hybrid rocket may result in a significant reduction in the performance of the propulsion system restricting the application of the technology. In this research, it was studied, theoretically and experimentally, feed-system coupled instabilities for hybrid rocket engines. Two test campaigns were performed to investigate the effects of the pre-combustion chamber and oxidizer injector configurations on engine pressure oscillation. Then, an extended mathematical formulation, including the injector pressure drop, the pre-combustion chamber residence time, the gas residence time, and the combustion time lag, has been proposed. The investigation was based on a transfer function using the stability limit analysis and the root locus method. It has been found that the configuration of pre-combustion chamber plays an important role in the nature of the feed

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“…The validation of the suggested low-cost winding technology was conducted by manufacturing small-scale composite casings to evaluate the thickness and fiber volume ratio of helical plies. The dimensions of the designed casing are close to the size of the test motor of a hybrid propellant decelerator [33].…”

Section: Introductionmentioning

confidence: 95%

A Low-Cost Filament Winding Technology for University Laboratories and Startups

et al. 2022

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This paper systematically explains the methodology and results of empirical work on the development of a low-cost filament winding technology for manufacturing axisymmetric polymer composite structures with a high length-to-diameter ratio, such as tubes, motor casings, and pressure vessels. The principal objective was to examine the experiences and most optimal practices in the development of computer-controlled equipment and auxiliary tooling for the wet filament-winding process. To preclude expensive commercial software for the automated control of a winding machine, analytical equations were derived for the winding trajectory of a four-axis filament-winding machine. The feasibility of the proposed equations was successfully validated by laying the fiber along the geodesic path marked on the surface of a cylindrical mandrel with hemispherical ends. Moreover, the carbon/epoxy cylindrical casings with hemispherical ends and port openings of the same diameter were wound to determine the thickness distribution in the hemispherical dome. The fiber volume ratio in the wound composite parts was evaluated using an optical technique.

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Concept and design of the hybrid test-motor for development of a propulsive decelerator of SARA reentry capsule

Cited by 5 publications

References 6 publications

Oxygen–Methane Torch Ignition System for Aerospace Applications

Oxygen–Methane Torch Ignition System for Aerospace Applications

Role of Precombustion Chamber Design in Feed-System Coupled Instabilities of Hybrid Rockets

A Low-Cost Filament Winding Technology for University Laboratories and Startups

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