Evaluation of pressure oscillations by a laboratory motor

Taherinezhad, Roohollah; Zarepour, Gholamreza

doi:10.1016/j.cja.2019.11.010

Cited by 3 publications

(5 citation statements)

References 44 publications

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“…During an unstable combustion the pressure oscillates in the range of 5% and up to 30% of the maximum chamber pressure (Sutton and Biblarz 2017). The origin of pressure oscillations may be some perturbation in the combustion chamber which gets amplified due to instantaneous increase in burn rate, chamber pressure and the thrust.…”

Section: Pressure Oscillationmentioning

confidence: 99%

“…Vortex shedding due to slot between two grain segments (Sutton and Biblarz 2017) 3 Mathematical model…”

Section: Measurement Of Combustion Instabilitymentioning

confidence: 99%

“…There are two types of combustion instability that occurs in a solid rocket motor: Pressure oscillations and Vortex shedding. Pressure oscillations occurs in all kind of motors and Vortex shedding occurs in some particular type of grains as given in Sutton and Biblarz (2017).…”

Section: Introductionmentioning

confidence: 99%

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Mechanisms and applications of vibration energy harvesting in solid rocket motors

Goel

Srinivas

2021

Microsyst Technol

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Energy harvesting has become a fascinating topic of research. As the world moves towards reducing its dependency on fossil fuels, new and innovative techniques of energy harvesting have been tested and developed. The use of piezoelectric materials to harvest the ambient vibrations from the surroundings is one method that has seen a dramatic rise in use for power harvesting. Remote sensors can be powered by these piezoelectric materials and could potentially act as a continuous source of energy. In space vehicles, energy is generated using solar panels which are bulky, heavy and expensive. Instead piezoelectric harvesters can be used to generate power and are much lighter, compact and relatively cheap when produced in bulk. This paper presents a theoretical study on energy harvesting from structural vibration caused by combustion instability of a solid rocket motor through the motor burnout. Vibration data of tested solid rocket motor was taken as a reference and was inputted as the boundary condition. The 3-D model of the harvester system was designed on Fusion360 and the simulation was performed on COMSOL. Finally, improvements needed in the system to enhance practicality were discussed.

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Section: Pressure Oscillationmentioning

confidence: 99%

“…Vortex shedding due to slot between two grain segments (Sutton and Biblarz 2017) 3 Mathematical model…”

Section: Measurement Of Combustion Instabilitymentioning

confidence: 99%

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Mechanisms and applications of vibration energy harvesting in solid rocket motors

Goel

Srinivas

2021

Microsyst Technol

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“…In the DNS method, the model is in three dimensional, and the solution is time dependent. A few studies have employed the DNS method to investigate the compressibility of velocity transformations [84] , droplet condensation [85] , vortex shedding [86] , and hydrodynamic forces in the cylinder [87] . However, only a limited number of geometrically simple flows were simulated via the DNS method; for instance, the flow over a flat plate or flow in a channel.…”

Section: Solver Of Turbulence Modelmentioning

confidence: 99%

Computational fluid dynamics modelling of human upper airway: A review

Faizal

Ghazali

Khor

et al. 2020

Computer Methods and Programs in Biomedicine

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Background and objective: Human upper airway (HUA) has been widely investigated by many researchers covering various aspects, such as the effects of geometrical parameters on the pressure, velocity and airflow characteristics. Clinically significant obstruction can develop anywhere throughout the upper airway, leading to asphyxia and death; this is where recognition and treatment are essential and lifesaving. The availability of advanced computer, either hardware or software, and rapid development in numerical method have encouraged researchers to simulate the airflow characteristics and properties of HUA by using various patient conditions at different ranges of geometry and operating conditions. Computational fluid dynamics (CFD) has emerged as an efficient alternative tool to understand the airflow of HUA and in preparing patients to undergo surgery. The main objective of this article is to review the literature that deals with the CFD approach and modeling in analyzing HUA.Methods: This review article discusses the experimental and computational methods in the study of HUA. The discussion includes computational fluid dynamics approach and steps involved in the modeling used to investigate the flow characteristics of HUA. From inception to May 2020, databases of PubMed, Embase, Scopus, the Cochrane Library, BioMed Central, and Web of Science have been utilized to conduct a thorough investigation of the literature. There had been no language restrictions in publication and study design of the database searches. A total of 117 articles relevant to the topic under investigation were thoroughly and critically reviewed to give a clear information about the subject. The article summarizes the review in the form of method of studying the HUA, CFD approach in HUA, and the application of CFD for predicting HUA obstacle, including the type of CFD commercial software are used in this research area.

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“…Existing research provides a more accurate fuel regression rate model and some other parameters at the same time. Moreover, deeper research on pressure oscillations of a solid rocket motor [6] and on combustion instability of a liquid rocket motor [7] can be further introduced into HRM studies. All of these establish the foundation for the application of HRM.…”

Section: Introductionmentioning

confidence: 99%

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Zhu

Wang

et al. 2021

International Journal of Aerospace Engineering

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In this paper, the effects of different grain shapes of a hybrid rocket motor (HRM) and different payload mass/orbit heights on the design of small launch vehicles (SLVs) are systematically discussed. An integrated overall design model for the hybrid rocket motor-powered small launch vehicle (HPSLV) is established, and two groups of three-stage SLVs capable of sending small payloads to the low earth orbit (LEO) are designed and optimized. In the first group, the SLVs with different grain shapes and different numbers of chambers in HRMs at the 1st and the 2nd stages are optimized and analyzed. In the second group, the SLVs capable of sending different payload mass to different orbit heights are optimized and analyzed. Pareto graphs of the design results show that the design of HRM at the 1st stage has the greatest impact on the take-off mass, total velocity increment, and maximum axial overload of the SLV. Self-organizing maps show that the take-off mass, maximum diameter, overall length, and velocity increment of the SLVs have the same variation tendency. For the 1-chamber HRM at the 1st stage, the wheel-shaped grain is better than circle-shaped and star-shaped grains in terms of reducing the total mass and length of the SLV, and the 4-chamber parallel HRM has more advantages over all 1-chamber designs for the same reason. The theoretical velocity increments are calculated by the Tsiolkovsky formula, and the actual velocity increments are obtained based on the trajectory simulation data. The results indicate that the HPSLV has a regular distribution in terms of the ratio of theoretical (actual) velocity increments at three different stages, and the estimated distribution ratio is around 1 : 1.55 : 1.69 (1 : 1.9 : 2.39), which can provide some reference for future development of HPSLV.

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Evaluation of pressure oscillations by a laboratory motor

Cited by 3 publications

References 44 publications

Mechanisms and applications of vibration energy harvesting in solid rocket motors

Mechanisms and applications of vibration energy harvesting in solid rocket motors

Computational fluid dynamics modelling of human upper airway: A review

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

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