scholarly journals Solid-Fuel Regression Rate Modeling for Hybrid Rockets

2013 ◽  
Vol 29 (1) ◽  
pp. 205-215 ◽  
Author(s):  
F. M. Favaró ◽  
W. A. Sirignano ◽  
M. Manzoni ◽  
L. T. DeLuca
Keyword(s):  
Solid Fuel ◽  
Regression Rate ◽  
Hybrid Rockets

scholarly journals Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 190
Author(s):  
Francesco Barato
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Diameter Ratio ◽  
Propulsion System ◽  
Burning Time ◽  
Regression Rate ◽  
Hybrid Propulsion ◽  
Deep Impact ◽  
Time Ratio ◽  
Hybrid Rockets

Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

An Accurate Performance Prediction of Solid Fuel Ramjets Using Coupled Intake-Combustor-Nozzle Simulation

2020 ◽  
Vol 36 (6) ◽  
pp. 933-941
Author(s):  
A. M. Tahsini
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Solid Phase ◽  
Three Dimensional ◽  
Flow Fields ◽  
Reacting Flow ◽  
Computational Domain ◽  
Regression Rate ◽  
Fuel Flow ◽  
Accurate Performance

ABSTRACTThe performance of the solid fuel ramjet is accurately predicted using full part simulation of this propulsion system, where the flow fields of the intake, combustion chamber, and the nozzle are numerically studied all together. The conjugate heat transfer is considered between the solid phase and the gas phase to directly compute the regression rate of the fuel. The finite volume solver of the compressible turbulent reacting flow is utilized to study the axisymmetric three dimensional flow fields, and two blocks are used to discretize the computational domain. It is shown that the combustion chamber's pressure is changed due to the fuel flow rate's increment which must be taken into account in predictions. The results demonstrate that omitting the pressure dependence of the regression rate and also the effect of the combustor's inlet profile on the regression rate, which specially exists when simulating the combustion chamber individually, under-predicts the solid fuel burning rate when the regression rate augmentation technique is applied to improve the performance of the solid fuel ramjets. It is also illustrated that using the inlet swirl to increase the regression rate of the solid fuel augments considerably the thrust level of the considered SFRJ, while the predictions without considering all parts of the ramjet is not accurate.

scholarly journals Biphasic Dispersion Fuels for High-Regression-Rate Hybrid Rockets

2019 ◽  
Vol 35 (5) ◽  
pp. 964-972 ◽  
Author(s):  
Joshua D. Mathews ◽  
Jason R. Gabl ◽  
Timothée L. Pourpoint
Keyword(s):  
Regression Rate ◽  
Hybrid Rockets

Three-Dimensionally Printed Polylactic Acid as Solid Fuel for Hydrogen Peroxide Hybrid Rockets

2021 ◽  
Vol 37 (1) ◽  
pp. 171-175
Author(s):  
Byeonguk Ahn ◽  
Jeongmoo Huh ◽  
Vikas Khandu Bhosale ◽  
Sejin Kwon
Keyword(s):  
Hydrogen Peroxide ◽  
Polylactic Acid ◽  
Solid Fuel ◽  
Hybrid Rockets

Role of Injection in Hybrid Rockets Regression Rate Behaviour

2005 ◽  
Vol 21 (4) ◽  
pp. 606-612 ◽  
Author(s):  
Carmine Carmicino ◽  
Annamaria Russo Sorge
Keyword(s):  
Regression Rate ◽  
Hybrid Rockets ◽  
Rate Behaviour

Solid-fuel regression rate and combustion behavior of vortex hybrid rocket engines

1999 ◽  
Author(s):  
William Knuth ◽  
Martin Chiaverini ◽  
Daniel Gramer ◽  
J. Sauer
Keyword(s):  
Solid Fuel ◽  
Rocket Engines ◽  
Hybrid Rocket ◽  
Regression Rate ◽  
Combustion Behavior
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