Investigation of Regression Rate under High-Pressure in Axial-Injection End-Burning Hybrid Rockets

2018 ◽  
Author(s):  
Yushi Okutani ◽  
Yuji Saito ◽  
Masaya Kimino ◽  
Ayumu Tuji ◽  
Kentaro Soeda ◽  
...  
Keyword(s):  
High Pressure ◽  
Axial Injection ◽  
Regression Rate ◽  
Hybrid Rockets

scholarly journals High Pressure Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets

2019 ◽  
Vol 35 (2) ◽  
pp. 328-341 ◽  
Author(s):  
Yuji Saito ◽  
Masaya Kimino ◽  
Ayumu Tsuji ◽  
Yushi Okutani ◽  
Kentaro Soeda ◽  
...  
Keyword(s):  
High Pressure ◽  
Axial Injection ◽  
Hybrid Rockets

Investigation of the Throttling Characteristics of Axial-injection End-burning Hybrid Rockets

2017 ◽  
Vol 65 (4) ◽  
pp. 157-167 ◽  
Author(s):  
Yuji SAITO ◽  
Toshiki YOKOI ◽  
Ayumu TSUJI ◽  
Kazunobu OMURA ◽  
Hiroyuki YASUKOCHI ◽  
...  
Keyword(s):  
Axial Injection ◽  
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.

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

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

scholarly journals Numerical Simulations of the Internal Ballistics of Paraffin–Oxygen Hybrid Rockets at Different Scales

Aerospace ◽  
2021 ◽  
Vol 8 (8) ◽  
pp. 213
Author(s):  
Mario Tindaro Migliorino ◽  
Daniele Bianchi ◽  
Francesco Nasuti
Keyword(s):  
Numerical Simulations ◽  
Radiation Effects ◽  
Scale Effects ◽  
Numerical Approach ◽  
Surface Radiation ◽  
Rocket Engines ◽  
Regression Rate ◽  
Internal Ballistics ◽  
Hybrid Rockets ◽  
Time Space

Hybrid rockets are considered a promising future propulsion alternative for specific applications to solid or liquid rockets. In order to raise their technology readiness level, it is important to perform predictive numerical simulations of their internal ballistics. The objective of this work is to describe and validate a numerical approach based on Reynolds-averaged Navier–Stokes simulations with sub-models for fluid–surface interaction, radiation, chemistry, and turbulence. Particular attention is given to scale effects by considering two different paraffin–oxygen hybrid rocket engines and a simplified grain evolution approach from the initial to the final port diameter. Moreover, a mild sensitivity of the computed regression rate to paraffin’s melting temperature, surface radiation emissivity, and Schmidt numbers is observed. Results highlight the increasing importance of radiation effects at larger scales and pressures. A numerical rebuilding of regression rate and pressure is obtained with simulations at the time-space-averaged port diameter, producing a reasonable agreement with the available experimental data, but a noticeable improvement is obtained by considering the grain evolution in time.

Visualization of Fuel Regression Rate in Axial-Injection End-Burning Hybrid Rocket

2020 ◽  
Author(s):  
Takumi Miwa ◽  
Ayumu Tsuji ◽  
Ryota Okuda ◽  
Shuichi Yokobori ◽  
Kentaro Soeda ◽  
...  
Keyword(s):  
Hybrid Rocket ◽  
Axial Injection ◽  
Regression Rate
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