scholarly journals Operation of solid rockets in comparison with hybrid rockets during the STERN project

2016 ◽  
Author(s):  
Katharina Schüttauf ◽  
Andreas Stamminger ◽  
Karsten Lappöhn ◽  
Helmut Ciezki ◽  
Wolfgang Kitsche
Keyword(s):  
Hybrid Rockets ◽  
Solid 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

Examining Port Geometry/Solid Loading for Additively Manufactured Fuels in Hybrid Rockets

2020 ◽  
pp. 1-9
Author(s):  
Gregory Young ◽  
Terrence L. Connell ◽  
Kyle Fennell ◽  
Steve Possehl ◽  
Michael Baier
Keyword(s):  
Solid Loading ◽  
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.

Flight Research of an Aerospike Nozzle Using High Power Solid Rockets

2005 ◽  
Author(s):  
Trong Bui ◽  
James Murray ◽  
Charles Rogers ◽  
Scott Bartel ◽  
Anthony Cesaroni ◽  
...  
Keyword(s):  
High Power ◽  
Solid Rockets ◽  
Aerospike Nozzle

Numerical Analysis of Nozzle Erosion in Hybrid Rockets and Comparison with Experiments

2021 ◽  
pp. 1-22
Author(s):  
Daniele Bianchi ◽  
Mario Tindaro Migliorino ◽  
Marco Rotondi ◽  
Landon Kamps ◽  
Harunori Nagata
Keyword(s):  
Numerical Analysis ◽  
Hybrid Rockets ◽  
Nozzle Erosion ◽  
Comparison With Experiments

Correction: Prediction of 3D Boundary Layer Blockage and the Grain Design Optimization of HVT Dual-thrust Hybrid Rockets

2018 ◽  
Author(s):  
VR Sanal Kumar ◽  
Vigneshwaran Sankar ◽  
Nichith Chandrasekaran ◽  
Pavithra Murugesh ◽  
Sulthan Ariff Rahman M ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Design Optimization ◽  
Hybrid Rockets

scholarly journals Correction to: A Computational Tool for the Design of Hybrid Rockets

2021 ◽  
Author(s):  
Paolo Maria Zolla ◽  
Mario Tindaro Migliorino ◽  
Daniele Bianchi ◽  
Francesco Nasuti ◽  
Rocco Carmine Pellegrini ◽  
...  
Keyword(s):  
Computational Tool ◽  
Hybrid Rockets
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