DEVELOPMENT OF TEST FACILITIES FOR 5 KN-THRUST HYBRID ROCKET ENGINES AND A SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINE FOR TECHNOLOGY DEMONSTRATION

2016 ◽  
Vol 15 (6) ◽  
pp. 435-451 ◽  
Author(s):  
Koki Kitagawa ◽  
Saburo Yuasa ◽  
Takashi Sakurai ◽  
S. Hatagaki ◽  
N. Shiraishi ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Rocket Engines ◽  
Hybrid Rocket ◽  
Flow Type ◽  
Technology Demonstration ◽  
Hybrid Rocket Engine

Static Burning Tests on a Bread Board Model of Altering-intensity Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine

2016 ◽  
Author(s):  
Kohei Ozawa ◽  
Tomoaki Usuki ◽  
Genki Mishima ◽  
Koki Kitagawa ◽  
Masato Yamashita ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Hybrid Rocket ◽  
Flow Type ◽  
Hybrid Rocket Engine

scholarly journals Burn Time Correction of Start-Up Transients for CAMUI Type Hybrid Rocket Engine

Aerospace ◽  
2021 ◽  
Vol 8 (12) ◽  
pp. 385
Author(s):  
Tor Viscor ◽  
Hikaru Isochi ◽  
Naoto Adachi ◽  
Harunori Nagata
Keyword(s):  
Rocket Engine ◽  
State Level ◽  
Impinging Jet ◽  
Rocket Engines ◽  
Transient Effects ◽  
Hybrid Rocket ◽  
Start Up ◽  
Time Correction ◽  
Hybrid Rocket Engine ◽  
Time Issue

Burn time errors caused by various start-up transient effects have a significant influence on the regression modelling of hybrid rockets. Their influence is especially pronounced in the simulation model of the Cascaded Multi Impinging Jet (CAMUI) hybrid rocket engine. This paper analyses these transient burn time errors and their effect on the regression simulations for short burn time engines. To address these errors, the equivalent burn time is introduced and is defined as the time the engine would burn if it were burning at its steady-state level throughout the burn time to achieve the measured total impulse. The accuracy of the regression simulation with and without the use of equivalent burn time is then finally compared. Equivalent burn time is shown to address the burn time issue successfully for port regression and, therefore, also for other types of cylindrical port hybrid rocket engines. For the CAMUI-specific impinging jet fore-end and back-end surfaces, though, the results are inconclusive.

scholarly journals Design, Production and Evaluation of 3D-Printed Mold Geometries for a Hybrid Rocket Engine

Aerospace ◽  
2021 ◽  
Vol 8 (8) ◽  
pp. 220
Author(s):  
Benedict Grefen ◽  
Johannes Becker ◽  
Stefan Linke ◽  
Enrico Stoll
Keyword(s):  
Solid Fuel ◽  
Degrees Of Freedom ◽  
Rocket Engine ◽  
Mold Material ◽  
Rocket Engines ◽  
Test Bed ◽  
Hybrid Rocket ◽  
Design Production ◽  
3D Printed ◽  
Hybrid Rocket Engine

The feasibility of 3D-printed molds for complex solid fuel block geometries of hybrid rocket engines is investigated. Additively produced molds offer more degrees of freedom in designing an optimized but easy to manufacture mold. The solid fuel used for this demonstration was hydroxyl-terminated polybutadiene (HTPB). Polyvinyl alcohol (PVA) was chosen as the mold material due to its good dissolving characteristics. It is shown that conventional and complex geometries can be produced reliably with the presented methods. In addition to the manufacturing process, this article presents several engine tests with different fuel grain geometries, including a short overview of the test bed, the engine and first tests.

Performance and Regression Rate Characteristics of 5-kN Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine

2017 ◽  
Vol 33 (4) ◽  
pp. 891-901 ◽  
Author(s):  
Takashi Sakurai ◽  
Saburo Yuasa ◽  
Hideyuki Ando ◽  
Koki Kitagawa ◽  
Toru Shimada
Keyword(s):  
Rocket Engine ◽  
Hybrid Rocket ◽  
Regression Rate ◽  
Flow Type ◽  
Hybrid Rocket Engine
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