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Estimation of Fuel Regression Rates in Hybrid Rocket Engines based on Pressure Measurement and Nozzle Throat Cross-section

Wüstenberg, Henrik (2019) Estimation of Fuel Regression Rates in Hybrid Rocket Engines based on Pressure Measurement and Nozzle Throat Cross-section. Other.

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Item URL in elib:https://elib.dlr.de/132194/
Document Type:Thesis (Other)
Additional Information:Studienarbeit
Title:Estimation of Fuel Regression Rates in Hybrid Rocket Engines based on Pressure Measurement and Nozzle Throat Cross-section
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Wüstenberg, HenrikHenrik.Wuestenberg (at) dlr.deUNSPECIFIED
Date:26 November 2019
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Number of Pages:123
Status:Published
Keywords:hybrid rocket engine, hydrogen peroxide, hydroxyl-terminated polybutadiene, htpb, slab burner, regression rate, measurement method, data analysis, performance, combustion chamber model, nozzle erosion
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):Project ATEK (old)
Location: Braunschweig
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, BS
Deposited By: Passern, Silke
Deposited On:07 Jan 2020 10:45
Last Modified:07 Jan 2020 10:45

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