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Characterization of Regression Rate and Combustion Process in a High-Pressure 2D Hybrid Rocket Engine with Optical Access

Poppe, Georg and Bozic, Ognjan and May, Stefan and Bierwagen, Nora Magdalena (2018) Characterization of Regression Rate and Combustion Process in a High-Pressure 2D Hybrid Rocket Engine with Optical Access. In: Proceedings of the International Astronautical Congress, IAC. 69th International Astronautical Congress 2018 (IAC), 01.-05. Oktober 2018, Bremen, Deutschland.

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A new slab combustion chamber employing hydrogen peroxide (H2O2) and hydroxyl-terminated polybutadiene (HTPB) was designed and commissioned by the German Aerospace Center (DLR), Institute for Aerodynamics and Flow Technology in Braunschweig at the DLR site Trauen. The combustion chamber has four helium-cooled quartz glass windows, which provide an insight into the combustion process above the fuel slab and enable its characterization with optical measurement techniques. The experiment allows studying the combustion process at pressures of up to 25 bars and oxidizer mass flows of up to 200 g/s. A H2O2 catalyst chamber, which delivers a mixture of hot water steam and oxygen, enables self-ignition without an additional igniter system. The regression rate during the test runs is measured with two ultrasonic probes and other methods. During the experiments a highspeed camera, a two-color pyrometer and infrared temperature measurements were also used. Three different fuel formulations based on HTPB with HDPE and PA6 polymeric particles at various chamber pressures and oxidizer mass flows have been examined. The preliminary results of the measured ignition times indicate a strong pressure dependency. Patterns on the fuel slab surfaces and images of the combustion process suggest a highly turbulent boundary layer flow. The regression rate seems to mainly depend on the oxidizer mass flow through the chamber with similar mass flow inclines for the HTPB and PA6 fuel formulations. In contrast the results for the HDPE formulation indicate a stronger incline at pressures of 15 bars, which might be caused by pre-test heat-up procedures.

Item URL in elib:https://elib.dlr.de/122751/
Document Type:Conference or Workshop Item (Speech)
Title:Characterization of Regression Rate and Combustion Process in a High-Pressure 2D Hybrid Rocket Engine with Optical Access
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Poppe, GeorgUNSPECIFIEDhttps://orcid.org/0000-0001-9003-3057144333684
Date:2 October 2018
Journal or Publication Title:Proceedings of the International Astronautical Congress, IAC
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:hybrid rocket engine, hydroxyl-terminated polybutadiene, hydrogen peroxide, slab burner, regression rate, catalytic ignition process
Event Title:69th International Astronautical Congress 2018 (IAC)
Event Location:Bremen, Deutschland
Event Type:international Conference
Event Dates:01.-05. Oktober 2018
Organizer:International Astronautical Federation (IAF)
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: Poppe, Georg
Deposited On:12 Nov 2018 14:49
Last Modified:13 Oct 2023 10:37

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