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An Advanced Hybrid Rocket Engine for an Alternative Upper Stage of the Brasilian VLM 1 LEO Launcher

Bozic, Ognjan and Poppe, Georg and Porrmann, Dennis (2014) An Advanced Hybrid Rocket Engine for an Alternative Upper Stage of the Brasilian VLM 1 LEO Launcher. In: 65th International Astronautical Congress (ISSN: xxxx ). International Astronautical Fedration. 65th International Astronautical Congress, 29 Sept. – 3 Oct. 2014, Toronto, Canada. ISSN xxxx

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Abstract

The Institute of Aeronautics and Space (IAE), on behalf of the Brazilian Space Agency (AEB), is developing a new launch system called Microsatellite Launch Vehicle (VLM-1). The development is supported by German Aerospace Center (DLR) and some German industrial companies. Basically, the VLM-1 is planned as a three stage launcher with solid rocket engines, which could deliver up to 200 kg payload in Low Earth Orbit (LEO). To propel the 1st and 2nd stage the launcher will be equipped with solid rocket engines of the type S50, which have identical structure for both stages. The only exception is a different nozzle expansion ratio. As a 3rd stage the solid rocket engine S44 combined with attached RCS system, based on cold gas engines, is planned. To overcome the maneuverability limitations at injection phase of payload into LEO, an alternative hybrid rocket engine (HRE) for the 3rd stage is analyzed by the Institute of Aerodynamics and Flow Technology of DLR Braunschweig. As a suitable propellant mixture for this engine High Test Peroxide (HTP) is selected as oxidizer, with concentrations higher than 87.5 wt%, and polymeric hydrocarbon fuels with different ingredients, which improves the regression rate and combustion efficiency. One of the analyzed propellant mixtures is verified in experiments carried out within the DLR AHRES program (Advanced Hybrid Rocket Engine Simulation) on the test facility Trauen, Germany. In this paper the predesign of the HRE concept possesses the ability of multi-ignition, due to a catalyst for the decomposition of hydrogen peroxide (HTP), throttle-ability in the range 1:3 of maximum thrust and also thrust vector control. For the design and optimization of the HRE the DLR software tool AHRES is applied. Within this paper, results of interior ballistic computations, heat transfer and temperature distribution inside the combustion chamber, as well as the properties of pressure feed system are shown and analyzed. The solid fuel grain geometry is designed using the burn-back module STAR (part of DLR AHRES software tool), which is coupled with optimizer NOMAD (based on direct search optimization algorithm). For the moveable nozzle with ablation, gas flow properties, temperature distribution within multilayer structure, radial and tangential stresses as well as structure dilatations for each CAD plane in longitudinal axis direction are presented.

Item URL in elib:https://elib.dlr.de/92805/
Document Type:Conference or Workshop Item (Speech)
Additional Information:Feasibility study for alternative upperstage of Brazilian launch system Microsatellite Launch Vehicle (VLM-1)
Title:An Advanced Hybrid Rocket Engine for an Alternative Upper Stage of the Brasilian VLM 1 LEO Launcher
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Bozic, Ognjanbozic.ognjan (at) dlr.deUNSPECIFIED
Poppe, Georggeorg.poppe (at) dlr.deUNSPECIFIED
Porrmann, Dennisdennis.porrmann (at) dlr.deUNSPECIFIED
Date:2 October 2014
Journal or Publication Title:65th International Astronautical Congress (ISSN: xxxx )
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Editors:
EditorsEmail
Higuchi, K.UNSPECIFIED
Publisher:International Astronautical Fedration
Series Name:DVD ROM
ISSN:xxxx
Status:Published
Keywords:Hybrid rocket engine, upper stage, AHREUS, interior ballistic, design, mass analysis, HTP
Event Title:65th International Astronautical Congress
Event Location:Toronto, Canada
Event Type:international Conference
Event Dates:29 Sept. – 3 Oct. 2014
Organizer:International Astronautic Federation
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Vorhaben AHRES (old)
Location: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Bozic, Dr.-Ing. Ognjan
Deposited On:01 Dec 2014 09:42
Last Modified:01 Dec 2014 09:42

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