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Layout and Design of a pressurised Structure for gelled Propellants for a Thrust controllable Sounding Rocket Upper Stage

Zurkaulen, Maximilian (2021) Layout and Design of a pressurised Structure for gelled Propellants for a Thrust controllable Sounding Rocket Upper Stage. 16th International Conference on Space Operations (SpaceOps 2021), 03.-05. Mai 2021, virtuell.

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Official URL: https://spaceops.iafastro.directory/a/proceedings/SpaceOps-2021/SpaceOps-2021/12/manuscripts/SpaceOps-2021,12,x1548.pdf


In-situ measurements in middle and higher atmosphere regions are often only possible by means of sounding rockets. The typical trajectory of a sounding rocket is a suborbital, elliptic flight path which practically leads to only several seconds during ascent as well as descent to perform the desired measurements. To improve scientific gain and provide longer measurement times in the relevant altitude regions, the Mobile Rocket Base (MORABA) and partners of the German Aerospace Center as well as industrial partners are working on a thrust controllable upper stage for sounding rocket applications. The upper stage will be powered by a gelled propellant engine and enable the payload to hover on a certain altitude level or perform different, non-ballistic flight paths. To achieve this, it will be equipped with an attitude control system consisting of a thrust vector control unit for the engine and additional cold gas thrusters. In this way, it would be possible to precisely target atmospheric phenomena and perform local measurements with an essentially extended local operating time in comparison to current sounding rocket concepts. The rocket engine will be pressure fed by the propellant tank system which is a key element of the upper stage, providing a sufficient fuel flow and pressure needed for the optimal combustion and different thrust levels. This paper concentrates on the development of a fuel tank for gelled propellants for the supply of the upper stage engine. The development process is described from defining the task over the concept development to a detailed CAD model concept. The peculiarities of this tank are the light and economical design as well as the integrated, pressure driven piston to feed the propellant. The focus of this work is the definition of the concept and the subsequent structural FEM analysis of the tank system.

Item URL in elib:https://elib.dlr.de/147910/
Document Type:Conference or Workshop Item (Speech)
Title:Layout and Design of a pressurised Structure for gelled Propellants for a Thrust controllable Sounding Rocket Upper Stage
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Date:3 May 2021
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:concept development, FEM, high pressure structure, propellant tank design, sounding rocket
Event Title:16th International Conference on Space Operations (SpaceOps 2021)
Event Location:virtuell
Event Type:international Conference
Event Dates:03.-05. Mai 2021
Organizer:South African National Space Agency (SANSA)
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):R - Technologies for sounding rockets
Location: Oberpfaffenhofen
Institutes and Institutions:Space Operations and Astronaut Training > Mobile Rocket Base
Deposited By: Völk, Dr. Stefan
Deposited On:10 Jan 2022 10:19
Last Modified:10 Jan 2022 10:19

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