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Thermal Protection-, Aerodynamics- and Control Simulation of an Electromagnetically Launched Projectile

Lancelle, Daniel und Božić, Dr. Ognjan (2014) Thermal Protection-, Aerodynamics- and Control Simulation of an Electromagnetically Launched Projectile. 17th Electromagnetic Launch Symposium, 2014-07-07 - 2014-07-11, San Diego, USA. doi: 10.1109/EML.2014.6920171.

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Kurzfassung

In recent years several ideas came up to apply electromagnetic launch technology for spaceflight applications. Using electric energy to propel a payload carrier promises the saving of propellant and therefore cost reduction for the transfer to orbit. The conducted studies mostly comprise of a rough estimation of the launcher and the vehicle size. Sometimes a Δv-budget is given to illustrate the energy expenditure. Some of the studies neglect the necessity of a rocket engine. Only by means of an electromagnetic launch without the capability to maneuver, an orbit is not achievable. The high acceleration and the high velocities at low altitude evoke high demands on the payload carrying vehicle. Its structure has to withstand the high acceleration forces during launch and the tremendous aerodynamic heat fluxes during the ascent flight in the dense atmosphere. Moreover a propulsion system, an attitude control system, and a flight controller are needed to bring the vehicle into a circular orbit. This paper presents a vehicle concept that addresses all these demands. The vehicle comprises of a two stage hybrid rocket engine system, a thermal protection system, high test peroxide monopropellant thrusters for attitude control, and a guidance, navigation and control system. A simulation model is created, that consists of a 6-DOF flight mechanics module, aerodynamics model, propulsion module, thermal protection system simulation, as well as of guidance and flight control simulation. Therefore, the complete ascent with all its aspects can be simulated. The simulation results show that a 710 kg vehicle launched with 2586 g and an initial velocity of 3642 m/s can carry 31.5 kg of payload into a 300 km circular orbit. The configuration of the vehicle can be defined by a set of input parameters. This allows using the model within an optimization tool.

elib-URL des Eintrags:https://elib.dlr.de/92528/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Thermal Protection-, Aerodynamics- and Control Simulation of an Electromagnetically Launched Projectile
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Lancelle, Danieldaniel.lancelle (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Božić, Dr. Ognjanognjan.bozic (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:2 Juli 2014
Referierte Publikation:Ja
Open Access:Ja
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
DOI:10.1109/EML.2014.6920171
Status:veröffentlicht
Stichwörter:railgun optimization launcher
Veranstaltungstitel:17th Electromagnetic Launch Symposium
Veranstaltungsort:San Diego, USA
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:7 Juli 2014
Veranstaltungsende:11 Juli 2014
Veranstalter :IEEE
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Vorhaben AHRES (alt)
Standort: Braunschweig
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge
Hinterlegt von: Lancelle, Daniel
Hinterlegt am:27 Nov 2014 11:11
Letzte Änderung:24 Apr 2024 19:58

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