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

Lancelle, Daniel and 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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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.

Item URL in elib:https://elib.dlr.de/92528/
Document Type:Conference or Workshop Item (Speech)
Title:Thermal Protection-, Aerodynamics- and Control Simulation of an Electromagnetically Launched Projectile
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Date:2 July 2014
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:railgun optimization launcher
Event Title:17th Electromagnetic Launch Symposium
Event Location:San Diego, USA
Event Type:international Conference
Event Start Date:7 July 2014
Event End Date:11 July 2014
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 - Vorhaben AHRES (old)
Location: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Lancelle, Daniel
Deposited On:27 Nov 2014 11:11
Last Modified:24 Apr 2024 19:58

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