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Reverse Engineering of Athena II Launcher

Dumont, Etienne and Johannsson, Magni (2012) Reverse Engineering of Athena II Launcher. DLR-Interner Bericht. SART TN-016/2012. Deutsches Zentrum für Luft- und Raumfahrt. 12 S. (Unpublished)

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This report gives details about the model of the Athena II launch vehicle that was created with the goal to use it in the frame of the AtILa study. The small and medium payload launch vehicle Athena II is analyzed with respect to its performance, mass, launch trajectory and orbit characteristics. The motor efficiencies of the first and second stage Castor 120 motor are calculated and compared to available public data. In addition, the third stage thrust and chamber pressure histories are also reverse engineered. A simplified mass estimation is then performed for each stage. Lastly, utilizing the calculated mass breakdown and performance characteristics, a trajectory and orbit analysis is conducted assuming a circular sun-synchronous orbit at 687 km (corresponding to the particular mission studied in the frame of the AtILa study). The results show that the vehicle is capable of launching 1198 kg of payload to this orbit, a difference of 4 % compared to value from available literature and where part of the discrepancy can be attributed to some inaccuracy and discrepancies in the published data. The analysis conclusively proves that the available data for the Athena II launch vehicle are indeed accurate and the reverse engineering process is successful. The calculated trajectory is also considered as representative of the real flight and is aimed to be used for the AtILa project.

Item URL in elib:https://elib.dlr.de/81078/
Document Type:Monograph (DLR-Interner Bericht)
Title:Reverse Engineering of Athena II Launcher
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Dumont, EtienneUNSPECIFIEDhttps://orcid.org/0000-0003-4618-0572UNSPECIFIED
Date:July 2012
Refereed publication:No
Open Access:No
Number of Pages:12
Keywords:Athena II, Castor 120, Orbus 21, reverse engineering, solid rocket propulsion, trajectory, mass breakdown, thrust law, AtILa
Institution:Deutsches Zentrum für Luft- und Raumfahrt
Department:Systemanalyse Raumtransport
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 - Raumfahrzeugsysteme - Systemanalyse Raumtransport (old)
Location: Bremen
Institutes and Institutions:Institute of Space Systems > Space Launcher Systems Analysis
Deposited By: Johannsson, Magni
Deposited On:14 Feb 2013 10:49
Last Modified:27 Oct 2016 09:27

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