MLA Airborne Micro-Launcher a Candidate For Aldebaran

Paper number

IAC-08.D2.4.9

Author

Mr. Michel Rigault, Dassault Aviation, France

Coauthor

Mr. André Beaurain, Snecma, France

Coauthor

Mr. Didier Boury, Snecma Propulsion Solide, France

Coauthor

Mr. Philippe Cloutet, SNPE Materiaux Energetiques, France

Coauthor

Mrs. Laurence Guénot, SNPE Materiaux Energetiques, France

Coauthor

Mr. Talbot Christophe, CNES, France

Coauthor

Mr. François Lemainque, Dassault Aviation, France

Coauthor

Mrs. Aude Copey, France

Coauthor

Mr. Michel ILLIG, CNES, France

Coauthor

Mr. Christophe Bonnal, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mr. Laurent Gathier, Dassault Aviation, France

Year

2008

Abstract

The operational and financial benefits of airborne launches led Dassault Aviation to conduct in the early 1990's the Eclat and Milan studies on a micro-launcher, borne by a Mirage IV, which weighed approximately four tons and was able to place 50 to 70 kilos at an altitude of 300 kilometers. The performance benefit of such a high energy platform was then evaluated, compared to the use of a subsonic aircraft, as e.g. by the Pegasus, which is  still today the only operational airborne launch system.

Since the end of 2004, this design has been revisited with the Rafale multirole fighter in the context of a CNES contract on the Airborne Micro-Launcher (MLA) project. This has involved pursuing prior studies, using a high performance, available aircraft, and drawing benefit from new technologies, in particular, electronic miniaturization.

An initial single body launcher (a storable solid propellant stage and a storable liquid propellant stage) was considered for linear installation under the central store station of the fuselage. This version allowed for 50 kilos to be placed in low earth orbit for an initial analysis, which is a remarkable feat for an airplane of a size significantly smaller than that of the Mirage IV.

Nevertheless this solution was not using the full loading capacity of the aircraft, and larger satellites (e.g. Myriade-class satellites) weighting about 150 kg were looking for an affordable launch mean, more flexible than the auxiliary payload adapter available on large launcher like Ariane 5. An innovative three body configuration was therefore proposed, with the central linear body being completed by two lateral high  energy solid propellant boosters, linked by arms not interfering with the volume needed for the landing gear deployment.

This study covers many critical aspects of the launcher (propulsion, structure, aerodynamics, avionics, GNC, separation phases, integration to the aircraft) with the participation of Snecma for the storable propellant third stage and SPS and SNPE Matériaux Energétiques for the solid rocket motors.

This 10-ton class launcher can be used in a wide variety of missions.  Its operational use can be simplified in comparison to traditional launchers, with a simple ground infrastructure for the integration. Its performance could be improved even further with  new propulsion technologies.

Abstract document

IAC-08.D2.4.9.pdf

Manuscript document

IAC-08.D2.4.9.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.