Structural Analysis of ESA Young Engineers Satellite 2 Ejection System

Paper number

IAC-05-C2.P.06

Author

Mr. Antonios Vavouliotis, University of Patras, Greece

Coauthor

Mr. Dimitrios Lamprou, University of Patras, Greece

Coauthor

Prof. Vassilis Kostopoulos, University of Patras, Greece

Coauthor

Mr. Jens Carlevi, Luleå Technical University, Sweden

Coauthor

Mr. Erik Van der Heide, Delta-Utec SRC, The Netherlands

Coauthor

Prof. Carlo Menon, Simon Fraser University, Canada

Year

2005

Abstract

Air launch is a potentially interesting technique for future launch systems of small satellites, as its main advantages compared to a ground launch are a potential weight reduction for the rocket part of the system and easier launch operations. Since 2005, Cnes and Onera have been investigating the potential of Unmanned-Aerial Vehicles (UAV) for air launch, through the DEDALUS studies (Design of Dual-use Air Launch UAV Systems).
This paper gives an overview of DEDALUS works, Cnes/Onera vision for future UAV-based solutions for future air launch systems and lessons learned. Different solutions are considered in the 10-150 kg range for payload in LEO. One of these solutions, which has been studied since the phase I of DEDALUS is an innovative concept based on a multirole UAV, optimized for both the air launch mission in LEO (150 kg payload launched in a 800 km polar orbit) and two other missions: a freighter mission (long range cargo transport) and a surveillance mission (endurance mission with carrying of an equipment pod at high altitude).The idea in this concept is to make the air-launch system more economically viable than solutions consisting in the design of a dedicated one-purpose carrier, or the adaptation of existing aircraft.
Phase I works have demonstrated the technical feasibility of the concept with satisfying performance for the launch mission as well as the other missions. Results have been obtained through a MDO approach (Multidisciplinary Design Optimization) coupling UAV design and launcher design, which have been improved in phase II.
Besides this concept of heavy (21 t gross take-off weight), multirole UAV, other solutions have been considered for smaller payloads, down to 10 kg in a 250 km polar LEO, which is the reference mission for Cnes’s PERSEUS student initiative focused on nanolauncher technologies and innovation. Results give an overview of the potential of UAV for small satellite air-launch systems, and insight about key issues such as jettison strategies and possible near-term solution including the adaptation of an existing UAV.

Abstract document

IAC-05-C2.P.06.pdf

Manuscript document

IAC-05-C2.P.06.pdf (🔒 authorized access only).

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