Preliminary Design of European Asteroid Mission Architectures

Paper number

IAC-06-A3.5.06

Author

Dr. Kian Yazdi, EADS Astrium Ltd., United Kingdom

Coauthor

Ms. Lisa Peacocke, EADS Astrium Ltd., United Kingdom

Coauthor

Mrs. Marie-Claire Perkinson, EADS Astrium Ltd., United Kingdom

Coauthor

Dr. Paolo D Arrigo, EADS Astrium Ltd., United Kingdom

Year

2006

Abstract

Near Earth Asteroids (NEA) are currently of great interest to space scientists, not only because these small bodies are still rather unknown territory, but also because they can provide invaluable insight into the history and formation of the solar system. Study and knowledge of their properties is also vital for the mitigation of any Earth impact threat. An asteroid mission to a NEA is a strong contender to be part of ESA’s Cosmic Vision programme and is being investigated by industry for a European Space Agency Technology Reference Study. 

Numerous challenges are associated with an asteroid mission and a wide range of possible mission and system conceptual options come into question to address these challenges. The purpose of the activity presented in this paper is to investigate and assess mission alternatives and configuration options to identify the most cost-effective low-risk mission baseline for a given set of scientific objectives, such as sample return of a significant amount of asteroid material, remote sensing of the asteroids internal structure and/or in-situ surface investigations of the asteroids surface and subsurface material. 

A sample return mission using a drill/corer for sample acquisition would offer the highest science return, obtaining not only surface material, but also pristine subsurface material of significant size and depth. However, this implies higher cost and risk due to the complex activities and technologies involved. Simpler mission profiles exist that reduce the resources needed, which in turn could be use to visit and investigate multiple asteroids and include redundancies ensuring mission success. For all scenarios, the mission will incorporate initial remote sensing of the asteroid to characterize the asteroid’s properties, including geometry and topology, in order to select possible landing sites. 

This paper summarizes the results of the major trade-offs performed concerning mission profile, targeted asteroids, propulsion systems, sampling mechanisms, spacecraft configurations and so forth. As a result of a conceptual design process, we present two mission baseline architectures feasible within a stringent financial scope. These baselines offer specific advantages serving different scientific philosophies, focusing either on sample return and Earth-based analysis, or on detailed in-situ investigations. The first baseline is a robust "touch \& go" sample return mission using solar electric propulsion and carrying multiple landers/Earth return vehicles. The second is an extended stay in-situ science mission with one target asteroid.  Details are provided concerning the mission, the system mass, power and payload capabilities. Concept flexibility and possible evolutions are outlined.

Abstract document

IAC-06-A3.5.06.pdf

Manuscript document

IAC-06-A3.5.06.pdf (🔒 authorized access only).

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