Search Results

An advanced ECLSS for long duration manned space missions - such as planetary flight missions or planetary bases - requires an almost complete closure of all relevant material loops. The current state of ESA development in the oxygen reclamation system does, however, not correspond to this requirement, because of considerable losses of hydrogen due to the production of methane in the Sabatier reactor. Concerning the recovery of hydrogen from methane, experimental and theoretical work on methane pyrolysis has been performed meanwhile. Different pyrolysis reactor concepts have been investigated. This paper will present the results of the experimental and theoretical investigations in addition to a preliminary design of a breadboard model for a methane pyrolysis system to close the hydrogen loop on the basis of a three-persons crewed space vehicle.

Presently, Europe is faced with the task of implementing the Columbus Space Program. In a stepwise approach the Columbus Initial Orbital Configuration will involve eventually into a European (permanently) Manned Space Infrastructure. Towards this goal, various technological challenges arise for the Environmental Control and Life Support System (ECLSS). Some of these have already been identified and are subject of initial investigations. To regain oxygen from the metabolic process, a physico-chemical chain of CO2-concentration, CO2-cracking and water electrolysis is under development. The present status of the preliminary breadboarding, composed of a steam desorbed solid amine concentrator and a Sabatier reactor will be discussed. The third item in this chain, the electrolyser, is not yet implemented in this breadboarding but is under test, demonstrating the technology for regenerative fuel cell application.

Environmental control and life support, ultimately tied to the presence of man in space is one of the key issues of the permanently manned space station initiated by the USA [1], [2].* Europe's participation in that programme is the COLUMBUS programme, the various elements and scenarios of which were subject of extensive studies [3], [4], [5]. This paper is devoted to the Environmental Control and Life Support Subsystem (ECLSS) of the Pressurized Module (PM), the latter being one of the COLUMBUS elements. The present COLUMBUS scenario for the PM comprises the PM either to be attached to the US Space Station (USSS), being one of the core elements of the USSS (integrated PM) or as a Man Tended Free Flyer (MTFF, a PM docked to the Resource Module, RM). The PM in the attached configuration is shown in Fig. 1. The present considerations center on the ECLSS of the PM in attached version which is taken as baseline.