Search Results

In the design process for Life Support Systems (LSS) a great multitude of concepts for and various combinations of subsystems and components exist. In order to find an optimal LSS solution, the parameters for the definition of the optimization must be determined. In the presented paper a new optimization criterion for LSS is suggested. At first the basic equivalent system mass (ESM) approach is discussed. Furthermore the basic ESM optimization concept is modified in order to represent system stability and risk analysis issues. The optimization scheme is completed by adding criteria for overall mission success, which are based on an extensive crew time analysis. All the mentioned parameters are summarized in the so-called integral reliability criterion. After the criterion introduction the paper focuses on the system modeling that is necessary to apply the previously described integral reliability criterion.

The combination of electrical engines with solar arrays, well shielded against radiation long-term LSS, and remote control robot-manipulator system named “Space Rover” is shown to be very promising tool for space exploration. General parameters of space ship based on already developed components, and parameters of flight are considered. Optimal structure of hybrid LSS for middle space range space missions is calculated. As optimization criteria minimum mass and maximum reliability are chosen. Combinations of biological and physical-chemical components are evaluated. It is shown that namely hybrid LSS provide the highest level of reliability and the best mass parameters.