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.

In the paper problems which seems to be significant and unavoidable for CELSS practical application are considered: 1) the problem of selection of appropriate CELSS composition, which is highly important for concentrating efforts and finance on the most promising version of CELSS; 2) the problem of comprehensive testing of CELSS and evaluating its reliability which is obligatory necessary for real applications; 3) the problem of reproducing and comparing different experimental data from different CELSS. Possible ways of solving this problems are considered.

Needs in LSS depend on the degree of human participation in space flight. On the other hand the decision of human participation in long-term space missions depends on ability to provide safety of crew. As a mission type which can provide satisfactory safety “Space Rover” mission can be considered “Space Rover” is a fully reusable space ship with ionic thrust and solar panels or nuclear reactor as power source. It contains highly autonomous (closed), reliable and comfortable LSS (including both higher plants and some back-up system). Planet exploration and exploitation are conducted with robots which are controlled via radio waves without time delay In the paper arguments pros and cons of “Space Rover” and traditionally discussed mission scenarios are considered.

Of the possible Life Support Systems evaluation criteria, the criterion of "integral reliability" is proposed. This criterion incorporates three main indices: reliability, mass, and quality of life. It is possible to interrelate these indices only if the space mission is considered as a whole. It is shown that there must exist a LSS mass optimum with respect to mission reliability. The specific form of "integral reliability" expression and the number of terms depend on the mission scenario. This work considers different LSS for orbital station, Lunar base, and Mars mission scenarios.

Different versions of lunar base Biological LSS (BLSS) are optimized, compared and discussed in terms of two criteria: well known criterion of minimal accumulated mass and the criterion of integral reliability which takes into account LSS reliability, LSS mass, the quality of human life, some aspects of lunar base servicing. In the paper different types of BLSS for lunar base are considered: LSS with hydrogen-oxidizing bacteria; LSS with micro-algae; LSS with higher plants. The influence of different power source usage on optimal BLSS structure is also investigated. The parameters of lunar base BLSS based on present level of closure technology are calculated.

To investigate LSS an EXCEL Spreadsheet is designed. The spreadsheet consists of data on two different LSS types: biological and physico-chemical. Biological LSS include those based on hydrogen-oxidizing bacteria, microalgae, higher plants, higher plants and mushrooms, and higher plants with physical/chemical incineration of wastes. Simulations using this spreadsheet, showed that LSS with higher plants realize different structure of LSS (ratio of biological species, their mass, etc.) with different operation time. Thus, the system with higher plants has been found to have three different structures if incineration is used and six structures in opposite case. In the case of a vegetarian diet, 100% closure can be obtained.