A Multicriteria Optimisation Design of SPSE for Adaptive LEO Satellites Missions Using the PSI Method

Ekpo, Sunday C ORCID: https://orcid.org/0000-0001-9219-3759, George, Danielle and Adebisi, Bamidele ORCID: https://orcid.org/0000-0001-9071-9120 (2013) A Multicriteria Optimisation Design of SPSE for Adaptive LEO Satellites Missions Using the PSI Method. In: AIAA SPACE 2013 Conference and Exposition, 10 September 2013 - 13 September 2013, San Diego, California.

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Abstract

The spacecraft power system engineering (SPSE) analysis for the radiation-prone space environment is a major critical satellite engineering definition for realising successful mission and post-mission capabilities. The dynamic operations and post-mission applications of capability-based small satellites require an adaptive architecture(s) which exhibits an enormous conceptual system engineering design task in terms of the trade space – which can be too large to explore, study, analyse and qualify – for a reliable and sustainable mission. This paper involves a multicriteria optimisation design of the SPSE subsystems for adaptive LEO satellites missions using the parameter space investigation (PSI) method. A three-axis stabilised 10-kg nanosatellite is considered for a meteorological spacecraft (METSAT) mission at 800 km altitude. The initial case study SE parameters considered include the required payload power and spacecraft power and mass contingencies. The PSI method allows for a large-scale multicriteria optimisation of dynamic engineering systems. This was implemented in the multicriteria optimisation and vector investigation (MOVI) software. Specific power profiles for LEO satellites were used for the mathematical modelling of the highly adaptive nanosatellite (HAN) system in LEO. In the multicriteria optimisation process, 2765 design vectors entered the test table out of which 2762 formed the feasible solutions set. The PSI was conservatively designed to yield 10 pareto optimal solutions; a pareto optimal solution of 12.36 W for the payload subsystem yielded HAN mass and power margins of 1.84 kg and 2.37 W respectively. From the analysis, the solar array capability was found to deliver 24.23 W for the mission; this forms the beginning-of-life design point. The actual on-orbit mass of the HAN system (with enhanced capabilities including post-mission reuse) was found to be 9.2 kg as opposed to a conventional 10-kg nanosat implementation. The findings serve to eliminate undue space-borne equipment oversizing and advance the state-of-the-art in the conceptual design of future-generations spacecraft at the subsystem and system levels. Adaptive space systems promise to enable capability-based, dynamic, cost-effective, reliable, multifunctional, multipurpose and optimal-performing space systems with recourse to post-mission re-applications. Furthermore, the PSI-MO results show that HASS architectures can be extended to implement higher satellite generation missions with economies of scale.