Layout Optimization of Microsatellite Components Using Genetic Algorithm

• Published in: Telkomnika Vol. 15; no. 1; p. 341
• Main Authors: Mukhayadi, Mohammad, Hermadi, Irman, Hardhienata, Soewarto
• Format: Journal Article
• Language: English
• Published: Yogyakarta Ahmad Dahlan University 01.03.2017
• Subjects: Complexity; Earth observations (from space); Genetic algorithms; Launch vehicles; Layouts; Microsatellites; Nutation; Optimization; Payloads; Polynomials; Rectangles; Satellite attitude control; Satellite observation; Spacecraft attitude control; Spin stabilization
• ISSN: 1693-6930; 2302-9293
• DOI: 10.12928/telkomnika.v15i1.3872

Abstract Placing the components into a container that is normally known as layout optimization problem belongs to NP-hard problems in terms of computational complexity. (ProQuest: ... denotes formulae omitted.) 1.Introduction The problem in making a layout solution is commonly known as a layout optimization problem (LOP), which leads to the non-deterministic polynomial-time hard (NP-hard) in term of computational complexity. [...]the research question is how to produce the optimal layout of satellite components that match the requirements of mission payloads, launcher and spacecraft attitude control. A satellite component generally has dimensions of length, width and height so it is easier to be represented as cuboid in three-dimensional space or rectangle in two-dimensional space. [...]this study uses rectangles in two-dimensional space to simplify a very broad space solution. To obtain a realistic result, the scope of the study is as the following: (1) The satellite carries out earth observation mission using cameras; (2) The satellite controls its attitude by spin stabilization; (3) The satellite is categorized as a microsatellite class with a maximum dimension of 600mm x 700mm x 800mm so it can make use of the auxiliary payload allocation of the launch vehicle [11]. Since the satellite uses spin stabilization, the spin axis and the major axis of satellite should coincide so the nutation or oscillation effects can be minimized [12]. The layout will take the result from the exploration of more possibilities in the space of solutions. [...]this research contribution will reduce the dependency of the satellite layout from the...