Spacecraft design optimisation for demise and survivability

TL;DR

This paper develops models and a multi-objective genetic algorithm to optimize spacecraft design for both demise and survivability, balancing material, geometry, and component placement to meet safety and mission requirements.

Contribution

It introduces a novel multi-objective optimization framework using genetic algorithms for the preliminary design of spacecraft considering demise and survivability trade-offs.

Findings

Identified Pareto optimal solutions balancing demise and survivability.

Demonstrated the effectiveness of genetic algorithms in nonlinear, mixed-variable optimization.

Provided insights into design choices affecting spacecraft safety and mission success.

Abstract

Among the mitigation measures introduced to cope with the space debris issue there is the de-orbiting of decommissioned satellites. Guidelines for re-entering objects call for a ground casualty risk no higher than 0.0001. To comply with this requirement, satellites can be designed through a design-for-demise philosophy. Still, a spacecraft designed to demise has to survive the debris-populated space environment for many years. The demisability and the survivability of a satellite can both be influenced by a set of common design choices such as the material selection, the geometry definition, and the position of the components. Within this context, two models have been developed to analyse the demise and the survivability of satellites. Given the competing nature of the demisability and the survivability, a multi-objective optimisation framework was developed, with the aim to identify trade-off solutions for the preliminary design of satellites. As the problem is nonlinear and involves the combination of continuous and discrete variables, classical derivative based approaches are unsuited and a genetic algorithm was selected instead. The genetic algorithm uses the developed demisability and survivability criteria as the fitness functions of the multi-objective algorithm. The paper presents a test case, which considers the preliminary optimisation of tanks in terms of material, geometry, location, and number of tanks for a representative Earth observation mission. The configuration of the external structure of the spacecraft is fixed. Tanks were selected because they are sensitive to both design requirements: they represent critical components in the demise process and impact damage can cause the loss of the mission because of leaking and ruptures. The results present the possible trade off solutions, constituting the Pareto front obtained from the multi-objective optimisation.