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This paper presents a novel method to generate robust optimal trajectories for spacecraft equipped with low-thrust propulsion under the effect of epistemic uncertainty. The uncertainties considered for this paper derive from a lack of knowledge on system’s and launcher’s parameters. This is a typical situation in the early stage of the design process when multiple options need to be evaluated and only a partial knowledge of each of them is available. Uncertainties are modelled with probability boxes, or p-boxes, embodying multiple families of distributions. Once the effect of uncertainty is propagated through the system one can calculate the Upper and Lower Expectations on the quantity of interest (for example the mass of propellant). The Lower Expectation defines the worst case effect of the uncertainty when uncertainty is expressed via a p-box. We also propose a method for its calculation, which requires solving an optimization problem. Once the low expectations on the quantities of interest are available, a novel efficient computational scheme is proposed to compute families of control laws that are robust against the effect of uncertainty. Robustness is here considered to be the ability to maximise the desired performance, under uncertainty, with a high probability of satisfying the constraints. The computational scheme proposed in this paper makes use of surrogate models of the Lower Expectations, to radically reduce the computational cost of the robust optimisation problem. This is combined with a dimensionality reduction technique, that allows one to construct surrogate models on low dimensional spaces, and an iterative refinement of the surrogate representation. The training points of the surrogate models are evaluated using FABLE (Fast Analytical Boundary value Low-thrust Estimator), an analytical tool for the fast design and optimisation of low-thrust trajectories. A memetic multi-objective optimisation algorithm, MACS (Multi Agent Collaborative Search), is then used to find the set of Pareto optimal control laws that maximise the Lower Expectation in the achievement of the desired values of objective function and constraints. The proposed approach is then applied to the design of a rendezvous mission to Apophis with a small spacecraft equipped with a low thrust engine.
|Number of pages||13|
|Publication status||Published - 25 Oct 2019|
|Event||70th International Astronautical Congress - Washington D.C., United States|
Duration: 21 Oct 2019 → 25 Oct 2019
|Conference||70th International Astronautical Congress|
|Period||21/10/19 → 25/10/19|
- epistemic uncertainty
- resilient satellite
- robust optimization
- lower expectation
- multi-objective optimization
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