Powered Descent Guidance via First-Order Optimization with Expansive Projection

TL;DR

This paper presents a novel first-order optimization method using expansive projection for powered descent guidance, effectively handling nonconvex constraints and improving trajectory feasibility and fuel efficiency over traditional convexification techniques.

Contribution

Introduces an expansive projection-based first-order method for PDG that directly manages nonconvex constraints, overcoming limitations of lossless convexification and linear approximation.

Findings

Produces feasible trajectories even with nonoptimal flight times

Reduces fuel consumption compared to conventional methods

Enhances flexibility in planetary soft landing scenarios

Abstract

This paper introduces a first-order method for solving optimal powered descent guidance (PDG) problems, that directly handles the nonconvex constraints associated with the maximum and minimum thrust bounds with varying mass and the pointing angle constraints on thrust vectors. This issue has been conventionally circumvented via lossless convexification (LCvx), which lifts a nonconvex feasible set to a higher-dimensional convex set, and via linear approximation of another nonconvex feasible set defined by exponential functions. However, this approach sometimes results in an infeasible solution when the solution obtained from the higher-dimensional space is projected back to the original space, especially when the problem involves a nonoptimal time of flight. Additionally, the Taylor series approximation introduces an approximation error that grows with both flight time and deviation from the reference trajectory. In this paper, we introduce a first-order approach that makes use of orthogonal projections onto nonconvex sets, allowing expansive projection (ExProj). We show that 1) this approach produces a feasible solution with better performance even for the nonoptimal time of flight cases for which conventional techniques fail to generate achievable trajectories and 2) the proposed method compensates for the linearization error that arises from Taylor series approximation, thus generating a superior guidance solution with less fuel consumption. We provide numerical examples featuring quantitative assessments to elucidate the effectiveness of the proposed methodology, particularly in terms of fuel consumption and flight time. Our analysis substantiates the assertion that the proposed approach affords enhanced flexibility in devising viable trajectories for a diverse array of planetary soft landing scenarios.