Interior-Point Approach to Trajectory Optimization

Tsourdos

IEEE Trans. Aerosp. Electron. Syst.

et al. 2018

This paper focuses on the application of model predictive control (MPC) for the spacecraft trajectory tracking problems. The motivation of the use of MPC, also known as receding horizon control, relies on its ability in dealing with control, state and path constraints that naturally arise in practical trajectory planning problems. Two different MPC schemes are constructed to solve the reconnaissance trajectory tracking problem. Since the MPC solves the online optimal control problems at each sampling instant, the computational cost associated with it can be high. In order to decrease the computational demand due to the optimization process, a newly proposed two-nested gradient method is used and embedded in the two MPC schemes. Simulation results are provided to illustrate the effectiveness and feasibility of the two MPC tracking algorithms combined with the improved optimization technique.

Section: Optimization Algorithmmentioning

confidence: 99%

Optimal Tracking Guidance for Aeroassisted Spacecraft Reconnaissance Mission Based on Receding Horizon Control

Tsourdos

IEEE Trans. Aerosp. Electron. Syst.

et al. 2018

Optim Control Appl Methods

“…Moreover, we consider the state constraint on the thermal flux, also considered in 1–4: with . (A different value is considered in 4.…”

Section: Model Of Atmospheric Reentrymentioning

confidence: 99%

“…The optimal control of the atmospheric reentry of a space shuttle is a challenging optimal control problem. It has been studied by many authors and solved using either direct methods (nonlinear programming), see 1–3 or indirect methods (multiple shooting), see 4–6. Shooting methods are based on the resolution of a two‐ (or multi‐)point boundary value problem, and favoured when a high precision is required to compute a reliable optimal trajectory.…”

Section: Introductionmentioning

confidence: 99%

Optimal control of the atmospheric reentry of a space shuttle by an homotopy method

Hermant

2010

Journal of Guidance, Control, and Dynamics

“…Different interior point methods have been proposed for the solution of the NLP problem. Forsgren and Gill [13] proposed an interior point method based on primal dual theory, and Laurent-Varin et al [14] applied a logarithmic penalty method to the atmospheric reentry problem using an indirect shooting approach for the optimal control solution.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Low-Thrust Reconfiguration Maneuvers for Spacecraft Flying in Formation

Massari

Bernelli‐Zazzera

2009

In this work, the problem of optimization of low-thrust reconfiguration maneuvers for spacecraft flying in formation is addressed. The problem is stated as the solution of an optimal control problem in which an objective function related to controls is minimized, satisfying a series of constraints on the trajectory that are both differential and algebraic. The problem has been faced by transcribing the differential constraints into a nonlinear programming problem with a parallel multiple-shooting method. The resulting problem has been solved with an interior point\ud method. The method that has been developed is particularly suited for the solution of problems in which the trajectory is constrained with a great number of inequalities on both states and controls. The method has been applied to the design of reconfiguration maneuvers for spacecraft flying in formation, for which the collision avoidance issue leads to the imposition of a large number of inequalities on states derived from the minimum distance constraint