Surrogate-based parameter optimization and optimal control for optimal trajectory of Halo orbit rendezvous

Reduced cost mission design using surrogate models

“…Surrogate models have a rich history in design and analysis for a variety of aerospace disciplines, including structural design (Barthelemy and Haftka, 1993), rocket engine component design (Farmer et al, 2000;Papila et al, 2002;Vaidyanathan et al, 2000), cavitating flows (Goel et al, (Glaz et al, 2009), and missile performance (Riddle et al, 2009). More recently, surrogate modeling has been applied to the field of astrodynamics, including interplanetary transfers and satellite constellation design (Gano et al, 2006), low thrust trajectory optimization (Peng et al, 2013), low thrust controls (Ghosh and Conway, 2013), and orbit uncertainty propagation . This section provides the necessary background on surrogate models and the model development process for application to the problem of spacecraft rendezvous in the CRTBP.…”

“…For these systems, no explicit solution exists for the acceleration acting on a spacecraft, and trajectory design and optimization methods traditionally rely on iterative integration of a system of ordinary differential equations (ODEs). Much recent effort has been focused on developing improved techniques for low thrust trajectory optimization in such systems (see Peng et al (2011Peng et al ( , 2013; ; , among others). However, some missions -particularly crewed missions -require the use of high thrust spacecraft; the current concept of operations for the Asteroid Redirect Mission (ARM), for example, calls for the rendezvous of the crewed Orion spacecraft with the Asteroid Redirect Vehicle (ARV) using impulsive maneuvers (Hinkel et al, 2014).…”

Linear and nonlinear control strategies for formation and station keeping of spacecrafts within the context of the three body problem

“…Wang et al [28] developed an eigenstructure assignment control for formation keeping around the liberation point. Peng et al [21] have further investigated a surrogate based parameter optimization approach for optimal rendezvous trajectory design in the Sun-Earth system. More recently, in 2014 Folta et al [6] studied the problem of Halo orbit station keeping using optimal control strategy and also performed the stability analysis of the problem.…”

Relative Orbit Stabilization Control for the Agile Satellite under Stochastic Disturbance

“…The research of relative motion control is focusing on the two aspects, namely, relative orbit control and relative attitude control. Some methods are proposed for relative orbit control, such as optimal control for the orbit rendezvous [3] and predictive control for the rendezvous maneuver [4]. The relative control methods include the centralized and decentralized approach [5].…”