A robust algorithm to solve the low-thrust fuel-optimal trajectory optimization problem for interplanetary spacecraft is developed in this article. The original nonlinear optimal control convexified and transformed into a parameter using an arbitrary-order Gauss–Lobatto discretization scheme with interpolation. homotopic approach that considers energy-to-fuel smoothing path combined adaptive se...

Abstract We study the surface of Gauss double points associated to a very general quartic and natural morphisms it.

In this paper, superconvergence points are located for the approximation of the Riesz derivative of order α using classical Lobatto-type polynomials when α ∈ (0, 1) and generalized Jacobi functions (GJF) for arbitrary α > 0, respectively. For the former, superconvergence points are zeros of the Riesz fractional derivative of the leading term in the truncated Legendre-Lobatto expansion. It is ob...

A novel numerical framework is discussed to simulate the time evolution of non-inertial particle size distributions (or number density functions) in flames. The generic form population balance equation considered featuring nucleation, surface growth/loss and agglomeration/coagulation. This first recast a that prone minimize spurious errors simulation collision integrals. Formally, this achieved...

A novel free–energy stable discontinuous Galerkin method is developed for the Cahn–Hilliard equation with non–conforming elements. This work focuses on dynamic polynomial adaptation (p–refinement) and constitutes an extension of by Manzanero et al. (2020) [8], which makes use summation–by–parts simultaneous–approximation term technique along Gauss–Lobatto points Bassi–Rebay 1 (BR1) scheme. The ...

a method for error estimation of isogeometric analysis of plane stress problems which is the based on stress recovery and using the super convergent properties of the gauss points, has been already introduced. this paper is devoted to the development of the method and study of the effects of these supercovergent points on the solution improvement and error estimation of axisymmetric problems by...

Launch vehicle design is a multidisciplinary process involving different disciplines such as aerodynamics, structure, propulsion and trajectory. This latter key discipline in the it used to assess overall performance of by solving an optimal control problem system nonlinear ordinary differential equations. Usual Multidisciplinary Design Optimization methods for launch consider trajectory auxili...