Cesar A. Ocampo

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We give numerical calculations of periodic orbits in the planar concentric restricted four-body problem. It is assumed that the motion of a massless body is governed by three primaries m1, m2 and m3. We suppose that m1 >> m2,m3 and that, in an m1 centered inertial reference frame, m2 and m3 move in different circles about m1 and m1 is fixed. Although the(More)
The modeling, design, and optimization of finite burn maneuvers for a generalized trajectory design and optimization system is presented. A generalized trajectory design and optimization system is a system that uses a single unified framework that facilitates the modeling and optimization of complex spacecraft trajectories that may operate in complex(More)
The fundamental methods are described for the general spacecraft trajectory design and optimization software system called Copernicus. The methods rely on a unified framework that is used to model, design, and optimize spacecraft trajectories that may operate in complex gravitational force fields, use multiple propulsion systems, and involve multiple(More)
The calculus of variations is used to develop the necessary theory and derive the optimality conditions for a spacecraft to transfer between a set of initial and final conditions, while minimizing a combination of fuel consumption and a function of the estimation error covariance matrix associated with the spacecraft state. The theory is developed in a(More)
On May 13, 1998, the Hughes Global Services 1 Spacecraft (HGS-1, originally known as AsiaSat 3) became the first commercial spacecraft to fly by the Moon on a trajectory to reposition it into a useful geosynchronous orbit. This was necessary due to the failure of the last stage of the launch vehicle that left it in a high inclination, eccentric, and(More)
A particular periodic orbit in the Earth-Sun circular restricted three body problem is shown to have the characteristics needed for a ballistic lunar capture transfer. An injection from a circular parking orbit into the periodic orbit serves as an initial guess for a targeting algorithm. By targeting appropriate parameters incrementally in increasingly(More)
This paper captures trajectory analysis of a representative low thrust, high power Solar Electric Propulsion (SEP) vehicle to move a mass around cislunar space in the range of 20 to 40 kW power to the Electric Propulsion (EP) system. These cislunar transfers depart from a selected Near Rectilinear Halo Orbit (NRHO) and target other cislunar orbits. The NRHO(More)