منابع مشابه
Iterative explicit guidance for low thrust spacecraft
A retargeting procedure is developed for use as a nonlinear low thrust guidance scheme. The selection of a control program composed of a sequence of inertially fixed thrust-acceleration vectors permits all trajectory computations to be made with closed form expressions, and allows the controls to be represented by constant parameters, thrust-acceleration vectors and thrusting times. By requirin...
متن کاملThrust - Limited Optimal Three - Dimensional Spacecraft Trajectories
Several optimal three-dimensional orbital transfer problems are solved for thrust-limited spacecrafts using collocation and nonlinear programming techniques. The solutions for full nonlinear equations of motion are obtained where the integrals of the free Keplerian motion in three dimensions are utilized for coasting arcs. In order to limit the solution space, interior-point constraints are use...
متن کاملMulti-Step Optimization Strategy for Fuel-Optimal Orbital Transfer of Low-Thrust Spacecraft
An effective method for the design of fuel-optimal transfers in twoand threebody dynamics is presented. The optimal control problem is formulated using calculus of variation and primer vector theory. This leads to a multi-point boundary value problem (MPBVP), characterized by complex inner constraints and a discontinuous thrust profile. The first issue is addressed by embedding the MPBVP in a p...
متن کاملExplicit Model Predictive Control Approach for Low-Thrust Spacecraft Proximity Operations
The key role of autonomous systems in future space missions has made model predictive control a very attractive guidance and control technique. However, the capability of low-power spacecraft processors to handle the real-time computational load of this technique still needs to be fully established, especially for complex control problems. This paper introduces a method to improve the computati...
متن کاملLow Thrust Cis-lunar Transfers Using a 40 Kw-class Solar Electric Propulsion Spacecraft
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 cannot be characterized in the classi...
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ژورنال
عنوان ژورنال: Journal of the Aerospace Sciences
سال: 1961
ISSN: 1936-9999
DOI: 10.2514/8.9012