Engineering topics
Publications and source records attributed to Tapley, B. D..
Regularized equations for a particular optimal trajectory are compared with unregularized equations with respect to computational characteristics, using perturbation type numerical optimization. In the case of the three dimensional, low thrust, Earth-Jupiter rendezvous, the regularized equations yield a significant reduction in computer time.
Fuel suboptimal attitude control of spin stabilized axisymmetric spacecraft
Numerical integration for continuously thrusting spacecraft optimal trajectory, considering rectangular Cartesian and polar cylindrical coordinates characteristics
Trajectory optimization of space vehicle with continuous thrust based on regularized equations, comparing perturbation method for earth-Jupiter rendezvous transfer
Short term motion of lunar satellite, discussing third body disturbing functions and perturbation solution of nonsingular orbit elements
Canonical transformation and Hamilton-Jacobi theories applied to space vehicle trajectory analysis, discussing elliptical coast arc and optimal low thrust problems
Apollo type reentry trajectory optimization numerical methods
Trajectory optimization of space vehicle with continuous thrust based on regularized equations, comparing perturbation method for earth-Jupiter rendezvous transfer
Short term motion of lunar satellite, discussing third body disturbing functions and perturbation solution of nonsingular orbit elements
Spacecraft libration point motion in restricted four body model including earth-moon orbit plane inclination to ecliptic, noting solar effects
Numerical method solution of nonlinear two point boundary value problem associated with optimum transfer of spacecraft
Spacecraft optimum low thrust trajectory analyzed by Hamilton-Jacobi perturbation theory, obtaining canonic constants of motion
Determining sign of second variation in optimal control theory
Numerical optimization methods compared for nonlinear two point boundary value problem associated with optimum spacecraft trajectory
Convergence acceleration procedure for steepest descent method for trajectory optimization
Numerical method solution of nonlinear two- point boundary value problem associated with optimum transfer of spacecraft
Motion of near lunar satellite in initially circular orbit analyzed by integrating equations for time rates of change of orbit elements
Error correcting problem in space trajectory of continuous powered space vehicle, discussing optimal terminal guidance