Add to ORKGTrajectories for launch vehicles and approximate solution for propagation of covariance matrix of er...
A high fidelity trajectory propagator for use in targeting and reference trajectory generation is de...
Dynamic programming and multistage decision processes in guidance, flight mechanics, and trajectory ...
Trajectories created with n-body orbit models were propagated in geocentric and interplanetary test ...
A mathematically rigorous derivation is given of first order corrections to multi-impulse approximat...
Mathematical models to approximate functions, bounds and power series for three-body problems, satel...
Numerical analysis of error bounds in digital computation of four parameters for strapdown inertial ...
A method developed to compute two-body, optimal, N-impulse trajectories was presented. The necessary...
Impulsive solution used to solve optimum trajectory problems with bounded thrust magnitud
Higher order optimum impulsive solutions to space trajectory problems with off-on thrust magnitude c...
Computer program for trajectory optimization and payload maximization in multistage launch vehicle
Solution to n-body space mechanics problems via numerical integration - ibm 7090 - fortran progra
An analysis was made of the guidance of a space vehicle approaching the earth at supercircular veloc...
Many optimization methods require accurate partial derivative information in order to ensure efficie...
Variational equations for maximum range three-dimensional quasisteady glide are given. Nonlinear osc...
Trajectories for launch vehicles and approximate solution for propagation of covariance matrix of er...
A high fidelity trajectory propagator for use in targeting and reference trajectory generation is de...
Dynamic programming and multistage decision processes in guidance, flight mechanics, and trajectory ...
Trajectories created with n-body orbit models were propagated in geocentric and interplanetary test ...
A mathematically rigorous derivation is given of first order corrections to multi-impulse approximat...
Mathematical models to approximate functions, bounds and power series for three-body problems, satel...
Numerical analysis of error bounds in digital computation of four parameters for strapdown inertial ...
A method developed to compute two-body, optimal, N-impulse trajectories was presented. The necessary...
Impulsive solution used to solve optimum trajectory problems with bounded thrust magnitud
Higher order optimum impulsive solutions to space trajectory problems with off-on thrust magnitude c...
Computer program for trajectory optimization and payload maximization in multistage launch vehicle
Solution to n-body space mechanics problems via numerical integration - ibm 7090 - fortran progra
An analysis was made of the guidance of a space vehicle approaching the earth at supercircular veloc...
Many optimization methods require accurate partial derivative information in order to ensure efficie...
Variational equations for maximum range three-dimensional quasisteady glide are given. Nonlinear osc...
Trajectories for launch vehicles and approximate solution for propagation of covariance matrix of er...
A high fidelity trajectory propagator for use in targeting and reference trajectory generation is de...
Dynamic programming and multistage decision processes in guidance, flight mechanics, and trajectory ...