Add to ORKGProgram determines if rendezvous in near space is possible, and performs an analysis to determine the approximate required values of the magnitude and direction of two thrust applications of the upper stage of a rocket firing. The analysis is performed by using ordinary Keplerian mechanics
Computational method for time optimal space rendezvous between rocket vehicle and circular orbit tar...
Closed-form solutions are presented for a two-burn orbit insertion, AOA, and ATO maneuver targets, a...
A the core of any autonomous rendezvous guidance system must be two algorithms for solving Lambert's...
Computational method for two impulse orbital transfer and rendezvous between two elliptical orbit
Flight scheduling in planar two burn minimum fuel rendezvous of interceptor with target vehicle
An investigation of a two-impulse plan for performing rendezvous on a once-a-day basis with a near-e...
Simplified and accurate relative equations of motion for two impulse orbital rendezvou
A FORTRAN computer program was developed which automatically targets two and three burn rendezvous m...
Collision and pursuit course closure maneuvers were studied for correcting position and velocity err...
Computer program has been designed to handle computations for low thrust missions rapidly and with a...
Minimum fuel rendezvous guidance of powered interceptor from parking orbit to target in coplanar cir...
Space trajectories Program studies the motion of a space probe confined to the solar system and infl...
A digital-computer simulation was made of the midcourse or ascent phase of a rendezvous between a fe...
Program computes turns required to point given spacecraft-fixed vector in direction of given inertia...
A digital-computer simulation was made of the midcourse (or ascent) phase of a rendezvous between a ...
Computational method for time optimal space rendezvous between rocket vehicle and circular orbit tar...
Closed-form solutions are presented for a two-burn orbit insertion, AOA, and ATO maneuver targets, a...
A the core of any autonomous rendezvous guidance system must be two algorithms for solving Lambert's...
Computational method for two impulse orbital transfer and rendezvous between two elliptical orbit
Flight scheduling in planar two burn minimum fuel rendezvous of interceptor with target vehicle
An investigation of a two-impulse plan for performing rendezvous on a once-a-day basis with a near-e...
Simplified and accurate relative equations of motion for two impulse orbital rendezvou
A FORTRAN computer program was developed which automatically targets two and three burn rendezvous m...
Collision and pursuit course closure maneuvers were studied for correcting position and velocity err...
Computer program has been designed to handle computations for low thrust missions rapidly and with a...
Minimum fuel rendezvous guidance of powered interceptor from parking orbit to target in coplanar cir...
Space trajectories Program studies the motion of a space probe confined to the solar system and infl...
A digital-computer simulation was made of the midcourse or ascent phase of a rendezvous between a fe...
Program computes turns required to point given spacecraft-fixed vector in direction of given inertia...
A digital-computer simulation was made of the midcourse (or ascent) phase of a rendezvous between a ...
Computational method for time optimal space rendezvous between rocket vehicle and circular orbit tar...
Closed-form solutions are presented for a two-burn orbit insertion, AOA, and ATO maneuver targets, a...
A the core of any autonomous rendezvous guidance system must be two algorithms for solving Lambert's...