Optimal guidance for ascent trajectories into circular orbits.
Optimal guidance equations for ascent trajectories into circular orbits, developing feedback guidance loop for real onboard control system
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Optimal guidance equations for ascent trajectories into circular orbits, developing feedback guidance loop for real onboard control system
Optimal control for linear system with respect to performance functional which includes trajectory sensitivity.
Trajectory design and computer programs for planetary mission analysis
Trajectory determination from optical and radar data of spacecraft
Modified quasi-linearization method for numerically solving trajectory optimization problems with undetermined terminal time
Optimization of Atlas-Agena trajectories via steepest ascent computer program
Simultaneous recording of rocket trajectory and rapid auroral variations using high sensitivity image orthicon TV system
Optimum trajectory control for minimum heating paths during manned vehicle reentry at hyperbolic speeds
Powered flight trajectory determination for Saturn V vehicles through computer method
Trajectory modes for manned and unmanned missions to Mercury, 1980-2000
Generalized indirect method solving two-point boundary value problems for rapid optimal trajectory computation
Trajectory optimization, performance and other factors in analysis of low thrust solar electric propulsion Jupiter flyby mission
Lagrange multipliers in two-point boundary condition problems for trajectory optimization estimated by direct method
Sequential trajectory estimation improved by implementing simple running estimates of observation error variances
The RAM C-3 flight experiment was launched to study the problem of radiofrequency blackout at an entry velocity of 24,300 ft/sec. The flight is described, and data for the entry trajectory and environment, which include the effects of actual temperature measured the day of launch, are presented. An analysis of entry spacecraft motions was performed. This analysis included the determination of wind angles from measured accelerations and estimates of wind angles at high altitudes from gyro-measured rotation rates. The maximum wind angles were found to be less than 5 deg to the point of pitch-roll resonance where the total wind angle increased to 8.5 deg and the roll rate started decreasing. A plausible cause for the decrease in roll rate was shown to be a combination of trim angle and an offset center of gravity.
In situ analysis of a cometary nucleus and return of a sample are high priority scientific goals. Rendezvous and sample return trajectories to comets using low-thrust ion propulsion are presented.
The icy moon of Europa is a hot topic in planetary exploration. This paper discusses the trajectory design of a Europa orbiter mission intended to find out if Europa is a possible habitat for extraterrestrial life.
This paper presents a new velocity blending approach to the problem of task space trajectory generation.