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Earth to Mars - Scenarios for early manned missions
Trajectories and mission types for a manned mission to Mars are reviewed, focusing on what can be undertaken relative to available technologies. The objectives of a manned mission are outlined and several mission scenarios are described. Space Station involvement, an interplanetary manned Mars space vehicle, and the role of artificial gravity are discussed. Possible launch vehicles, surface systems options, and space vehicle configurations are examined.
TRAJECTORY DESIGN FOR RANGER AND MARINER MISSIONS
Trajectory optimization for lunar and inter- planetary missions - ranger project
Interplanetary trajectory selection criteria for Voyager Mars missions.
Trajectory design criteria for Voyager Mars missions toward standardization of launch vehicle, shroud, spacecraft bus, capsule and propulsion systems
Mission and trajectory design for a Venus radar mapper mission
Results are presented for a mission and trajectory design for a Venus Radar Mapper mission that will place a SAR in a nearly polar orbit around Venus. The mission is intended to obtain images of at least 70% of the planet's surface at a line-pair resolution of 1 km and to produce global maps of the planet's topography and gravity field. The mission design criteria are discussed, along with the spacecraft flight system, the mission performance and domains, a mission profile, the mapping orbit and SAR coverage, and the data acquisition strategy.
TRAJECTORY CONSIDERATIONS FOR THE RETURN TO EARTH PHASE OF LUNAR MISSIONS
Trajectories for return to earth phase of lunar missions
Guidance, flight mechanics and trajectory optimization. Volume 16 - Mission constraints and trajectory interfaces
Mission constraints and trajectory interfaces for launch, rendezvous, spatial, deorbit, and entry phases of earth orbital mission
A general method for selection and optimization of trajectories.
Space mission trajectory optimization by iterative minimizing of residual vector, using linear correction
A general method for selection and optimization of trajectories.
Space mission trajectory optimization by iterative minimizing of residual vector, using linear correction
TRAJECTORY CONSIDERATIONS FOR THE RETURN TO EARTH PHASE OF LUNAR MISSIONS
Trajectory requirements for lunar injection and earth reentry conditions are considered in the return-to-earth phase of lunar missions
Trajectory analysis and optimization of a low- thrust solar electric Jupiter flyby mission.
Trajectory optimization, performance and other factors in analysis of low thrust solar electric propulsion Jupiter flyby mission
A trajectory aiming plane to assist in satellite orbit selection for planetary reconnaissance missions
Trajectory aiming plane in optimum satellite orbit selection for planetary flyby and orbiter missions
Comparison of trajectory profiles and nuclear-propulsion-module arrangements for manned Mars and Mars-Venus missions
Trajectory profiles and nuclear propulsion vehicle configurations for manned Mars and Mars-Venus missions
To encounter a star - The Solar Probe mission
Trajectory and technology requirements for the Solar Probe mission, whereby a spacecraft will attain a perihelion of a few solar radii, are discussed. Planetary gravity assist trajectories are considered that use Jupiter and possibly the earth, and that are needed for large payloads to be carried. Hardware technology development includes a lightweight thermal shield, a high energy propulsion module, and new power generation capability. Also discussed are a drag compensation system making the spacecraft drag free to a level of 10 to the -10th g, and a telecommunications system with doppler tracking accuracy of 0.1 mm/sec.
Apollo mission 11, trajectory reconstruction and postflight analysis, volume 1
Apollo mission 11 trajectory reconstruction and postflight analysis
Mission and trajectory design for the Venus orbiting imaging radar
Results of mission and trajectory design for the Venus Orbiting Imaging Radar are presented. Because of the application of the aerobraking technique, for the first time to a planetary mission, the conventional mission design criteria in the selection of the launch/arrival dates must be modified and new mission constraints must be imposed. Venus itself poses an interesting aspect in trajectory design for an orbiting spacecraft due to its dense lower atmosphere and its slow retrograde rotation. Some recent results in the method of averaging applied to an orbiting spacecraft about this unique planet are given.
End-to-End Mission Design & Trajectory Optimization
The ability to compute end-to-end mission optimized trajectories is a critical component needed for the next generation of complex human spaceflight design and operations (Orion, HLS, Gateway, Mars). This project created a new interface for two of NASA’s trajectory tools: Copernicus and Genesis, enabling them to be used together for end-to-end mission design and optimization of all flight phases, including Earth ascent, lunar ascent, rendezvous, and lunar descent. This capability can also serve as a pathfinder for developing a future autonomous, onboard trajectory optimizer.
End-to-End Mission Design & Trajectory Optimization
The ability to compute end-to-end mission optimized trajectories is a critical component needed for the next generation of complex human spaceflight design and operations (Orion, HLS, Gateway, Mars). This project created a new interface for two of NASA’s trajectory tools: Copernicus and Genesis, enabling them to be used together for end-to-end mission design and optimization of all flight phases, including Earth ascent, lunar ascent, rendezvous, and lunar descent. This capability can also serve as a pathfinder for developing a future autonomous, onboard trajectory optimizer.