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Results for “trajectory design”
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Cassini Trajectory Design Description
The Cassini spaecraft will be the first one to visit the Saturnian system in more than two decades after the unprecedented flybys of the Voyager spacecraft in 1980 and 1981.
Cassini Trajectory Design Description
The Cassini mission to Saturn will start a second phase in the exploration of the Saturnian system
Europa Lander trajectory design: case studies for the direct-to-earth architecture
This paper presents interesting phasing problems that came up in support of design studies for a potential Europa Lander mission. Recent system trades were performed after the Mission Concept Review in fall 2017, when the NASA board recommended the Europa Lander project design a Direct-to-Earth architecture, i.e. where the Lander would communicate directly to the Earth, without data relay from the carrier vehicle.
Improvements to the Flight Analysis and Simulation Tool (FAST) and Initial Development of the Genesis Flight Mechanics Simulation for Ascent, Aerocapture, Entry, Descent, and Landing (A2EDL) Trajectory Design
The NASA Engineering and Safety Center (NESC) was requested to provide significant enhancements to the Flight Analysis and Simulation Tool (FAST), a generic, variable-degree-of-freedom, multi-body ascent, aerocapture, entry, descent, and landing (A2EDL) flight simulation code and a key Agency analysis tool. This report details the upgrades to FAST that were completed, describes a change to the assessment’s scope that allowed its goals to be exceeded with a new and innovative approach, and discusses the results of the modified approach.
James Webb Space Telescope Trajectory Design Overview
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Neptune Odyssey Mission and Entry Descent Trajectory Design
Neptune is a prime destination for future exploration missions. This study designed the mission concept including the Flagship-class orbiter and atmospheric probe to the Neptune-Triton system. The results of this study will be used as the Decadal Survey considers on NASA’s planetary science priorities from 2022-2032.This poster will focus on the design of the entry and descent sequence for the atmospheric probe.
Trajectory Design for a Spacecraft Capable of Deploying Probes to the Martian Surface en Route to Low Mars Orbit
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Uranus Probe Entry and Descent Trajectory Design
Uranus has been recently selected as the priority destination for a future Flagship-class mission. The present study designed a mission concept including an orbiter and an atmospheric probe to Uranus. Specific concerns explored by this study included meeting structural requirements under high deceleration loads, designing a Thermal Protection System (TPS) to withstand the high heat fluxes for Uranus entry, and ensuring communication availability for science data up-link between the probe and the orbiter. The results of the study were used to support the 2023-2032 Planetary Science and Astrobiology Decadal Survey.
Trajectory Design Considerations for Low Lunar Orbit to Near Rectilinear Halo Orbit Transfers
NASA’s Artemis program plans to use a Near-Rectilinear Halo Orbit (NRHO) to stage assets for a lunar exploration campaign. While the proximity operations in the NRHO are simple and very similar to flat-space dynamics, the far-field ren-dezvous has considerations that are non-intuitive, especially to those that may be steeped in the dynamics of rendezvous in Keplerian orbits. This paper will discuss some key drivers to the delta-V performance of far-field rendezvous from Low Lunar Orbit to the Gateway space station in its 9:2 resonant south-ward NRHO.
Trajectory Design Considerations for Lunar Surface to Near Rectilinear Halo Orbit Rendezvous
NASA’s Artemis program plans to use a 9:2 resonant southward Near-Rectilinear Halo Orbit (NRHO) at the Earth-Moon’s L2 libration point to stage assets for a sustained lunar exploration campaign. This architecture includes the use of the Gateway space station positioned in this orbit. While the proximity operations in the NRHO are similar to field-free space dynamics, the far-field rendezvous aspect of the problem is more complicated. We analyze the key drivers of the ΔV performance of the far-field rendezvous problem from low lunar orbit to the Gateway. We find that lunar latitudinal libration is a driving factor to ΔV performance for surface ascent missions that rendezvous with the NRHO, and that transfer time from low lunar orbit to NRHO affects more aspects of the geometry and performance than expected from rendezvous in Keplerian orbits.
Robust Solar Sail Trajectory Design under Uncertainty with Application to NEA Scout Mission
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