Interplanetary mission design techniques for flagship-class missions

Kevin W Kloster, Purdue University

Abstract

Trajectory design, given the current level of propulsive technology, requires knowledge of orbital mechanics, computational resources, extensive use of tools such as gravity-assist and V ∞ leveraging, as well as insight and finesse. Designing missions that deliver a capable science package to a celestial body of interest that are robust and affordable is a difficult task. Techniques are presented here that assist the mission designer in constructing trajectories for flagship-class missions in the outer Solar System. These techniques are applied in this work to spacecraft that are currently in flight or in the planning stages. By escaping the Saturnian system, the Cassini spacecraft can reach other destinations in the Solar System while satisfying planetary quarantine. The patched-conic method was used to search for trajectories that depart Saturn via gravity assist at Titan. Trajectories were found that fly by Jupiter to reach Uranus or Neptune, capture at Jupiter or Neptune, escape the Solar System, fly by Uranus during its 2049 equinox, or encounter Centaurs. A "grand tour," which visits Jupiter, Uranus, and Neptune, departs Saturn in 2014. New tools were built to search for encounters with Centaurs, small Solar System bodies between the orbits of Jupiter and Neptune, and to minimize the ΔV to target these encounters. Cassini could reach Chiron, the first-discovered Centaur, in 10.5 years after a 2022 Saturn departure. For a Europa Orbiter mission, the strategy for designing Jovian System tours that include Io flybys differs significantly from schemes developed for previous versions of the mission. Assuming that the closest approach distance of the incoming hyperbola at Jupiter is below the orbit of Io, then an Io gravity assist gives the greatest energy pump-down for the least decrease in perijove radius. Using Io to help capture the spacecraft can increase the savings in Jupiter orbit insertion ΔV over a Ganymede-aided capture. The tour design is guided by Tisserand graphs overlaid with a simple and accurate radiation model so that tours including Io flybys can maintain an acceptable radiation dosage. While Io flybys increase the duration of tours that are ultimately bound for Europa, they offer ΔV savings and greater scientific return, including the possibility of flying through the plume of one of Io's volcanoes. Different combinations of interplanetary trajectories and are considered with a focus on options that could enable flagship-class missions to Uranus. A patched-conic method is used to identify trajectories to Uranus with launch dates between 2015 and 2050. Flight time is constrained to be less than 14 years. A graphical technique is introduced to identify the most efficient launch opportunities and gravity-assist paths to Uranus. Several trajectories emerge as attractive options including classical paths such as Venus-Earth-Earth-Jupiter, with launch V1 as low as 3.6 km/s. A baseline ΔV cost is established for capture at Uranus via chemical propulsion. Ballistic reduction of orbital inclination using flybys of the satellites of Uranus is investigated; Oberon is shown to have greater inclination change capability than Titania despite Oberon being less massive.

Degree

Ph.D.

Advisors

Longuski, Purdue University.

Subject Area

Aerospace engineering

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