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Tour Design Techniques for the Europa Clipper Mission

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Tour Design Techniques for the Europa Clipper Mission 69th International Astronautical Congress, Bremen, Germany. Copyright c 2018 by the authors. All rights reserved. IAC{18{C1.9.11x44026 Tour Design Techniques for the Europa Clipper Mission Stefano Campagnola Jet Propulsion Laboratory, California Institute of Technology, [email protected] Brent B. Buffington, Try Lam, Anastassios E. Petropoulos, Etienne Pellegrini Jet Propulsion Laboratory, California Institute of Technology Europa is one of the most scientifically interesting targets of the solar system, as it may possess the three necessary ingredients for life: an extensive ocean of liquid water, an energy source from tidal heating, and a suite of biogenic elements. To explore the habitability of Europa, NASA is developing the Europa Clipper mission, currently scheduled to be launched in 2022. Europa resides deep inside the gravity well of Jupiter, in a region of the magnetosphere with many trapped ionized particles that get accelerated to near relativistic speeds; a Europa orbiter mission would require a large amount of ∆V for an orbit insertion maneuver, and would only return limited science data before being critically exposed to radiation. To mitigate these issues, Europa Clipper instead only utilizes Europa flybys, connected by Europa-resonant and non-resonant orbits. Science data is collected during high-radiation passes, and returned to Earth during the rest of the Jovian orbits, at a much lower radiation dose exposure. This paper will present several tour tools techniques developed for the design of the Europa Clipper flyby trajectory. In particular, the paper will describe different ways to perform fast line-of-apsides rotations; a new approach to improve the coverage of Europa's trailing and leading edges, with the lighting conditions considerations; parametric studies of the expected radiation dose and time-of-flight as function of the Europa resonance; and a quick way to estimate the radiation dose for Jovian tours. Other techniques, that were already presented in previous papers, will be reviewed for completeness. We then implement some of the new approaches in the 18F17 tour. I. Introduction lysts have developed advanced techniques in simpli- fied models to search for high quality tour options Planetary satellites are some of the most intriguing with high science return and adhere to ground sys- targets for planetary science, as they hold the keys to tem and flight system requirements while mitigating understand the origin of the solar system and often mission risks prior to ultimately converging in a high- possess the potential ingredients for life.1 Satellite fidelity flight software. These techniques helped mis- exploration missions are enabled by complex, wind- sion analyst to design tours for Galileo, Europa Clip- ing trajectories, called satellite or moon tours, that per, Cassini, JUICE, and for several proposed mis- can last years but have characteristic time scales of sions to Neptune, Uranus, among others. Yet more days (the orbit periods of the satellites). Tours use advanced tour design techniques are needed, as space tens of flybys to attain both close-up science obser- missions becomes more complex, building on the suc- vations and to change the spacecraft orbit around cess of Galileo and Cassini. For example, in prepara- the planet. Their design is challenging because of the tion to the Critical Design Review (CDR) in 2019, the large number of flybys (which increases the dimension Europa Clipper project is designing new tours with of the design space while imposing tight encounter more science return, enhanced robustness, but sub- constraints) and because of the many operational and ject to the same requirements levied on the mission environmental requirements. In addition, the space- design from the ground system (i.e., operational ca- craft motion is perturbed by the non-spherical gravity dence types of requirements) and flight system, com- harmonics of the planet, by the gravitational pull of pared to the Preliminary Design Review (PDR) base- multiple satellites acting at the same time, and for line tour 17F12.2 large orbits, by the Sun gravity. The optimization of This will paper present new techniques that en- even a single end-to-end moon tour in a high-fidelity able the design of higher quality tours, specifically, model is a difficult, time-consuming task, and com- including: a quick way to estimate the radiation dose pletely exploring such a chaotic, high-dimensional so- for Jovian tours; parametric studies of the expected lution space is impractical. Instead, mission ana- radiation dose and time-of-flight as function of the IAC{18{C1.9.11x44026 Page 1 of 15 69th International Astronautical Congress, Bremen, Germany. Copyright c 2018 by the authors. All rights reserved. Europa resonance; different ways to perform fast line- Jovian orbit, when the radiation levels are very low of-apsides rotations; and a new approach to improve (Fig. 1). the coverage of Europa's trailing and leading edges, The Europa Clipper architecture is thus enabled with lighting conditions considerations. An example by a tour with more than 40 Europa flybys designed tour, 18F17-beta, is discussed to exhibit the results to attain global-regional coverage under specific solar of utilizing these techniques in order to attain the illumination conditions, relative velocity, and range, desired tour enhancements. which vary depending on the instrument performing the measurements. After a 300-km Ganymede flyby and a large Jupiter insertion maneuver (JOI), all Eu- ropa Clipper tour designs start with a ~200-day cap- ture orbit followed by 5 phases:2, 4, 5 1. The Pump-Down Phase, where Ganymede fly- bys reduce the orbit period and inclination, and target the first Europa flyby with the right ge- ometry and illumination conditions;6 2. The Europa Campaign 1 (EC-1) Phase, where Europa flybys mostly at 2-week cadence pro- vide observations over the lit, anti-Jovian hemi- sphere. The location of EC-1 flybys range from o o LEu ≈ −15 to LEu ≈ 60 , where LEu is the projection of the Sun-Jupiter-Europa angle on Europa's orbit∗; 3. The Transition to Europa Campaign 2 Phase, where the Europa Clipper orbits and the location Fig. 1: Radiation Environment and Overall Mission of the Europa flybys are rotated of 180o; Design Strategy. Representative orbit with a 14.2- day period. Approximately 70% of the orbit is 4. The Europa Campaign 2 (EC-2) Phase, where spent outside the harsh radiation environment Europa flybys provide observation over the lit (~10 days).3 sub-Jovian hemisphere, and over the night-side anti-Jovian hemisphere; II. Background 5. The Disposal Phase, where the spacecraft is de- signed to impact Jupiter. II.i Europa Clipper mission and typical tours Europa resides deep within Jupiter's gravity well, The current baseline tour, 17F12, was the first tour in a region of the magnetosphere with many trapped adopted by the Project that was designed to meet ionized particles that get accelerated to near relativis- (most of) the 300+ constraints levied on trajectory tic speeds, creating a radiation environment that is design by the NASA-selected payload and by the detrimental to unprotected spacecraft electronics; as flight system. For CDR the Mission Design Team such, a Europa orbiter mission would only return lim- is designing new tours, that would maintain the cur- ited science data before being critically exposed to rent quality of 17F12 in terms of science return and radiation and would also require a large amount of mission costs and risks, but could also include with propellant to insert into orbit around Europa. To the following enhancements: mitigate these issues, Europa Clipper Mission will instead execute a high number of Europa flybys in Enhancement 1: ≥ 1 pass over Europa's leading o o o a highly eccentric orbit around Jupiter. The flight point region (within 15 from 0 lat, 270 E system will collect a large volume of science data Long), at < 2000 km altitude, and with local h h at each Europa flyby (where the radiation will be solar time (LST) between 9 and 15 . the strongest), and then quickly escape the intense ∗ More precisely, L(ga) is argument of latitude of the gravity radiation environment near Europa to downlink the assist moon, measured from the projection of the Jupiter-Sun Europa science data to Earth over the remainder of direction on the moon's orbital plane. IAC{18{C1.9.11x44026 Page 2 of 15 69th International Astronautical Congress, Bremen, Germany. Copyright c 2018 by the authors. All rights reserved. Enhancement 2: increase the time-of-flight be- tween between the first and second Europa flyby to ≥ 2 months, for instrument calibration and to test the flight system in the Europa environment; also include some robustness to missed flyby ob- servations. Enhancement 3: a lower flyby cadence to reduce Fig. 2: v1 vector in with the pump α and crank κ an- the operational complexities, if possible. gles, and the body-fixed reference frame of tidally- locked moon on circular orbits. The remainder of this section describes some of the previously developed tour techniques. The subse- quent sections of this paper present a candidate tour that meets these three goals (at varying levels), and the specific techniques developed for its design. Resonant and non-resonant transfers II.ii Standard tour design techniques Tour design techniques are developed in low- Each conic transfer in the tour is determined by fidelity models to allow broad searches of solutions the epoch t and the v1 of the flyby at the begin- in lower-dimensional spaces. The techniques are used ning of the leg (departure) or at the end of the leg to design portions of the tour that serve as an initial (arrival). When the departure and arrival moons are guess for high-fidelity trajectory optimization soft- the same, then the corresponding v1's are also the ware.
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