Cassini maneuver experience - Launch and early cruise

Goodson, Troy; Gray, David; Hahn, Yungsun; Peralta, Fernando

doi:10.2514/6.1998-4224

Cited by 17 publications

(13 citation statements)

References 4 publications

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“…Seven large main engine maneuvers were used to estimate and update the proportional MEA error model terms. The new model accounted for several improvements made after these first TCMs to improve future maneuver accuracy [14]. Two flight software corrections, both relating to the accelerometer, were made after TCM-2.…”

Section: A Maneuver Execution Errorsmentioning

confidence: 99%

Cassini In-Flight Navigation Adaptations

Roth

Hahn

Owen

et al. 2018

2018 SpaceOps Conference

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In the nearly two decades of Cassini flight, adaptations to navigation processes were applied as characteristics unique to Cassini were identified and spacecraft configuration changes were implemented. Additionally, operational experience was leveraged into more efficient processes, better modeling, and more robust contingency strategies. Trajectory adjustments were implemented to allow further investigation of surprising science discoveries meriting more attention. Unique analyses were performed to determine how to best accomplish atypical science observations while maintaining acceptable risk levels. Descriptions of the most significant adaptations are organized according to the affected navigation subsystems: trajectory design, orbit determination, optical navigation, and maneuver design.

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Section: A Maneuver Execution Errorsmentioning

confidence: 99%

Cassini In-Flight Navigation Adaptations

Roth

Hahn

Owen

et al. 2018

2018 SpaceOps Conference

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“…Previously written papers describe maneuvers planned and performed during interplanetary cruise and the first three years of the Saturn tour. [5][6][7][8][9][10] The prime tour experiences were utilized for extended tour maneuver planning.…”

Section: Figure 1 Interaction Within Cassini Navigationmentioning

confidence: 99%

Orbit Control Operations for the Cassini-Huygens Mission

Williams

Gist

Goodson

et al. 2008

SpaceOps 2008 Conference

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The Cassini-Huygens spacecraft was launched in 1997 as an international and collaborative mission to study Saturn and its many moons. After a seven-year cruise, Cassini began orbiting Saturn for a four-year tour. This paper gives an overview of the maneuver operations component of Cassini navigation. Specifically, this paper reviews the orbit control and staffing strategies developed and executed as a result of these maneuver experiences. Examples of maneuver processing and analysis are also shown.

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“…VILTs have been implemented in several missions (Farquhar et al 1995;Goodson et al 1998;Kowalkowski et al 2008;McAdams et al 2006) and are the subject of several papers (Hollenbeck 1975;Sims et al 1997;Strange and Sims 2001;Strange et al 2009a;Brinkerhoff and Russell 2009;Campagnola and Russell 2010a,b). The VILT is primarily used to efficiently increase or decrease excess hyperbolic velocity relative to a planet or planetary moon.…”

Section: Introductionmentioning

confidence: 98%

A fast tour design method using non-tangent v-infinity leveraging transfer

Campagnola

Strange

Russell

2010

Celest Mech Dyn Astr

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The announced missions to the Saturn and Jupiter systems renewed the space community interest in simple design methods for gravity assist tours at planetary moons. A key element in such trajectories are the V-Infinity Leveraging Transfers (VILT) which link simple impulsive maneuvers with two consecutive gravity assists at the same moon. VILTs typically include a tangent impulsive maneuver close to an apse location, yielding to a desired change in the excess velocity relative to the moon. In this paper we study the VILT solution space and derive a linear approximation which greatly simplifies the computation of the transfers, and is amenable to broad global searches. Using this approximation, Tisserand graphs, and heuristic optimization procedure we introduce a fast design method for multiple-VILT tours. We use this method to design a trajectory from a highly eccentric orbit around Saturn to a 200-km science orbit at Enceladus. The trajectory is then recomputed removing the linear approximation, showing a v change of <4%. The trajectory is 2.7 years long and comprises 52 gravity assists at Titan, Rhea, Dione, Tethys, and Enceladus, and several deterministic maneuvers. Total v is only 445 m/s, including the Enceladus orbit insertion, almost 10 times better then the 3.9 km/s of the Enceladus orbit insertion from the Titan-Enceladus Hohmann transfer. The new method and demonstrated results enable a new class of missions that tour 123 166 S. Campagnola et al.and ultimately orbit small mass moons. Such missions were previously considered infeasible due to flight time and v constraints.

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Cassini maneuver experience - Launch and early cruise

Abstract: Interplanetary Trajectory Optimization

Cited by 17 publications

References 4 publications

Cassini In-Flight Navigation Adaptations

Cassini In-Flight Navigation Adaptations

Orbit Control Operations for the Cassini-Huygens Mission

A fast tour design method using non-tangent v-infinity leveraging transfer

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