Cassini-Huygens Engineering Operations at Saturn

Standley, Shaun

doi:10.2514/6.2006-5516

Cited by 10 publications

(4 citation statements)

References 3 publications

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“…The Huygens Recovery Task Force (HRTF), a joint NASA/ESA team, was convened in 2001 to analyze the anomaly and propose corrective actions. The task force recommended redesigning Cassini's trajectory to reduce the Doppler shift on the probe signal [10]. Unfortunately, a software fix to the probe support avionics was not possible due to the firmware used in the receiver.…”

Section: Huygens Probe Receiver Anomalymentioning

confidence: 99%

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Twenty years of systems engineering on the Cassini-Huygens Mission

Manor-Chapman

2013

2013 IEEE Aerospace Conference

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Over the past twenty years, the Cassini-Huygens Mission has successfully utilized systems engineering to develop and execute a challenging prime mission and two mission extensions. Systems engineering was not only essential in designing the mission, but as knowledge of the system was gained during cruise and science operations, it was critical in evolving operational strategies and processes. This paper discusses systems engineering successes, challenges, and lessons learned on the Cassini-Huygens Mission gathered from a thorough study of mission plans and developed scenarios, and interviews with key project leaders across its twenty-year history.

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Section: Huygens Probe Receiver Anomalymentioning

confidence: 99%

“…The purpose of HIT was to ensure a coordinated implementation of the Huygens mission. HIT performed systems engineering and mission analysis tasks for the redesigned mission [10].…”

Section: Huygens Probe Receiver Anomalymentioning

confidence: 99%

Twenty years of systems engineering on the Cassini-Huygens Mission

Manor-Chapman

2013

2013 IEEE Aerospace Conference

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“…Goodson et al [28], Standley [29], and Wagner et al [30] describe the engineering operations and maneuver experience during the mission. The Cassini primary mission ended in July 2008 [11], with an extended mission planned until June 2010 [12].…”

Section: Background Of the Cassini-huygens Missionmentioning

confidence: 99%

Saturn Impact Trajectories for Cassini End-of-Mission

Yam

Davis

Longuski

et al. 2009

Journal of Spacecraft and Rockets

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Potential end-of-mission scenarios to be considered for the Cassini spacecraft must satisfy planetary quarantine requirements designed to prevent contamination of a pristine environment, which could include Titan and the other Saturnian moons. One assumed acceptable option for safe disposal of the spacecraft includes Saturn impact trajectories. Two classes of impact trajectories are investigated: short-period orbits characterized by periods of 6-10 days and long-period orbits with periods greater than 850 days. To impact Saturn with short-period orbits, a series of successive Titan flybys is required to increase inclination and decrease periapsis to within Saturn's atmosphere, while simultaneously avoiding the rings and mitigating V expenditures. To ensure that the spacecraft is not prematurely damaged by material in the rings, Tisserand graphs are employed to determine when the ring-plane crossing distance is within the F-G ring gap: the necessary geometry for the penultimate transfer. For long-period impact trajectories, solar gravity is exploited to significantly lower periapsis. Depending on the size and orientation of the long-period orbit, a maneuver (<50 m=s) at apoapsis must be added to ensure impact. For sufficiently large orbits with favorable characteristics, solar gravity alone drops the spacecraft's periapsis into Saturn's atmosphere. No maneuver is necessary after the final Titan flyby, providing an attractive "flyby-and-forget" option. Nomenclature a = semimajor axis, km or R S e = eccentricity h = specific angular momentum, km 2 =s h p = flyby altitude, km i rel = inclination relative to the gravity-assist body's orbit, deg J 2 = Saturn's oblateness coefficient m = number of gravity-assist body orbits about the central body n = number of spacecraft orbits about the central body p = semilatus rectum, km or R S R S = Saturn's radius, km (R S 60; 268 km) R T = Titan's radius, km (R T 2575 km) r = position vector from the central body, km or R S r = radial distance from center of Saturn to spacecraft, km or R S r a = radius of apoapsis from central body, km or R S r enc = radial distance of encounter from central body, km or R S r p = radius of periapsis from central body, km or R S r vac = radial distance of vacant node from central body, km or R S T = orbital period, day V = velocity vector relative to the central body, km=s V 1 = hyperbolic excess velocity vector, km=s v = velocity magnitude relative to the central body, km=s v 1 = hyperbolic excess velocity magnitude, km=s = pump angle, deg = flight-path angle, deg V = change in velocity magnitude, km=s = flyby bending angle, deg = flyby B-plane angle, deg = crank angle, deg = gravitational parameter, km 3 =s 2 = orientation of the spacecraft orbit relative to the sunSaturn line, deg Subscripts ga = quantity for the gravity-assist body sc = quantity for the spacecraft

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“…The 8 paneled sponge provided control of propellant for center of gravity purposes, and to keep propellant near the tank outlet, even under unfavorable conditions such as attitude control. [76][77][78][79][80][81][82][83][84]. It has since provided surface and atmospheric data of numerous other bodies within the Saturn system.…”

Section: Vehicles and Missionsmentioning

confidence: 99%

A Detailed Historical Review of Propellant Management Devices for Low Gravity Propellant Acquisition

Hartwig

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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This paper presents a comprehensive background and historical review of Propellant Management Devices (PMDs) used throughout spaceflight history. The purpose of a PMD is to separate liquid and gas phases within a propellant tank and to transfer vapor-free propellant from a storage tank to a transfer line en route to either an engine or receiver depot tank, in any gravitational or thermal environment. The design concept, basic flow physics, and principle of operation are presented for each type of PMD. The three primary capillary driven PMD types of vanes, sponges, and screen channel liquid acquisition devices are compared and contrasted. For each PMD type, a detailed review of previous applications using storable propellants is given, which include space experiments as well as space missions and vehicles. Examples of previous cryogenic propellant management are also presented.

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Cassini-Huygens Engineering Operations at Saturn

Cited by 10 publications

References 3 publications

Twenty years of systems engineering on the Cassini-Huygens Mission

Twenty years of systems engineering on the Cassini-Huygens Mission

Saturn Impact Trajectories for Cassini End-of-Mission

A Detailed Historical Review of Propellant Management Devices for Low Gravity Propellant Acquisition

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