Project Galileo: The Jupiter Mission
Project Galileo is ecstatic to report that as of December 7, 1995, there are seventeen known satellites of Jupiter--the seventeenth being the first artificial satellite--the Galileo Orbiter!
Galileo↗
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Project Galileo: completing Europa, preparing for Io
Galileo has completed the Europa leg of the Galileo Europa Mission, and is now pumping down the apojove in each succeeding orbit in preparation for the Io phase. Including three encounters earlier in the primary mission, the total of ten close passes by Europa have provided a wealth of interesting and provocative information about this intriguing body. The results presented include new and exciting information about Europa's interactions with Jupiter's magnetosphere, its interior structure, and its tantalizing surface features, which strongly hint at a watery subsurface layer. Additional data concerning Callisto, and its own outlook for a subsurface ocean are also presented. In addition the engineering aspects of operating the spacecraft during the past year are explored, as well as a brief examination of what will be the challenges to prepare for the Io encounters. The steadily increasing radiation dosage that the spacecraft is experiencing is well beyond the original design parameters, and is contributing to a number of spacecraft problems and concerns. The ability of the flight team to analyze and solve these problems, even at the reduced staffing levels of an extended mission, is a testament to their tenacity and loyalty to the mission. The engineering data being generated by these continuing radiation-induced anomalies will prove invaluable to designers of future spacecraft to Jupiter and its satellites. The lessons learned during this arduous process are presented. c 2000 International Astronautical Federation. Published by Elsevier Science Ltd. All rights reserved.
long duration↗
Constrained maneuver strategies for Project Galileo
The design of maneuvers for Project Galileo is constrained by thruster configuration, modes of thruster usage and limitations required for the safety of the spacecraft and its instruments. The methods used to analyze maneuvers with respect to these constraints is described. The velocity changes necessary for the implementation of a candidate trajectory have been studied and some general conclusions are described.
Stanford, R. H.↗
Project Galileo mission design
The mission design for Project Galileo is described. Details are presented on the design of the trajectory from launch through completion of the satellite tour, with emphasis on how this design is influenced both by science requirements on the mission and by the interaction of this design with the various elements of the Project. A number of features contribute to the uniqueness of the mission design for this Project. Among the more salient of these that are described in this paper are the use of numerous planetary or satellite encounters for gravity assisted trajectory shaping, and closely related to this, the threading of a trajectory through the Galilean satellite system which meets the mission objectives with a minimum of propulsive trajectory corrections.
Mitchell, R. T.↗
Interplanetary trajectory options for project Galileo
The paper explores interplanetary trajectory options for project Galileo. The classes of trajectory options studied include direct earth-Jupiter trajectories for combined and split orbiter/probe missions, Mars powered swingbys, earth-Venus-earth gravity assists, and earth-deep space delta V-earth gravity assists.
Nock, K. T.↗
'Dogleg' maneuvers for Project Galileo
This paper describes the analysis and design of 'dog-leg' maneuvers for the spin-stabilized spacecraft of Project Galileo. These maneuvers involve a turn from one attitude to a firing attitude and then, following the motor burn, a turn to a new attitude. In general, the three attitudes (initial, firing and final) are noncoplanar. A computer program has been developed to find the firing attitude for the optimum conservation of propellant, while attaining a desired velocity change for the spacecraft. Results for several cases are presented.
Stanford, Richard H.↗
Attitude and articulation control system testing for Project Galileo
A type of facility required to integrate and test a complex autonomous spacecraft subsystem is presented, using the attitude and articulation control subsystem (AACS) of Project Galileo as an example. The equipment created for testing the AACS at both the subsystem and spacecraft system levels is described, including a description of the support equipment (SE) architecture in its two main configurations, closed loop simulation techniques, the user interface to the SE, and plans for the use of the facility beyond the test period. This system is capable of providing a flight-like functional environment through the use of accurate real-time models and carefully chosen points of interaction, and flexible control capability and high visibility to the test operator.
Rasmussen, R. D.↗
Project Galileo or The Little Spacecraft That Could
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Project Galileo Spacecraft journey↗
Spin-Down and Active Nutation Controller /SDANC/ for the Galileo project
The Spin-Down and Active Nutation Controller stabilizes the Galileo spacecraft during spin-down from approximately 70 to 1 rpm. Angular motion of the spacecraft is sensed through a pair of accelerometers and a sun sensor which is needed only at low spin rates. Spin and nutation information is derived by a set of 'loosely coupled' spin and transverse rate estimators. Spin rate is reduced by two spin-down thrusters. The transverse angular rate is compared with a variable threshold; exceeding the threshold activates axial thrusters which impart appropriate transverse torque to reduce the nutation. The scheme was verified by extensive computer simulations and has been demonstrated over a wide range of initial conditions.
Lin, H. S.↗
Attitude and articulation control solutions for Project Galileo
Design problems and the solutions adopted for them in the attitude and articulation control subsystem for the Galileo spacecraft are discussed as an illustration of the application of dual-spin control to an interplanetary spacecraft. Following a review of the baseline design of the Galileo system and mission, consideration is given to problems encountered in the areas of autonomous attitude determination, attitude control, spacecraft dynamics and software margins. Design issues raised by subsequent changes in spacecraft configuration are also indicated. It is pointed out that although difficulties associated with control system complexity in a dual-spin interplanetary spacecraft have been satisfactorily resolved for the Galileo mission, the future application of dual spin in interplanetary flight is in doubt.
Rasmussen, R. D.↗
Return to Jupiter - Project Galileo
The mission profile, instrumentation, and mission objectives of the Galileo probe are described. Scheduled for Shuttle launch in 1986, with a boost from the Centaur upper stage, the probe will require over 2 yr to reach the Jovian system. An atmospheric entry probe will be released during Jupiter approach, and the orbiting module will relay the temperature, pressure, radio signals, spectroscopy, magnetometry, and particle counts, originating from the parachuting probe. The orbiting module will then continue on to a series of flybys and orbits around the Jovian moons by using a gravity assist from Jupiter after each pass of a moon. The orbiter will record spectrometric, radiometric, dust, visual, magnetic, and radio propagation data. The television camera is a CCD device with 640,000 diodes forming an 800 x 800 array in one square centimeter.
Johnson, T. V.↗
Single event upset immune integrated circuits for Project Galileo
Tests showed that bipolar chips in the attitude control computer of the Galileo spacecraft would likely cause catastrophic mission failure due to single particle upset. This paper describes the design and testing of CMOS replacements which are speed compatible with the bipolar parts and are immune to upset by 165-MeV krypton ions.
Giddings, A. E.↗
Project Galileo
Galileo is now enroute to Jupiter to do its intensive and comprehensive investigation of the Jupiter System. The Galileo Spacecraft consists of a Jupiter Orbiter and an Atmospheric Entry Probe. The Galileo mission at Jupiter is described. The design and operation of the Probe and Orbiter are discussed in some detail. The history of the many Shuttle upper stage changes Galileo experienced during development is outlined. The VEEGA trajectory Galileo is flying to achieve enough energy to reach Jupiter is explained. Science of opportunity on the circuitous VEEGA route is identified. Galileo Mission Operations are described. The paper concludes with an inflight mission status statement.
O'Neil, William J.↗
Project Galileo: final mission status
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Galileo Jupiter Europa flyby↗
Project Galileo: final mission status
A summary of spacecraft performance in the harsh jovian environment and a report of final subsystem and instrument status are provided.
Galileo Jupiter↗