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NASA NTRS1996

Overview of the Galileo Probe Mission to Jupiter

The Galileo Probe entered the atmosphere of Jupiter on December 7, 1995, for the first time directly sampling the atmosphere of one of the outer planets. The entry was the most difficult ever attempted in terms of heat and deceleration loads. The probe and all scientific instruments functioned successfully, and returned data on composition, clouds, thermal structure, winds, energy balance, lightning, and inner radiation belts. A probe mission overview is presented, highlighting the key mission events and major science objectives. The purpose of the overview is to set the stage for the following papers which describe findings from the probe scientific investigations and discuss implications of the probe results.

Young, Richard E.↗

NASA NTRS2005

Project Prometheus and Future Entry Probe Missions

A viewgraph presentation on project Prometheus and future entry probe missions is shown. The topics include: 1) What Is Project Prometheus?; 2) What Capabilities Can Project Prometheus Offer? What Mission Types Are Being Considered?; 3) Jupiter Icy Moons Orbiter (JIMO); 4) How Are Mission Opportunities Changing?; 5) Missions Of Interest a Year Ago; 6) Missions Now Being Considered For Further Study; 7) Galileo-Style (Conventional) Probe Delivery; 8) Galileo-Style Probe Support; 9) Conventional Delivery and Support of Multiple Probes; 10) How Entry Probe Delivery From an NEP Vehicle Is Different; and 11) Concluding Remarks.

Spilker, Thomas R.↗

NASA NTRS2003

Science Rationale for Jupiter Entry Probe as Part of JIMO

A Jupiter atmospheric entry probe as part of JIMO is a cost effective way to address fundamental science questions identified in the National Research Council Solar System Exploration Decadal Survey (SSEDS): New Frontiers in the Solar System, An Integrated Ex- ploration Strategy. Compared to either the cost of an entirely separate Jupiter mission, or the cost of JIMO itself, inclusion of such a probe on JIMO would be cost advantageous. The probe itself could be relatively simple, and could build on the Galileo Probe heritage. The SSEDS specifically identified the distribution of water across the Solar System as a Key Scientific Question. Correspondingly, knowing the water abun dance on Jupiter is fundamental to understanding almost every aspect of the evolution of the early solar nebula. The Galileo Probe obtained the abundance of several key elements in Jupiter's atmosphere, which data have already caused major rethinking of theories of how Jupiter formed and how the early solar nebula evolved. However, because of a combination of circumstances, the global abundance of the key element oxygen, in the form of water, was not obtained. Without knowledge of the jovian water abundance, further progress in understanding Solar System evolution and planet formation will be greatly inhibited. Therefore, quantifying jovian water abundance should be a goal of the very next mission to the jovian system. Such a measurement would be impossible via remote sensing from the JIMO orbiter because of the large distances the JIMO orbiter maintains from Jupiter. A Jupiter atmospheric entry probe as part of JIMO could achieve the fundamental water measurement. In order that a probe avoid repeating the Galileo probe's experience of failing to obtain the jovian water abundance, the probe should go deep, to at least 100 bars pressure. Probes to 100 bars have been accomplished many times in descending to the surface of Venus, and at 100 bars the temperature of the jovian atmosphere is 60-70 K less than the surface temperature of Venus.

Young, R. E.↗

NASA NTRS1981

Survey of the supporting research and technology for the thermal protection of the Galileo Probe

The Galileo Probe, which is scheduled to be launched in 1985 and to enter the hydrogen-helium atmosphere of Jupiter up to 1,475 days later, presents thermal protection problems that are far more difficult than those experienced in previous planetary entry missions. The high entry speed of the Probe will cause forebody heating rates orders of magnitude greater than those encountered in the Apollo and Pioneer Venus missions, severe afterbody heating from base-flow radiation, and thermochemical ablation rates for carbon phenolic that rival the free-stream mass flux. This paper presents a comprehensive survey of the experimental work and computational research that provide technological support for the Probe's heat-shield design effort. The survey includes atmospheric modeling; both approximate and first-principle computations of flow fields and heat-shield material response; base heating; turbulence modelling; new computational techniques; experimental heating and materials studies; code validation efforts; and a set of 'consensus' first-principle flow-field solutions through the entry maneuver, with predictions of the corresponding thermal protection requirements.

Howe, J. T.↗

NASA NTRS1978

Effects of atmospheric structure on radiative heating for Jupiter entry probe

New estimates of the radiative heat load to a Jupiter entry probe have been obtained for revised models of Jupiter's atmosphere based on the latest data from Pioneer 10 and 11 missions and earth-based experiments. The new estimates of the radiative heat load are compared with results obtained for the previous atmospheric models. The changes in Jupiter's atmospheric models cause a substantial reduction in the radiative heat load for the atmosphere denoted as 'cool', but only moderate reductions for the atmospheres denoted as 'nominal' and 'warm'. Results are also presented showing the effects of inertial entry angle for off-equatorial entries in the revised model atmospheres.

Sutton, K.↗

NASA NTRS1981

Trends in unmanned planetary entry systems

Entry systems used in unmanned planetary exploration are discussed in terms of future missions and more complex demands made upon the design configurations of orbiters and atmospheric space probes. The presently on-going Galileo project involving a Jupiter orbiter and a probe of the Jovian atmosphere is mentioned, and the difficult entry requirements at a velocity of 48 km/sec and an angle of minus seven to minus 10 degrees into an atmosphere composed largely of hydrogen, are described. Re-entry parameters determined by the respective entry environment, type of entry approach (hyperbolic or elliptical orbit) entry velocity, and guidance technology are given attention. Aerobraking, involving relatively slow circularization of an initial elliptical orbit by repeated passes through the atmosphere, is investigated. Aerocapture, by which vehicles using controlled flight paths through the atmosphere, can go directly from a hyperbolic flyby trajectory to low circular orbit is described. Major attractions of aerobraking and aerocapture are analyzed in terms of modest technology needs and relatively small impact on spacecraft design.

French, J. R.↗

NASA NTRS1983

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.↗

NASA NTRS1982

The Galileo Delta-VEGA mission to Jupiter

Project Galileo is to perform a more comprehensive investigation of the Jupiter system than was possible with Voyager. The Galileo spacecraft consists of both a planetary Orbiter and an atmospheric entry Probe. In connection with budgetary considerations and schedule problems, plans concerning the implementation of the project were changed a number of times. For the first seven months of 1982, the project Galileo was baselined as a Delta-VEGA transfer to be launched in 1985 by the Space Shuttle using the U.S. Air Force two-stage IUS as the upper stage augmented by a spacecraft Injection Module. The new mission and systems aspects of this 1985 Galileo Delta-VEGA baseline are compared to the prior 1985 Centaur direct transfer baseline. The techniques developed to virtually restore all the mission science in spite of greatly reduced launch vehicle performance are discussed. In July 1982, the U.S. Government reinstated the Centaur development and stipulated that Galileo be launched by Shuttle/Centaur in 1986.

Oneil, W. J.↗

NASA NTRS1974

Advanced planning activity

Selected mission concepts for interplanetary exploration through 1985 were examined, including: (1) Jupiter orbiter performance characteristics; (2) solar electric propulsion missions to Mercury, Venus, Neptune, and Uranus; (3) space shuttle planetary missions; (4) Pioneer entry probes to Saturn and Uranus; (5) rendezvous with Comet Kohoutek and Comet Encke; (6) space tug capabilities; and (7) a Pioneer mission to Mars in 1979. Mission options, limitations, and performance predictions are assessed, along with probable configurational, boost, and propulsion requirements.

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NASA NTRS1979

Flow-field analyses for future planetary entry

Scientific exploration of the planets by means of instrumented probes and landers provides a means of enhancing our knowledge concerning the solar system. A prime requirement for a successful planetary entry mission is that the design of a vehicle be based on a reliable definition of the aerothermal environment encountered during entry. This paper briefly reviews some of the past developments and current examples of computational flow-field analyses for predicting the aerothermal environment of planetary probes. All of the flow-field solutions presented are for a very severe aerothermal entry environment, representative of the entry environment that the Galileo probe will encounter when it enters Jupiter's atmosphere in 1985. Finally, areas for analysis improvements and extensions are identified for current and future planetary missions.

Moss, J. N.↗

NASA NTRS1996

Overview of the Galileo Probe Mission to Jupiter

Young, R. E.↗

NASA NTRS1989

Galileo Probe: Spacecraft Mission to Jupiter Press Release

This video is a compilation of three short videos related to the Galileo mission. The first section shows animation of the descent of the Galileo probe into the atmosphere of Jupiter. It includes cutaway views of the atmosphere showing the different layers. This descent will represent the first entry into the atmosphere of an outer planet in our solar system. A second section shows some live shots of the development and drop chute tests of the Galileo spacecraft. A third section is an animation that shows the Probe mission. It shows visualizations from the launch, including the Venus flyby, the separation of the probe and the orbiter, and the trajectory of the planetary arrival. It also shows the descent of the probe into the atmosphere.

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NASA NTRS1972

Outer planet entry probe system study. Volume 2: Supporting technical studies

The environment, science investigations, and general mission analysis considerations are given first. These data are followed by discussions of the studies pertaining to the planets Jupiter, Saturn, Uranus, and Neptune. Except for Neptune, each planet discussion is divided into two parts: (1) parametric activities and (2) probe definition for that planet, or the application of a given probe for that planet. The Neptune discussion is limited to parametrics in the area of science and mission analysis. Each of the probe system definitions consists of system and subsystem details including telecommunications, data handling, power pyrotechnics, attitude control, structures, propulsion, thermal control, and probe to spacecraft integration. The first configuration is discussed in detail and the subsequent configuration discussions are limited to the differences. Finally, the hardware availability to support a probe system and commonality of science, missions, and subsystems for use at the various planets are considered.

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NASA NTRS2006

Mitigating Extreme Environments for In-Situ Jupiter and Venus Missions

In response to the recommendations by the National Research Council (NRC), NASA's Solar System Exploration (SSE) Roadmap identified the in situ exploration of Venus and Jupiter as high priority science objectives. For Jupiter, deep entry probes are recommended, which would descend to approx.250 km - measured from the 1 bar pressure depth. At this level the pressure would correspond to approx.100 bar and the temperature would reach approx.500(deg)C. Similarly, at the surface of Venus the temperature and pressure conditions are approx.460(deg)C and approx.90 bar. Lifetime of the Jupiter probes during descent can be measured in hours, while in{situ operations at and near the surface of Venus are envisioned over weeks or months. In this paper we discuss technologies, which share commonalities in mitigating these extreme conditions over proposed mission lifetimes, specially focusing on pressure and temperature environments.

Venus↗

NASA NTRS1983

Galileo mission overview

The Galileo mission has three major and equally important scientific objectives: the investigation of the chemical composition and physical state of the Jupiter atmosphere, the study of the composition and state of the Jovian satellites, and the probing of the structure and physical dynamics of the Jovian magnetosphere. The Galileo spacecraft comprises an Orbiter and an atmospheric entry Probe, which will be released on a ballistic entry trajectory from the Orbiter about 150 days before Jupiter arrival. After Probe release, the Orbiter will overfly the Probe during entry in order to relay its data to earth. The Orbiter will then insert itself into a 200-day orbit around Jupiter. Attention is given to the radio science, remote sensing and fields and particles instruments to be carried for the mission.

Oneil, W. J.↗

NASA NTRS1966

Advanced planetary probe study. Volume 3 - Alternate spacecraft and missions Final technical report

Evaluation of 3-axis stabilized, 50-lb science payload spacecraft, Jupiter flyby and orbiter missions, flyby missions to planets beyond Jupiter, capsule entry, and cost effectiveness

PLANETARY SPACECRAFT↗

NASA NTRS1988

Cassini - A mission to the Saturnian system

This international (NASA/ESA) mission, planned for a Titan IV/Centaur G-prime launch in the 1995-1997 era, consists of a Saturn Orbiter (a U.S. Mariner Mark II spacecraft) and a Titan Atmospheric Entry Probe (an ESA product). The mission profile is highly sophisticated in its astrodynamic aspects - a deep space Delta-V maneuver, followed by earth and Jupiter gravity assist flybys, with asteroid encounter(s) along the way. Saturn arrival is characterized by further multiple maneuvers resulting in the Titan probe delivery and a close orbiter flyby, to be followed by a 4-year Saturn system tour. Details of the trajectory design process are discussed.

Sergeyevsky, Andrey B.↗

NASA NTRS1972

Outer planet entry probe system study. Volume 1: Summary

General mission considerations and science prospectus, which are of a general nature that applies to several or all planetary applications, are presented. Five probe systems are defined: nominal Jupiter probe system, and Jupiter probe-dedicated alternative probe system, Jupiter spacecraft radiation-compatible alternative probe system, Saturn probe system, and Saturn probe applicability for Uranus. Parametric analysis is summarized for mission analysis of a general nature, and then for specific missions to Jupiter, Saturn, Uranus, and Neptune. The program is also discussed from the hardware availability viewpoint and the aspect of commonality.

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