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  • 1
    Electronic Resource
    Electronic Resource
    Springer
    Space science reviews 60 (1992), S. 23-78 
    ISSN: 1572-9672
    Source: Springer Online Journal Archives 1860-2000
    Topics: Physics
    Notes: Abstract The Galileo spacecraft was launched by the Space Shuttle Atlantis on October 18, 1989. A two-stage Inertial Upper Stage propelled Galileo out of Earth parking orbit to begin its 6-year interplanetary transfer to Jupiter. Galileo has already received two gravity assists: from Venus on February 10, 1990 and from Earth on December 8, 1990. After a second gravity-assist flyby of Earth on December 8, 1992, Galileo will have achieved the energy necessary to reach Jupiter. Galileo's interplanetary trajectory includes a close flyby of asteroid 951-Gaspra on October 29, 1991, and, depending on propellant availability and other factors, there may be a second asteroid flyby of 243-Ida on August 28, 1993. Upon arrival at Jupiter on December 7, 1995, the Galileo Orbiter will relay data back to Earth from an atmospheric Probe which is released five months earlier. For about 75 min, data is transmitted to the Orbiter from the Probe as it descends on a parachute to a pressure depth of 20–30 bars in the Jovian atmosphere. Shortly after the end of Probe relay, the Orbiter ignites its rocket motor to insert into orbit about Jupiter. The orbital phase of the mission, referred to as the satellite tour, lasts nearly two years, during which time Galileo will complete 10 orbits about Jupiter. On each of these orbits, there will be a close encounter with one of the three outermost Galilean satellites (Europa, Ganymede, and Callisto). The gravity assist from each satellite is designed to target the spacecraft to the next encounter with minimal expenditure of propellant. The nominal mission is scheduled to end in October 1997 when the Orbiter enters Jupiter's magnetotail.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2003-01-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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  • 3
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    In:  Other Sources
    Publication Date: 2011-08-24
    Description: The trajectory design of the Galileo spacecraft is examined. The Galileo spacecraft was launched on a six-year long trip to Jupiter in October 1989. A new Venus-Earth-Earth-Gravity Assist (VEEGA) trajectory mode is being used for the transfer to Jupiter and involves two phasing orbits around the sun and gravity-assist flybys with Venus. The aggregate delta V acquired from these flybys is 18.3 km/s. The interplanetary trajectory includes a close flyby of asteroid 951-Gaspra in October 1991 and a possible flyby of 243-Ida in August 1993. After arrival at Jupiter in December 1995, the previously released Galileo atmospheric probe will relay data to earth via the Galileo Orbiter. The orbital phase of the mission will involve 10 orbits of Jupiter over a 22 month period. In this phase the Orbiter will use repeated gravity-assisted flybys of Europa, Ganymede and Callisto during which Jupiter, its magnetosphere and the Galilean satellites will be investigated. The mission is scheduled to end in October 1997.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Space Science Reviews (ISSN 0038-6308); 60; 1-4,
    Format: text
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  • 4
    Publication Date: 2011-08-19
    Description: A study has been performed to assess the feasibility of using a second Galileo spacecraft for a Titan-probe/Saturn-orbiter mission that would be launched on a Shuttle/Centaur in the early 1990s. The interplanetary transfer is accomplished by means of a Delta-V earth-gravity-assist trajectory with a 3-year flight time from launch to earth flyby. Just prior to arrival at Saturn, the Titan probe is released, and the orbiter is used to relay data from the probe back to earth as it performs a close gravity-assist flyby of Titan. The orbiter then conducts a satellite tour containing multiple encounters with Saturn's satellites. Discussed in detail are the optimal trajectory design, Saturn approach trajectory design (Titan flyby, probe relay, and initial orbit selection), satellite tour design, and mission performance.
    Keywords: ASTRODYNAMICS
    Type: Journal of the Astronautical Sciences (ISSN 0021-9142); 37; 307-331
    Format: text
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  • 5
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    Publication Date: 2019-06-28
    Description: Free return trajectories in earth-Mars mission opportunities between 2000 and 2020 are identified and tradeoffs in mission design involving such trajectories are considered. A method of searching for trajectories containing no deterministic maneuvers is developed which is suitable for generating contours. Sample contours are presented for the trajectories and are used to show the variations in trajectory parameters found in the real world.
    Keywords: ASTRODYNAMICS
    Type: AAS PAPER 91-123 , In: Spaceflight mechanics 1991; Proceedings of the 1st AAS(AIAA Annual Spaceflight Mechanics Meeting, Houston, TX, Feb. 11-13, 1991. Pt. 1 (A93-17901 05-13); p. 317-329.
    Format: text
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  • 6
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    Publication Date: 2018-06-08
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  • 7
    Publication Date: 2019-07-13
    Description: Ground-based optical navigation (OpNav) using pictures taken by the Naviga-tion camera on the Stardust spacecraft provided the target-relative information needed to design maneuvers during its approach to comet Tempel 1. Hardware problems, limited downlink bandwidth, and changes in the flight profile affected the OpNav picture schedule, sometimes in near-real time. The Stardust naviga-tion camera and attitude control presented challenges. Picture-processing techniques were developed during approach that included background estimation, co-addition, and co-registration. These techniques, along with adaptive picture scheduling, successfully addressed the challenges.
    Keywords: Optics; Mechanical Engineering; Lunar and Planetary Science and Exploration; Space Communications, Spacecraft Communications, Command and Tracking
    Type: 2011 AAS/AIAA Astrodynamics Specialist Conference; Jul 31, 2011 - Aug 04, 2011; Girdwood, AK; United States
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  • 8
    Publication Date: 2019-07-13
    Description: Mars landers to date have flown ballistic entry trajectories with no trajectory control after the final maneuver before entry. Improvements in landing accuracies (from approx.150 km from the target for Mars Pathfinder to approx.30-40 km for MER and Phoenix) have been driven by approach navigation improvements. MSL will fly the first guided-entry trajectory to Mars, further improving accuracy to approx.10-12 km from the target.
    Keywords: Spacecraft Design, Testing and Performance
    Type: IEEEAC Paper 1209 , 2011 IEEE Aersopace Conference; Mar 05, 2011 - Mar 12, 2011; Big Sky, MT; United States
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  • 9
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    Publication Date: 2019-07-13
    Description: This slide presentation reviews the technology developments required to achieve pinpoint landing for a Mars landing of a future unmanned vehicle. It addresses some of the challenges to achieving accurate landing (i.e., to 2-3 kilometers) of a designated landing site. The major challenge though is to reduce the possible propellant requirement to achieve this pinpoint landing capability which requires minimizing delivery error at powered descent ignition.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: MSR Technology Workshop; Jan 01, 2008; Houston, TX; United States
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  • 10
    Publication Date: 2019-07-13
    Description: Attempts have been made to design the trajectory of the Galileo orbiter so that it passes behind Jupiter, as viewed from earth, as many times as possible during the mission. During this type of pass, or occultation, the thick Jovian atmosphere acts as a lens, refracting a portion of the radio signal from the spacecraft toward earth. A method for calculating antenna aiming vectors during occultations is presented. This method meets the necessary accuracy requirements while offering a reduction in terms of complexity and usage of computer resources.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Type: AAS PAPER 87-484 , AAS/AIAA Astrodynamics Conference; Dec 06, 1987 - Dec 09, 1987; Kalispell, MT; United States
    Format: text
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