Английская Википедия:Galileo (spacecraft)

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Шаблон:Short description Шаблон:Italic title Шаблон:About Шаблон:Good article Шаблон:Infobox spaceflight

Galileo was an American robotic space probe that studied the planet Jupiter and its moons, as well as the asteroids Gaspra and Ida. Named after the Italian astronomer Galileo Galilei, it consisted of an orbiter and an entry probe. It was delivered into Earth orbit on October 18, 1989, by Шаблон:OV, during STS-34. Galileo arrived at Jupiter on December 7, 1995, after gravitational assist flybys of Venus and Earth, and became the first spacecraft to orbit an outer planet.[1]

The Jet Propulsion Laboratory built the Galileo spacecraft and managed the Galileo program for NASA. West Germany's Messerschmitt-Bölkow-Blohm supplied the propulsion module. NASA's Ames Research Center managed the atmospheric probe, which was built by Hughes Aircraft Company. At launch, the orbiter and probe together had a mass of Шаблон:Convert and stood Шаблон:Convert tall.

Spacecraft are normally stabilized either by spinning around a fixed axis or by maintaining a fixed orientation with reference to the Sun and a star. Galileo did both. One section of the spacecraft rotated at 3 revolutions per minute, keeping Galileo stable and holding six instruments that gathered data from many different directions, including the fields and particles instruments.

Galileo was intentionally destroyed in Jupiter's atmosphere on September 21, 2003. The next orbiter to be sent to Jupiter was Juno, which arrived on July 5, 2016.

Development

Шаблон:Main Шаблон:For timeline Jupiter is the largest planet in the Solar System, with more than twice the mass of all the other planets combined.[2] Consideration of sending a probe to Jupiter began as early as 1959.Шаблон:Sfn NASA's Scientific Advisory Group (SAG) for Outer Solar System Missions considered the requirements for Jupiter orbiters and atmospheric probes. It noted that the technology to build a heat shield for an atmospheric probe did not yet exist, and facilities to test one under the conditions found on Jupiter would not be available until 1980.Шаблон:Sfn NASA management designated the Jet Propulsion Laboratory (JPL) as the lead center for the Jupiter Orbiter Probe (JOP) project.Шаблон:Sfn The JOP would be the fifth spacecraft to visit Jupiter, but the first to orbit it, and the probe would be the first to enter its atmosphere.Шаблон:Sfn

Файл:Galileo Preparations - GPN-2000-000672.jpg
In the Vertical Processing Facility (VPF), Galileo is prepared for mating with the Inertial Upper Stage booster.

An important decision made at this time was to use a Mariner program spacecraft like that used for Voyager for the Jupiter orbiter, rather than a Pioneer. Pioneer was stabilized by spinning the spacecraft at 60 rpm, which gave a 360-degree view of the surroundings, and did not require an attitude control system. By contrast, Mariner had an attitude control system with three gyroscopes and two sets of six nitrogen jet thrusters. Attitude was determined with reference to the Sun and Canopus, which were monitored with two primary and four secondary sensors. There was also an inertial reference unit and an accelerometer. This allowed it to take high-resolution images, but the functionality came at a cost of increased weight. A Mariner weighed Шаблон:Convert compared to just Шаблон:Convert for a Pioneer.Шаблон:Sfn

John R. Casani, who had headed the Mariner and Voyager projects, became the first project manager.[3] He solicited suggestions for a more inspirational name for the project, and the most votes went to "Galileo" after Galileo Galilei, the first person to view Jupiter through a telescope. His 1610 discovery of what is now known as the Galilean moons orbiting Jupiter was important evidence of the Copernican model of the solar system. It was also noted that the name was that of a spacecraft in the Star Trek television show. The new name was adopted in February 1978.Шаблон:Sfn

The Jet Propulsion Laboratory built the Galileo spacecraft and managed the Galileo mission for NASA. West GermanyШаблон:'s Messerschmitt-Bölkow-Blohm supplied the propulsion module. NASA's Ames Research Center managed the atmospheric probe, which was built by Hughes Aircraft Company.[4] At launch, the orbiter and probe together had a mass of Шаблон:Convert and stood Шаблон:Convert tall.[4] Spacecraft are normally stabilized either by spinning around a fixed axis or by maintaining a fixed orientation with reference the Sun and a star; Galileo did both. One section of the spacecraft rotated at 3 revolutions per minute, keeping Galileo stable and holding six instruments that gathered data from many different directions, including the fields and particles instruments.[5] Back on the ground, the mission operations team used software containing 650,000 lines of code in the orbit sequence design process; 1,615,000 lines in the telemetry interpretation; and 550,000 lines of code in navigation.[4] All of the spacecraft components and spare parts received a minimum of 2,000 hours of testing. The spacecraft was expected to last for at least five years—long enough to reach Jupiter and perform its mission.Шаблон:Sfn

Файл:STS-34 Launch 2.jpg
Launch of Space Shuttle Atlantis on STS-34, carrying Galileo into Earth orbit

On December 19, 1985, it departed the JPL in Pasadena, California, on the first leg of its journey, a road trip to the Kennedy Space Center in Florida.Шаблон:SfnШаблон:Sfn Due to the Space Shuttle Challenger disaster, the May launch date could not be met.Шаблон:Sfn The mission was re-scheduled October 12, 1989. The Galileo spacecraft would be launched by the STS-34 mission in the Шаблон:OV.[6] As the launch date of Galileo neared, anti-nuclear groups, concerned over what they perceived as an unacceptable risk to the public's safety from the plutonium in the GalileoШаблон:'s radioisotope thermoelectric generators (RTGs) and General Purpose Heat Source (GPHS) modules, sought a court injunction prohibiting GalileoШаблон:'s launch.[7] RTGs were necessary for deep space probes because they had to fly distances from the Sun that made the use of solar energy impractical.[8]

The launch was delayed twice more: by a faulty main engine controller that forced a postponement to October 17, and then by inclement weather, which necessitated a postponement to the following day,[9] but this was not a concern since the launch window extended until November 21.[10] Atlantis finally lifted off at 16:53:40 UTC on October 18, and went into a Шаблон:Convert orbit.[9] Galileo was successfully deployed at 00:15 UTC on October 19.Шаблон:Sfn Following the IUS burn, the Galileo spacecraft adopted its configuration for solo flight, and separated from the IUS at 01:06:53 UTC on October 19.[11] The launch was perfect, and Galileo was soon headed towards Venus at over Шаблон:Convert.[12] Atlantis returned to Earth safely on October 23.[9]

Файл:Galileo Diagram.jpg
GalileoШаблон:'s main components

Command and Data Handling (CDH)

The CDH subsystem was actively redundant, with two parallel data system buses running at all times.Шаблон:Sfn Each data system bus (a.k.a. string) was composed of the same functional elements, consisting of multiplexers (MUX), high-level modules (HLM), low-level modules (LLM), power converters (PC), bulk memory (BUM), data management subsystem bulk memory (DBUM), timing chains (TC), phase locked loops (PLL), Golay coders (GC), hardware command decoders (HCD) and critical controllers (CRC).Шаблон:Sfn

The CDH subsystem was responsible for maintaining the following functions:

  1. decoding of uplink commands
  2. execution of commands and sequences
  3. execution of system-level fault-protection responses
  4. collection, processing, and formatting of telemetry data for downlink transmission
  5. movement of data between subsystems via a data system bus.Шаблон:Sfn

The spacecraft was controlled by six RCA 1802 COSMAC microprocessor CPUs: four on the spun side and two on the despun side. Each CPU was clocked at about 1.6 MHz, and fabricated on sapphire (silicon on sapphire), which is a radiation-and static-hardened material ideal for spacecraft operation. This 8-bit microprocessor was the first low-power CMOS processor chip, similar to the 6502 that was being built into the Apple II desktop computer at that time.[13]

The Galileo Attitude and Articulation Control System (AACSE) was controlled by two Itek Advanced Technology Airborne Computers (ATAC), built using radiation-hardened 2901s. The AACSE could be reprogrammed in flight by sending the new program through the Command and Data Subsystem.Шаблон:Sfn The attitude control system software was written in the HAL/S programming language,Шаблон:Sfn which was also used in the Space Shuttle program.Шаблон:Sfn

Memory capacity provided by each BUM was 16K of RAM, while the DBUMs each provided 8K of RAM. There were two BUMs and two DBUMs in the CDH subsystem and they all resided on the spun side of the spacecraft. The BUMs and DBUMs provided storage for sequences and contain various buffers for telemetry data and interbus communication. Every HLM and LLM was built up around a single 1802 microprocessor and 32K of RAM (for HLMs) or 16K of RAM (for LLMs). Two HLMs and two LLMs resided on the spun side while two LLMs were on the despun side. Thus, total memory capacity available to the CDH subsystem was 176K of RAM: 144K allocated to the spun side and 32K to the despun side.Шаблон:Sfn Each HLM was responsible for the following functions:

  1. uplink command processing
  2. maintenance of the spacecraft clock
  3. movement of data over the data system bus
  4. execution of stored sequences (time-event tables)
  5. telemetry control
  6. error recovery including system fault-protection monitoring and response.Шаблон:Sfn

Each LLM was responsible for the following functions:

  1. collect and format engineering data from the subsystems
  2. provide the capability to issue coded and discrete commands to spacecraft users
  3. recognize out-of-tolerance conditions on status inputs
  4. perform some system fault-protection functions.Шаблон:Sfn

Propulsion

Файл:Galileo propulsion module.jpg
Propulsion module

The propulsion subsystem consisted of a Шаблон:Cvt main engine and twelve Шаблон:Cvt thrusters, together with propellant, storage and pressurizing tanks and associated plumbing. The 10 N thrusters were mounted in groups of six on two Шаблон:Convert booms. The fuel for the system was Шаблон:Convert of monomethylhydrazine and nitrogen tetroxide. Two separate tanks held another Шаблон:Convert of helium pressurant. The propulsion subsystem was developed and built by Messerschmitt-Bölkow-Blohm and provided by West Germany, the major international partner in Project Galileo.[13]

Electrical power

At the time, solar panels were not practical at Jupiter's distance from the Sun; the spacecraft would have needed a minimum of Шаблон:Convert of panels. Chemical batteries would likewise be prohibitively large due to technological limitations. The solution was two radioisotope thermoelectric generators (RTGs) which powered the spacecraft through the radioactive decay of plutonium-238. The heat emitted by this decay was converted into electricity through the solid-state Seebeck effect. This provided a reliable and long-lasting source of electricity unaffected by the cold environment and high-radiation fields in the Jovian system.[13][14]

Each GPHS-RTG, mounted on a Шаблон:Convert boom, carried Шаблон:Convert of Шаблон:Chem2. Each RTG contained 18 separate heat source modules, and each module encased four pellets of plutonium(IV) oxide, a ceramic material resistant to fracturing.[14] The plutonium was enriched to about 83.5 percent plutonium-238.Шаблон:Sfn The modules were designed to survive a range of potential accidents: launch vehicle explosion or fire, re-entry into the atmosphere followed by land or water impact, and post-impact situations. An outer covering of graphite provided protection against the structural, thermal, and eroding environments of a potential re-entry into Earth's atmosphere. Additional graphite components provided impact protection, while iridium cladding of the RTGs provided post-impact containment.[14] The RTGs produced about 570 watts at launch. The power output initially decreased at the rate of 0.6 watts per month and was 493 watts when Galileo arrived at Jupiter.Шаблон:Sfn

Telecommunications

Шаблон:Main The spacecraft had a large high-gain antenna which failed to deploy while in space, so the low-gain antenna was used instead, although at slower data transfer speeds.[15]

Instruments

Scientific instruments to measure fields and particles were mounted on the spinning section of the spacecraft, together with the main antenna, power supply, the propulsion module and most of GalileoШаблон:'s computers and control electronics. The sixteen instruments, weighing Шаблон:Convert altogether, included magnetometer sensors mounted on an Шаблон:Convert boom to minimize interference from the spacecraft; a plasma instrument for detecting low-energy charged particles and a plasma-wave detector to study waves generated by the particles; a high-energy particle detector; and a detector of cosmic and Jovian dust. It also carried the Heavy Ion Counter, an engineering experiment to assess the potentially hazardous charged particle environments the spacecraft flew through, and an extreme ultraviolet detector associated with the UV spectrometer on the scan platform.[4]

The despun section's instruments included the camera system; the near infrared mapping spectrometer to make multi-spectral images for atmospheric and moon surface chemical analysis; the ultraviolet spectrometer to study gases; and the photopolarimeter-radiometer to measure radiant and reflected energy. The camera system was designed to obtain images of Jupiter's satellites at resolutions 20 to 1,000 times better than VoyagerШаблон:'s best, because Galileo flew closer to the planet and its inner moons, and because the more modern CCD sensor in GalileoШаблон:'s camera was more sensitive and had a broader color detection band than the vidicons of Voyager.[4]

Despun section

Solid-state imager (SSI)

Файл:Galileo Solid- State Imaging.jpg
Solid-state imager

The SSI was an 800-by-800-pixel charge-coupled device (CCD) camera. The optical portion of the camera was a modified flight spare of the Voyager narrow-angle camera; a Cassegrain telescope.[16] The CCD had radiation shielding a Шаблон:Convert thick layer of tantalum surrounding the CCD except where the light enters the system. An eight-position filter wheel was used to obtain images at specific wavelengths. The images were then combined electronically on Earth to produce color images. The spectral response of the SSI ranged from about 400 to 1100 nm. The SSI weighed Шаблон:Convert and consumed, on average, 15 watts of power.[17][18]

Near-infrared mapping spectrometer (NIMS)

Файл:Galileo - NIMS photo - nims1.jpg
Near-infrared mapping spectrometer

The NIMS instrument was sensitive to 0.7-to-5.2-micrometer wavelength infrared light, overlapping the wavelength range of the SSI. NIMS used a Шаблон:Convert aperture reflecting telescope. The spectrometer used a grating to disperse the light collected by the telescope. The dispersed spectrum of light was focused on detectors of indium, antimonide and silicon. NIMS weighed Шаблон:Convert and used 12 watts of power on average.[19][20]

Ultraviolet spectrometer / extreme ultraviolet spectrometer (UVS/EUV)

Файл:Galileo - UVS photo - uvs1.jpg
Ultraviolet spectrometer

The Cassegrain telescope of the UVS had a Шаблон:Convert aperture. Both the UVS and EUV instruments used a ruled grating to disperse light for spectral analysis. Light then passed through an exit slit into photomultiplier tubes that produced pulses of electrons, which were counted and the results sent to Earth. The UVS was mounted on GalileoШаблон:'s scan platform. The EUV was mounted on the spun section. As Galileo rotated, EUV observed a narrow ribbon of space perpendicular to the spin axis. The two instruments combined weighed about Шаблон:Convert and used 5.9 watts of power.[21][22]

Photopolarimeter–radiometer (PPR)

The PPR had seven radiometry bands. One of these used no filters and observed all incoming radiation, both solar and thermal. Another band allowed only solar radiation through. The difference between the solar-plus-thermal and the solar-only channels gave the total thermal radiation emitted. The PPR also measured in five broadband channels that spanned the spectral range from 17 to 110 micrometers. The radiometer provided data on the temperatures of Jupiter's atmosphere and satellites. The design of the instrument was based on that of an instrument flown on the Pioneer Venus spacecraft. A Шаблон:Convert aperture reflecting telescope collected light and directed it to a series of filters, and, from there, measurements were performed by the detectors of the PPR. The PPR weighed Шаблон:Convert and consumed about 5 watts of power.[23][24]

Spun section

Dust-detector subsystem (DDS)

Файл:Galileo - DDS photo - dds1.jpg
Dust-detector subsystem

The dust-detector subsystem (DDS) was used to measure the mass, electric charge, and velocity of incoming particles. The masses of dust particles that the DDS could detect go from Шаблон:10^ to Шаблон:10^ grams. The speed of these small particles could be measured over the range of Шаблон:Convert. The instrument could measure impact rates from 1 particle per 115 days (10 megaseconds) to 100 particles per second. Such data was used to help determine dust origin and dynamics within the magnetosphere. The DDS weighed Шаблон:Convert and used an average of 5.4 watts of power.[25][26]

Energetic-particles detector (EPD)

The energetic-particles detector (EPD) was designed to measure the numbers and energies of ions and electrons whose energies exceeded about Шаблон:Convert. The EPD could also measure the direction of travel of such particles and, in the case of ions, could determine their composition (whether the ion is oxygen or sulfur, for example). The EPD used silicon solid-state detectors and a time-of-flight detector system to measure changes in the energetic particle population at Jupiter as a function of position and time. These measurements helped determine how the particles got their energy and how they were transported through Jupiter's magnetosphere. The EPD weighed Шаблон:Convert and used 10.1 watts of power on average.[27][28]

Heavy-ion counter (HIC)

Файл:Galileo Heavy Ion Counter.jpg
Heavy-ion counter

The HIC was, in effect, a repackaged and updated version of some parts of the flight spare of the Voyager cosmic-ray system. The HIC detected heavy ions using stacks of single crystal silicon wafers. The HIC could measure heavy ions with energies as low as Шаблон:Convert and as high as Шаблон:Convert per nucleon. This range included all atomic substances between carbon and nickel. The HIC and the EUV shared a communications link and, therefore, had to share observing time. The HIC weighed Шаблон:Convert and used an average of 2.8 watts of power.[29][30]

Magnetometer (MAG)

Файл:Galileo - MAD photo - mag1.jpg
Magnetometer (stowed)

The magnetometer (MAG) used two sets of three sensors. The three sensors allowed the three orthogonal components of the magnetic field section to be measured. One set was located at the end of the magnetometer boom and, in that position, was about Шаблон:Convert from the spin axis of the spacecraft. The second set, designed to detect stronger fields, was Шаблон:Convert from the spin axis. The boom was used to remove the MAG from the immediate vicinity of Galileo to minimize magnetic effects from the spacecraft. However, not all these effects could be eliminated by distancing the instrument. The rotation of the spacecraft was used to separate natural magnetic fields from engineering-induced fields. Another source of potential error in measurement came from the bending and twisting of the long magnetometer boom. To account for these motions, a calibration coil was mounted rigidly on the spacecraft to generate a reference magnetic field during calibrations. The magnetic field at the surface of the Earth has a strength of about 50,000 nT. At Jupiter, the outboard (11 m) set of sensors could measure magnetic field strengths in the range from ±32 to ±512 nT, while the inboard (6.7 m) set was active in the range from ±512 to ±16,384 nT. The MAG experiment weighed Шаблон:Convert and used 3.9 watts of power.[31][32]

Plasma subsystem (PLS)

The PLS used seven fields of view to collect charged particles for energy and mass analysis. These fields of view covered most angles from 0 to 180 degrees, fanning out from the spin axis. The rotation of the spacecraft carried each field of view through a full circle. The PLS measured particles in the energy range from Шаблон:Convert. The PLS weighed Шаблон:Convert and used an average of 10.7 watts of power.[33][34]

Plasma-wave subsystem (PWS)

Файл:Galileo - PWS photo - pws1.jpg
Plasma-wave subsystem

An electric dipole antenna was used to study the electric fields of plasmas, while two search coil magnetic antennas studied the magnetic fields. The electric dipole antenna was mounted at the tip of the magnetometer boom. The search coil magnetic antennas were mounted on the high-gain antenna feed. Nearly simultaneous measurements of the electric and magnetic field spectrum allowed electrostatic waves to be distinguished from electromagnetic waves. The PWS weighed Шаблон:Convert and used an average of 9.8 watts.[35][36]

Galileo entry probe

Шаблон:See also Шаблон:Infobox spaceflight

Файл:Descent Module.jpeg
Inner Descent Module of the Galileo Entry Probe

The atmospheric probe was built by Hughes Aircraft Company's Space and Communications Group at its El Segundo, California plant.[37][38] It weighed Шаблон:Convert and was Шаблон:Convert high.[4] Inside the probe's heat shield, the scientific instruments were protected from extreme heat and pressure during its high-speed journey into the Jovian atmosphere, entering at Шаблон:Convert.[39] Temperatures reached around Шаблон:Cvt.[40] NASA built a special laboratory, the Giant Planet Facility, to simulate the heat load, which was similar to the convective and radiative heating experienced by an ICBM warhead reentering the atmosphere.Шаблон:Sfn[41]

Batteries

The probe's electronics were powered by 13 lithium sulfur dioxide batteries manufactured by Honeywell's Power Sources Center in Horsham, Pennsylvania. Each cell was the size of a D battery so existing manufacturing tools could be used.Шаблон:SfnШаблон:Sfn They provided a nominal power output of about 7.2-ampere hours capacity at a minimal voltage of 28.05 volts.Шаблон:Sfn

Scientific instruments

The probe included seven instruments for taking data on its plunge into Jupiter:Шаблон:Sfn[42]

Scientific instruments
Instrument Function Mass Power consumption Principal investigator Organizations
Atmospheric structure instrument Measuring temperature, pressure and deceleration Шаблон:Convert 6.3 W Alvin Seiff Ames Research Center and San Jose State University Foundation
Neutral mass spectrometer Analyze the gas composition of the atmosphere Шаблон:Convert 29 W Hasso Niemann Goddard Space Flight Center
Helium Abundance Detector An interferometer supporting atmospheric composition studies Шаблон:Convert 1.1 W Ulf von Zahn University of Bonn, University of Rostock
Nephelometer Cloud location and cloud-particle observations Шаблон:Convert 14 W Boris Ragent Ames Research Center and San Jose State University Foundation
Net-flux radiometer Measuring the difference between upward and downward radiant flux at each altitude Шаблон:Convert 7.0 W L. Sromovsky University of Wisconsin
Lightning and radio emission detector and energetic particles instrument Measuring light and radio emissions associated with lightning, and fluxes of protons, electrons, alpha particles and heavy ions Шаблон:Convert 2.3 W Louis Lanzerotti Bell Laboratories, University of Florida and Federal Republic of Germany
Radio equipment Measuring wind speeds and atmospheric absorption David Atkinson University of Idaho

In addition, the probe's heat shield contained instrumentation to measure ablation during descent.Шаблон:Sfn

Termination

Lacking the fuel to escape Jupiter's gravity well, at the end of GalileoШаблон:'s life, the probe was deliberately crashed into Jupiter on September 21, 2003, to prevent forward contamination of possible life of Jupiter's moon Europa.[43]

Names

The Galileo Probe had COSPAR ID 1989-084E while the orbiter had id 1989-084B.Шаблон:Sfn Names for the spacecraft include Galileo Probe or Jupiter Entry Probe abbreviated JEP.Шаблон:Sfn The related COSPAR IDs of the Galileo mission were:[44]

  • 1989-084A STS 34
  • 1989-084B Galileo
  • 1989-084C IUS (Orbus 21)
  • 1989-084D IUS (Orbus 6E)
  • 1989-084E Galileo Probe

Шаблон:Clear right

See also

Notes

Шаблон:Reflist

References

Шаблон:Refbegin

Шаблон:Refend


External links

Шаблон:Commons category

Шаблон:Solar System probes Шаблон:Jupiter spacecraft Шаблон:Venus spacecraft Шаблон:Jet Propulsion Laboratory Шаблон:Orbital launches in 1989 Шаблон:Galileo Galilei Шаблон:Portal bar Шаблон:Authority control Шаблон:Use mdy dates Шаблон:Use American English

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