ပိုင်အိုနီးယား ၁၀

ပိုင်အိုနီးယား ၁၀ အာကာသယာဉ်သည် ၂၅၈ ကီလိုဂရမ်အလေးချိန်ရှိသည့် အာကာသစူးစမ်းလေ့လာရေး စက်ရုပ်ယာဉ်ဖြစ်သည်။ ဂျူပီတာဂြိုဟ်သို့ ပထမဆုံးခရီးနှင်ခဲ့ပြီး နေအဖွဲ့အစည်းမှ လွတ်မြောက်အလျင်ဖြင့်ထွက်ခွာနိုင်ခဲ့သော ပထမဆုံးယာဉ်ဖြစ်သည်။ စီမံကိန်းကို အမေရိကန်အမျိုးသားလေကြောင်းနှင့်အာကာသစီမံမှုအဖွဲ့ (နာဆာ)၏ အမ်းစ်သုတေသနဌာနက ကိုင်တွယ်ခဲ့ပြီး TRW Inc က ယာဉ်ကို ပုံစံထုတ်ခဲ့သည်။ ပိုင်အိုနီးယား ၁၀ ကို အချင်း၂.၇၄ မီတာရှိသည့်စလောင်း၊ ယင်းတွင်ဆက်စပ်တပ်ဆင်ထားသည့် ဆဌဂံပုံကိုယ်ထည်၊ ဖမ်းယူမှုမြင့်မားသည့် အင်တင်နာချောင်းကြီးတစ်ချောင်းတို့ဖြင့် ဖွဲ့စည်းထားသည်။ လိုအပ်သည့်စွမ်းအင်ကို ရေဒီယိုအိုင်ဆိုတုပ် အပူလျှပ်စစ်ဓာတ်အားထုတ်စက်လေးခုပေါင်းမှ စတင်ပစ်လွှတ်ချိန်တွင် ၁၅၅ ဝပ်ရရှိသည်။

ပိုင်အိုနီးယား ၁၀ ကို ၁၉၇၂ခုနှစ် မတ်လ၂ရက်နေ့တွင် ဖလော်ရီဒါရှိ ကိပ်ကာနီဗယ်အာကာသလွှတ်တင်ရေးစခန်းမှလွှတ်တင်ခဲ့သည်။ ဇွန် ၁၅ ရက်နေ့တွင် ဂြိုဟ်သိမ်ဂြိုဟ်မွှားများပတ်လမ်းကိုဖြတ်သွားသော ပထမဆုံးအာကာသယာဉ် ဖြစ်လာသည်။ ၁၉၇၃၊ နိုဝင်ဘာ ၆ ရက်မှစတင်၍ ကီလိုမီတာ၂၅ သန်းအကွာအဝေးမှ ဂျူပီတာဂြိုဟ်၏ဓာတ်ပုံများကို စတင်ပေးပို့ခဲ့သည်။ စုစုပေါင်းဓာတ်ပုံ ၅၀၀ ကျော်ပေးပို့ခဲ့သည်။ ၁၉၇၃၊ ဒီဇင်ဘာတွင် ဂြိုဟ်နှင့်အနီးဆုံး ၁၃၂, ၂၅၂ ကီလိုမီတာအကွာသို့ ရောက်ရှိခဲ့သည်။ ခရီးစဉ်တွင် ယာဉ်ပေါ်တွင် တပ်ဆင်ပေးလိုက်သော ကိရိယာများသည် ဂြိုဟ်သိမ်ဂြိုဟ်မွှားပတ်လမ်းခါးပတ်ကွင်း၊ ဂျူပီတာဂြိုဟ်ပတ်ဝန်းကျင်၊ နေမုန်တိုင်းများ၊ အာကာသရောင်ခြည်များကိုလေ့လာနိုင်ခဲ့သည်။ ယခုအခါနေစကြဝဠာအတွင်းအစွန်ဆုံးရှိ ဟေလီယိုစပီးယားအလွှာ (နေစကြဝဠာ နယ်နိမိတ်အစွန်)သို့ရောက်ရှိနေပြီဖြစ်သည်။ ၂၀၀၃၊ ဇန္နဝါရီ ၂၃ တွင် ကမ္ဘာမှ ကီလိုမီတာ ၁၂ ဘီလျံ (၈၀ AU)အရောက်တွင် ယာဉ်ပေါ်တွင်ဓာတ်အားနည်းပါးလာမှုကြောင့် ဆက်သွယ်မှုပြတ်တောက်ခဲ့သည်။

ယာဉ်ဒီဇိုင်း
The Pioneer 10 bus measures  deep and with six  long panels forming the hexagonal structure. The bus houses propellant to control the orientation of the probe and eight of the eleven scientific instruments. The equipment compartment lies within an aluminum honeycomb structure to provide protection from meteoroids. A layer of insulation, consisting of aluminized mylar and kapton blankets, provides passive thermal control. Heat is generated by the dissipation of 70 to 120 watts (W) from the electrical components inside the compartment. The heat range is maintained within the operating limits of the equipment by means of louvers located below the mounting platform. The spacecraft had a launch mass of .

At launch, the spacecraft carried  of liquid hydrazine monopropellant in a  diameter spherical tank. Orientation of the spacecraft was maintained with six 4.5 N, hydrazine thrusters mounted in three pairs. Pair one maintained a constant spin-rate of 4.8-rpm, pair two controlled the forward thrust, and pair three controlled the attitude. The attitude pair were used in conical scanning maneuvers to track Earth in its orbit. Orientation information was also provided by a star sensor able to reference Canopus, and two sun sensors.

သိပ္ပံပစ္စည်းများ
 Helium Vector Magnetometer (HVM) 150pxThis instrument measures the fine structure of the interplanetary magnetic field, maps the Jovian magnetic field, and provides magnetic field measurements to evaluate solar wind interaction with Jupiter. The magnetometer consists of a helium-filled cell mounted on a 6.6–m boom to partly isolate the instrument from the spacecraft's magnetic field.
Principal investigator: Edward Smith / JPL
Data: PDS/PPI data catalog , NSSDC data archive  Quadrispherical Plasma Analyzer 150pxPeers through a hole in the large dish-shaped antenna to detect particles of the solar wind originating from the Sun.
Principal investigator: Aaron Barnes / NASA Ames Research Center (archived website)
Data: PDS/PPI data catalog , NSSDC data archive  Charged Particle Instrument (CPI) 150pxDetects cosmic rays in the Solar System.
Principal investigator: John Simpson / University of Chicago
Data: NSSDC data archive  Cosmic Ray Telescope (CRT) 150pxCollects data on the composition of the cosmic ray particles and their energy ranges.
Principal investigator: Frank B. McDonald / NASA Goddard Space Flight Center
Data: PDS/PPI data catalog , NSSDC data archive  Geiger Tube Telescope (GTT) Surveys the intensities, energy spectra, and angular distributions of electrons and protons along the spacecraft's path through the radiation belts of Jupiter.
Principal investigator: James A. Van Allen / University of Iowa (website )
Data: PDS/PPI data catalog , NSSDC data archive  Trapped Radiation Detector (TRD) 150pxIncludes an unfocused Cerenkov counter that detects the light emitted in a particular direction as particles pass through it recording electrons of energy, 0.5 to 12 MeV, an electron scatter detector for electrons of energy, 100 to 400 keV, and a minimum ionizing detector consisting of a solid-state diode that measures minimum ionizing particles (<3 MeV)  and protons in the range of 50 to 350 MeV.
Principal investigator: R. Fillius / University of California San Diego
Data: NSSDC data archive  Meteoroid Detectors 150pxTwelve panels of pressurized cell detectors mounted on the back of the main dish antenna record penetrating impacts of small meteoroids.
Principal investigator: William Kinard / NASA Langley Research Center
Data: NSSDC data archive list  Asteroid/Meteoroid Detector (AMD) 150pxMeteoroid-asteroid detector looks into space with four non-imaging telescopes to track particles ranging from close-by bits of dust to distant large asteroids.
Principal investigator: Robert Soberman / General Electric Company
Data: NSSDC data archive  Ultraviolet Photometer 150pxUltraviolet light is sensed to determine the quantities of hydrogen and helium in space and on Jupiter.
Principal investigator: Darrell Judge / University of Southern California
Data: PDS/PPI data catalog , NSSDC data archive  Imaging Photopolarimeter (IPP) 150pxThe imaging experiment relies upon the spin of the spacecraft to sweep a small telescope across the planet in narrow strips only 0.03 degrees wide, looking at the planet in red and blue light. These strips were then processed to build up a visual image of the planet.
Principal investigator: Tom Gehrels / University of Arizona
Data: NSSDC data archive list  Infrared Radiometer 150pxProvides information on cloud temperature and the output of heat from Jupiter.
Principal investigator: Andrew Ingersoll / California Institute of Technology

ပိုင်အိုနီးယား သတ္တုပြား
At the behest of Carl Sagan, Pioneer 10 and Pioneer 11 carry a  gold-anodized aluminum plaque in case either spacecraft is ever found by intelligent life-forms from another planetary system. The plaques feature the nude figures of a human male and female along with several symbols that are designed to provide information about the origin of the spacecraft. Paper on the background of the plaque. Pages available online: 1 , 2 , 3 , 4  The plaque is attached to the antenna support struts to provide some shielding from interstellar dust.

မစ်ရှင် ရာဇဝင်

ပစ်လွှတ်မှုနှင့်လမ်းကြောင်း

The Pioneer 10 probe was launched on March 3, 1972 at 01:49:00 UTC (March 2 local time) by the National Aeronautics and Space Administration from Space Launch Complex 36A at Cape Canaveral, Florida aboard an Atlas/Centaur launch vehicle. The third stage consisted of a solid fuel TE364-4 developed specifically for the Pioneer missions. This stage provided about 15,000 pounds of thrust and spun up the spacecraft. The spacecraft had an initial spin rate of 30 revolutions per minute. Twenty minutes following the launch, the vehicle's three booms were extended, which slowed the rotation rate to 4.8 per minute. This rate was maintained throughout the voyage. The launch vehicle accelerated the probe for net interval of 17 minutes, reaching a velocity of 51,682 kilometers/hour (32,114 miles/hour).

After the high-gain antenna was contacted, several of the instruments were activated for testing while Pioneer 10 was moving through the Earth's radiation belts. Ninety minutes after launch, the spacecraft reached interplanetary space. Pioneer 10 passed by the Moon in 11 hours and become the fastest man-made object at that time. Two days after launch, the scientific instruments were turned on, beginning with the cosmic ray telescope. After ten days, all of the instruments were active.

During the first seven months of the journey, the spacecraft made three course corrections. The on-board instruments underwent checkouts, with the photometers examining Jupiter and the Zodiacal light, and experiment packages being used to measure cosmic rays, magnetic fields and the solar wind. The only anomaly during this interval was the failure of the star sensor, which instead required the spacecraft to maintain its orientation using the two sun sensors.

While passing through interplanetary medium, Pioneer 10 became the first mission to detect interplanetary atoms of helium. It also observed high-energy ions of aluminum and sodium in the solar wind. On July 15, 1972, Pioneer 10 was the first spacecraft to enter the asteroid belt, located between the orbits of Mars and Jupiter. The project planners expected a safe passage through the belt, and the closest the trajectory would take Pioneer 10 to any of the known asteroids was  (). One of the nearest approaches was to the asteroid 307 Nike on December 2, 1972.

The on-board experiments demonstrated a deficiency of particles below a micrometer (μm) in the belt, as compared to the vicinity of the Earth. The density of dust particles between 10–100 μm did not vary significantly during the trip from the Earth to the outer edge of the belt. Only for particles with a diameter of 100 μm to 1.0 mm did the density show an increase, by a factor of three-fold in the region of the belt. No fragments larger than a millimeter were observed in the belt, indicating these are likely rare; certainly much less common than anticipated. As the spacecraft did not collide with any particles of substantial size, it passed safely through the belt, emerging on the other side about February 15, 1973.

အာကာသနက်
150px|thumb|နေစကြဝဠာအပြင်ဘက်မှ ပိုင်အိုနီးယား ၁ဝ ၏ အနုပညာရှင်လက်ရာ

Pioneer 10 crossed the orbit of Saturn in 1976 and the orbit of Uranus in 1979. On June 13, 1983, Pioneer 10 crossed the orbit of Neptune, becoming the first man-made object to leave the proximity of the major planets of our solar system. The mission came to an official end on March 31, 1997, when it had reached a distance of 67 AU from the Sun, though the spacecraft was still able to transmit coherent data after this date.

Analysis of the radio tracking data from the Pioneer 10 and 11 spacecraft at distances between 20–70 AU from the Sun has consistently indicated the presence of a small but anomalous Doppler frequency drift. The drift can be interpreted as due to a constant acceleration of  directed towards the Sun. Although it is suspected that there is a systematic origin to the effect, none was found. As a result, there is sustained interest in the nature of this so-called "Pioneer anomaly". Extended analysis of mission data by Slava Turyshev and colleagues has determined the source of the anomaly to be asymmetric thermal radiation. In July 2012, the Pioneer anomaly was explained as a thermal recoil force (heat escaping) acting on the face of the Pioneers away from the Sun.Support for the thermal origin of the Pioneer anomaly , Slava G. Turyshev et al, Physical Review Letters, accepted 11 April 2012, accessed 19 July 2012

After March 31, 1997, Pioneer 10'''s weak signal continued to be tracked by the Deep Space Network to aid the training of flight controllers in the process of acquiring deep space radio signals. There was an Advanced Concepts study applying chaos theory to extract coherent data from the fading signal.

The last successful reception of telemetry was received from Pioneer 10 on April 27, 2002; subsequent signals were barely strong enough to detect, and provided no usable data. The final, very weak signal from Pioneer 10 was received on January 23, 2003 when it was 12 billion kilometers (80 AU) from Earth."This Month in History", Smithsonian magazine, June 2003. Further attempts to contact the spacecraft were unsuccessful. The final attempt was made on the evening of March 4, 2006, the last time the antenna would be correctly aligned with Earth. No response was received from Pioneer 10''. NASA decided that the RTG units had probably fallen below the power threshold needed to operate the transmitter. Hence, no further attempts at contact were made.

 အချိန်ဇယား 
 ပျံသန်းသွားသည့် အချိန်ဇယား နေ့စွဲ ဖြစ်ရပ်   အာကာသယာဉ်အား ပစ်လွှတ်ခဲ့သည်  အင်္ဂါဂြိုဟ်ပတ်လမ်းအား ဖြတ်သွား  ဥက္ကာခဲခါးပတ်သို့ ဝင်ရောက်  ဂျူပီတာအား စတင်လေ့လာ
 နေ့စွဲ ဖြစ်ရပ်   Encounter with Jovian system  Callisto flyby at 1,392,300 km  Ganymede flyby at 446,250 km  Europa flyby at 321,000 km  Io flyby at 357,000 km   Jupiter closest approach at 200,000 km  Jupiter equator plane crossing  Io occultation entry  Io occultation exit  Jupiter occultation entry  Jupiter shadow entry  Jupiter occultation exit  Jupiter shadow exit  အစီစဉ် ရပ်တန့်  ပိုင်အိုနီးယား ကြယ်တာရာခရီး စတင်
 ပို၍  The US Post Office issued a commemorative stamp featuring the Pioneer 10 space probe (See image).  Crossed orbit of Pluto, still defined as a planet at the time (Pluto's irregular orbit meant it was closer to the Sun than Neptune).  Crossed orbit of Neptune, the furthest planet away from the Sun at the time, to become the first man-made object to depart the solar system.  End of mission. Contact is maintained with spacecraft to record telemetry.  Voyager 1 overtakes Pioneer 10 as the most distant man-made object from the Sun, at 69.419 AU. Voyager 1 is moving away from the Sun over 1 AU per year faster than Pioneer 10.  Successful reception of telemetry. 39 minutes of clean data received from a distance of 79.83 AU  Last successful reception of telemetry. 33 minutes of clean data received from a distance of 80.22 AU  Final signal received from the spacecraft. Reception was very weak and subsequent signals were barely strong enough to detect.  Unsuccessful attempt to contact spacecraft  Pioneer 10 was projected to be 89.7 AU, traveling at a velocity of 12.51 kilometers/second (28,000 miles/hour), which is approximately 0.000041 the speed of light.  Projections indicate that Pioneer 10 reached 100 AU. At this point, the spacecraft is approximately 271,000 AU from the nearest star, Proxima Centauri.

လက်ရှိ အခြေနေ
၂ဝ၁၂ ခုနှစ် စက်တင်ဘာလ ၉ ရက်နေ့တွင် ပိုင်အိုနီးယား ၁ဝ သည် ကမ္ဘာမြေမှ ၁ဝ၆.၆၉၆ AUအကွာ၊ နေမှ ၁ဝ၆.၆၇၆AU အကွာသို့ ရောက်ရှိခဲ့ပြီး နေနှင့်နှိုင်းကာ တစ်စက္ကန့်လျင် ၁၂.ဝ၃၇ ကီလိုမီတာ (တစ်နာရီလျင် မိုင်ပေါင်း ၂၆၉၃ဝ)၊ တစ်နှစ်လျင် ၂.၅၃၉ AU နှုန်းဖြင့် ပျံသန်းလျက်ရှိသည်။ 
ပိုင်အိုနီးယား ၁ဝ သို့နေရောင်ခြည်ရောက်ရှိရန် ၁၄.၇၉ နာရီကြာမြင့်မည်ဖြစ်သည်။ အာကာသယာဉ်မှ နေမင်း၏ တောက်ပနှုန်းသည် -၁၆.၆ ဖြစ်သည်။ ပိုင်အိုနီးယား ၁ဝ သည် ကြယ်စုတန်း တောရပ်ဆီသို့ ဦးတည်နေသည်။ 

အကယ်၍ အနှောက်အယှက်မရှိပါက ပိုင်အိုနီးယား ၁ဝ နှင့် ညီအစ်မ ပိုင်အိုနီးယား ၁၁ တို့သည် ဗွိုင်ယေဂျာ အာကာသယာဉ်နှင့် ပူးပေါင်းကာ ကြယ်တာရာခရီးအား ဆက်လက်ပြီး ပျံသန်းပါလိမ့်မည်။ ယာဉ်လမ်းကြောင်းသည်  Aldebaran ဆိုသည့်ကြယ်ဆီသို့ ဦးတည်နေသည်။ ယင်းကြယ်သည် အလင်းနှစ် ၆၈ နှစ်အကွာတွင် တည်ရှိသည်။ အကယ်၍ ယင်းကြယ်သည် အလျင်သုညရှိမည်ဆိုပါက ယာဉ်အနေဖြင့် ထိုကြယ်ဆီသို့ ရောက်ရှိရန် နှစ်သိန်းပေါင်း ၂ ခုကြာမြင့်ပေလိမ့်မည်။

 အခြား ကြည့်ရန် 
  ကာစီနီ-ဟိုင်ဂင်အာကာသယာဉ်
 New Horizons, Jupiter flyby
 ပိုင်အိုးနီးယား ၁၁
 ဗွိုင်ယေဂျာ ၁  & ဗွိုင်ယေဂျာ ၂, Jupiter flybys

 ကျမ်းကိုး 

Bibliography

 ပြင်ပ လင့်များ 
 Pioneer Project Archive Page 
 Pioneer 10 Profile  by NASA's Solar System Exploration
 NSSDC Pioneer 10 page 
 A distant Pioneer whispers to Earth - CNN article, December 19, 2002
 2005 Pioneer Anomaly Conference - Mentions March 4, 2006 Contact Attempt

ကဏ္ဍ:ပိုင်အိုနီးယား စီမံကိန်း
ကဏ္ဍ:ဂျူပီတာဂြိုဟ်သို့ စေလွှတ်မှုများ
Category:နာဆာ စီမံကိန်းများ