|ဤဆောင်းပါးကို မြန်မာဘာသာသို့ ပြန်ဆိုရန် လိုအပ်နေသေးသည်။
Soyuz spacecraft (TMA version)
|မူလနိုင်ငံ||ဆိုဗီယက် ယူနီယံ ရုရှား|
|အော်ပရေတာ||Soviet space program/Russian Federal Space Agency|
|အသုံးအဆောင်များ||Carry cosmonauts to orbit and back; originally intended for Soviet Moonshot|
|ဒီဇိုင်းသက်တမ်း||Up to six months docked to station|
|Regime||ကမ္ဘာပတ်လမ်းနိမ့် circumlunar spaceflight during early program)|
|ပထမဆုံး ပစ်လွှတ်||Soyuz 1, 1967|
ဆိုယုဇ် (ရုရှား: Сою́з, IPA: [sɐˈjus]), Union)အာကာသယာဉ်တွဲသည် အစဦးက ၁၉၆၀တွင် ကိုရိုယက်ဗ်ဒီဇိုင်းအဖွဲ့ က ဆိုဗီယက်အာကာသစီမံကိန်း အတွက် ဒီဇိုင်းရေးဆွဲခဲ့ခြင်းဖြစ်ပြီး ယခုအချိန်ထိဆက်လက်သုံးစွဲလျက်ရှိသည်။ ဆိုယုဇ်သည် ဗော့စတော့အာကာသယာဉ်ကိုအမွေဆက်ခံပြီး မူလက ဆိုဗီယက်လကမ္ဘာသို့လူလွှတ်ရေးစီမံကိန်း၏အစိတ်အပိုင်းတစ်ခုဖြစ်သည်။
ဆိုယုဇ်အာကာသယာဉ်ကို ရုရှားတို့၏အားအကိုးရဆုံးသော၊ မကြာခဏအသုံးပြုလေ့ရှိသောဆိုယုဇ်ဒုံးပျံဖြင့်ပစ်လွှတ်သည်။  The Soyuz rocket design is based on the Vostok launcher, which in turn was based on the 8K74 or R-7A Semyorka, a Soviet intercontinental ballistic missile. Soyuz spacecraft are launched from the Baikonur Cosmodrome in Kazakhstan.
The first unmanned Soyuz mission was launched November 28, 1966; the first Soyuz mission with a crew (Soyuz 1) was launched April 23, 1967, but the cosmonaut on board, Vladimir Komarov, died during the flight's crash-landing. Soyuz 2 was an unmanned mission, and Soyuz 3, launched on October 26, 1968, was the first successful Soyuz manned mission. The only other fatal mission, Soyuz 11, killed the crew of three also during re-entry due to premature cabin depressurization. Despite these early fatalities, Soyuz is presently widely considered the world's safest, most cost-effective human spaceflight system as demonstrated by its unparalleled length of operational history.
Soyuz spacecraft were used to carry astronauts to and from Salyut and later Mir Soviet space stations, and are now used for transport to and from the International Space Station (ISS). At least one Soyuz spacecraft is docked to ISS at all times for use as an escape craft in the event of an emergency.
- ၁ ဒီဇိုင်း
- ၂ Variants
- ၃ Related craft
- ၄ Operators
- ၅ အခြားကြည့်ရန်
- ၆ ဓါတ်ပုံများ
- ၇ ကိုကား
- ၈ ပြင်ပလင့်
- A spheroid ဂြိုဟ်ပတ်မော်ဂျူး, which provides accommodation for the crew during their mission;
- A small aerodynamic reentry module, which returns the crew to Earth;
- A cylindrical service module with solar panels attached, which contains the instruments and engines.
ဂြိုဟ်ပတ်မော်ဂျူးနှင့်အထိန်းမော်ဂျူးတို့မှာတစ်ခါသုံးဖြစ်ပြီး လေထုထဲပြန်လည်ဝင်ရောက်လာချိန်တွင်ပျက်စီးသွားသည်။ The orbital and reentry portions are habitable living space. By moving as much equipment as possible into the orbital module, which does not have to be shielded or decelerated during atmospheric re-entry, the Soyuz is both larger and lighter than the contemporary Apollo spacecraft's command module. The Apollo command module had more than six cubic meters (6.2 m³) of living space and a mass of 5000 kg; the three-part Soyuz (command, orbital and service modules) provides the same crew (since the Soyuz T in 1980) with more than seven cubic meters of living space (5 m³ in OM, plus 2.5 m³ in RM), an airlock, and a service module for the mass of the Apollo capsule alone (mass of empty Soyuz was 5600 kg). On the other hand Apollo was operating with three astronauts in spacesuits and was able to land with five astronauts in spacesuits in 1973 (prepared rescue mission for second Skylab crew), Soyuz was for two cosmonauts in spacesuits in the 1960s and 1970s, and for three since 1980 (Soyuz T). On nine Apollo missions (9 through 17) the astronauts also had access to the Lunar Module, which added 6.7 cubic meters of volume but also another 2200 kg of mass (if counting just the empty ascent stage as being somewhat equivalent to the Soyuz orbital module, although including empty fuel tanks, engine and RCS system — 14700 kg when including the descent stage and fuel).
ဆိုယုဇ်ယာဉ်သည် လူသုံးဦးတင်ဆောင်နိုင်ပြီး လူတစ်ယောက်အတွက်ရက်ပေါင်း၃၀စာ ရိက္ခာသယ်ဆောင်နိုင်သည်။ The life support system provides a nitrogen/oxygen atmosphere at sea level partial pressures. The atmosphere is regenerated through KO2 cylinders, which absorb most of the CO2 and water produced by the crew and regenerates the oxygen, and LiOH cylinders which absorb leftover CO2.
The vehicle is protected during launch by a nose fairing, which is jettisoned after passing through the atmosphere. It has an automatic docking system. The ship can be operated automatically, or by a pilot independently of ground control.
The forepart of the spacecraft is the orbital module (Russian: бытовой отсек (БО); Bytovoi otsek (BO)), also known as Habitation section. It houses all the equipment that will not be needed for reentry, such as experiments, cameras or cargo. The module also contains a toilet, docking avionics and communications gear. Internal volume is 6 m³, living space 5 m³. On the latest Soyuz versions (since Soyuz TM), a small window was introduced, providing the crew with a forward view.
A hatch between it and the descent module can be closed so as to isolate it to act as an airlock if needed, crew members exiting through its side port (near the descent module). On the launch pad, the crew enter the spacecraft through this port.
This separation also lets the orbital module be customized to the mission with less risk to the life-critical descent module. The convention of orientation in zero gravity differs from that of the descent module, as crew members stand or sit with their heads to the docking port.
Separation of the Orbital Module is critical for a safe landing. Without separation of the OM it is not possible for the crew to survive landing – that’s why the orbital module was separated before the ignition of the return engine. After the issue with the landing of Soyuz TM-5 in September 1988 this procedure was changed and the OM is separated after the return maneuver, which is more dangerous. Also the rescue of the crew whilst on the launch pad or with SAS system is complicated because of the orbital module.
အဆင်းမော်ဂျူး (ရုရှဘာသာအားဖြင့်: спускаемый аппарат (СА); Spuskaemyi apparat (SA)) is used for launch and the journey back to Earth. Half of the reentry module is covered by a heat-resistant covering to protect it during re-entry; this half faces the Earth during re-entry. It is slowed initially by the atmosphere, then by a braking parachute, followed by the main parachute which slows the craft for landing. At one meter above the ground, solid-fuel braking engines mounted behind the heat shield are fired to give a soft landing. One of the design requirements for the reentry module was for it to have the highest possible volumetric efficiency (internal volume divided by hull area). The best shape for this is a sphere, but such a shape can provide no lift, which results in a purely ballistic reentry. Ballistic reentries are hard on the occupants due to high deceleration and cannot be steered beyond their initial deorbit burn. That is why it was decided to go with the "headlight" shape that the Soyuz uses—a hemispherical forward area joined by a barely angled conical section (seven degrees) to a classic spherical section heat shield. This shape allows a small amount of lift to be generated due to the unequal weight distribution. The nickname was thought up at a time when nearly every headlight was circular. Small dimensions of the reentry module led to it having only two-man crews after the death of the Soyuz 11 crew. The later Soyuz T spacecraft solved this issue. Internal volume of Soyuz SA is 4 m³; 2.5 m³ is usable for crew (living space).
At the back of the vehicle is the service module (Russian: приборно-агрегатный отсек (ПАО); Priborno-Agregatnyi Otsek (PAO)). It has a pressurized container shaped like a bulging can (Instrumentation compartment, PO (Priborniy Otsek) that contains systems for temperature control, electric power supply, long-range radio communications, radio telemetry, and instruments for orientation and control. A non-pressurized part of the service module (Propulsion compartment, AO (Agregatniy Otsek)) contains the main engine and a liquid-fuelled propulsion system for maneuvering in orbit and initiating the descent back to Earth. The ship also has a system of low-thrust engines for orientation, attached to the Intermediate compartment (PkhO or Perekhodnoi Otsek). Outside the service module are the sensors for the orientation system and the solar array, which is oriented towards the sun by rotating the ship. An incomplete separation between the Service and Reentry modules led to emergency situations during Soyuz 5, Soyuz TMA-10 and Soyuz TMA-11, which led to an incorrect reentry orientation (crew ingress hatch first). The failure of several explosive bolts did not cut the connection between the Service/Reentry modules on the latter two flights.
The Soyuz uses a method similar to the Apollo Command/Service modules to de-orbit itself. The spacecraft is turned engine-forward and the main engine is fired for de-orbiting fully 180° ahead of its planned landing site. This requires the least propellant for re-entry, the spacecraft traveling on an elliptical Hohmann orbit to a point where it will be low enough in the atmosphere to re-enter.
Early Soyuz spacecraft would then have the service and orbital modules detach simultaneously from the reentry module. As they are connected by tubing and electrical cables to the reentry module, this would aid in their separation and avoid having the descent module alter its orientation. Later Soyuz spacecraft detached the orbital module before firing the main engine, which saved propellant. Since the Soyuz TM-5 landing issue, the orbital module is once again detached only after the re-enter firing, which led to (but not caused) emergency situations of Soyuz TMA-10 and TMA-11. The orbital module cannot remain in orbit as an addition to a space station, as the airlock hatch between the orbital and reentry modules is a part of reentry module, and the orbital module therefore depressurizes after separation.
Re-entry firing is usually done on the "dawn" side of the earth, so that the spacecraft can be seen by recovery helicopters as it descends in the evening twilight, illuminated by the sun when it is above the shadow of the Earth. The Soyuz craft is designed to come down on land, usually somewhere in the deserts of Kazakhstan in central Asia. This is in contrast to early US manned missions which "splashed down" in the ocean.
- Thermal Control System—Sistema Obespecheniya Teplovogo Rezhima, SOTR
- Life Support System—Kompleks Sredstv Obespecheniya Zhiznideyatelnosti, KSOZh
- Power Supply System—Sistema Elektropitaniya, SEP
- Communication and Tracking Systems—Rassvet (Dawn) radio communications system, Onboard Measurement System (SBI), Kvant-V spacecraft control, Klyost-M television system, Orbit Radio Tracking (RKO)
- Onboard Complex Control System—Sistema Upravleniya Bortovym Kompleksom, SUBK
- Combined Propulsion System—Kompleksnaya Dvigatelnaya Ustanovka, KDU
- Chaika-3 Motion Control System (SUD)
- 'Optical/Visual Devices (OVP)—VSK-4 (Vizir Spetsialniy Kosmicheskiy-4),Night Vision Device (VNUK-K, Visir Nochnogo Upravleniya po Kursu), Docking light, Pilot's Sight (VP-1, Vizir Pilota-1), Laser Range Finder (LPR-1, Lazerniy Dalnomer-1)
- Kurs rendezvous system
- Docking System—Sistema Stykovki i Vnutrennego Perekhoda, SSVP
- Teleoperator Control Mode—Teleoperatorniy Rezhim Upravleniya, TORU
- Entry Actuators System—Sistema Ispolnitelnikh Organov Spuska, SIO-S
- Landing Aids Kit—Kompleks Sredstv Prizemleniya, KSP
- Portable Survival Kit—Nosimiy Avariyniy Zapas, NAZ, containing a TP-82 or other pistol
- Soyuz Launch Escape System—Sistema Avariynogo Spaseniya, SAS
- ဂြိုဟ်ပတ်မော်ဂျူး (A)
- 1 ဆိုက်ကပ်စက်ပိုင်းများ
- 2 ကားစ်အင်တင်နာ
- 4 ကားစ်အင်တင်နာ
- 3 ရုပ်သံထုတ်လွှင့်သည့်အင်တင်နာ
- 5 ကင်မရာ
- 6 နောက်ဖုံး
- 7 လေထီးခန်း
- 9 ချောင်းကြည့်ပေါက်
- 11 အပူကာဒိုင်း
- အထိန်းမော်းဂျူး (C)
- 10 and 18 အမြင့်ထိန်းအင်ဂျင်များ
- 21 အောက်ဆီဂျင်အိုး
- 12 ကမ္ဘာအာရုံခံကိရိယာ
- 13 နေအာရုံခံကိရိယာ
- 14 နေရောင်ဖမ်းပြားချိတ်ရန်ငုတ်များ
- 16 ကားစ်အင်တင်နာ
- 15 အပူအာရုံခံကိရိယာ
- 17 ပင်မတွန်းကန်အား
- 20 လောင်စာအိုး
- 19 ဆက်သွယ်ရေးအင်တင်နာ
The Soyuz spacecraft has been the subject of continuous evolution since the early 1960s. Thus several different actual versions, proposals and projects exist.
|Version:||Soyuz A (1963)||Soyuz 7K-OK (1967–1971)||Soyuz 7K-L3 (LOK)||Soyuz 7K-T (1973–1981)||Soyuz 7K-TM (1975)||Soyuz-T (1976–1986)||Soyuz-TM (1986–2002)||Soyuz-TMA (2003–2012 )||Soyuz TMA-M (2010–.... )|
|Mass (kg)||5 880||6 560||9 850||6 800||6 680||6 850||7 250||7 220||7 150|
|Max Diameter (m)||2 .50||2 .72||2 .930||2 .72||2 .72||2 .72||2 .72||2 .72||2 .72|
|Span (m)||?||9 .80||?||9 .80/–||8 .37||10 .6||10 .6||10 .7||10 .7|
|Orbital Module (BO)|
|Mass (kg)||1 000||1 100||-||1 350||1 224||1 100||1 450||1 370|
|Length (m)||3 .00||3 .45||2 .26||2 .98||3 .10||2 .98||2 .98||2 .98|
|Diameter (m)||2 .20||2 .25||2 .3||2 .26||2 .26||2 .26||2 .26||2 .26|
|Volume (m³)||2 .20||5 .00||-||5 .00||5 .00||5 .00||5 .00||5 .00|
|Reentry module (SA)|
|Mass (kg)||2 480||2 810||2 804||2 850||2 802||3 000||2 850||2 950|
|Length (m)||2 .30||2 .24||2 .19||2 .24||2 .24||2 .24||2 .24||2 .24|
|Diameter (m)||2 .17||2 .17||2 .2||2 .17||2 .17||2 .17||2 .17||2 .17|
|Volume (m³)||4 .00||4 .00||-||3 .50||4 .00||4 .00||3 .50||3 .50|
|Service module (PAO)|
|Mass (kg)||2 400||2 650||-||2 700||2 654||2 750||2 950||2 900|
|Usable mass (kg)||830||500||3152||500||500||700||880||880|
|Length (m)||2 .10||2 .26||2 .82||2 .26||2 .26||2 .26||2 .26||2 .26|
|Diameter (m)||2 .50||2 .72||2 .2||2 .72||2 .72||2 .72||2 .72||2 .72|
Soyuz 7K (part of the 7K-9K-11K circumlunar complex) (1963)[ပြင်ဆင်ရန်]
Korolyov initially promoted the Soyuz A-B-V circumlunar complex (7K-9K-11K) concept (also known as L1) in which a two-man craft Soyuz 7K would rendezvous with other components (9K and 11K) in Earth orbit to assemble a lunar excursion vehicle, the components being delivered by the proven R-7 rocket.
The manned Soyuz spacecraft can be classified into design generations. Soyuz 1 through Soyuz 11 (1967–1971) were first-generation vehicles, carrying a crew of up to three without spacesuits and distinguished from those following by their bent solar panels and their use of the Igla automatic docking navigation system, which required special radar antennas. This first generation encompassed the original Soyuz 7K-OK and the Soyuz 7K-OKS for docking with the Salyut 1 space station. The probe and drogue docking system permitted internal transfer of cosmonauts from the Soyuz to the station.
The Soyuz 7K-L1 was designed to launch a crew from the Earth to circle the moon, and was the primary hope for a Soviet circumlunar flight. It had several test flights in the Zond program from 1967–1970 (Zond 4 to Zond 8), which produced multiple failures in the 7K-L1's re-entry systems. The remaining 7K-L1s were scrapped. The Soyuz 7K-L3 was designed and developed in parallel to the Soyuz 7K-L1, but was also scrapped. Soyuz 1 was plagued with technical issues, and cosmonaut Vladimir Komarov was killed when the spacecraft crashed during its return to Earth. This was the first in-flight fatality in the history of spaceflight.
The next manned version of the Soyuz was the Soyuz 7K-OKS. It was designed for space station flights and had a docking port that allowed internal transfer between spacecraft. The Soyuz 7K-OKS had two manned flights, both in 1971. Soyuz 11, the second flight, depressurized upon re-entry, killing its three-man crew.
It was developed out of the military Soyuz concepts studied in previous years and was capable of carrying 2 cosmonauts with Sokol space suits (after the Soyuz 11 accident). Several models were planned, but none actually flew in space. These versions were named Soyuz 7K-P, Soyuz 7K-PPK, Soyuz R, Soyuz 7K-VI, and Soyuz OIS (Orbital Research Station).
Soyuz 7K-TM was the spacecraft used in the Apollo-Soyuz Test Project in 1975, which saw the first and only docking of a Soyuz spacecraft with an Apollo spacecraft. It was also flown in 1976 for the earth-science mission, Soyuz 22. Soyuz 7K-TM served as a technological bridge to the third generation.
The third generation Soyuz-T (T: транспортный, Transportnyi meaning transport) spacecraft (1976–1986) featured solar panels allowing longer missions, a revised Igla rendezvous system and new translation/attitude thruster system on the Service module. It could carry a crew of three, now wearing spacesuits.
The Soyuz-TM crew transports (M: модифицированный, Modifitsirovannyi meaning modified) were fourth generation Soyuz spacecraft, and were used from 1986 to 2003 for ferry flights to Mir and the International Space Station.
Soyuz-TMA (2003–2012 )[ပြင်ဆင်ရန်]
Soyuz TMA (A: антропометрический, Antropometricheskii meaning anthropometric) features several changes to accommodate requirements requested by NASA in order to service the International Space Station, including more latitude in the height and weight of the crew and improved parachute systems. It is also the first expendable vehicle to feature "glass cockpit" technology. Soyuz-TMA looks identical to a Soyuz-TM spacecraft on the outside, but interior differences allow it to accommodate taller occupants with new adjustable crew couches.
Soyuz TMA-M (2010/....)[ပြင်ဆင်ရန်]
In 2004, Russian space officials announced that they intended to replace Soyuz with the new Kliper and Parom spacecraft by early 2011. Since then, Kliper appears to have been indefinitely postponed due to lack of government funding. It has since been announced that the Soyuz will use a new digital interior displays and updated docking equipment. This new version, known as Soyuz TMA-M, debuted on 7 October 2010 with the launch of TMA-01M, carrying the ISS Expedition 25 crew.
Soyuz ACTS (2012/....)[ပြင်ဆင်ရန်]
Soyuz ACTS (Advanced Crew Transportation System), also known as Soyuz-K, is a proposed version of the Soyuz design capable of achieving lunar orbit. The upgrades could include a new habitation module developed by the European Space Agency. A novel, rocket-based precision landing system may also be implemented. Missions could be launched from Baikonur or Guiana Space Centre.
The unmanned Progress spacecraft were derived from Soyuz and are used for servicing space stations.
General Electric published their Apollo D-2 in December 1961 at the American Astronautical Society symposium in Denver, CO. This American design has many similarities to the early Russian spacecraft designs.
||This section contains a gallery of images.|
|ဤ ဆောင်းပါးသည် စိစစ်အတည်ပြုနိုင်ရန်အတွက် နောက်ထပ်ကိုးကားချက်များ လိုအပ်နေသည်။ (September 2007)|
- Soyuz launch vehicle: The most reliable means of space travel, ESA
- France and Russia agree: Soyuz will launch from Kourou in French Guyana, SpaceRef
- Russia thriving again on the final frontier, MSNBC
- Zak၊ Anatoly (2011-06-30)။ PTK NP 2011။ Anatoly Zak။ 5 October 2011 တွင် ပြန်စစ်ပြီး။
- Lunar Orbital Spacecraft (LOK)
- Soyuz 100 Times More Reliable Than Shuttle။ Spacedaily.com။ 2012-04-27 တွင် ပြန်စစ်ပြီး။
- Anatoly Zak။ "Russia mulls rocket power 'first'"၊ BBC၊ 29 April 2009။
- Advanced Crew Transportation System, ACTS
- Russia New Russian spaceship will be able to fly to Moon - space corp
- RSC Energia: Concept Of Russian Manned Space Navigation Development
- Mir Hardware Heritage
- Information on Soyuz spacecraft
- OMWorld's ASTP Docking Trainer Page
- NASA - Russian Soyuz TMA Spacecraft Details
- Space Adventures circum-lunar mission - details
- ရုပ်ရှင်ဇတ်လမ်းတိုအား Four in the Cosmos (1969) Internet Archive တွင် အခမဲ့ ဒေါင်းလုတ်ဆွဲနိုင်သည်။
- Russian space agency video of roll-out and launch.
- Apollo D-2 Proposal by General Electric, Encyclopedia Astronautica