![Development of Orbital Stations Development of Orbital Stations](/img/1243/image275.png)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image278.jpg)
The Soyuz transport spacecraft (of 7K-T type) docked to the Salyut station.
The first longterm orbital station (DOS – 7K had only one docking assembly.
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Crew, men 3
Orbital module flight time, days, no more than 90
Total autonomous flight time for transport spacecraft, days, no more than 3
Total flight time transport vehicle, days, no more than
As part of DOS-7K #1, 2 30
As part of DOS-7K#3. 4 cn
Orbital parameters
Inclination 51.6U±5‘
Initial orbit for orbital module
Perigee 220±4,5
apogee 260±11
Orbit of orbital module
After ascent, KM 255
Assembly orbit, KM 190-220
Thrust, KGF
Primary engine 417H5
Backup engine 411 ±25
Length, M
Orbital module 16
Orbital station 23
Maximum diameter orbital module, M 4,15
Total mass station after docking. KG 24 900
Mass scientific research instruments and equipment, KG, no more than 1500
The Salyut orbital station on the mounting bogie.
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image281_0.jpg)
Preparation of the orbital station for mating with the Proton launch vehicle.
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![Development of Orbital Stations Подпись:](/img/1243/image282.png)
The Proton launch vehicle with the first Zarya orbital station, which was called Salyut in the press, on the launch pad.
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image284_1.jpg)
The Salyut-4 orbital station on the mounting bogie.
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The Salyut-4 orbital station.
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image285.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image288_0.jpg)
![Development of Orbital Stations Подпись: 200-350](/img/1243/image289.png)
Orbital parameters,
altitude. KM inclination, penod, min
The Soyuz-type transport spacecraft (7K-T) used to supply the first generation orbital stations.
The Soyuz-IO spacecraft (7K-T) and subsequent craft had docking assemblies with a central transfer hatch through which cosmonauts could transfer from one spacecraft to the other without egressing into space.
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image291_0.jpg)
The Soyuz type spacecraft in its assembly jig.
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Emergency Descent System Operating Sequence During Ascent
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Backup parachute system activation
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The Soyuz descent vehicle landing. The descent vehicle was about 3 tons in mass, and 2.2 meters in diameter (over thermal protection). Its configuration is similar to a "head-light" (the lift-to-drag ratio was 0.30).
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The Soyuz T spacecraft descent vehicle at the landing site.
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image296_0.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image297_0.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image298.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image131.png)
Operation of the Soyuz spacecraft landing complex.
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Descent on primary parachute system
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Eject cover, deploy braking parachute
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Descent on braking parachute
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Discard braking parachute and deploy main parachute
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Descent on reefed main parachute
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Discard frontal heat shield
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Prelanding operations descent on main parachute
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Fire soft landing engines
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Landing, release chute cords
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Descent on reserve parachute system
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image299.png) |
Descent on reefed reserve parachute
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Discard of frontal heat shield
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Prelanding operations. descent on reserve parachute
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Fire soft landing engines
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image300_0.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image301.png)
Stages of the Salyut orbital station development
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The Salyut-6 orbital station (second generation station) had two docking assemblies to which the transport and cargo spacecraft could be docked.
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Crew. men.
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2-4
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Orbital flight time, days no more than
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180
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Overall manned flight time with life support resources for two crew men, days
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95-110
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Flight time of one transport spacecraft attached to station. days
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5-60
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Orbital parameters attitude. KM
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350
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inclination.
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51.6
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Attitude precision.
orbital system coordinates
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-30-50
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inertial system coordinates (utilizing AO-1 or S-2)
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-10-20
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Solar array average daily capacity (dependant on position in orbit and station attitude ) KW
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1-3
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Length orbital station (with 2 spacecraft). M
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28,55
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Maximum diameter of the station orbital module. M
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4.15
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Total mass station
(after docking with 2 spacecraft). T
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-32
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Mass of research and experiment equipment, T no more than
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2.5
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Transport spacecraft:
for docking from transfer compartment side
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N*39,40
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for docking from propulsion module side
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N■41,42
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Scope of work on orbital module
1 Propulsion module manufacturing with docking assembly and peripheral propulsion unit
based on article 11F32
2 Installation of additional set of "IGLA" antennas
3 Addition of secondary docking system control module
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image305_0.jpg)
The Salyut-6 orbital station (second generation station) had two docking assemblies to which the transport and cargo spacecraft could be docked.
The Salyut-6 orbital station with the docked SoyuzT spacecraft in flight..
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image306_0.jpg)
The Salyut-7 orbital station with the docked SoyuzT spacecraft in flight.
The Salyut-7 orbital station with the Cosmos-686 cargo spacecraft in automatic flight mode.
The Soyuz T transport spacecraft with solar arrays.
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image309.png) |
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The I I AS 11Y launch vehicle with the 7K.-ST (SoyuzT) spacecraft.
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image312.png) |
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image313.png) |
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Launch vehicle
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11А511У
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11А511У-2
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Initial orbital parameters:
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inclination, …*
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51.6
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64.8
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altitude (average). KM
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220
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Lift-off mass, T:
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carrier stage and nose fairing with payload
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3097
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ЗЮ.0
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spacecraft
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6.855
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6 740
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Crew, men
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2-3
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2-3
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Number stages on launch vehicle
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3
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Stage 1
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module A. B.V. G.D
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Stage 2
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module A
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Stage 3
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module 1
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Fuel component
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module A
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oxygen
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♦ oxygen t
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kerosene
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cycline
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module B. V.G. D,I
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oxygen ♦ kerosene
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Maximum engine thrust TC
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Stage 1
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on Earth
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413.3
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420 0
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in vacuum
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505.3
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509 5
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Stage 2 – in vacuum
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99.7
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103.1
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Stage 3 – in vacuum
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30.4
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Length of launch vehicle and
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nose fairing with payload
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51.1
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51.3
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Maximum transverse dimensions. M
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10.3
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image314.png) |
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image315.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image316.png)
The launch vehicle with the Progress spacecraft.
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The Progress cargo spacecraft.
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Mass spacecraft. KM 7020
Delivered payload weight. KG -2300
including:
in cargo module. KG. not more than 1300 in propellant module, KG not more than 1000
Maximum length. M 7,94
Maximum diameter
pressurized module. M 22
Launch vehicle "Soyuz“
Flight time. days, not more than:
autonomous 3
with orbital station 30
Orbital parameters
altitude. KM 200-350
inclination. 51.6
period, min
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image317.png) |
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image318.png) |
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![Development of Orbital Stations Development of Orbital Stations](/img/1243/image319_0.jpg)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image320.png)
![Development of Orbital Stations Development of Orbital Stations](/img/1243/image321_0.jpg)
Yuri Pavlovich Semenov
General Director and General Designer of S. P. Korolev NPO Energia since 1989