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.
|
|
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.
|
Preparation of the orbital station for mating with the Proton launch vehicle.
|
|
The Proton launch vehicle with the first Zarya orbital station, which was called Salyut in the press, on the launch pad.
|
The Salyut-4 orbital station on the mounting bogie.
|
|
|
The Salyut-4 orbital station.
|
|
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.
|
The Soyuz type spacecraft in its assembly jig.
|
|
Emergency Descent System Operating Sequence During Ascent
|
|
|
|
|
|
|
Backup parachute system activation
|
|
 |
 |
 |
 |
|
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).
|
|
|
The Soyuz T spacecraft descent vehicle at the landing site.
|
|
|
Operation of the Soyuz spacecraft landing complex.
|
|
|
Descent on primary parachute system
|
|
|
Eject cover, deploy braking parachute
|
|
|
Descent on braking parachute
|
|
|
Discard braking parachute and deploy main parachute
|
|
|
Descent on reefed main parachute
|
|
|
Discard frontal heat shield
|
|
|
Prelanding operations descent on main parachute
|
|
|
Fire soft landing engines
|
|
|
Landing, release chute cords
|
|
|
Descent on reserve parachute system
|
|
|
|
 |
|
Descent on reefed reserve parachute
|
|
|
Discard of frontal heat shield
|
|
|
Prelanding operations. descent on reserve parachute
|
|
|
|
|
Fire soft landing engines
|
|
|
Stages of the Salyut orbital station development
|
|
|
The Salyut-6 orbital station (second generation station) had two docking assemblies to which the transport and cargo spacecraft could be docked.
|
|
 |
|
|
|
|
|
|
|
Crew. men.
|
2-4
|
|
Orbital flight time, days no more than
|
180
|
|
Overall manned flight time with life support resources for two crew men, days
|
95-110
|
|
Flight time of one transport spacecraft attached to station. days
|
5-60
|
|
Orbital parameters attitude. KM
|
350
|
|
inclination.
|
51.6
|
|
Attitude precision.
orbital system coordinates
|
-30-50
|
|
inertial system coordinates (utilizing AO-1 or S-2)
|
-10-20
|
|
|
|
Solar array average daily capacity (dependant on position in orbit and station attitude ) KW
|
1-3
|
|
Length orbital station (with 2 spacecraft). M
|
28,55
|
|
Maximum diameter of the station orbital module. M
|
4.15
|
|
Total mass station
(after docking with 2 spacecraft). T
|
-32
|
|
Mass of research and experiment equipment, T no more than
|
2.5
|
|
Transport spacecraft:
for docking from transfer compartment side
|
N*39,40
|
|
for docking from propulsion module side
|
N■41,42
|
|
|
|
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
|
|
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..
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.
|
|
 |
|
|
|
|
The I I AS 11Y launch vehicle with the 7K.-ST (SoyuzT) spacecraft.
 |
|
|
 |
|
|
|
|
|
Launch vehicle
|
11А511У
|
11А511У-2
|
|
Initial orbital parameters:
|
|
|
|
|
inclination, …*
|
51.6
|
|
64.8
|
|
altitude (average). KM
|
|
220
|
|
|
Lift-off mass, T:
|
|
|
|
|
carrier stage and nose fairing with payload
|
3097
|
|
ЗЮ.0
|
|
spacecraft
|
6.855
|
|
6 740
|
|
Crew, men
|
2-3
|
|
2-3
|
|
Number stages on launch vehicle
|
|
3
|
|
|
Stage 1
|
module A. B.V. G.D
|
|
|
Stage 2
|
|
module A
|
|
|
Stage 3
|
|
module 1
|
|
|
Fuel component
|
|
|
|
|
module A
|
oxygen
|
♦ oxygen t
|
|
kerosene
|
|
cycline
|
|
module B. V.G. D,I
|
oxygen ♦ kerosene
|
|
Maximum engine thrust TC
|
|
|
|
|
Stage 1
|
|
|
|
|
on Earth
|
413.3
|
|
420 0
|
|
in vacuum
|
505.3
|
|
509 5
|
|
Stage 2 – in vacuum
|
99.7
|
|
103.1
|
|
Stage 3 – in vacuum
|
|
30.4
|
|
|
Length of launch vehicle and
|
|
|
|
|
nose fairing with payload
|
51.1
|
|
51.3
|
|
Maximum transverse dimensions. M
|
|
10.3
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
|
 |
|
The launch vehicle with the Progress spacecraft.
|
|
|
The Progress cargo spacecraft.
|
|
|
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
|
|
 |
 |
|
|
Yuri Pavlovich Semenov
General Director and General Designer of S. P. Korolev NPO Energia since 1989
