Протон

Подготовил:
Головкин А.А. СМ12-41
Proton (UR-500 - Universal rocket, "Proton-K", "ProtonM") is a heavy-class launch vehicle designed to launch
automatic spacecraft into Earth orbit and further into
outer space. It is capable of launching cargoes up to 3.3
tons into geostationary orbit. Developed in 1961-1967
in a subdivision of the Khrunichev State Research and
Production Space Center, which was part of VN
Chelomey's OKB-52.
The original two-stage version of the
Proton carrier (UR-500) became one of
the first carriers of the medium-heavy
class, and the three-stage Proton-K the heavy one.
The Proton launch vehicle was the launch
vehicle for all Soviet and Russian orbital
stations Salyut-DOS and Almaz, modules
of the Mir and ISS stations, the planned
manned spacecraft TKS and L-1 / Zond
(Soviet lunar flight program ), as well as
heavy satellites for various purposes and
interplanetary stations.
The missile was developed both in combat
versions: a global orbital and intercontinental
ballistic missile (12,000 km) for hitting a superpowerful thermonuclear warhead (power - 150
megatons) of especially important targets
anywhere in the world, and in the version of a
carrier rocket for heavy satellites.
“Proton-M” is a heavy rocket
Head part:
Upper stage
+
spacecraft
Starting weight:
Third stage
Kilo
Kilo
Lagrange point
Rocket
height
Second stage
Kilo
Low space orbit
First stage
It is 1.5 times
more than the
mass of the ISS
Head fairing
Head fairing
Head fairing
Payload
Head fairing
Payload
Payload
Payload
Oxygen tank
Kerosene tank
Upper stage
Oxidizer tank
(N2O4)
Oxidizer tank
(N2O4)
Engines
Oxidizer tank
(N2O4)
Fuel tank
Fuel tank
Fuel tank
Fuel tank
Oxidizer tank (N2O4)
Engines
Engines
Engines
Engines
Engines
Oxidizer tank
(N2O4)
Proton
Oxidizer tank
(N2O4)
Oxidizer tank
(N2O4)
Oxidizer tank
(N2O4)
Fuel tank
Fuel tank
Fuel tank
Engines
Engines
Engines
Oxidizer tank
(N2O4)
Fuel tank
Fuel tank
Engines
Engines
Proton-M
Oxidizer tank
(N2O4)
Fuel tank
Oxidizer tank
(N2O4)
Fuel tank
Engines
Engines
Proton-K
Proton-K with
upper stage
Characteristic
Name
ДМ-2
ДМ-2М
ДМ-03
On Earth
3,2
In Space
2,3
2,2
Fuel
Sintin+liquid
oxygen
Sintin+liqui Sintin+liquid
d oxygen oxygen
Unsymmetrical
dimethylhydrazine
Fuel reserve
15,1
15,1
18,7
до 20
Main engine
11Д58М
11Д58С
11Д58М /
11Д58МДФ
14Д30
Thrust in vacuum
8,5
8,5
8,5
2
Specific impulse
360
361
361 / 367
329
Number of engine starts
Up to 5
Up to 5
Up to 5
Up to 8
2,4
2,5
2,95
Weight
Payload mass in GSO
Start of operation
«Proton-K»
3,245
«Бриз-М»
«Proton-М» (third stage)
1982
1994
2,35
2,5
3,44
3,7
2007
1999
PayLoad=40T
PayLoad=30T
Proton-M
PayLoad=35T
PayLoad=45T
Payload
Rocket
Numbers
The First flight of launches
per y.
Width
Starting
weight
LEO
GTO
GSO
Diametr
Success
Price of
ful
launch
flights
ProtonM
2001
8—12 (109) 46°
705
23
6,35
3,25
4,35
90
65—70[
Zenit 3SL
1999
4—5 (36)
0°
473
13,7
6,06
2,6
4,15
91
80
Ariane
5 ECA
2002
6 (74)
5°
780
20
10
5,4
97,2
220
Delta
IV Heavy
2004
1 (12)
35° и
28°
732
23
10,75
6,57
5,1
97,56
265
Delta IV
M+(5,4)[
2009
2—3 (8)
35° и
28°
399
13,5
5,5
3,12
5,1
97,56
170
2003
2 (2)
419
13,49
4,88
2,63
5,4
97
160
541
18,8
6,86
3,90
5,4
97
190
549
22,8
5,5—8,3
5,2
98,86
62
Atlas
V 521
Atlas V
551
Falcon 9
FT
Falcon
Heavy
2006
2015
35° и
28°
35° и
1 (3)
28°
35° и
18—26 (92)
28°
2018
1—2 (3)
28°
1421
63,8
8,0—
26,7
5,2
100
90—150
H-IIB
2009
2 (5)
30°
531
19
8
5,1
100
182
CZ-3B
1996
4 (22)
28°
426
11,2
5,1
4,2
91
50—70
2