PROTON-M Launch Vehicle
Companies & Organizations:
Rosoboronexport Open Joint Stock Company
27, Stromynka Street
Moscow, 107076
The Proton-M heavy-class launch vehicle is an upgraded version of the Proton-K. The LV is able to deliver payloads directly into designated geostationary orbit points, thus making possible the insertion of satellites which are not equipped with an apogee propulsion unit. It can lift-off from launch pads currently operational at the Baikonur Cosmodrome.
The Proton-M is designed as a tandem LV with transverse separation of stages. It is composed of three stages and spacehead with Breeze-M upper stage as forth stage. All stages of the LV and upper stage are fueled by hypergolic propellant components: unsymmetrical dimethyl hydrazine as fuel, and nitrogen tetroxide as oxidizer.
The Proton-M has a larger payload fairing as compared with Proton-K in order to double the space available for payloads. Upgrading (replacement) of the control system enables to improve power performance as well as operational and environment characteristics of the LV. The Breeze-M upper stage enables to deliver heavier payloads (up to 3.0-3.2 tonnes) into geostationary orbit.
Type LV liquid propellant, four-stage
Control system autonomous, inertial
LV liftoff mass, t
700
Length (without the upper stage), m
42.34
LV Span, m
7.4
Payload capacity, kg:
low Earth mass payload (h=200 km, i=51,6°)
22,000
low Earth mass payload (h=350 km, i=51,6°)
19,700
geostationary orbit mass payload
(h=36000 km, i=0±0,25°)
3,000-3,200
transfer orbit mass payload
(ha=36000 km, hп=5500 km, i=7-25°)
4,800-5,500
Lunar departure trajectory mass
up to 6,200
Mars departure trajectory mass
up to 5,000
Venus departure trajectory mass
up to 5,400
Injection accuracy:
altitude, km up to ±15
orbital period, sec up to ±8
inclination, angular min up to ±1.5
Payload space available, m3
98-150
Flight reliability
0.97