Rus-M

Rus-M

Function	Human-rated orbital launch vehicle
Manufacturer	TsSKB-Progress
Country of origin	Russia
Size
Height	61.1 m
Diameter	11.6 m
Mass	673,000 kg
Stages	2
Capacity
Payload to LEO	23,800 kg
Launch history
Status	Cancelled
Launch sites	Vostochny Cosmodrome
Total launches	0
First stage
Engines	3 RD-180
Thrust	4.15 MN (933,400 lbf) each
Specific impulse	338 sec
Burn time
Fuel	LOX / RP-1
Second stage
Engines	4 RD-0146
Thrust	392.4 kN
Specific impulse	463 sec
Burn time
Fuel	LOX / LH2

Rus-M was a proposed launcher design which was intended to become Russia's main launch vehicle for crewed spaceflight after 2018, and an integral part of the Prospective Piloted Transport System which included a new manned spacecraft being developed to replace the Soyuz.

Rus-M was being developed by TsSKB-Progress, beginning in 2009. The program was halted in October 2011; "We have come to the conclusion that we do not need a new rocket, we can continue using those we already have," said Vladimir Popovkin, head of Russia's space agency, according to the Novosti news agency. According to the CEO of TsNIIMash, the rocket is to be ready in 2018.

History

In spring of 2009 TsSKB-Progress won a government contract to develop a new launcher for Russia's human space program. The project was featured in MAKS 2009 Airshow, and preliminary design of the vehicle was expected to be submitted to the Russian space agency Roskosmos by August 2010.

Requirements

Safety requirements put forward by Roscosmos emphasized that the launcher design is to be extremely reliable; safe abort options for crewed vehicles must be available at any stage of flight, and vehicle departure from the launch pad must be guaranteed for the case of an emergency during an early stage of the launch sequence. The launcher was planned to provide a basis for a future heavy launcher capable to carry a payload of 50—60 tons, as well as for a super-heavy design lifting 130—150 tons.

Description

As of 2009, Rus-M was to use three Energomash RD-180 kerosene and liquid oxygen engines for its first stage and four RD-0146 hydrogen/oxygen engines developed by Chemical Automatics Design Bureau for its upper stage. It would have been able to lift a cargo or satellite payload of 23.8 tons to a 200-km, 51.7-degree circular orbit, a crew vehicle of 18.8 tons to a 135 by 400-km orbit, 7.0 tons to geostationary transfer orbit and 4.0 tons to geostationary orbit.

Development

TsSKB Progress was responsible for overall project leadership, system integration, second stage development and production. First stage development was to be led by Makeev KB Mash, while NPO Avtomatiki was to provide the rocket's flight control system.

See also

• Comparison of orbital launch systems

External links

• Launch vehicle for PPTS spacecraft