Rubin 3-DSI [OHB]
Rubin 4-DSI [OHB] Rubin 5 similar
Official name RUBIN 4/SL-8
Alternative name Cosmos 3 second stage (S3) (Cosmos 3M (11K65M))
Cospar ID 2003-042B
Norad ID 27940
Launch date 2003-09-27
Launch site PKMTR
Launch vehicle Kosmos-3M
Country/Organization Germany
Type application Technology
Operator OHB-System
RCS size LARGE
Decay date ON ORBIT
Period (min) 98.15
Inclination (deg) 98.31
Perigee (km) 662
Apogee (km) 679
Eccentricity 0.0126771066368382
Mean motion (revs. per day) 14.6714212939378
Semi-Major axis (km) 7048.635
Raan (deg) 281.8027
Arg of perigee (deg) 252.875
Shape Cyl
Mass (kg) 1479
Diameter (m) 2.4
Height (m) 4.2
Span (m^2) 4.2
Lifetime 3 years (#3)
Contractors OHB-System
Propulsion none (in orbit)
Configuration Experiment container bolted to Kosmos-3M second stage
Power Batteries

The mission goal of Rubin-3-DSI (DSI = dopolnitel'naya sistema izmereniya = Additional Measurement System) is to test the launch vehicle tracking possibilities outside the launch site telemetry system visibility areas. The most important ascent status parameters are transmitted via the Orbcomm constellation in near real time mode directly to the customer via e-mails (payload separation confirmation, flight event time etc).

The orbital telematics experiment Rubin-4-DSI is located on the upper stage of the Kosmos-3M and transmits information on the rocket's acceleration, vibration load and position. Rubin will transmit this information to earth via e-mail using the Orbcomm satellite communications system. In this way, it will be possible to track the rocket in orbit reliably and without any data loss.

Satellite COSPAR Date LS Launch Vehicle Remarks
RUBIN 3/SL-8 2002-054C 2002-11-28 PKMTR Kosmos-3M with Mozhayets 3, AlSat 1
RUBIN 4/SL-8 2003-042B 2003-09-27 PKMTR Kosmos-3M with STSAT 1, Bilsat 1, NigeriaSat 1, UK-DMC 1, Mozhayets 4, Larets