Strela (UR-100N)

NPO Mashinostroyenya

Die Strela ist eine modifizierte UR-100N aus dem zur Konversion freigegebenen militärischen Arsenal. Die Strela wird von NPO Mashinostroyenya (Rußland) entwickelt und auch selbst vermarktet. Bisher sind jedoch noch keine Buchungen bekannt.
Die Strela ist mit der Rockot verwandt. Sie hat wie diese die gleiche zweistufige Basis-Konfiguration. Die erste Stufe ist mit vier Einkammertriebwerken RD-0233 und die zweite mit einem einzelnen Triebwerk RD-0235 bestückt. Als Treibstoffe werden UDMH/Distickstofftetroxid verwendet. Die Startmasse des Launchers beträgt 105 t. Die max. Länge beträgt 29,20 m, der Durchmesser 2,50 m. Als Nutzlast können bis 1,7 t in einen LEO transportiert werden.
Als Nutzlastverkleidungen werden zwei Fairings angeboten, die Ladungen von 2,70 bzw. 4,60 m Länge bei 2,20 bzw. 1,55 m Durchmesser aufnehmen können.
Der erste Test-Start einer Strela mit einer Nutzlast (Kondor-E mockup) wurde am 05.12.2003 absolviert.


The Strela launch vehicle is based on a decommissioned Russian missile, like Rockot, but is marketed by a different organization. NPO Mashinostroyenya was given permission by the Russian government to market the UR-100N under the name Strela. Unlike Rockot, the Strela configuration apparently involves minimal changes to the UR-100N hardware, with only minor flight software changes for orbital missions. Strela does not use the Breeze upper stage.
The sole new component incorporated into the design of  Strela compared to its prototype is the measuring equipment compartment of the ascent unit. The new compartment sized 2.4 m in diameter and 0.55 m in height accommodates the equipment required to provide telemetry and ground-supported trajectory measurements, the 1st and 2nd stage booster emergency cutoff system, the auxiliary coast flight phase stabilization system (with RD-237) and the power supply equipment. The ascent unit that contains the measuring equipment compartment and the payload support pad can be protected optionally by two different fairings.

Strela launch vehicle (LV) is a liquid two-stage missile of light class with the mechanisms and instruments section which functions as a booster section . Strela LV is designed for injection of payloads of up to 2000 kg mass into the earth-centered orbits or upper atmosphere layers.The launch vehicle is designed through a tandem scheme with the cross separation of stages. The take-off mass is roughly 105 tons, maximum length is 29.2 m and diameter is 2.5 m. The launch vehicle consists of booster section, mechanisms and instruments section, space head section. Booster section of UR-100N ICBM is used as two first stages with no modifications.
The mechanisms and instruments section (MIS) is designed for accommodation of the autonomous control system with the onboard power source and propulsion plant, which energy can be used during the boost phase after separation from the second stage booster or in the apogee of the ascending trajectory. Thus, MIS functions as an expendable booster section.
Strela LV can be equipped with one of two types of space head sections (SHS-1 or  SHS-2) with different nose caps and as a result the different areas of payload accommodation.
The nose fairing consists of two halves made of metal sheet with transverse and longitudinal ribs. The altitude of nose fairing cap jettison is dictated by the requirements for the altitude of spacecraft injection, restrictions of the spacecraft exposure to heat and lies within 110…150 km. To reduce a heat flow coming to the spacecraft during boost phase the inner surface of the cap is covered with thermal insulation material.
Application of a concrete type of the space head section is dictated by the features of the payload to be injected into orbit. In all cases the space head section includes:

• instrumentation compartment with adapter ;
• mating stage;
• nose fairing;
• spacecraft;

In the process of exploitation Strela LV is placed in the transporting and launching container. It is launched from a silo launcher. The main cosmodrome for Strela LV launches is Svobodny. The first launch of LV Strela is scheduled for 2003 year.
From Tyuratam, the Strela would be able to enter the orbit with the inclination 62.8 degrees toward the Equator delivering around 1,400 kilograms of payload to the altitude of about 200 kilometers. Around 500 kilograms could be boosted to the altitude of 1,800 kilometers with the same inclination.
When flying from Svobodny, the Strela would be able to access a wide range of orbits with the inclinations from around 52 to 61 degrees and near-polar orbits from 90 to 97 degrees toward the Equator. Under 1,600 kilograms could be inserted into a 200-kilometer orbit with the inclination 51.8 degrees and 1,110 kilograms could be boosted to the Sun-synchronous orbit, overflying North and South poles of Earth.

The first test flight
2003 Dec. 5: After years of delays, the Strela booster flew its first orbital mission from Tyuratam. The vehicle blasted off from the underground silo facility. The rocket then successfully delivered its payload into a 404 by 465-kilometer orbit with the inclination 67 degrees.