The Microspace-2 aerospace launch system is designed for launching nanosatellites into a wide range of orbit altitudes (500 to 1000 km) and inclinations (0°-98°).
The Microspace-2 aerospace launch system comprises an aviation segment (Su-27 upgraded fighter interceptor, ground support facilities, airfield support facilities and systems) and a space launch segment (solid-propellant launch vehicle, onboard launch complex, technical facilities, data acuisition and processing system).
Initial launch conditions:
Velocity: 500 m/s
Altitude: 15 km
Vehicle velocity angle with respect to local horizon: 10…40°
BASIC SPECIFICATIONS
Number of stages
3
Dimensions, mm
Length
Stages diameter
Stage 1
Stage 2
Stage 3
Fairing diameter
7710
1271
982
860
860
Launch mass, tons
6,6
Propellants
Stage 1
Stage 2
Stage 3
НТРВ
ТР-Н-3340
ТР-Н-3340
Thrust, ton-force
Stage 1
Stage 2
Stage 3
16,297
5,739
3,280
Payload capability into sun-synchronous orbit, kg
40
Payload fairing cleanliness class (FED STD 209E)
100 000
SU-27 BASIC SPECIFICATIONS
Wing span, m
14,7
Length, m
21,94
Height, m
5,93
Maximum takeoff mass, kg
30000-33000
Maximum fuel weight (in internal tanks), kg
9900-10000
Maximum velocity, km/h
2500
Operational ceiling, m
18500
Operational range, km
3680
Maximum load, kg
8000
