Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
AVUM
N2O4/UDMH propellant rocket stage. The AVUM propulsion module was composed of a UDMH/NTO bipropellant main engine with a re-ignition capability and a cold gas attitude control system, based on two clusters of three thrusters, each having a 50 N thrust.

Status: In production. Thrust: 2.45 kN (551 lbf). Gross mass: 650 kg (1,430 lb). Unfuelled mass: 150 kg (330 lb). Specific impulse: 315 s. Burn time: 317 s. Height: 1.74 m (5.70 ft). Diameter: 1.90 m (6.20 ft). Span: 1.90 m (6.20 ft).

The AVUM upper stage performed the following functions:

  • roll control during second, third and fourth stage flights
  • attitude control during coasting phase
  • correction of axial velocity error due to solid rocket motor
  • performance scatter
  • generation of the required velocity change for orbit circularization
  • satellite pointing
  • payload(s) release maneuvers

The AVUM avionics module provided the following services:

  • flight control and mission management
  • telemetry
  • localization and neutralization
  • power supply and distribution



Country: Italy. Propellants: N2O4/UDMH.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z
© 1997-2017 Mark Wade - Contact
© / Conditions for Use