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
Topaze
Topaze
Topaze
SEP N2O4/UDMH rocket engine. Out of production. Used on Diamant launch vehicle. First flight 1965.

Status: Out of production. Number: 4 . Thrust: 120.10 kN (27,000 lbf). Gross mass: 3,000 kg (6,600 lb). Unfuelled mass: 306 kg (674 lb). Specific impulse: 255 s. Specific impulse sea level: 225 s. Burn time: 39 s. Height: 7.10 m (23.20 ft). Diameter: 0.80 m (2.62 ft). Apogee: 80 km (49 mi).

Thrust (sl): 106.000 kN (23,829 lbf). Thrust (sl): 10,804 kgf. Engine: 306 kg (674 lb). Thrust to Weight Ratio: 40.0163398692811.



Subtopics

Topaze VE111-1 N2O4/UDMH propellant rocket stage.

Topaze VE111L-1 N2O4/UDMH propellant rocket stage.

Diamant-2 N2O4/UDMH propellant rocket stage. .

Soleil NA803 Nord solid rocket engine. 2200 kg Isolane propellant. Stretched version of the NA802. Used on Topaze launch vehicle. First flight 1964.

Soleil Mammouth French solid rocket engine. 1500 kg Isolane propellant. Used on Topaze launch vehicle. First flight 1962.

Family: Storable liquid. Country: France. Launch Vehicles: Diamant. Propellants: N2O4/UDMH. Stages: Diamant-2.

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