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

---

Transtar

---

Status: Development completed 1987. Thrust: 16.70 kN (3,754 lbf). Unfuelled mass: 76 kg (167 lb). Specific impulse: 328 s. Height: 1.27 m (4.16 ft).

The Transtar system was an upper stage engine using injector(s), chamber, and nozzle derived from the OMS system. These propellants are pump-fed which increase chamber pressure and Isp. They also permit the use of low-pressure lightweight tanks.. Manufacturer: Aerojet Propulsion Division. Applications: upper stage. Mounting: gimbaled ( 10 degrees by two electromechanical actuators. Mixture Ratio: 1.8:1. Cooling Method: fuel regenerative for chamber, radiative for extension. Burn Time: not available, 15 starts.

Engine: 76 kg (167 lb). Chamber Pressure: 23.80 bar. Area Ratio: 132. Thrust to Weight Ratio: 22.36.