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The FG-36 was a Chinese spin stabilized apogee kick motor burning HTPB-based composite propellant. It was developed by China Hexi Chemical and Machinery Corporation for use in the Fengyun 2 satellite bus for insertion into GSO orbit.
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The S5.80 is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the Soyuz-TMA-M spacecraft propulsion module KTDU-80, and its sibling, the S5.79 rocket engine, is still used as the main propulsion of the Zvezda ISS module. The S5.80 generates 2.95 kN (660 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of 302 s (2.96 km/s). It is rated for 30 starts with a total firing time of 890 seconds. The engine, without the pressurization system or propellant tanks, weighs 310 kg (680 lb) and is an integrated unit that is 1.2 m (47 in) long with a diameter of 2.1 m (83 in).
References
- 1 2 3 Norbert Bgügge. "Some Chinese solid fuel aerospace motors". B14643.DE. Archived from the original on 2015-09-26. Retrieved 2015-07-25.
- 1 2 "Chapter 2.4 — CTS Introduction". LM-2C User's Manual. Issue 1999. CASC. 1999. pp. 2–15. Retrieved 2015-07-08.
- ↑ "CZ-2C/SD". Encyclopedia Astronautica. Archived from the original on 2016-03-04. Retrieved 2015-07-25.
- ↑ "SpaB-54". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-07-25.
- ↑ Norbert Bgügge. "Propulsion CZ-2E, CZ-2F". B14643.DE. Retrieved 2015-07-25.
- ↑ Krebs, Gunter Dirk (2013-09-21). "CZ-2C (2) SD (Chang Zheng-2C (2) SD)" . Retrieved 2015-07-25.
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