FG-46
Chinese solid rocket motor
The FG-46 (a.k.a. EPKM and SpaB-170 ) is a Chinese spin stabilized solid rocket motor burning HTPB -based composite propellant .[4] It was developed by China Hexi Chemical and Machinery Corporation (also known as the 6th Academy of CASIC ) for use in the Long March 2E on GTO missions. It first flew as a prototype SPTS-M14 on July 16, 1990 on the Badr A mission. It had its first commercial mission orbiting the AsiaSat 2 on November 28, 1995 and exactly one month later, on December 28 its second and last mission for EchoStar 1 .[1] [4] [5]
It has a total nominal mass of 6,001 kg (13,230 lb), of which 5,444 kg (12,002 lb) is propellant load and its burn out mass is 529 kg (1,166 lb). It has an average thrust of 190 kN (43,000 lbf) with a specific impulse of 292 seconds burning for 87 seconds, with a total impulse of 1.589 MN (357,000 lbf ). It is spin stabilized at 40 rpm and the propellant mass can be reduced by up to 350 kg (770 lb) eight months before launch or up to 15 kg (33 lb) on the launch site.[1]
References
Liquid fuel
Cryogenic
Hydrolox (LH2 / LOX )
China
Europe
India
Japan
Russia
USA
Methalox (CH4 / LOX )
Semi- cryogenic
Kerolox (RP-1 / LOX )
China
India
Russia
NK-15
NK-33, 44
RD-58
RD-0105, 0109
RD-0107, 0108, 0110
RD-0110R
RD-0124
RD-107, 108, 117, 118
RD-120
RD-170, 171
RD-180
RD-191, 151, 181
RD-193
S1.5400
Spain
Ukraine
USA
Storable
Hypergolic (Aerozine , UH 25 , MMH , or UDMH / N2 O4 , MON , or HNO3 )
China
Europe
India
Israel
North Korea
Russia
17D61
RD-0202 to 0206, 0208 to 0213
RD-0207, 0214
RD-0216, 0217, 0235
RD-0233, 0234
RD-0236
RD-0237
RD-0243 to 0245
RD-0255 to 0257
RD-215 to 219
RD-250 to 252, 261, 262
RD-253, 275
RD-263, 268, 273
RD-270
S5.92
S5.98M
Ukraine
USA
Other
Solid fuel
China
Europe
India
Iran
Israel
Japan
USA
* Different versions of the engine use different propellant combinations
Engines in italics are under development