| Country of origin | China |
|---|---|
| First flight | 1995-11-28 |
| Designer | China Hexi Chemical and Machinery Corporation |
| Application | Kick engine |
| AssociatedLV | Long March 2E |
| Status | Out of production |
| Solid-fuel motor | |
| Propellant | AP /HTPB |
| Casing | Fiberglass |
| Performance | |
| Thrust, vacuum | 190 kN (43,000 lbf) |
| Specific impulse, vacuum | 293 s (2.87 km/s) |
| Total impulse | 1.589 MN (357,000 lbf) |
| Burn time | 87s |
| Dimensions | |
| Length | 2,936 mm (115.6 in) |
| Diameter | 1,700 mm (67 in) |
| Empty mass | 557 kg (1,228 lb) |
| Used in | |
| Long March 2E EPKM | |
| References | |
| References | [1][2][3] |
TheFG-46 (a.k.a.EPKM andSpaB-170) is a Chinesespin stabilizedsolidrocket motor burningHTPB-basedcomposite propellant.[4] It was developed byChina Hexi Chemical and Machinery Corporation (also known as the 6th Academy ofCASIC) for use in theLong March 2E onGTO missions. It first flew as a prototypeSPTS-M14 on July 16, 1990 on theBadr A mission. It had its first commercial mission orbiting theAsiaSat 2 on November 28, 1995 and exactly one month later, on December 28 its second and last mission forEchoStar 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 aspecific impulse of 292 seconds burning for 87 seconds, with a total impulse of 1.589 MN (357,000 lbf). It is spin stabilized at 40rpm 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]
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| Solid fuel |
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