Country of origin | China |
---|---|
First flight | 1997-09-01 |
Designer | China Hexi Chemical and Machinery Corporation |
Application | Kick engine |
Associated LV | Long March 2C CTS |
Status | In Production |
Solid-fuel motor | |
Propellant | AP / HTPB |
Performance | |
Thrust, vacuum | 9.8 kN (2,200 lbf) |
Specific impulse, vacuum | 288 s (2.82 km/s) |
Total impulse | 353 kN (79,000 lbf) |
Burn time | 36s |
Dimensions | |
Length | 852 mm (33.5 in) |
Diameter | 542 mm (21.3 in) |
Used in | |
CTS | |
References | |
References | [1] [2] [3] |
The FG-47 (a.k.a. SpaB-54) is a Chinese solid rocket motor burning HTPB-based composite propellant. [1] [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 2C SD/CTS/SMA third stage. It had its inaugural flight on the Iridium-MFS demonstration mission on September 1, 1997. [1] [2] [5] [6]
It has a total nominal mass of 160 kg (350 lb), of which 125 kg (276 lb) is propellant load. It has an average thrust of 9.8 kN (2,200 lbf) with a specific impulse of 288 seconds burning for 35 seconds, with a total impulse of 353 kN (79,000 lbf).
Country of origin | China |
---|---|
First flight | 1997-09-01 |
Designer | China Hexi Chemical and Machinery Corporation |
Application | Kick engine |
Associated LV | Long March 2C CTS |
Status | In Production |
Solid-fuel motor | |
Propellant | AP / HTPB |
Performance | |
Thrust, vacuum | 9.8 kN (2,200 lbf) |
Specific impulse, vacuum | 288 s (2.82 km/s) |
Total impulse | 353 kN (79,000 lbf) |
Burn time | 36s |
Dimensions | |
Length | 852 mm (33.5 in) |
Diameter | 542 mm (21.3 in) |
Used in | |
CTS | |
References | |
References | [1] [2] [3] |
The FG-47 (a.k.a. SpaB-54) is a Chinese solid rocket motor burning HTPB-based composite propellant. [1] [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 2C SD/CTS/SMA third stage. It had its inaugural flight on the Iridium-MFS demonstration mission on September 1, 1997. [1] [2] [5] [6]
It has a total nominal mass of 160 kg (350 lb), of which 125 kg (276 lb) is propellant load. It has an average thrust of 9.8 kN (2,200 lbf) with a specific impulse of 288 seconds burning for 35 seconds, with a total impulse of 353 kN (79,000 lbf).