Long March 6

The Long March 6 (Chinese: 长征六号运载火箭) or Chang Zheng 6 as in pinyin, abbreviated LM-6 for export or CZ-6 within China, is a Chinese liquid-fuelled launch vehicle of the Long March family, which was developed by the China Aerospace Science and Technology Corporation (CASC) [7] and the Shanghai Academy of Spaceflight Technology (SAST). The rocket was developed in the 2000s, and made its maiden flight in 2015.[8] As one of the new generation rocket family, the Long March 6 was designed to be a light capacity, "high-speed response" rocket, complementing the heavy lift Long March 5 and the mid-heavy lift Long March 7 rocket families. It is capable of placing at least 1,000 kg (2,200 lb) of payload into a Sun-synchronous orbit.[9][8] The first stage of the Long March 6 was derived from the booster rockets being developed for the Long March 5 rocket. It is powered by a YF-100 engine, which generates 1,340 kN (300,000 lb_f) of thrust from burning kerosene and LOX as rocket fuel and oxidiser.[8] This was the first flight of the new engine design.[3]

Long March 6

Maiden flight of Long March 6 rocket
Function	Small launch vehicle
Manufacturer	Shanghai Academy of Spaceflight Technology [1]
Country of origin	China
Size
Height	29 m (95 ft)
Diameter	3.35 m (11.0 ft)
Mass	103,000 kg (227,000 lb)
Stages	3 [2]
Capacity
Payload to 700 km (430 mi) SSO
Mass	1,080 kg (2,380 lb)
Associated rockets
Family	Long March
Comparable	Minotaur-C, PSLV-CA
Launch history
Status	Active
Launch sites	Taiyuan, LA-16
Total launches	4
Success(es)	4
First flight	19 September 2015 [3]
Last flight	6 November 2020
First stage
Diameter	3.35 m (11.0 ft)
Propellant mass	61,000 kg (134,000 lb) to 76,000 kg (168,000 lb)
Engines	1 YF-100
Thrust	1,188 kN (267,000 lbf) [4]
Specific impulse	300 seconds (sea level) 335 seconds (vacuum) [5]
Fuel	RP-1/LOX
Second stage
Diameter	2.25 m (7 ft 5 in)
Propellant mass	15,000 kg (33,000 lb)
Engines	1 YF-115
Thrust	180 kN (40,000 lbf) [4]
Specific impulse	341.5 seconds (vacuum) [6]
Fuel	RP-1/LOX
Third stage
Diameter	2.25 m (7 ft 5 in)
Engines	1
Thrust	6.5 kN (1,500 lbf) [4]
Specific impulse	306.9 seconds
Fuel	N2O4 / UDMH[4]

A boosted variant, with a payload of 4000 kg to Sun-synchronous orbit, is under development.