Win the adventure of a lifetime!

UNITED24 - Make a charitable donation in support of Ukraine!

Space


CZ-4 Space Launch Vehicle

The third currently operational series in the CZ family is the CZ-4 (also referred to as the CZ-4A) which has been employed for inserting payloads into sun-synchronous orbits. The CZ-4 is a 3-stage launch vehicle carrying UDMH and nitrogen tetroxide for all stages. The CZ-4 first stage uses the same power plant as the CZ-3A but is nearly two meters taller. Likewise, the CZ-4 second stage is similar to that of the CZ-3A. The CZ-4 third stage is a specially designed unit powered by the YF-40 main engine. The payload capacity of the CZ-4 into a sun-synchronous orbit is cited as 2.5 metric tons (References 159, 189-190).

The Long March 4 is a three-stage launch vehicle with storable propellant. The LM-4 is developed and manufactured by the Shanghai Academy of Spaceflight Technology. Its first stage is essentially the same as that of the LM-3 and the second stage is identical to that of the LM-3. The LM-4's third stage, however, is newly developed, featuring a thin wall common intertank bulkhead tankage and two-engine cluster with both engines gimbling about two perpendicular axes. The 3rd stage engine cluster connects to the tank aft bulkhead through the engine bay. The LM-4 has two payload fairing configurations: Type-A and Type-B.

The LM-4 is suitable for launching different kinds of polar and sun-synchronous satellites. The LM-4's typical payload capability is 1,650kg for a 600km SSO and 4,680kg for a 200km circular orbit.

On September 7, 1988, the LM-4 made its first flight, successfully injecting China's first experimental meteorological satellite into a predetermined SSO. Another meteorological satellite was successfully launched by an LM-4 on September 3, 1990.

CZ-4A

CZ-4B

LM-4

Background Information
First Launch:
1988
Flight Rate:
2-3 per year?
Launch Site:
Taiyun Space Launch Center, China
Capability:

History

  • Chinese rocket program started in the late 1950s
  • Evolved from Chinese surface-to-surface series IRBMs
  • LM-4A is a three-stage version of the LM-2D

Description

  • Three-stage liquid fueled vehicle
  • Stage 1 consists of four YF-20 motors burning UDMH/N2O4 providing a total thrust of 626,000 lb
  • Stage 2 uses one YF-22 engine and four YF-23 verniers burning UDMH/N2O4 for a total thrust of 171,300 lb
  • Stage 3 uses one YF-40 burning UDMH/N2O4

Profile

Length:
131 ft
Launch Weight:
421,000 lb
Diameter:
11 ft
Liftoff Thrust:
626,000 lb
Payload Fairing:
31.0 ft x 11.0 ft

Stage

1st

2nd

3rd

Mass of Propellant (t)

182

35.4

14.3

Propellant

N2O4/UDMH

Engine

YF-21B

DaFY-20

YF-40

Engine Trust (kN)

2962

742(main) 46.1(Vernier)

100.85

Engine Specific Impulse (N.Sec/kg)

2550

2910(Main) 2762(Vernier)

2971

Diameter (m)

3.35

2.90

Lift-off Mass (t)

249

Overall Length (m)

44.156(Type A) 45.776(Type B)

Fairing Diameter (m)

2.90(Type A) 3.35(Type B)




NEWSLETTER
Join the GlobalSecurity.org mailing list



 
Page last modified: 21-07-2011 00:50:09 ZULU