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During the 1990s CALT developed an improved version of the DF-4 to test the reentry vehicle warheads of the DF-31.[6][7][8] They took advantage of this development and offered it as the Long March 1D for commercial application. The modifications included:

  • An DF-4 improved first stage, which used the new version of the YF-2B, and switched propellants to UDMH/N2O4 for improved performance.
  • The replacement of the DF-4 second stage motor YF-3A. The proposed replacement was the Long March 4 third stage engine, the YF-40.
  • A new inline inter-stage would replace the existing tapered connector between the second and third stages, which allowed for an additional 70cm diameter to be added to the third stage skirt. This would allow for the addition of RCS to the third stage.
  • A new third stage with a new motor, the FG-36 and an optional RCS.
  • A new computer inertial guidance system which enabled the third stage to be 3-axis stabilised for added precision.[1][3]
Long March 1D[1][2][3][4]
FunctionOrbital launch vehicle
ManufacturerCALT
Country of originChina
Size
Height28.22 m (92.6 ft)
Diameter2.25 m (7.4 ft)
Mass81,650 kg (180,010 lb)
Stages3
Capacity
Payload to LEO930 kg (2,050 lb)
Associated rockets
FamilyLong March 1
ComparableMu 1-3-4
Launch history
StatusRetired
Launch sitesTaiyuan LC-1
Total launches3
Successes2
Failures1
First flight1995-06-01
Last flight2002-01-03
Notable payloadsreentry vehicle tests
First stage
Length18.20 m (59.7 ft)
Diameter2.25 m (7.4 ft)
Empty mass4,100 kg (9,000 lb)
Gross mass65,000 kg (143,000 lb)
Propellant mass61,100 kg (134,700 lb)
Engines1 YF-2B (4 x YF-1B)[5]
ThrustSL: 1,101.2 kN (247,600 lbf)
Vac: 1,214.4 kN (273,000 lbf)
Specific impulseSL: 242.5 seconds (2.378 km/s)
Vac: 267.4 seconds (2.622 km/s)
Burn time131.5 seconds
FuelUDMH/N2O4
Second stage
Length6.04 m (19.8 ft)
Diameter2.25 m (7.4 ft)
Empty mass1,620 kg (3,570 lb)
Gross mass14,000 kg (31,000 lb)
Propellant mass12,380 kg (27,290 lb)
Engines2 YF-40[5]
Thrust98.1 kN (22,100 lbf)
Specific impulse295.2 seconds (2.895 km/s)
Burn time365 seconds
FuelUDMH/N2O4
Third stage
Length1.7 m (5.6 ft)
Diameter2.05 m (6.7 ft)
Empty mass665 kg (1,466 lb)
Gross mass1,315 kg (2,899 lb)
Propellant massMain: 650 kg (1,430 lb)
RCS: 147 kg (324 lb)
EnginesMain: FG-36 SRM
RCS: DaFY2-1 monopropellant thrusters[5]
Thrust44 kN (9,900 lbf)
Specific impulse289 seconds (2.83 km/s)
Burn time43 seconds
FuelMain: HTPB
RCS: hydrazine

The new design did not had a good reception and was only used for reentry vehicle tests. It flew three suborbital missions from Taiyuan LC-1 with two successes and a failure on the final mission. The first launch was on June 1, 1995 and the second one was on November 1997. The final and failed on was on January 3, 2002.[9][10][11]

ReferencesEdit

  • Data from Aerospace China magazine
  1. ^ a b Norbert Bgügge. "Chang Zheng CZ-1 & CZ-1D". B14643.DE. Retrieved 2015-07-25.
  2. ^ "CZ-1D". Encyclopedia Astronautica. Archived from the original on 2013-12-30. Retrieved 2015-07-25.
  3. ^ a b "Chang Zheng-1". SinoDefence. Archived from the original on 2015-07-16. Retrieved 2015-07-25.
  4. ^ Norbert Bgügge. "DF-4 & CZ-1 Design". B14643.DE. Retrieved 2015-07-25.
  5. ^ a b c Norbert Bgügge. "Propulsion CZ-1 & CZ-1D". B14643.DE. Retrieved 2015-07-25.
  6. ^ Norbert Bgügge. "The Chinese DF-3 missile". B14643.DE. Archived from the original on 2015-10-17. Retrieved 2015-07-25.
  7. ^ "Dong Feng-3 (CSS-2)". SinoDefence. Archived from the original on 2015-11-23. Retrieved 2015-07-25.
  8. ^ "Dong Feng-4 (CSS-3)". SinoDefence. Archived from the original on 2015-11-23. Retrieved 2015-07-25.
  9. ^ "CZ-1". Encyclopedia Astronautica. Retrieved 2015-07-25.
  10. ^ "CZ-1". Encyclopedia Astronautica. Archived from the original on 2013-12-03. Retrieved 2015-07-25.
  11. ^ Gunter Dirk Krebs. "CZ-1 (Chang Zheng-1)". Gunter's Space Page. Retrieved 2015-07-25.

External linksEdit