Long March 1D

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Long March 1D[1][2][2][3][4]
Function Orbital launch vehicle
Manufacturer CALT
Country of origin China
Size
Height 28.22 m (92.6 ft)
Diameter 2.25 m (7.4 ft)
Mass 81,650 kg (180,010 lb)
Stages 3
Capacity
Payload to LEO 930 kg (2,050 lb)
Associated rockets
Family Long March 1
Comparable Mu 1-3-4
Launch history
Status Retired
Launch sites Taiyuan LC-1
Total launches 3
Successes 2
Failures 1
First flight 1995-06-01
Last flight 2002-01-03
Notable payloads reentry vehicle tests
First stage
Length 18.20 m (59.7 ft)
Diameter 2.25 m (7.4 ft)
Empty mass 4,100 kg (9,000 lb)
Gross mass 65,000 kg (143,000 lb)
Propellant mass 61,100 kg (134,700 lb)
Engines 1 YF-2B (4 x YF-1B)[5]
Thrust SL: 1,101.2 kN (247,600 lbf)
Vac: 1,214.4 kN (273,000 lbf)
Specific impulse SL: 242.5 seconds (2.378 km/s)
Vac: 267.4 seconds (2.622 km/s)
Burn time 131.5 seconds
Fuel UDMH/N2O4
Second stage
Length 6.04 m (19.8 ft)
Diameter 2.25 m (7.4 ft)
Empty mass 1,620 kg (3,570 lb)
Gross mass 14,000 kg (31,000 lb)
Propellant mass 12,380 kg (27,290 lb)
Engines 2 YF-40[5]
Thrust 98.1 kN (22,100 lbf)
Specific impulse 295.2 seconds (2.895 km/s)
Burn time 365 seconds
Fuel UDMH/N2O4
Third stage
Length 1.7 m (5.6 ft)
Diameter 2.05 m (6.7 ft)
Empty mass 665 kg (1,466 lb)
Gross mass 1,315 kg (2,899 lb)
Propellant mass Main: 650 kg (1,430 lb)
RCS: 147 kg (324 lb)
Engines Main: FG-36 SRM
RCS: DaFY2-1 monopropellant thrusters[5]
Thrust 44 kN (9,900 lbf)
Specific impulse 289 seconds (2.83 km/s)
Burn time 43 seconds
Fuel Main: HTPB
RCS: hydrazine

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 modification 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 use switch of the second stage YF-3A, for the Long March 4 third stage engine, the YF-40.
  • A new, cylinder interstage between the second and third stage, which enabled to add RCS to the third stage. The olde one was tapered.
  • 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 stabilized for added precision.[1][3]

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]

References[edit]

  • Data from Aerospace China magazine
  1. ^ a b Norbert Bgügge. "Chang Zheng CZ-1 & CZ-1D". B14643.DE. Retrieved 2015-07-25. 
  2. ^ a b "CZ-1D". Encyclopedia Astronautica. Retrieved 2015-07-25. 
  3. ^ a b "Chang Zheng-1". SinoDefence. 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. Retrieved 2015-07-25. 
  7. ^ "Dong Feng-3 (CSS-2)". SinoDefence. Retrieved 2015-07-25. 
  8. ^ "Dong Feng-4 (CSS-3)". SinoDefence. Retrieved 2015-07-25. 
  9. ^ "CZ-1". Encyclopedia Astronautica. Retrieved 2015-07-25. 
  10. ^ "CZ-1". Encyclopedia Astronautica. Retrieved 2015-07-25. 
  11. ^ Gunter Dirk Krebs. "CZ-1 (Chang Zheng-1)". Gunter's Space Page. Retrieved 2015-07-25. 

External links[edit]