CTS (rocket stage)

CTS
ManufacturerCALT
Country of originChina
Used onLong March 2C third stage
General characteristics
Height0.9 m (35 in)[1]
Diameter0.54 m (21 in)[1]
Gross mass160 kg (350 lb)[1]
Propellant mass121.7 kg (268 lb)[1]
Associated stages
Derived fromSD
DerivativesSMA
Launch history
Total launchesSD: 7
CTS: 2
SMA: 2
Successes
(stage only)		SD: 7
CTS: 2
SMA: 2
Failed0
Lower stage
failed		0
First flightSD: 1997-09-01
CTS: 2003-12-29
SMA: 2008-09-06
Last flightSD: 1999-06-12
CTS: 2004-07-26
SMA: 2012-10-14
CTS
Powered by1 FG-47 SRM[2][3]
16 thrusters[1]
Maximum thrust10.780 kN (2,423 lbf)[4]
Specific impulse286 seconds (2.80 km/s)[1]
Burn time35s[1]
PropellantHTPB/AP (SRM)[5]
hydrazine (monopropellant thrusters)[1]

The CTS is an upper stage developed by the China Academy of Launch Vehicle Technology (CALT) to improve the performance of the Long March 2C to high (>400 km of altitude) LEO missions like SSO. The two stage LM-2 delivers the payload and stage to an elliptical orbit with the desired apogee and the CTS points the stack in the direction of the correct vector and activates the solid rocket motor (SRM) main engine to circularize it. It then dispenses the spacecraft and does a passivisation procedure.[1]

  1. ^ a b c d e f g h i Cite error: The named reference casc-lm2c-1999 was invoked but never defined (see the help page).
  2. ^ Cite error: The named reference b14643-chinesesolids was invoked but never defined (see the help page).
  3. ^ Cite error: The named reference b14643-cz2prop was invoked but never defined (see the help page).
  4. ^ Cite error: The named reference gs-cz2ccts was invoked but never defined (see the help page).
  5. ^ Cite error: The named reference b14643-cz2desc was invoked but never defined (see the help page).