CTS (rocket stage)

CTS
Manufacturer CALT
Country of origin China
Used on Long March 2C third stage.
General characteristics
Height 0.9 m (35 in)[1]
Diameter 0.54 m (21 in)[1]
Gross mass 160 kg (350 lb)[1]
Propellant mass 121.7 kg (268 lb)[1]
Associated stages
Derived from SD
Derivatives SMA
Launch history
Total launches SD: 7
CTS:2
SMA:2
Successes
(stage only)		 SD: 7
CTS:2
SMA:2
Failed 0
Lower stage
failed		 0
First flight SD: 1997-09-01
CTS: 2003-12-29
SMA:2008-09-06
Last flight SD: 1999-06-12
CTS: 2004-07-26
SMA:2012-10-14
Engine details
Engines 1 FG-47 SRM[2][3]
16 thrusters[1]
Thrust 10.780 kN (2,423 lbf)[4]
Specific impulse 286s[1]
Burn time 35s[1]
Fuel HTPB (SRM)[5]
hydrazine (monopropellant thrusters)[1]

The CTS is an upper stage developed by 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]

History

It was initially developed as the SD stage for the initial deployment of the initial deployment of the Iridium constellation in 1997.[6] In the 1999 LM-2C User Manual it was offered as the CTS option and flew to deploy the Double Star mission. Later it flew twice as part of the dual deployment system SMA, first for the deployment of the Huanjing 1A and 1B[7] and in 2012 for the Shijian 9A and Shijian 9A technology demonstrator missions.[8][9]

Date Carrier Rocket Designation Launch site Mission Result
1997-09-01Long March 2CSDTaiyuanIridium-MFS 1 / Iridium-MFS 2[6]Success
1997-12-08Long March 2CSDTaiyuanIridium 42 / Iridium 44Success
1998-03-25Long March 2CSDTaiyuanIridium 51 / Iridium 61Success
1998-05-02Long March 2CSDTaiyuanIridium 69 / Iridium 71Success
1998-08-19Long March 2CSDTaiyuanIridium 76 / Iridium 78Success
1998-12-19Long March 2CSDTaiyuanIridium 88 / Iridium 89Success
1999-06-10Long March 2CSDTaiyuanIridium 92 / Iridium 93Success
2003-12-29Long March 2CCTSXichangDouble Star Equatorial (TC 1)Success
2004-07-26Long March 2CCTSTaiyuanDouble Star Polar (TC 2)Success
2008-09-06Long March 2CSMATaiyuanHuanjing 1A / Huanjing 1BSuccess
2012-10-14Long March 2CSMATaiyuanShijian 9A[8] / Shijian 9A[9]Success

Design

It is composed of the Spacecraft Adapter and Orbital Maneuver System (OMS). The Spacecraft Adapter is customized to the user's requirement, particularly in the separation environment and pointing accuracy.[1] The OMS is composed by:

  • Main structure
  • Control system (avionics)
  • Telemetry system
  • Solid rocket motor (SRM)
  • Reaction control system (RCS)

Versions

The basic system has been offered in three different versions:

  • SD: Initial version used exclusively for the Iridium fleet deployment.[6][10][11][12][13]
  • CTS: Improved commercial version offered in the 1999 User Manual with 3 axis stabilization.[7][11][14]
  • SMA: Government version which includes a dual payload adapter.[15]

See also

References

  1. 1 2 3 4 5 6 7 8 9 10 "Chapter 2.4 – CTS Introduction". LM-2C User's Manual. Issue 1999. CASC. 1999. pp. 2–15. Retrieved 2015-07-08.
  2. ↑ Norbert Bgügge. "Some Chinese solid fuel aerospace motors". B14643.DE. Archived from the original on 2015-09-26. Retrieved 2015-07-25.
  3. ↑ Norbert Bgügge. "Propulsion CZ-2, CZ-2C, CZ-2D". B14643.DE. Retrieved 2015-07-25.
  4. ↑ "CZ-2C/CTS Long March Space Launch Vehicles". GlobalSecurity. Retrieved 2015-07-08.
  5. ↑ Norbert Bgügge. "Chang Zheng CZ-2C & CZ-2D". B14643.DE. Retrieved 2015-07-25.
  6. 1 2 3 Krebs, Gunter Dirk (2013-09-21). "CZ-2C (2) SD (Chang Zheng-2C (2) SD)". Retrieved 2015-07-25.
  7. 1 2 Krebs, Gunter Dirk (2014-04-05). "HJ 1A, 1B (SMMS 1)". Retrieved 2015-07-25.
  8. 1 2 Krebs, Gunter Dirk (2014-04-02). "Shijian 9A". Retrieved 2015-07-25.
  9. 1 2 Krebs, Gunter Dirk (2014-04-03). "Shijian 9B". Retrieved 2015-07-25.
  10. ↑ "CZ-2C/SD Space Launch Vehicle". GlobalSecurity. Retrieved 2015-07-08.
  11. 1 2 "CZ-2C/SD". Encyclopedia Astronautica. Archived from the original on 2013-11-30. Retrieved 2015-07-25.
  12. ↑ "SpaB-54". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-07-25.
  13. ↑ Norbert Bgügge. "Photo Gallery CZ-2CS/SD". B14643.DE. Retrieved 2015-07-25.
  14. ↑ Norbert Bgügge. "Photo Gallery CZ-2CS/SM". B14643.DE. Retrieved 2015-07-25.
  15. ↑ Norbert Bgügge. "Photo Gallery CZ-2CS-4/SMA". B14643.DE. Retrieved 2015-07-25.
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