The Long March 2C is a Chinese medium-lift, two-stage orbital launch vehicle developed by the China Academy of Launch Vehicle Technology (CALT). It uses storable N2O4/UDMH propellants and has several variants for different mission profiles.
Long March 2C (LM-2C / CZ-2C)
The Long March 2C is a Chinese medium-lift, two-stage orbital launch vehicle developed by the China Academy of Launch Vehicle Technology (CALT). It uses storable N2O4/UDMH propellants and has several variants for different mission profiles.
Description
The Long March 2C (LM-2C), also known as the Chang Zheng 2C (CZ-2C), is a Chinese orbital launch vehicle and a member of the Long March 2 rocket family. Developed and manufactured by the China Academy of Launch Vehicle Technology (CALT), it first launched on September 9, 1982. It is primarily a two-stage launch vehicle utilizing storable N2O4/UDMH propellants, and its design was derived from the DF-5 ICBM. The Long March 2C is capable of delivering payloads to Low Earth Orbit (LEO), Sun-synchronous Orbit (SSO), and Geostationary Transfer Orbit (GTO) with the use of an optional third stage. Several variants exist, including the 2C/SD for commercial satellite launches with a multi-satellite smart dispenser, the 2C/SM for small satellites to high orbits, and the 2C/SMA, an improved version of the 2C/SM. Recent developments include the addition of aerodynamic grid fins in 2019 to guide falling stages away from populated areas and testing of a fairing recovery system via parachutes to improve control of debris landing. The rocket has a long operational history with numerous successful launches.
Specifications
| Function | Medium-lift launch vehicle |
|---|---|
| Manufacturer | China Academy of Launch Vehicle Technology |
| Country of origin | China |
| Height | 42 m (138 ft) |
| Diameter | 3.35 m (11.0 ft) |
| Mass | 233,000 kg (514,000 lb) |
| Stages | 2 |
| Payload to low earth orbit mass | 3,850 kg (8,490 lb) |
| Payload to sun-synchronous orbit mass | 2C: 1,400 kg (3,100 lb) |
| Payload to sun-synchronous orbit mass (2) | 2C/SMA: 1,900 kg (4,200 lb) |
| Payload to GTO mass | 2C/SM: 1,250 kg (2,760 lb) |
| Family | Long March |
| Status | Active |
| Total launches | 87 |
| Success (es) | 85 |
| Failure | 1 |
| Partial failure | 1 |
| First flight | 9 September 1982 |
| Last flight | 27 March 2026 (most recent) |
| First stage height | 25.72 m |
| First stage diameter | 3.35 m |
| First stage propellant mass | 162,706 kg (358,705 lb) |
| First stage powered by | 4 × YF-21C |
| First stage maximum thrust | 2,961.6 kN (665,800 lbf) |
| First stage specific impulse | 2,556.5 m/s (8,387 ft/s) |
| First stage propellant | N2O4 / UDMH |
| Second stage height | 7.757 m |
| Second stage diameter | 3.35 m |
| Second stage propellant mass | 54,667 kg (120,520 lb) |
| Second stage powered by | 1 × YF-24E (with 1 × YF-22E main engine and 4 × YF-23C vernier engines) |
| Second stage maximum thrust (main) | 741.4 kN (166,700 lbf) |
| Second stage maximum thrust (vernier) | 47.1 kN (10,600 lbf) |
| Second stage specific impulse (main) | 2,922.37 m/s (297.999 s) |
| Second stage specific impulse (vernier) | 2,834.11 m/s (288.999 s) |
| Second stage propellant | N2O4 / UDMH |
| Third stage – (optional) height | 1.5 m |
| Third stage – (optional) diameter | 2.7 m |
| Third stage – (optional) propellant mass | 125 kg (276 lb) |
| Third stage – (optional) powered by | 1 solid motor |
| Third stage – (optional) maximum thrust | 10.78 kN (2,420 lbf) |
| Third stage – (optional) specific impulse | 2,804 m/s (285.9 s) |
| Third stage – (optional) propellant | AP / HTPB |
| Third stage (optional) – yz-1s powered by | 1 × YF-50D |
| Third stage (optional) – yz-1s maximum thrust | 6.5 kN (1,500 lbf) |
| Third stage (optional) – yz-1s specific impulse | 315.5 s (3.094 km/s) |
| Third stage (optional) – yz-1s propellant | N2O4 / UDMH |
