CZ-6 _ CZ-6A _ CZ-6C

Description:

CZ-6

The first all-new Chinese orbital launcher introduced in nearly two decades, the CZ-6 has been positioned as a small-load orbital launcher for small- and micro-satellites of under 1,000 kg mass, filling a launch capacity gap in the existing Chang Zheng launch vehicle family. This put the CZ-6 in the same class as the European Space Agency Vega and the Russian Angara-1. China began the development of the new-generation Chang Zheng launchers in 2000. The most significant improvement over the current generation Chang Zheng rockets was the abandoning of the toxic N2O4/UDMH propellant in favour of the cleaner Liquid Oxygen (LOX)/Kerosene and LOX/LH2 propellents. The CZ-6 is the first member of the new generation rocket family to fly. It is to be followed by two further models — the medium-load CZ-7 and the heavy-load CZ-5, which are due to make their maiden flights in 2016 and 2017 respectively.

Original Concept:

• China’s new generation expandable space launcher rocket family was first announced in February 2001, followed by more detailed descriptions during the Zhuhai Air Show in late 2002. The original concept was to assemble launchers of various capabilities from three baseline rocket modules of 2.25 m, 3.35 m and 5.00 m diameter. These modules would be powered by either the 120 t thrust liquid engine YF-100 or the 50 t thrust liquid engine YF-77.
• The smallest launcher of the family was to be based on the 2.25 m diameter module powered by a single YF-100 engine. Under the modular design principle, the same module could also serve as the strap-on booster for the medium- and heavy-load launchers.
• The small-load launcher rocket was to be added with a LOX/LH2 upper-stage powered by a YF-73 engine derived from the CZ-3’s third-stage, giving a launch capability of up to 1,500 kg payload to the low Earth orbit (LEO), or up to 1,000 kg to the 700 km Sun Synchronous Orbit (SSO).
• According to the calculations, a rocket 2.25 m in diameter would need to be around 35 m in length in order to carry enough propellant to achieve the intended payload capacity. At this length-to-diameter ratio the rocket would require extra enhancements in its structural strength and flight control. In addition, the rocket’s payload capacity to SSO would be limited to under 500 kg if the launch mission would only rely on land-based tracking stations within Chinese territory.
• As an alternative, the design team produced an additional two proposals based on an enlarged first stage either 3.00 m or 3.35 m in diameter. Eventually a three-stage design with a 3.35 m diameter first-stage and 2.25 m diameter second- and third-stage (Design Proposal C) was chosen as the final design.

Technical Data:

CZ-6A:

An enlarged variant, the Long March 6A, which has four strap-on solid boosters, an elongated stage one, a new stage two with the same diameter as the first stage, and a payload capacity of at least 4000 kg to Sun-synchronous orbit, made its maiden flight on 29 March 2022.

CZ-6A

CZ-6C

CZ-6C:

A further iteration named the Long March 6C with a slightly shorter length than the 6A and without the four strap-on solid boosters had its successful maiden launch on 7 May 2024.

Launch List:

External links:

• Wikipedia: Rocket Information
• Sinodefence.com: Rocket Information