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In 1949 Tsien Hsue-shen, the leading expert in high-speed aerodynamics working in America, applied the knowledge learned from German rocket developments to the design of a practical intercontinental rocket transport. He proposed a 5,000 km single stage winged rocket clearly derived from V-2 aerodynamics. The 22,000 kg rocket would carry ten passengers from New York to Los Angeles in 45 minutes. It would take off vertically, with the rocket burning out after 60 seconds at 14,740 kph at 160 km altitude. After a coast to 500 km, it would re-enter the atmosphere and enter a long glide at 43 km altitude. Landing speed was to be 240 kph. Tsien�s fundamental theoretical work on this concept lead to him being called the �Father of the Dyna-soar� (a 1950�s/1960�s delta winged spaceplane that was the ancestor of the space shuttle).

Definitive low earth orbit launch vehicle derived from DF-5 ICBM, FB-1 launch vehicle. Provided basis for subsequent family of launch vehicles.The Long March 2C was a two-stage launch vehicle with storable propellants, suitable for launching a variety of low earth orbit satellites. The CZ-2C's typical payload capability was 2,800 kg into a 200 km circular orbit. The CZ-2C could be launched from either the Jiuquan or Taiyuan launch sites. On October 6, 1992, the Swedish Freja satellite was successfully launched as a copassenger on the CZ-2C's thirteenth flight.

On April 28, 1993, the Chinese Great Wall Industrial Corporation and Motorola signed a launch services contract for multiple launch of Iridium communications satellites using CZ-2C/SD launch vehicles. The main differences between the CZ-2C and the CZ-2C/SD were: a modified fairing with a diameter of 3.35m; a newly developed Smart Dispenser; improved second stage fuel and oxidizer tanks; and second stage engines with higher expansion ratio nozzles. The Smart Dispenser included a solid rocket kick motor for insertion of the Iridium satellites into a 780 km circular orbit. Each CZ-2C/SD had the capacity of delivering two Iridium system satellites. A successful CZ-2C/SD demonstration launch was conducted from Taiyuan on September 1, 1997. The first three deployment launches for the Iridium program were successfully conducted on December 8, 1997, March 26, 1998 and May 2, 1998.

The Long March 2D was a two-stage launch vehicle with storable propellants, suitable for launching a variety of low earth orbit satellites. Developed and manufactured by the Shanghai Academy of Spaceflight Technology, the CZ-2D had a typical payload capability of 3,500kg in a 200 km circular orbit. Its first stage was identical to that of the CZ-4. The second stage was essentially the same as that of the CZ-4, except for an improved vehicle equipment bay.

The Long March 3 was a three-stage launch vehicle designed for delivery of satellites of 1,500 kg mass into geosynchronous transfer orbit. The first and second stages were based on the CZ-2C, and designed and manufactured by the Shanghai Academy of Spaceflight Technology. The majority of the technology and flight hardware used in the CZ-3 had been qualified and proven on the CZ-2C. The third stage, manufactured by CALT, was equipped with an LOX/LH2 cryogenic engine. Long March 3 was also capable of placing spacecraft into an elliptical or circular low earth orbit and sun synchronous orbit.

The Long March 4 was a three-stage launch vehicle using storable propellants. The CZ-4 was developed and manufactured by the Shanghai Academy of Spaceflight Technology. Its first stage was essentially the same as that of the CZ-3 and the second stage was identical to that of the CZ-3. The CZ-4's third stage, however, is newly developed, featuring a thin wall common intertank bulkhead tankage and two-engine cluster with both engines gimbling about two perpendicular axes. The 3rd stage engine cluster connects to the tank aft bulkhead through the engine bay. The CZ-4 had two payload fairing configurations: Type-A and Type-B. The CZ-4 was designed for launching satellites into polar and sun-synchronous orbits. The CZ-4's typical payload capability is 1,650kg into a 600km sun-synchronous orbitsand 4,680 kg into a 200km circular orbit. On September 7, 1988, the CZ-4A made its first flight, successfully launching China's first experimental meteorological satellite. Another meteorological satellite was successfully launched by a CZ-4A on September 3, 1990. The CZ-4B introduced in 1999 was an improved model with enhanced third stage and fairing. It measured 44.1 metres in length with a first stage thrust of 300 tonnes.

Masses, performance estimated based on two strap-on boosters identical to CZ-2 first stage on a CZ-2 core.

The stages were sized at 4.5 m diameter to allow rail transport from the factory to the launch site at Jiuquan. Lateral clustering of the boosters allowed the height of the vehicle to be kept at no more than 60 m.

The Long March 3A was a three-stage launch vehicle. By incorporating the mature technologies of the CZ-3 and adding a more powerful cryogenic third stage and more capable control system, the CZ-3A had a greater geosynchronous transfer orbit capability, greater flexibility for attitude control, and better adaptability to a variety of launch missions. The CZ-3A's geosynchronous transfer orbit payload capability was 2,700kg. By June 30, 1998, the CZ-3A had made three consecutive successful launches, and was offered to international customers.

The Long March 3B was the most powerful Long March launch vehicle. It could inject a 5,000 kg payload into geosynchronous transfer orbit. The CZ-3B was developed on the basis of the CZ-3A, but had enlarged propellant tanks, larger fairing, and four boosters strapped onto the core stage. The CZ-3B boosters were identical to those of the CZ-3A.

China's new generation launch vehicle as announced in February 2001 was to be a modular design that consisted of three types of core stages with diameters of 2.25 m, 3.35 m and 5.0 m and two types of engines using Lox/Kerosene and Lox/LH2. Various models of heavy launcher were planned based on the 5.0 m core stage + 3.35 m strap-ons. Also planned were a 3.35 m core stage + 2.25 m strap-ons medium launcher and a 2.25 m core small launcher. The new launcher was to be capable of lifting up to 25 tonnes to LEO and up to 13 tonnes to GTO.