
Beijing Zhongke Aerospace Exploration Technology Co., Ltd. is the first domestic aerospace enterprise with mixed ownership, and it is also the target enterprise that Oriental Aerospace Port focuses on introducing. Relying on the scientific research strength and resource advantages of the Institute of Mechanics of the Chinese Academy of Sciences and the Aerospace Flight Technology Center of the Chinese Academy of Sciences, China Aerospace Science and Technology has been committed to the research and development and integration of space technology and aerospace vehicles as a platform for the transformation of major national scientific research projects, as well as the transformation and provision of technological achievements. Aerospace launch service. The Lijian-1 rocket project also adds a brand-new name card to the Oriental Space Port, which will surely promote the construction of the Oriental Space Port to take a solid step forward.

The Lijian-2 Y1 carrier rocket successfully launched a space test spacecraft, serving major national strategies and engineering projects
At 19:00 on March 30, 2026 Beijing time , the Lijian-2 Y1 carrier rocket, designated “International Textile City,” successfully launched from the Dongfeng Commercial Aerospace Innovation Test Zone, accurately sending the Xinzhengcheng 01 satellite, Xinzhengcheng 02 satellite, and Tianshi Satellite 01 into their predetermined orbits. The launch mission was a complete success, and the maiden flight mission serves major national strategies and engineering projects. The LiJian-2, my country’s first launch vehicle with a Common Booster Core (CBC) configuration, features a universal core stage with a diameter of 3.35 meters, a fairing diameter of 4.2 meters in its maiden flight, a total length of 53 meters, a liftoff weight of 625 tons, a liftoff thrust of 753 tons, a payload capacity of 8 tons to a 500 km sun-synchronous orbit, and a payload capacity of 12 tons to a 200 km low Earth orbit.








Developed with high payload capacity, low cost, and high frequency of use as its goals, the LiJian-2 adheres to the advanced concepts of universalization, modularization, and assembly. Its major components are designed as independent modules, enabling efficient reuse and flexible combination of different modules, significantly improving R&D and production efficiency. Subsequent use of the same modules in various combinations allows for flexible configurations supporting 0/2/4 bundled configurations—either bare or bundled with 2/4 liquid boosters—covering a low Earth orbit payload capacity range of 2 to 20 tons. It also enables clustered recovery, demonstrating excellent flexibility and strong modular adaptability. At the same time, it can be combined with the company’s independently developed PV-1 upper stage to further and significantly expand the orbits that the rocket can cover, meeting the needs of multi-satellite deployment in medium and high orbits such as geostationary orbit, geostationary transfer orbit, and geostationary transfer orbit

The Qingzhou prototype test spacecraft, developed by the Innovation Academy for Microsatellites of the Chinese Academy of Sciences, weighs only 4.2 tons. It adopts a single-module integrated configuration, allowing for flexible adaptation to multiple rocket types and possessing excellent launch compatibility. This flight test carried 27 items, including technology reserves, on-orbit verification, scientific exploration, and popular science works, with a total payload of 1.02 tons. It will orbit at an altitude of 200 to 600 kilometers …


he first and second stage separation is similar to that of the Long March 7A, employing a cluster separation (i.e., the two boosters separate from the first stage as a single unit). For this purpose, a total of 14 solid-propellant rockets for interstage cooling separation are configured: 8 separation retro-propulsion rockets (Figure 1), each with a thrust of 45-50 kN, an actuation time of 50 ms, and a nozzle offset of 20°; and 6 bottom-mounted forward-propulsion rockets (Figure 2), each with a thrust of 6 kN, an actuation time of 4.5 s, and a nozzle offset of 24°
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