Tiangong-1 Uses Carbon Fiber.

Tiangong-1 is very successful this evening. People are curious that it can withstand thousands of high temperatures and will be in space for two years.

The science and Technology Daily reporter contacted some experts of China General Building Materials Research Institute, who took part in the research and development tasks of some materials.

The most important task of Tiangong-1's trip is space rendezvous and docking. This is universally acknowledged space technology.

Ordinary glass and even ordinary quartz glass will be black and opaque under high intensity cosmic rays, resulting in the failure of attitude control.

In the absence of completely blank technology, in 1987, academician Gu Zhenan and his research team began to bite the hard bone of radiation resistant quartz glass. After several years of research and repeated experiments, the technical problems of doping in high purity silica glass were solved, and many technical difficulties such as melting and melting of high temperature, uneven radiation and cosmic ray irradiation were overcome.

In 1995, "radiation resistant quartz glass" was first applied to satellites and achieved good results.

The glass used for Tiangong-1 has made new improvements in the later stage of heat treatment and other processes, greatly improving the product.

If we compare Tiangong-1 to a bird, then it will depend on the resource capsule to fly all over the mountains like birds, and to change all kinds of flying positions in the air.

The advanced composite load-bearing cone is an important structural part of Tiangong-1.

The Tiangong-1 space laboratory resource module includes engines and power devices, etc., to provide orbital and attitude control, power supply and thermal control, providing power for orbital maneuver and providing energy for flight.

However, the main bearing structure of the propulsion subsystem of the resource cabin is large in size, small in structure space and weight, and hard in load conditions.

The Harbin FRP Research Institute of China Building Materials Group uses the CFRP bearing cone structure scheme, creatively uses honeycomb sandwich structure and composite cross beam composite structure as main bearing structure, which is superior to the metal panel scheme, and solves the problem of small space of the propulsion subsystem and difficult layout of payload.

In the process of product design and development, researchers have cracked the finite element design method of large composite structure and its bearing capacity under complex loads, and the design calculation method of honeycomb sandwich structure. The key technologies such as product mold design technology, cross beam overall forming process, honeycomb panel forming technology with high precision of main bearing capacity and assembly technology of large complex structure have been overcome, which meets the manufacturing requirements of Tiangong-1 bearing cone technology.

The use of CFRP on Tiangong-1 is almost everywhere.

In order to satisfy the application of space optical structure, the design of the camera bracket as an important load-bearing structure requires five "high" requirements: high dimensional accuracy and accuracy of shape and position, high requirement of linear expansion coefficient, high modulus of elasticity of structure, and order of magnitude of deformation, and high fundamental frequency of the product, up to 100Hz.

In 2006, Harbin FRP Research Institute undertook the task of developing Tiangong-1 carbon fiber composite camera support components.

The parameterized calculation model is established by using the large-scale simulation analysis software, and the optimization design of composite components is carried out. Three major technical problems are successfully solved: irregular, unequal thickness, unequal width, large section reinforced structure technology, the forming technology of composite reinforced sandwich structure and the precision control of high-precision double-layer reinforcement structure.

Similarly, the mounting support for the structural pmission shaft of the application space optical camera system is mainly made of carbon fiber composite material, which is composed of carbon fiber spindle, countershaft cover, base and titanium alloy shaft sleeve.

Because it requires higher dimensional stability, and the main structure is from high modulus.