Applications of Fiberglass Products in Spacecraft


Release time:

2017-03-23

The phenomenon in which fiberglass‑reinforced plastic materials are degraded by thermal decomposition and volatilization is called ablation. The cooling and insulating effects generated by ablation—such as those described above—are referred to as ablation‑cooling effects. Materials that absorb substantial amounts of heat during ablation exhibit strong ablation‑cooling performance; their ablation proceeds slowly, making them classified as ablation‑resistant materials. Phenolic‑based fiberglass composites are excellent examples of such ablation‑resistant materials. When these materials are used to fabricate spacecraft hulls, a thicker design can be adopted: as the spacecraft traverses the atmosphere, the outermost layer undergoes ablation, and the resulting cooling and thermal insulation effectively protect the underlying structure.

  The phenomenon by which fiberglass‑reinforced plastic materials are degraded through vaporization and decomposition upon exposure to heat is called ablation. The cooling and thermal‑insulation effects arising from ablation, as described above, are known as ablation‑cooling effects. Materials that absorb substantial amounts of heat during ablation exhibit strong ablation‑cooling performance; such materials undergo ablation very slowly and are referred to as ablation‑resistant materials. Phenolic‑based fiberglass composites are excellent examples of ablation‑resistant materials. When these materials are used to fabricate spacecraft hulls, a thicker design can be adopted. As the spacecraft traverses the atmosphere, the outermost layer is ablated, while the cooling and insulating effects generated by this process protect the underlying unablated layers. In this way, the spacecraft can safely exit the atmosphere, with its occupants and onboard instruments remaining undamaged.
 
  In addition to its excellent ablation resistance, which makes it ideal for aerospace applications, fiberglass‑reinforced plastic (FRP) boasts high mechanical strength, low density, a low coefficient of thermal expansion, and the ability to be readily molded into a wide variety of shapes—qualities that are particularly desirable in spaceflight, especially its low specific gravity. By increasing the use of FRP components on spacecraft, their overall weight can be significantly reduced. In the field of astronautics, reducing spacecraft mass is of paramount importance: even a one‑kilogram reduction in weight can substantially lower the propellant requirements of the launch vehicle, enabling corresponding redesigns of both the spacecraft and the launch system and potentially yielding weight savings of several hundred kilograms. Consequently, aerospace engineering strives to employ lightweight materials that meet stringent performance criteria; for instance, high‑strength, high‑stiffness honeycomb‑structured FRP panels are commonly used for spacecraft hulls and instrument mounting bases.
 
  In addition to phenolic‑based fiberglass composites, space‑flight technology also employs other high‑temperature‑resistant fibers in place of glass fiber to produce superior ablation‑resistant materials, such as asbestos fiber, quartz fiber, certain synthetic fibers, carbon fiber, and boron fiber. Of course, the resin matrix is not limited to phenolic resin; an increasing number of thermosetting and thermoplastic resins with even better heat resistance are being adopted, including silicone resin and polyimide resin.
 
  On the “Messenger‑1B” experimental satellite, launched on October 4, 1960, the outer shell consisted of two hemispherical fiberglass components. The satellite featured an octahedral aluminum‑welded frame to which three honeycomb‑structured fiberglass panels were attached, serving as a platform for mounting the electronic instruments. Both the fiberglass shell and the launch vehicle’s rocket were joined using fiberglass flanges. Furthermore, titanium oxide was incorporated into the surface resin of the satellite’s shell, creating a white reflective coating that could deflect intense light and other forms of radiation, thereby helping to maintain a more favorable internal environment. There are numerous examples of fiberglass being used for spacecraft hulls; for instance, the early U.S. Mercury and Apollo spacecraft employed phenolic fiberglass or asbestos‑fiber‑reinforced phenolic plastics as thermal insulation layers.
 
  Rockets used to launch satellites or spacecraft into space also widely employ fiberglass-reinforced plastics and other reinforced composites. For example, the United States began using fiberglass‑reinforced plastic rockets to launch satellites in 1966; in 1970 alone, nearly a hundred satellites were launched aboard such vehicles, including the Vanguard, the Europa, Earth‑observation satellites, and international telecommunications satellites. Today, the fabrication of fiberglass‑reinforced plastic shells for artificial satellites, spacecraft, and rockets typically relies on two primary forming techniques: filament winding and compression molding.
 
  In addition to ablative and thermal‑insulating materials used for spacecraft hulls and nozzles, fiberglass‑reinforced plastics and other advanced composites are widely employed in various components of spacecraft, satellites, and launch vehicles. These include bases for electronic equipment, protective covers, instrument panels, flooring, transparent windows, sealing gaskets, and even the spacesuits worn by astronauts—all manufactured from fiber‑reinforced composites.
 
 

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