NOSE FAIRING OF CARRIER ROCKET Russian patent published in 2019 - IPC F42B10/46 B64G1/64 

FIELD: missiles.

SUBSTANCE: invention relates to nose fairing (NF) of carrier rocket (CR), which is burnt after separation from CR at atmospheric section of launching trajectory. NF is a three-layer structure of polymer composite materials in form of a two-wing shell of variable curvature, comprising external and internal bearing layers of material consisting of binder and carbon tape (MBL). Filler arranged between outer and inner load-carrying layers of NF consists of high-energy material and plastic intended for release during combustion of required amount of heat, determined from MBL heating conditions to its ignition temperature. Filler material (FM) is selected based on a mixture of high-energy material, such as a mixture of potassium chlorate or potassium perchlorate. Powder of magnesium, aluminum, titanium, or their alloys, which retain their thermophysical characteristics, including ignition temperature, strength at all stages of its life cycle, are selected as powdered metal, including preparation of material for making aggregate and entire three-layer structure of NF, as well as in section of trajectory of CR launching and trajectory of NF launching after separation from CR. MBL material is selected from the condition of simultaneous ignition of binder and plastic, in form of composite polymer material such as carbon fiber, in particular carbon tape and binder, having a close ignition temperature in range of 700–800 °C.

EFFECT: technical result consists in enabling combustion of NF during movement along trajectory of descent in layers of atmosphere, elimination of fact of NF falling to surface of Earth and thus exclusion of need to allocate area for their fall.

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