3D printing solid propellant/heat insulation layer formula and its integrated preparation method

Abstract

The invention discloses a 3D printing solid propellant / heat insulation layer formula and its one The bulk preparation method, wherein the propellant includes the following raw materials in terms of mass fraction: 15%~25% of photosensitive resin prepolymer, 10%~20% of reactive diluent monomer, 1%~3% of photoinitiator, crosslinking agent 1%~4%, oxidant 50%~65%, metal fuel 5%~10%, functional additive 1: 1%~3%; in the heat insulation layer, photosensitive resin prepolymer 20%~40%, active dilution Body 10%~30%, photoinitiator 2%~5%, crosslinking agent 1%~4%, heat insulation and ablation resistant solid phase filler 30%~40%, functional additive 2: 5%~10%. The propellant / insulation layer formula of the present invention adopts the same light-curable resin adhesive system, which improves the interface bonding quality of the propellant and the insulation layer, increases the bonding strength of the interface, and avoids problems caused by problems such as weak interface bonding in solid motors. Potential safety hazards, realize the 3D printing of the propellant and the integration of the inner and outer structures of the thermal insulation layer, and provide a new solution for the manufacture of solid engines.

Description

technical field [0001] The invention relates to the technical field of composite solid propellants, in particular to a 3D printing solid propellant / heat insulation layer formulation and an integrated preparation method thereof. Background technique [0002] With the development of missile weapon technology, the charge design of solid motors is becoming more and more complex. The deficiencies and limitations of traditional charge technology in the manufacture of complex charge-type solid motors are becoming more and more prominent, which are mainly reflected in the following two aspects: (1) For The charge column with a complex internal combustion surface structure is limited by the design and removal of the mandrel, and its manufacturing and processing are difficult; (2) The thermal insulation layer and the propellant are assembled by step-by-step forming to complete the charge, and the assembly surface is realized by the lining layer. Bonding and interface debonding cannot ...

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Problems solved by technology

[0004] The invention provides a 3D printing solid propellant / thermal insulation layer formula and its integrated preparation method, which can realize the integrated 3D printing and manufacturing of propellant / thermal insulation layer, and solve the interface bonding between the propellant and the thermal insulation layer in the existing production process Not firm, easy to debond and other problems

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