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Study on Combination of UV Curing and Hot Curing Liner in Solid Rocket Engine

Author: YangShiMin
Tutor: ZhuHui；GanXiaoDong
School: National University of Defense Science and Technology
Course: Materials Engineering
Keywords: UV curing Thermal curing Lining
CLC: V435
Type: Master's thesis
Year: 2008
Downloads: 169
Quote: 0
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Abstract

Compared with the conventional heat curing liner, the composite curing liner has a pre-curing time is short, the characteristics of the low production costs. In this study, using a hand-held UV curing instrument and means of Fourier transform infrared spectrometer, rotor viscometer, electronic universal testing machine, linear ablation instrument, SEM and thermal analyzers and other analytical testing, research the composite curing lining viscosity, gelation speed , polyester urethane acrylate content (SM6402), the composite light the content of the initiator, the content of the bonding agent (MAPO), and SiO ₂ content on the mechanical properties and density of the lining is measured liner adhesive properties of the layer and the related interface, ablation rate, thermal decomposition temperature and glass transition temperature, and a micro-phase structure and morphology of the liner. The composite curing lining of solid rocket motor developed by the two system components: 1) by SM6402 and benzophenone ketone (BP) / of benzoin diethyl ether (BE) composite light trigger agent composed of light curing system; 2) of HTPB and different Buddha Chalcone diisocyanate (IPDI), consisting of thermal curing system. Developed a composite curing liner is mainly composed of HTPB: 50.0% to 60.0% IPDI: 10.8% to 16.9%, SM6402: 30.0% to 40.0%, BP / BE: 2.0% ~ 4.0% of MAPO: 1.7% to 2.5%, SiO ₂: 5.5% ~ 6.5%. The overall performance of the composite curing lining to meet the development requirements. The results show that: 1) in 50 ℃ below, the increase in the viscosity of the composite curing liner slow, the applicable period is greater than 3H, able to meet the engine combustor liner coating requirements; 2) composite optical generally choose the content of the initiator system 2.0% ~ 4.0%; 3) determining a composite pre-curing process the cured liner 4) the tensile strength and elongation of the liner: 365nm UV light irradiation distance control in 40mm ~ 60mm, the illumination time between 5s ~ 10s; maximum HTPB/SM6402 mass ratio of 60/10, SM6402 a light curing system with HTPB thermal curing system is an interpenetrating network (IPN) are obviously complementary; 5) composite optical initiator content of composite curing liner anti tensile strength, elongation, and a density of no significant effect; 6) With the increase of the amount of the MAPO, elongation of the liner downward trend exists, MAPO in an amount of 1.7% is more appropriate; 7) Lightweight silica content increases , leading to lining the flow properties and the coating process performance deteriorated, the appropriate dosage is in the range of 5.5% to 6.5%; 8) SEM photograph shows that the section and the surface of the composite curing liner there are significant phase separation, showing non- homogeneous island-like structure, the composite curing an interpenetrating network between cross-penetration forming a mechanical entanglement; 9) composite cured liner, the glass transition temperature of -64.9 ° C, the thermal decomposition temperature of 366.9 ° C.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Propulsion system ( engine, propeller ) > Solid propellant rocket motor
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