Alkynyl-functionalization of carbon nanotubes to promote anchoring potential in glycidyl azide polymer-based binders via Huisgen reaction for solid propellant application

Hu, Wen; Qi, Chun; Guo, Xiang; Pang, Aimin; Zhou, Na; Lü, Jun; Tang, Gen; Gan, Lin; Huang, Jin

doi:10.1007/s10965-021-02468-3

Cited by 5 publications

(4 citation statements)

References 32 publications

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“…As for the PTA composites, there is only one existing weight‐loss stage between 360 and 480°C that belongs to the decomposition of copolyether. According to our previous works, 42 the lower heat‐resistance index ( T HRI ), obtained from Equation (), referred to a better combustion effect.

T_{Heat - reasistance index} = 0.49 \times [T_{5} + 0.6 \times (T_{30} - T_{5})]

where T 5 and T 30 are the corresponding decomposition temperature at 5 and 30 wt% of weight loss, respectively. As listed in Table 4, the T HRI first increased and then decreased as the R increased for both the PUTA and PTA composites.…”

Section: Resultsmentioning

confidence: 99%

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Inserting urethane into 1,2,3‐triazole click‐cured solid propellant binder to form microphase separation and enhance mechanical and combustible performances

Zhang

Gan

et al. 2023

J of Applied Polymer Sci

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Huisgen‐click curing systems are widely used in solid propellant binders due to their low humidity sensitivity and mild reaction conditions. However, the rigid triazole rings from the Huisgen‐click reaction decrease the molecular moving ability and increase decomposition temperature, lowering the mechanical and combustion performance. Thus, we bonded the Huisgen‐click system and polyester binders with urethane, forming microphase separation and improving chemical stability. The results show that the elongation at break, tensile strength, and Young's modulus of the binders increase by 533.3%, 201.2%, and 1263.9%, respectively. Furthermore, the urethane reduces the thermal resistance index of the binders from 191.2 to 179.2°C, which means better combustion performance. Further mechanism study reveals that the urethane leads to microphase separation, which aggregates the hard segments and weakens their restriction effect on the molecular motion of polyether. Such a microphase separation brings comprehensive improvement in the mechanical properties of the solid propellants and probably can be used in other multi‐component systems of energetic materials.

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T_{Heat - reasistance index} = 0.49 \times [T_{5} + 0.6 \times (T_{30} - T_{5})]

Section: Resultsmentioning

confidence: 99%

“…40,41 As for the PTA composites, there is only one existing weight-loss stage between 360 and 480 C that belongs to the decomposition of copolyether. According to our previous works, 42 the lower heat-resistance index (T HRI ), obtained from Equation (4), referred to a better combustion effect.…”

Section: Microphase Morphology Of Triazolecured Bindersmentioning

confidence: 97%

Inserting urethane into 1,2,3‐triazole click‐cured solid propellant binder to form microphase separation and enhance mechanical and combustible performances

Zhang

Gan

et al. 2023

J of Applied Polymer Sci

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“…Zhang et al [13] employed SEM to characterize the fracture morphology of CMDB propellant after tensile test and found that a host of large particles were dehumidified with the matrix. The particle-matrix interface is the weakest link in the structural integrity of propellant, and debonding of the particle-matrix interface is considered to be the main reason of composite solid propellant failure under tensile stress [14][15][16].…”

Section: Introductionmentioning

confidence: 99%

Correlation between microstructural evolution and mechanical properties of CMDB propellant during uniaxial tension

Wu,

Liu,

et al. 2023

Propellants Explo Pyrotec

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Numerical simulation of the deformation and damage evolution process of composite modified double base (CMDB) propellant based on the microstructure is of great significance for improving its macro‐mechanical properties. The macro‐mechanical properties and damage evolution of CMDB propellant were studied experimentally and numerically in current work. To establish the correlation between microstructural evolution and the macro‐mechanical response of the propellant, a three‐dimensional microstructure model of the CMDB propellant was constructed utilizing the molecular dynamics particle filling approach. At the interface between RDX particles and the nitrocellulose‐nitroglycerine (NC‐NG) matrix, the conventional cohesive element was replaced by cohesive contact, and the parameters of the cohesive zone model (CZM) at the interface between the particles and the matrix were obtained by parameter inversion based on the Hooke‐Jeeves parameter optimization algorithm. The processes of damage initiation, propagation, convergence, and failure at the cohesive interface were simulated using the bilinear cohesive zone model (BCZM). The results revealed that the fracture strength of NC‐NG propellant with added RDX particles was significantly increased and the fracture elongation was reduced. The three‐dimensional microstructure model can accurately describe the microstructure of CMDB, and dewetting at the interface is the primary cause of propellant degradation when subjected to an external load, which compromises the mechanical properties of the propellant.

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“…Marthinus C J [4] studied the microstructure deformation and fracture behavior of a hydroxyl-terminated polybutadiene (HTPB) propellant by using in-situ uniaxial tensile experiments conducted on a scanning electron microscope (SEM). Above all, the experimental methods explore the particle-matrix interfacial debonding as the main source of failure of the composite solid propellant [5,6].…”

Section: Introductionmentioning

confidence: 99%

Effect of Microstructure on Micro-Mechanical Properties of Composite Solid Propellant

Han

et al. 2021

Micromachines

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This study was aimed at determining the effect of microstructure on the macro-mechanical behavior of a composite solid propellant. The microstructure model of a composite solid propellant was generated using molecular dynamics algorithm. The correlation of how microstructural mechanical properties and the effect of initial interface defects in propellant act on the macro-mechanics were studied. Results of this study showed that the mechanical properties of propellant rely heavily on its mesoscopic structure. The grain filling volume fraction mainly influences the propellant initial modulus, the higher the volume fraction, the higher initial modulus. Additionally, it was found that the ratio of particles influences the tensile strength and breaking elongation rate of the propellant. The big particles could also improve the initial modulus of a propellant, but decrease its tensile strength and breaking elongation rate. Furthermore, the initial defects lowered the uniaxial tensile modulus, tensile strength, and the relaxation modulus of propellant, but did not affect the relaxation behavior of the propellant.

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Alkynyl-functionalization of carbon nanotubes to promote anchoring potential in glycidyl azide polymer-based binders via Huisgen reaction for solid propellant application

Cited by 5 publications

References 32 publications

Inserting urethane into 1,2,3‐triazole click‐cured solid propellant binder to form microphase separation and enhance mechanical and combustible performances

Inserting urethane into 1,2,3‐triazole click‐cured solid propellant binder to form microphase separation and enhance mechanical and combustible performances

Correlation between microstructural evolution and mechanical properties of CMDB propellant during uniaxial tension

Effect of Microstructure on Micro-Mechanical Properties of Composite Solid Propellant

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