Investigations on the thermal response of a solid rocket motor with complex charge structure using CL-20/GAP propellant

Wang, Yiyao; Wen, Junjie; Yang, Junsen; Zhang, Guanglong; Wang, Ningfei; Wu, Yi

doi:10.1016/j.csite.2022.102257

Cited by 12 publications

(2 citation statements)

References 29 publications

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“…Although there are significant differences in the porosity of samples in medium area (3 mm side height) from various formulations, the overall curve shapes are similar, exhibiting a trend of increasing and then decreasing with axial distance: the maximum porosity values for each sample are not located at the bottom in direct contact with the heater (axial distance d = 0), but slightly above the bottom at the heated position covered by the heater. This is similar to the temperature distribution of propellants obtained from slow cook-off tests mentioned in [30]. The internal decomposition reaction of the GAP propellant is faster than at the bottom, raising the internal temperature and subsequently increasing the porosity for micro-CT sections at corresponding axial distances.…”

Section: Effect Of Heating Areasupporting

confidence: 83%

Thermal structural damage and thermal decomposition characterization of GAP propellants with nitrate ester plasticizers

Jin,

Wu,

et al. 2024

Propellants Explo Pyrotec

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GAP and nitrate ester compounds are introduced into the solid propellant formulation as energetic binders and energetic plasticizing agents, respectively, to further enhance the energy level of solid propellants. However, under abnormal thermal conditions, various components within GAP propellants, especially nitrate ester plasticizers, can collectively result in the generation of a large number of voids within the propellant due to factors such as thermal stress and slow component decomposition. This phenomenon can impact the safety of solid rocket engines, necessitating research into their thermal decomposition processes and thermal damage structures. In this study, the thermal decomposition characteristics and gas products of GAP propellants with different nitrate ester plasticizer formulations were investigated using DSC‐TG and FT‐IR. The damage structure of GAP propellants heated under unignited conditions was studied through Micro‐CT, examining the influence of heating conditions and nitrate ester plasticizers on the thermal damage structure of GAP propellants. During heating, the thermal damage structure of GAP propellants was found to include voids generated within the GAP binder and cracks at the interface between the GAP binder and particles, with nitroglycerin as a plasticizer exacerbating the thermal damage of GAP propellants (about 2.2–2.9 times).

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Section: Effect Of Heating Areasupporting

confidence: 83%

Thermal structural damage and thermal decomposition characterization of GAP propellants with nitrate ester plasticizers

Jin,

Wu,

et al. 2024

Propellants Explo Pyrotec

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“…The HMX@PDA@MO samples were prepared by a microfluidic method using PDA as the coating medium. The morphology, composition and thermal decomposition behavior of the samples were characterized by SEM-EDS, XRD, DSC and other methods, [8][9][10][11][12][13] , and the apparent activation energy was calculated by Kissinger, Flynn-Wall-Ozawa, Friedman and Starink methods based on DSC data [14,15] .…”

Section: Introductionmentioning

confidence: 99%

Microfluidic preparation and thermal properties of HMX@PDA@MO

Yao

et al. 2023

J. Phys.: Conf. Ser.

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Metal oxides can effectively promote the thermal decomposition of energetic materials. However, the traditional physical mixing process has potential safety hazards and cannot achieve uniform and stable coating. To address this issue, this study provides adhesion sites for metal oxides through the rough coating formed by polydopamine on the surface of HMX, which improves the coating stability. Taking advantage of the safety and efficient mixing of microfluidic technology, HMX@PDA@MO samples with good dispersion were prepared. The samples were characterized by SEM-EDS, XRD and DSC. The XRD results demonstrate the successful preparation of HMX@PDA@CuO and HMX@PDA@PbO samples. SEM-EDS images show that polydopamine forms a rough coating on the surface of HMX, and the increase in the total flow rate is beneficial to enhance the dispersion of metal oxides. The DSC data showed that the addition of 3% and 20% CuO advanced the thermal decomposition temperature and apparent activation energy of HMX@PDA by 0.3K, 40.13 kJ·mol−1 and 2K, 108.83 kJ·mol−1, respectively, PbO is 0.1K, 111.94 kJ·mol−1, and 4.5K, 205.02 kJ·mol−1. It shows that the increase of metal oxide content will promote thermal decomposition. For HMX, PbO has better catalytic activity than CuO. PbO has better catalytic activity than CuO for HMX.

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Friction-induced ignition study of HTPB propellant based on a coupled chemo-mechano-thermodynamic model under ultrahigh acceleration overload conditions

Wang,

Gao

et al. 2023

Case Studies in Thermal Engineering

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Investigations on the thermal response of a solid rocket motor with complex charge structure using CL-20/GAP propellant

Cited by 12 publications

References 29 publications

Thermal structural damage and thermal decomposition characterization of GAP propellants with nitrate ester plasticizers

Thermal structural damage and thermal decomposition characterization of GAP propellants with nitrate ester plasticizers

Microfluidic preparation and thermal properties of HMX@PDA@MO

Friction-induced ignition study of HTPB propellant based on a coupled chemo-mechano-thermodynamic model under ultrahigh acceleration overload conditions

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