Heterobimetallic Catalysts for the Thermal Decomposition of Ammonium Perchlorate: Efficient Burning Rate Catalysts for Solid Rocket Motors and Missiles

2021 ◽  
Vol 60 (3) ◽  
pp. 1436-1448
Author(s):  
Juan Luis Arroyo ◽  
Ángel Norambuena ◽  
Héctor Reyes ◽  
Cristian Valdebenito ◽  
Gabriel Abarca ◽  
...  
Keyword(s):  
Thermal Decomposition ◽  
Burning Rate ◽  
Ammonium Perchlorate ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Solid Rocket ◽  
Heterobimetallic Catalysts

scholarly journals Effect of Metal Nanopowders on the Performance of Solid Rocket Propellants: A Review

Nanomaterials ◽  
2021 ◽  
Vol 11 (10) ◽  
pp. 2749
Author(s):  
Weiqiang Pang ◽  
Yang Li ◽  
Luigi T. DeLuca ◽  
Daolun Liang ◽  
Zhao Qin ◽  
...  
Keyword(s):  
Burning Rate ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Rocket Propellants ◽  
Different Types ◽  
Composite Fuel ◽  
Solid Rocket ◽  
Double Base ◽  
Friction Sensitivity ◽  
Solid Rocket Propellants

The effects of different types of nano-sized metal particles, such as aluminum (nAl), zirconium (nZr), titanium (nTi), and nickel (nNi), on the properties of a variety of solid rocket propellants (composite, fuel-rich, and composite modified double base (CMDB)) were analyzed and compared with those of propellants loaded with micro-sized Al (mAl) powder. Emphasis was placed on the investigation of burning rate, pressure exponent (n), and hazardous properties, which control whether a propellant can be adopted in solid rocket motors. It was found that nano-sized additives can affect the combustion behavior and increase the burning rate of propellants. Compared with the corresponding micro-sized ones, the nano-sized particles promote higher impact sensitivity and friction sensitivity. In this paper, 101 references are enclosed.

scholarly journals The effect of reduced graphene oxide on the catalytic activity of Cu–Cr–O–TiO2 to enhance the thermal decomposition rate of ammonium perchlorate: an efficient fuel oxidizer for solid rocket motors and missiles

RSC Advances ◽  
2017 ◽  
Vol 7 (58) ◽  
pp. 36594-36604 ◽  
Author(s):  
Harish Kumar ◽  
Prahalad N. Tengli ◽  
Vijay Kumar Mishra ◽  
Pankaj Tripathi ◽  
Awani Bhushan ◽  
...  
Keyword(s):  
Thermal Decomposition ◽  
Graphene Oxide ◽  
Catalytic Activity ◽  
Reduced Graphene Oxide ◽  
Decomposition Rate ◽  
Composite Propellant ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Reduced Graphene ◽  
Solid Rocket

Schematic image of rocket having solid composite propellant modified with prepared catalyst.

scholarly journals Synthesis and catalytic activity of Cu–Cr–O–TiO2 composites for the thermal decomposition of ammonium per-chlorate: enhanced decomposition rate of fuel for solid rocket motors

RSC Advances ◽  
2017 ◽  
Vol 7 (21) ◽  
pp. 12486-12495 ◽  
Author(s):  
Harish Kumar ◽  
Prahalad N. Tengli ◽  
Vijay Kumar Mishra ◽  
Pankaj Tripathi ◽  
Dan Bahadur Pal ◽  
...  
Keyword(s):  
Thermal Decomposition ◽  
Catalytic Activity ◽  
Decomposition Rate ◽  
Sol Gel ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Gel Method ◽  
Sol Gel Method ◽  
Solid Rocket ◽  
Catalytic Effects

This study presents the synthesis of Cu–Cr–O·nTiO2 particles via sol–gel method and their catalytic effects on thermal decomposition of AP.

scholarly journals Precise Design of Solid Rocket Motor Heat Insulation Layer Thickness under Nonuniform Dynamic Burning Rate

2019 ◽  
Vol 2019 ◽  
pp. 1-13
Author(s):  
Ran Wei ◽  
Futing Bao ◽  
Yang Liu ◽  
Weihua Hui
Keyword(s):  
Open Source ◽  
Burning Rate ◽  
High Performance ◽  
Traditional Approach ◽  
Computation Time ◽  
Solid Rocket Motor ◽  
Validation Data ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Solid Rocket

With the purpose of obtaining optimal designs of the heat insulating layers in solid rocket motors, we have proposed a numerical approach to compute the ideal thickness of the heat insulating layer. The proposed method is compatible with solid rocket motors that have any shape and any manner of erosion. The nonuniform dynamic burning rate is taken into consideration to achieve higher accuracy. A high-performance code is developed that uses triangular geometry as an input to allow exchanging data from any CAD platform. An improved geometric intersection algorithm is developed to generate the required sampling points, saving 35% computation time compared to its open source equivalent. Parallel computing technology is utilized to further improve the performance. All operations of the proposed approach can be executed automatically by programs, eliminating the manual work of gathering data from CAD software in the traditional approach. Validation data shows that the proposed approach saves 3.85% of the mass compared to the ordinary design approach. Performance profiling shows that the implemented code operates within 5 seconds, which is much faster than the unoptimized open source version.

Magnetic field control of burning rate and thrust in solid rocket motors

1995 ◽  
Vol 11 (4) ◽  
pp. 824-829 ◽  
Author(s):  
Igor G. Borovskoi ◽  
Alexander B. Vorozhtsov
Keyword(s):  
Magnetic Field ◽  
Burning Rate ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Field Control ◽  
Solid Rocket
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