Strain rate and temperature dependence of the compressive behavior of a composite modified double-base propellant

Sun, Chaoxiang; Xu, Jie; Chen, Xiong; Zheng, Jian; Zheng, Yanying; Wang, Wenqiang

doi:10.1016/j.mechmat.2015.06.002

Cited by 58 publications

(23 citation statements)

References 40 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The propellants samples, which had a density of 1.66 g · cm À3 , were processed to be cylindrical with a size of 5 mm for diameter and 150 mm for length. The burning rates were measured at a range of pressure (8)(9)(10)(11)(12)(13)(14)(15)(16)(17)(18) in nitrogen atmosphere at 20 8C. Five tests were carried out at each pressure, and the burning rate at a certain pressure was characterized as the average value of five tests.…”

Section: Combustion Performance Testmentioning

confidence: 99%

“…Jin's group [12] found that the burning rate of RDX-CMDB propellant increased after adding catalyst. Sun and his co-operators [13] reported the mechanical properties of CMDB propellant at different strain rates and temperatures and the results showed that the yield stress increased with both increasing strain rate and decreasing temperature. In addition, the strain rate effect was more obvious than the temperature effect.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Application and Properties of Nano‐sized RDX in CMDB Propellant with Low Solid Content

Liu

Xiao

et al. 2017

Propellants Explo Pyrotec

View full text Add to dashboard Cite

Composite modified double‐base (CMDB) propellant, benefitting from the outstanding performances of high energy and low signature, has attracted increasing focus in the past decade. To improve the integrative performance, such as enhancing the mechanical property and decreasing the sensitivity, CMDB propellant with low solid content containing nano‐sized RDX has been prepared. The microstructure, mechanical properties, sensitivity and combustion performance of the prepared propellant are studied. Results have shown that the interface of the CMDB propellant contained nano‐sized RDX (N‐CMDB) is more compact and the internal defects are less than those of the CMDB propellant with micro‐sized RDX (M‐CMDB). Compared with the maximum tensile strength (σm) and the corresponding elongation at maximum tensile strength (ϵm) of M‐CMDB, the σm values of N‐CMDB are improved by 37.4 % at +50 °C, 27.5 % at +20 °C and 26.7 % at −40 °C, and the ϵm values are increased by 16.1 %, 19.4 % and 39.6 %, separately. Moreover, the friction and impact sensitivities of N‐CMDB propellant are decreased by 51.3 % and 50.4 %, respectively. In the range of 8–18 MPa, the combustion performance of N‐MCDB propellant has been demonstrated more attractive with higher burning rate coefficient (8.692→10.950) and lower pressure exponent (0.384→0.299). All these results lead us to believe that the usage of nano‐sized explosives will contribute to improve the comprehensive performance of CMDB propellants and promote their application in weapon system.

show abstract

Section: Combustion Performance Testmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Application and Properties of Nano‐sized RDX in CMDB Propellant with Low Solid Content

Liu

Xiao

et al. 2017

Propellants Explo Pyrotec

View full text Add to dashboard Cite

show abstract

“…It is widely accepted that modified double-base (MDB) propellants are evolved from double-base propellants by introduction of energetic fillers such as HMX or RDX [1][2][3]. There is also another trend to introduce potential oxidizers such as ammonium perchlorate (AP) or potassium perchlorate (KP) as well as active metal fuels such as aluminum, magnesium, and boron into MDB propellants [2,4,5].…”

Section: Introductionmentioning

confidence: 99%

“…Consequently, MDB propellants can offer wide range of burning rate and specific impulse [6]; this is why MDB propellants have recently been used in booster, sustainer, and dual thrust rocket motors [7]. MDB propellants have wide applications in tactical missiles due to their advantages including superior mechanical properties, aging capabilities, and good operational characteristics [1,2,8,9]. One of the main operational (ballistic) characteristics of extruded double base propellants, is their high specific impulse and burning rate which could be up to 220 s and 40 mm/s, respectively [10,11].…”

Section: Introductionmentioning

confidence: 99%

Certain Ballistic Performance and Thermal Properties Evaluation for Extruded Modified Double-base Propellants

Fahd¹,

Mostafa²,

Elbasuney³

2017

Cent. Eur. J. Energ. Mater.

View full text Add to dashboard Cite

Abstract:The main advantages of modified double-base (MDB) propellants are wide range of burning rates, high energy output, as well as enhanced thrust. This study reports on the effect of potential oxidizers − potassium perchlorate (KP) or ammonium perchlorate (AP), stoichiometric binary mixture of the oxidizer (KP or AP) with metal fuel (Al), and energetic nitramine (HMX) on combustion characteristics of MDB propellants. MDB propellant formulations based on these additives, constituting 10 wt.% of total mass of the MDB formulation, were manufactured by solventless extrusion process. The impact of these additives on ballistic performance particularly the burning rate as well as on the characteristic exhaust velocity of gaseous product (C * ), was evaluated using small-scale ballistic evaluation test motor. KP and AP exhibit different effects; KP positively impacts the burning rate, AP positively impacts C * . Stoichiometric binary mixture of AP/ Al positively impacts both the burning rate and C * ; HMX substantially enhances C * . These energetic additives could alter the combustion mechanism, by thinning the induction zone, allowing the luminous flame zone to be more adjacent to the burning surface. Therefore, the combustion reaction could proceed faster. The developed MDB propellant formulations were found to be more energetic with an increase in calorific value in comparison to reference formulation (using bomb calorimeter); they exhibited similar ignition temperature by means of cook off test. DSC measurements demonstrated similar onset and maximum decomposition temperature of developed MDB propellant formulations to reference DB propellant formulation but with an increase in total heat released (J/g).

show abstract

“…Zhang et al had conducted quasi-static tensile tests at low temperatures (298-223 K) and room temperature after storage at low temperatures to study the low temperature mechanical properties of HTPB propellant [7]. Using a conventional universal testing machine and a modified split Hopkinson pressure bar (SHPB) apparatus, Sun et al had studied the compressive behaviors of a composite modified doublebase (CMDB) propellant at low temperatures (298-233 K) and different strain rates (10 -4 -10 3 s -1 ) [8]. However, up to now, to the best of our knowledge, there are few analyses on the high strain rate (1-10 2 s -1 ) behaviors of solid propellants at low temperatures.…”

Section: Introductionmentioning

confidence: 99%

Effects of Low Temperature and High Strain Rate on the Tensile Behaviors of High-Performance Energetic Composite

Wang¹,

Qiang²,

Guang³

et al. 2016

MATEC Web Conf.

View full text Add to dashboard Cite

Strain rate and temperature dependence of the compressive behavior of a composite modified double-base propellant

Cited by 58 publications

References 40 publications

Application and Properties of Nano‐sized RDX in CMDB Propellant with Low Solid Content

Application and Properties of Nano‐sized RDX in CMDB Propellant with Low Solid Content

Certain Ballistic Performance and Thermal Properties Evaluation for Extruded Modified Double-base Propellants

Effects of Low Temperature and High Strain Rate on the Tensile Behaviors of High-Performance Energetic Composite

Contact Info

Product

Resources

About