Effect of Cumulative Damage on Rocket Motor Service Life

Gligorijević, Nikola; Živković, Sanja; Subotić, Sredoje; Rodić, Vesna; Gligorijević, Ivan

doi:10.1080/07370652.2014.970245

Cited by 26 publications

(40 citation statements)

References 27 publications

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“…During an earlier study [2,8,11], a mathematical model for the time distribution of the temperature was formed.…”

Section: Temperature Load Analysismentioning

confidence: 99%

“…In the papers [2,3], this terminology is considered in more detail. Instead of the term "damage fraction", the term "current damage" is used.…”

Section: Introductionmentioning

confidence: 99%

“…Similarly, the work [10] also ignores the effect of damage accumulation in the initial storage period. However, based on our experience [2,8,11] this factor can be high even in the initial period. It depends on variation of the ambient temperature, geometrical characteristics of the grain (Fig.1), mechanical properties of the propellant and case, and especially on the difference between thermal expansion coefficients of the propellant and case.…”

mentioning

confidence: 96%

“…One of the authors who pay attention on this feature is Heller [4,6,7]. His model for defining the mechanical properties of viscoelastic material during long-term storage includes natural (chemical) aging and the weakening due to the effect of cumulative damage under the environmental loads, equations 4 and 5:  is a property of the polymeric material and can be determined by periodic tensile tests [2,6,8,9]. It is usually considered that the values of the factor ( ) D , that define the accumulated damage, are too small for fresh propellant, in the initial period after production.…”

mentioning

confidence: 99%

See 3 more Smart Citations

Effect of cyclic loads on structural damage of rocket propellant grain

Gligorijević¹,

Rodić²,

Pavkovic³

et al. 2019

Sci Tech Rev

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Rocket motor propellant grain, cast or bonded into the motor chamber or solid coating, is exposed to various loads during its service life. Rocket propellant is a viscoelastic material, whose mechanical properties strongly depend on temperature and strain rate. Application of cyclic loads, primarily thermal, onto a rocket motor on the field stock, may cause an undesirable mechanical damage of the grain. Over time, after long storage, it may grow up and lead to the grain failure. One of the ways for evaluation of this phenomenon is to determine a cumulative damage law. In this example, this law has been evaluated for hydroxy terminated polybutadiene (HTPB) composite rocket propellant by exposing a number of specimens to different long term stress levels. Using this law, it is possible to calculate a probability of failure and time distribution of the structural reliability of the grain in order to determine the useful life. Besides, the analysis has shown that there is a possible correlation between tensile strength of the propellant and the cumulative damage law. This fact can be used instead of carrying a longterm experiment for the exact determination of the law

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“…During an earlier study [2,8,11], a mathematical model for the time distribution of the temperature was formed.…”

Section: Temperature Load Analysismentioning

confidence: 99%

“…In the papers [2,3], this terminology is considered in more detail. Instead of the term "damage fraction", the term "current damage" is used.…”

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 96%

mentioning

confidence: 99%

See 2 more Smart Citations

Effect of cyclic loads on structural damage of rocket propellant grain

Gligorijević¹,

Rodić²,

Pavkovic³

et al. 2019

Sci Tech Rev

Self Cite

View full text Add to dashboard Cite

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“…Theoretically, for the linear-viscoelastic material, the mathematical model for the calculation of cumulative damage and service life can be applied. [9,[17][18][19][20].…”

Section: Safety Factor Estimate In the Case Of Multiple Loadsmentioning

confidence: 99%

Thermal and acceleration load analysis of new 122 mm rocket propellant grain

Gligorijević¹,

Antonovic²,

Živković³

et al. 2016

Sci Tech Rev

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In order to achieve very strong inter-ballistic requirements, a unusual free standing rocket motor propellant grain was designed, with variable channel diameter. Due to its very high length, it was expected for the grain to be exposed to dangerous combination of different loads during the design phase. Structural analysis of viscoelastic propellant grain is always very complex and it differs substantially from an elastic analysis, because the propellant mechanical properties depend on temperature and strain rate. The most complex case in the analysis occurs when multiple loads operate simultaneously. In this paper, the structural analysis has been done during the initial period of rocket flight, when the grain is under very fast load due to acceleration and at the same time under a slow load due to surface pressure, created as a result of temperature dilatation. In the absence of data on mechanical properties of the new propellant composition, the properties over the whole time-temperature range were estimated comparing by a similar composition that have been completely tested earlier. Using finite element method (ANSYS program) two different design solutions were examined and the more reliable one was adopted.

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Effects of Superimposed Pressure on the Mechanical Properties of HTPB Propellant in a Wide Temperature Range

Zhang

Shen

2020

Propellants Explo Pyrotec

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Considering the propellant of solid rocket motor with tube grain is in the state of superimposed pressure after ignition, the effect of pressures, temperatures, and tensile rates on the mechanical properties of solid propellant were investigated together. A test system with wide temperature‐ambient pressure range was developed to investigate the effects of superimposed pressure on the performance of propellant. The uniaxial constant tensile rate tests for a certain HTPB propellants under different superimposed pressures and temperatures were performed at different tensile rates. Research shows that there are no apparent dewetting points in the propellant stress‐strain curves under superimposed pressures. Moreover, the performance of propellant under superimposed pressure related to propellant itself such as composition of the propellant was evaluated by comparing to another propellant. Relevant methods and conclusions can provide a reference for structural analysis and storage life prediction of solid rocket motors.

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Effect of Cumulative Damage on Rocket Motor Service Life

Cited by 26 publications

References 27 publications

Effect of cyclic loads on structural damage of rocket propellant grain

Effect of cyclic loads on structural damage of rocket propellant grain

Thermal and acceleration load analysis of new 122 mm rocket propellant grain

Effects of Superimposed Pressure on the Mechanical Properties of HTPB Propellant in a Wide Temperature Range

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