Reliability Assessment of Solid-Propellant Rocket Motors Under Storage and Transportation Loads

Yılmaz, Okan; Kuran, Bayindir; Özgen, Gökhan O.

doi:10.2514/1.a33777

Cited by 30 publications

(12 citation statements)

References 17 publications

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“…These data can confirm the key parts of solid rocket motor for evaluating solid rocket motor technical status [6][7][8][9]. Domestic and foreign scholars [11][12][13][14] have carried out finite element analysis and research on the situation of solid rocket motor long-term storage, road transportation, carrier on duty and so on, and judged its reliability according to the damage criterion of grain, it provides a certain basis for motor life evaluation. However, the input condition of vibration load is low frequency vibration load, especially the period of ship motion is 10s, so the measured vibration data is not taken as the input condition.…”

Section: Introductionmentioning

confidence: 54%

Research on Fatigue Characteristics of Bonding interface of Solid Rocket Motor Propellant

et al. 2022

J. Phys.: Conf. Ser.

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With the continuous expansion of the combat mission of the Chinese Navy, the solid rocket motor will be on duty at sea for a long time. During the service period of solid rocket motor, the bonding interface will bear a large number of cyclic fatigue loads. According to the design test, the influence of the strain amplitude and frequency of loading on the bonding interface was studied. The results show that the cyclic loading frequency made no difference on the cyclic damage number in the high frequency. The natural logarithm of the cyclic loading times and cyclic loading accord with linear fitting equation.

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Section: Introductionmentioning

confidence: 54%

Research on Fatigue Characteristics of Bonding interface of Solid Rocket Motor Propellant

et al. 2022

J. Phys.: Conf. Ser.

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“…The transfer of stress and strain between the case and the propellant depends on the good buffering effect of the insulation. During storage and use, the coated charge must withstand a variety of stresses, including thermal stress caused by changes in ambient temperature, internal stress caused by the mass of the propellant or charge structure, and stress caused by overloads such as vibration and impact during engine ignition [1], transportation, and rocket flight [2]. The coating must maintain good mechanical properties to effectively reduce the external impact and protect the propellant from destruction in storage and transportation.…”

Section: Introductionmentioning

confidence: 99%

The aging property and storage life prediction of EPDM

shuang-hong,

chang-sheng,

chao-fan

2023

J. Phys.: Conf. Ser.

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The performance change of Ethylene propylene diene monomer (EPDM) was studied by the accelerated aging experimental method, and its lifespan was predicted. The results showed that the thermal oxidation aging of EPDM is dominated by the crosslinking reaction. With the extension of the thermal oxidation aging time, the total crosslinking density and tensile permanent deformation gradually decrease, while the tensile strength and hardness increase gradually. The life prediction formula of EPDM under the thermal-oxidative aging condition was obtained by the linearization method of the kinetic curve. When tensile permanent deformation was used as the evaluation index, the life was 30 a at the temperature of 296.15 K.

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“…Under storage and transportation conditions, the reliability of solid propellant rocket motors must be considered carefully, especially the degradation of the structural capability of the propellant must be investigated and controlled within a certain range [19]. Three-dimensional constitutive models were proposed to explain the mechanical phenomena of solid propellants, and then implemented in finite element analyses [20][21][22].…”

Section: Introductionmentioning

confidence: 99%

Study on the Viscoelastic Damage Properties of NEPE Solid Propellant with Different Cyclic Stress Ratios

Fang

Sha³

et al. 2022

Propellants Explo Pyrotec

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Viscoelastic damage properties of NEPE (Nitrate Ester Plasticized Polyether) solid propellant have been studied in this work. This work focuses on the creep and fatigue damage evolution. Cyclic loading tests for NEPE solid propellants are conducted with different stress ratios. Then a modified model incorporating viscoelasticity and damage evolution is presented and used to fit the experimental data. The fitting results show that the model is suitable to characterize the viscoelastic damage properties of NEPE propellants with different stress ratios. Based on the model with parameters for NEPE propellants, the damage parameter D are obtained. The damage evolution curves under different loading conditions are given. It is shown that, from the predicted damage evolution curves, the critical damage parameter Dcr at the fracture points can be used to predict the fatigue lives under different loading conditions.

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Reliability Assessment of Solid-Propellant Rocket Motors Under Storage and Transportation Loads

Cited by 30 publications

References 17 publications

Research on Fatigue Characteristics of Bonding interface of Solid Rocket Motor Propellant

Research on Fatigue Characteristics of Bonding interface of Solid Rocket Motor Propellant

The aging property and storage life prediction of EPDM

Study on the Viscoelastic Damage Properties of NEPE Solid Propellant with Different Cyclic Stress Ratios

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