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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->Structural Integrity Analysis of Solid Rocket Moto]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Progress and development trend of composite solid propellant constitutive model research]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As an important energy source of solid rocket motors, the mechanical properties of composite solid propellants have always been the focus of attention in the engineering field. The macroscopic constitutive model and the fine-scale mechanical model in the characterisation of propellant mechanical properties was focused on. The development of the two types of models was systematically sorted out. The differences between the models were clarified. The applicable conditions of various models were pointed out. The difficulties and challenges of macro and fine mechanical models in the characterisation of propellant mechanical properties at the present stage were analysed. The proposal of mechanical models represented by cross-scale mechanical models will help to solve the problem of propellant mechanical property characterisation. The key in the future modelling of propellant mechanical characterization is the experimental research under complex conditions, focusing on the development of high precision and high performance multiscale numerical computation methods, as well as the integration of data-driven technology represented by artificial intelligence technology into model innovation.]]></description>
<pubDate>2025/1/20 0:00:00</pubDate>
<category><![CDATA[Structural Integrity Analysis of Solid Rocket Moto]]></category>
<author><![CDATA[XU Yihang, LI Daokui, ZHOU Shiming]]></author>
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<atom:name>XU Yihang, LI Daokui, ZHOU Shiming</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mechanical properties experiment of HTPB propellant under extreme temperature]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study the mechanical properties and failure mechanism of the solid propellant under extreme low temperature environment, the uniaxial tensile test of a three-component butyl hydroxyl propellant was carried out under different temperatures, wide range of superimposed pressure values and high strain rate conditions by adopting the self-developed wide-temperature-superimposed pressure loading test system, and the  fracture morphology was observed by electron microscope scanning.  The effect of temperature, tensile rate and peripheral pressure value on the mechanical properties of the propellant was analysed, and the damage mechanism of the propellant under different working conditions was discussed. Results show that when the tensile rate increases, the superimposed pressure increases and the temperature decreases, the elongation of the dewetting point of the propellant decreases, the dewetting point moves forward, and dewetting occurs inside the propellant. There are superimposed pressure and strain rate thresholds, above which the propellant is more prone to dewetting behaviour. At low temperature, the maximum elongation of propellant is more sensitive to the change of high tensile rate, and its maximum tensile strength and maximum elongation both tend to increase with the increase of the value of the peripheral pressure, and the maximum elongation is 28.8% under the extreme tensile condition of -55 ℃, 10 MPa, and 4 200 mm/min. The failure mode of the propellant is affected by a combination of dewetting damage, matrix fracture, and particle cracking, as the temperature decreases and the tensile rate increases.]]></description>
<pubDate>2025/1/20 0:00:00</pubDate>
<category><![CDATA[Structural Integrity Analysis of Solid Rocket Moto]]></category>
<author><![CDATA[SUN Haitao, YANG Geng, YUAN Jiehong, SHEN Zhibin, HUO Liang]]></author>
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<atom:name>SUN Haitao, YANG Geng, YUAN Jiehong, SHEN Zhibin, HUO Liang</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Low-frequency fatigue characteristics of NEPE solid propellant]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To investigate the damage evolution process of low-frequency fatigue-loaded NEPE (nitrate ester plasticized polyether) solid propellant and get the influence law of fatigue loading history on tensile mechanical properties of NEPE solid propellant, the NEPE solid propellant low-frequency fatigue tests and uniaxial tensile tests with constant strain rate were conducted by the electronic universal testing machine. Based on the microscopic morphology and testing curves of test piece after fatigue loading, the influential mechanism of microscopic and mesoscopic damage on the NEPE solid propellant macroscopic mechanical behavior was further analyzed. Results indicate that the NEPE solid propellant matrix microcracks and voids at the matrix/particle interface are induced by low-frequency fatigue loads, leading to nonnegligible stress-softening behavior and residual strain. During and after fatigue loading, the attenuations of macroscopic mechanical properties of NEPE solid propellant are all exponentially related to the maximum loading strain. Part of microscopic damage by low-frequency fatigue load can recover, while the remaining fatigue damage may enhance the molecular chain orientation ability, and thus lead to the fatigue-strengthening phenomenon in materials.]]></description>
<pubDate>2025/1/20 0:00:00</pubDate>
<category><![CDATA[Structural Integrity Analysis of Solid Rocket Moto]]></category>
<author><![CDATA[ZHANG Wenqin, ZHANG Dapeng, LEI Yongjun, SHEN Zhibin, WU Fanji]]></author>
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<atom:name>ZHANG Wenqin, ZHANG Dapeng, LEI Yongjun, SHEN Zhibin, WU Fanji</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501003]]></guid><cfi:id>4</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of tensile rate on parallel rheological framework  model of  HTPB propellant]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the effect of different combinations of stretching rates of four-component HTPB propellant on the accuracy of the parallel rheological framework model, a nonlinear viscoelastic constitutive model of the propellants was developed based on the parallel rheological framework method. A constitutive model was constructed by combining experiments with different tensile rates, the corresponding constitutive model parameters were obtained and compared with experimental results using finite element models and numerical calculations. The constitutive model errors of the calibration for different rate groups were compared and analyzed. The results show that the model can be calibrated more accurately when a combination of high rate and low rate groups is used, without the need for extensive experiments at intermediate rates. And the high rate propellant tensile test rate can be up to 3 000 mm/min, no need to increase the rate. This analysis provides justified suggestions for simplifying propellant material tests and improving the efficiency of the experiments. Concurrently, it paves an effective way to rapidly predict the mechanical properties of propellant materials.]]></description>
<pubDate>2025/1/20 0:00:00</pubDate>
<category><![CDATA[Structural Integrity Analysis of Solid Rocket Moto]]></category>
<author><![CDATA[ZHOU Shiming, XU Yihang, LI Daokui, SHEN Zhibin]]></author>
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<atom:name>ZHOU Shiming, XU Yihang, LI Daokui, SHEN Zhibin</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Tension-compression asymmetric viscoelastic plastic constitutive model of HTPB propellant]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Tensile and compressive creep behavior of propellants in solid motors due to the influence of the gravity and long-term storage might affect the interior ballistics and structural integrity. In order to investigate the change trends of tensile and compressive creep for HTPB propellant, the 1 000 s tensile, 1 000 s compression and 28 d tensile creep tests were designed and carried out in this work. Meanwhile, the Saint-Venant body and the compressive-tensile asymmetry factor were introduced to establish a propellant viscoelastic plastic constitutive model that takes into account compressive-tensile asymmetry. The range of application of this equation was obtained by fitting and analyzing the parameters in the constitutive equation. The results indicate that the compressive creep process of propellant was mainly dependent on stress level. At the same stress level, viscoelastic deformation of tensile creep is about 1.62 times that of compressive creep, while compressive yield stress is 3.82 times that of tensile yield stress. The tension-compression asymmetric viscoelastic plastic constitutive model can well characterize the tensile-compression creep response of propellants at the lower stress levels. The conclusions and research method in this work can provide reference for structural integrity analysis and storage life evaluation of solid motor.]]></description>
<pubDate>2025/1/20 0:00:00</pubDate>
<category><![CDATA[Structural Integrity Analysis of Solid Rocket Moto]]></category>
<author><![CDATA[DENG Kuangwei, LI Haiyang, SHEN Zhibin]]></author>
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<atom:name>DENG Kuangwei, LI Haiyang, SHEN Zhibin</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501005]]></guid><cfi:id>2</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of fiber bragg grating sensor in monitoring of internal strain of solid rocket motor grain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202501006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An embedded strain measurement method based on fiber bragg grating sensor was proposed to solve difficult problems in measuring the internal strain response of solid rocket motor grain. The solid rocket motor tester of embedded fiber bragg grating strain sensor was designed, and the cold pressurization test was carried out on the tester. The axial and circumferential strains in the grain structure were obtained under cold pressurization test. Research shows that the proposed test method can obtain the circumferential strain and axial strain in internal grain. The research results can lay a foundation for the further application of fiber bragg grating sensor in the measurement of solid motor grain structure, and can provide a reference for the development and application of solid motor monitoring and detection technology.]]></description>
<pubDate>2025/1/20 0:00:00</pubDate>
<category><![CDATA[Structural Integrity Analysis of Solid Rocket Moto]]></category>
<author><![CDATA[ZHANG Tao, LI Haiyang, SHEN Zhibin, WU Guofu, BIAN Yunlong, WANG Limin]]></author>
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<atom:name>ZHANG Tao, LI Haiyang, SHEN Zhibin, WU Guofu, BIAN Yunlong, WANG Limin</atom:name>
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