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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->航空宇航科学与技术·机械工程]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Advance on calculation methods of fluid-solid coupled heat transfer with regenerative cooling system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250511]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Fluid-solid coupled heat transfer is regarded as a key challenge in the refined design of regenerative cooling thermal protection systems. From the perspective of fluid-solid heat transfer, the calculation methods for heat transfer between hot gas and the solid chamber wall were introduced, the heat transfer calculation methods of coolants within cooling channels were presented, and the special factors affecting heat transfer between the coolant and the wall were analyzed, including secondary flow, supercritical effects, and cracking characteristics, etc. For regenerative cooling systems, three fluid-solid coupled heat transfer calculation methods were proposed: the whole-domain solution method, the partition solution method based on correlation criteria, and the partition solution method based on continuity boundary conditions. In the field of unsteady heat transfer, the research progress of fluid-solid coupled unsteady calculation methods was reviewed, and the possible future development directions of this field were preliminarily discussed.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[HU Tianyong, SHEN Binxian, ZENG Lei, TANG Zhigong]]></author>
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<atom:name>HU Tianyong, SHEN Binxian, ZENG Lei, TANG Zhigong</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250511]]></guid><cfi:id>7</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[Theoretical and experimental study on suppressing galloping ofcylinder by nonlinear targeted energy transfer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250512]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A vibration control strategy based on NTET (nonlinear targeted energy transfer) for suppressing galloping of the cylinder was proposed. The effect of NTET on controlling galloping responses was explored from both theoretical and experimental aspects. The fluid force was described based on the quasi-steady theory. The dynamic theoretical model was constructed based on the energy method for the coupling of cylinder galloping and NTET. The theoretical model was validated by comparing the predicted results with experiments. The linear dynamic analysis shows that increasing the spring pretension can increase the coupled damping ratio and frequency. As a result, the onset wind speed of galloping for the square cylinder is decreased. The nonlinear dynamics analysis reveals that the NTET′s linear and nonlinear stiffness have an effect on the vibration responses. There is an optimal value of linear stiffness where the suppressing effect is the best. The larger the nonlinear stiffness is, the better the control effect of the NTET. Whats more, the smaller the spring pretension of the NTET, the larger the spring stiffness, and the lower the amplitude of the cylinder. This study can provide theoretical support and experimental data for effectively designing galloping control strategies in engineering applications.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[DAI Huliang, XING Haoran, HE Yixiang, LU Zi, ZHANG Lanbin, WANG Lin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DAI Huliang, XING Haoran, HE Yixiang, LU Zi, ZHANG Lanbin, WANG Lin</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250512]]></guid><cfi:id>6</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[Approximate optimization method for constraints dynamic relaxation of black box model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250513]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The surrogate model-based optimization method provides an effective technical approach for the application of high-precision simulation models in optimal design due to its efficient search capability. To address the problem of time-consuming black-box constraint processing for optimization problems, a multi-constraint adaptive sampling method based on improved feasible rules was proposed, an elite archive-driven inexact search method and an <i>ε</i>-constraint-preserving pseudo-feasible domain construction method were established, and the algorithms ability to explore the boundaries of the feasible domain was enhanced by dynamically scaling the feasible domain to accept high-quality nonfeasible samples during the iterative process, which improved the surrogate model-based optimization search ability. Simulation results of the Congress on Evolutionary Computation constraint optimization standard function indicate that the <i>ε</i>- onstraint maintenance optimization method is effective in solving the multi-constraint surrogate model optimization problem compared with the existing methods. The results for the solid rocket motor rear wing pillar charge design show that the algorithm has the potential to be applied to complex engineering problems.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[MA Shuaichao, WU Zeping, YANG Jiawei, GAO Jingwei]]></author>
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<atom:name>MA Shuaichao, WU Zeping, YANG Jiawei, GAO Jingwei</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250513]]></guid><cfi:id>5</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[Optimization method for high-precision multi-satellite rendezvous using multi-round iterative correction]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250514]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the high-precision rendezvous trajectory optimization problem of a single chase satellite serving multiple target satellites on orbit, a three-step serial optimization method based on the multi-round iterative correction was proposed. The rendezvous sequence and approximate impulse solutions based on the analytical J2 perturbation model were obtained by using the differential evolution algorithm, and the high-precision solution of the first rendezvous maneuvering impulses was obtained by using the local optimization of the sequential quadratic programming algorithm. Moreover, a multi-round iterative correction model was constructed to update the subsequent target satellites′ states and maneuvering impulses to reduce the influence of the error diffusion between different models. Simulation results show that the proposed method can stably obtain the high-precision maneuvering parameters with approximate least cost in a few iterations.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[ZHANG Jin, WANG Kemao, YAN Bing, WANG Liyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jin, WANG Kemao, YAN Bing, WANG Liyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250514]]></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[Analysis of flow field characteristics of shock wave/turbulent boundary layer interaction under conjugate heat transfer conditions]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250515]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Shock wave/boundary layer interaction results in significant aerodynamic heating on the surface of the aircraft. The original flow field structure is also affected by the increase in wall temperature. To investigate the flow field characteristics of shock wave/boundary layer interaction under CHT (conjugate heat transfer) conditions, numerical simulations were performed. The flow field structure, wall parameters and solid domain temperature distribution were analyzed under different wall materials, aerodynamic heating time and total temperature. The numerical results indicate that: the length of the separation bubble obtained using the CHT method is between the results for isothermal and adiabatic walls. As the thermal diffusivity of the wall material decreases and the aerodynamic heating time increases, the length of the separation bubble increases. At the same time, the wall temperature peak increases, and the heat flux peak decreases. For the same material and heating time, an increase in total temperature reduces the length of the separation bubble. This suggests that the change in Reynolds number caused by the total temperature dominates the separation characteristics. Additionally, for the solid domain at the corresponding position of the reattachment zone downstream of the interaction, a significant temperature rise is observed. The high-temperature zone inside the bakelite wall diffuses very slowly and exhibits a flaky distribution.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[LIN Yujing, LIU Weidong, WEI Feng, YANG Rui, YU Jiangfei]]></author>
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<atom:name>LIN Yujing, LIU Weidong, WEI Feng, YANG Rui, YU Jiangfei</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250515]]></guid><cfi:id>3</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[Mathematical model for single-course resistance torque of spacesuit soft joints]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250516]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the problems of low accuracy and large shape error of existing models for single-course resistance torque of spacesuit soft joints, an improved B-W(Bouc-Wen) mathematical model was established. By analyzing the hysteresis curve characteristics of single-course resistance torque of spacesuit soft joints, the B-W hysteresis model was introduced and improved to eliminate the redundancy and symmetry of the model, which was used to characterize single-course resistance torque of soft joints mathematically. The individual genetic process of multi-island genetic algorithm was operated by using the probability thought of simulated annealing algorithm to identify the parameters of improved B-W model with high accuracy and efficiency. Based on the verification of experiments and simulations of different soft joints of spacesuit, the improved B-W model compared with the J-A(Jiles-Atherton) model is more suitable for the mathematical characterization of single-course resistance torque of spacesuit soft joints. The variance of resistance torque of improved B-W model is two orders of magnitude lower than that of J-A model. It shows that the mathematical model has high accuracy when applied to single-course resistance torque of spacesuit soft joints, and has strong applicability to different soft joints of spacesuit.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[DONG Changlin, ZHOU Shiming, LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DONG Changlin, ZHOU Shiming, LI Daokui</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250516]]></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[Vertical damping of the superconducting electrodynamic suspension system and its improving measure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/20250517]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Due to the low damping characteristic of the superconducting EDS (electrodynamic suspension) system which may cause suspension instability problem, a six degree-of-freedom dynamic model for the high speed maglev sled system was established, and it was found that the suspension damping would become negative when the traveling speed exceeds 23.6 m/s, resulting in suspension instability to the maglev sled. The vertical damping ratio of the EDS system was calculated using the least square fitting method, and the relationship between the vertical damping and the speed was obtained. To stabilize the suspension system, a distributed DVA (dynamic vibration absorbers) scheme was proposed, and the effects of the DVA parameters on the suspension stability were investigated. To minimize the influence of the DVA scheme on the acceleration performance of the maglev sled, the feasibility of applying low mass (≤1 kg) DVAs to the maglev sled was discussed. Further, the vibration suppression effect of this scheme was investigated considering the vertical misalignments of guideway girders. Results shows that the proposed scheme can significantly increase the damping and stability of the suspension system, and it also well suppresses the vibration of the sled-body caused by misalignments of the ground suspension coils. This scheme provides a useful reference for the design of the suspension system of the maglev sled system, the vacuum tube high speed maglev train, etc.]]></description>
<pubDate>2025/10/8 0:00:00</pubDate>
<category><![CDATA[航空宇航科学与技术·机械工程]]></category>
<author><![CDATA[ZHOU Danfeng, ZHU Pengxiang, TAN Yiqiu, WANG Lianchun, LI Jie, CHEN Qiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Danfeng, ZHU Pengxiang, TAN Yiqiu, WANG Lianchun, LI Jie, CHEN Qiang</atom:name>
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