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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->航天工程·数学与系统科学]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Current status and trend of dynamic atomization characteristics of swirl injector under oscillating environment in liquid rocket engines]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to master the atomization characteristics of oscillating spray and its relationship with unstable combustion, research and development of gas-liquid coaxial swirl injectors and liquid-liquid coaxial swirl injectors, which are widely used in liquid rocket engines, are reviewed from three aspects of excited oscillation, self-pulsation, and interactions of spray oscillation with combustion stability, so as to deepen our understanding of them. According to the review, for the excited oscillation, the research on the upstream pressure oscillation caused by flow oscillation of supply system under normal temperature and pressure conditions is relatively sufficient. However, the research on the backpressure oscillation caused by pressure oscillation in the combustion chamber and the research on the excited oscillation of spray under supercritical conditions are lack. For the self-pulsation, the current research is focused on the liquid-centered coaxial swirl injectors. There are few studies on the gas-centered coaxial swirl injectors and liquid-liquid coaxial swirl injectors. The optical diagnosis technology is far from enough to extract the single combustion flow field information.]]></description>
<pubDate>2023/6/7 0:00:00</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[JIANG Chuanjin, REN Yongjie, TONG Yiheng, XIE Yuan, CHU Wei, LI Xiuqian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Chuanjin, REN Yongjie, TONG Yiheng, XIE Yuan, CHU Wei, LI Xiuqian</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303001]]></guid><cfi:id>8</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[Experimental analysis of early stage frosting characteristics on the surface of Ni-based GH3536 superalloy plate]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Ni-based GH3536 superalloy smooth surface and microporous structured surface with hydrophobic properties were used as the object of study, and the early stage frosting characteristics of the surface were studied. The impact of surface temperature, relative humidity, and surface wettability on frost crystal shape and growth rate were investigated quantitatively. Results indicate that with the decrease of the surface temperature, the initial time of frost crystal formation is shortened, the growth rate of frost crystals is enlarged, and four types of frost crystal shapes are captured. The increase of relative humidity can increase the number of frost crystal and change frost crystal morphology, while the condensation and freezing time of droplets are independent of it. For the same frost crystal morphology, increasing the relative humidity has a certain promotion effect on the frost crystal growth, while when the frost crystal morphology changes, the change in relative humidity will result in significant differences in frost crystal height and growth rate. The hydrophobic surface made of micro-holes structures can evidently delay the formation of the crystal by increasing the nucleation barrier and contact thermal resistance. However, the impacts on frost crystal growth and shape are negligible.]]></description>
<pubDate>2023/6/7 0:00:00</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[ZHANG Duo, WANG Yuan, YUAN Xueqiang, YUE Xiaofei, LIU Jun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Duo, WANG Yuan, YUAN Xueqiang, YUE Xiaofei, LIU Jun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303002]]></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[Flow field structures and mode decomposition analysis of dual synthetic jets impinging plate]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To reveal the flow field characteristics of dual synthetic jets impinging plate, the large eddy simulation method was used to numerically study the flow of dual synthetic jets impinging plate. The Lagrangian coherent structure of the flow field was identified on the basis of the finite-time Lyapunov exponents, and the results were compared with the vorticity results in the Euler frame. It is found that the vortex structure of the jet core area of dual synthetic jets is exceeding complex and rich under the alternating action of periodical jets, and there is a pair of stable vortex structure far away from the core. Lagrangian coherent structures are well corresponding to the vorticity, provided guidance for the layout design of dual synthetic jets impingement cooling. Proper orthogonal decomposition analysis is performed on the flow field of dual synthetic jets. The results show that the first-order mode is approximately symmetrical about the central axis of the exit of the actuator, and its energy accounts for 35% of the total energy, and the first 6 modes account for 80%. According to the characteristics of the flow field reflected by the first 6 modes, the flow field of dual synthetic jets impinging plate has a high degree of symmetry.]]></description>
<pubDate>2023/6/7 0:00:00</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[DENG Xiong, LIU Qiang, WANG Qiuwang, LUO Zhenbing, CHENG Pan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DENG Xiong, LIU Qiang, WANG Qiuwang, LUO Zhenbing, CHENG Pan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303003]]></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[Design of extended mission to flyby multi small celestial bodies using lunar probe]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For a full utilization of the probe after the lunar exploration, the extended mission using the probe for flybys of multi small celestial bodies from the Moon or Earth orbit was proposed. Combined with the flight status of the probe after the lunar exploration mission, the energy requirement for escaping from the Moon or the Earth was emphatically analyzed, together with other necessary conditions for the flyby mission, such as the brightness of small celestial bodies, the capacity of onboard equipment, etc. The methods of selecting small celestial bodies and trajectory design were studied. Aiming at the problems of large search space, large amount of computation and hard optimization of multi target sequences caused by large number of targets, a multi-layer optimal search algorithm for small celestial bodies was designed. Taking Chang′e-5 as an example, the search yielded several feasible solutions for small celestial bodies′ flyby detection. The result shows that the orbiter can approach up to five asteroids under given constraints, including the large Asteroid 12923. The study conclusion can be used for the Chang′e-5 extended mission, and provide beneficial reference for the future missions of the Moon and small celestial bodies.]]></description>
<pubDate>2023/6/7 9:08:55</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[LIU Lei, CHEN Ming, ZHANG Yao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Lei, CHEN Ming, ZHANG Yao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303004]]></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[Test verification of multi-point injection air and ethanol gas generator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to effectively solve the shortcomings of the existing gas ejection source, as well as meet the needs of large mass flowrate and miniaturization of an injection system, a gas generator with multi-point injection structure using air and alcohol as propellants was developed based on the comprehensive analysis of various gas injection source schemes, and the experimental research under various working conditions was carried out. Research results show as bellows:the multi-point injection scheme greatly improves the space utilization rate, which effectively meets the miniaturization requirements of ejection system. Spray performance is good, and the spray cone angle and particle diameter are superior to the index requirements. Ignition reliability is high, which solves the shortcomings of low ignition reliability of the existing gas generator in the field. The operation curve indicates a rapid ignition, stable combustion and uniform temperature field of gas generator. The excess air coefficient range for stable operation is 2.52～4.34, showing a wide mass flow-rate range. In addition, efficient film cooling on the combustion liner inner wall effectively ensures the long time operation of the gas generator.]]></description>
<pubDate>2023/6/7 9:08:55</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[ZHAO Fang, REN Zebin, WANG Fei, SHI Yu, LI Xianfeng, LUO Zhifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Fang, REN Zebin, WANG Fei, SHI Yu, LI Xianfeng, LUO Zhifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303005]]></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[Simulation of key parameters in engineering design of anode gas distribution ring of low-power Hall thruster]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the uniformity of the neutral atom distribution in the discharge channel of the low-power Hall thruster, the finite element method was used to optimize the key structural parameters of the anode gas distribution ring. Aiming at the double-chamber anode gas distribution ring structure, the influence of key parameters such as the volume ratio of the buffer chambers and the number of diversion holes between the buffer chamber partitions on the uniformity of anode gas supply was analyzed. The research results show that with the increase of the volume ratio, the difference of the anode gas distribution ring outlet pores decreases rapidly and then stabilizes. When the ratio <i>k</i>=1.0, the average difference rate and the maximum difference rate are 1.77% and 3.79%, respectively; when the number of diversion holes between the buffer chamber partitions increases from 8 to 14, the difference rate of the air outlets shows the characteristics of the bathtub curve, and when number of the diversion holes is 10, the average difference rate and the maximum difference rate are 1.8% and 3.8%, respectively. The research results can provide theoretical support for the engineering design of the anode gas distribution ring of the Hall thruster.]]></description>
<pubDate>2023/6/7 9:08:55</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[LONG Jianfei, LUO Wei, CHENG Mousen, YANG Wei, SUN Mingming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LONG Jianfei, LUO Wei, CHENG Mousen, YANG Wei, SUN Mingming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303006]]></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[Calculation of ground proximity warning envelope based on flight simulation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The ground proximity warning envelope in TSO-C151b standard is a general model design without considering the characteristics of the aircraft. In order to accurately give the warning envelope of excessive descent rate of a certain aircraft, the alarm mechanism was analyzed by combining the aerodynamic characteristics and control characteristics of the aircraft, and a six degree of freedom simulation program was established. Based on the aircraft engine data, aerodynamic data and quality characteristics data, simulation models and operation procedures were established to simulate the operation response process of each rudder surface, as well as the motion attitude and flight path of the aircraft in real time. The loss height pulled up by the aircraft at different descent rates was calculated, and the ground proximity warning envelope was designed. The actual flight test data verified that the model design is reasonable and the calculation results are accurate. The alarm envelope obtained by simulation is compared with TSO-C151b, and the suggestions for the use of the ground proximity warning envelope are given to ensure the flight safety of the aircraft.]]></description>
<pubDate>2023/6/7 9:08:55</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[ZHENG Fengmin, WEI Tao, LI Zehua, LIU Chen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Fengmin, WEI Tao, LI Zehua, LIU Chen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303007]]></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[Reliability modeling of <i>k</i>-out-of-<i>n</i> system with one repairman having variant vacations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the impact of maintenance scheduling on equipment training and reliability in equipment support, the maintenance work of multiple ships supported by the detachment-level repair station was abstracted into a single maintenance station to support the dispatching and distribution of maintenance forces for multiple systems, the variable vacation strategy of repairman was introduced to describe it. Take the common <i>n</i> out of <i>k</i> system in the equipment structure as the research object, aiming at the problem of excessively strict model constraints caused by typical distributions such as exponential distributions in previous studies, continuous Phase-type distribution was used to describe the system-dependent random variables and build system reliability analysis model.Finally, the model applicability was verified using numerical application, and it was analyzed the influences of whether the repairman was on vacation, the changes of system components numbers, and the effect of repairman vacation rate and maintenance rate on system reliability. Numerical example results show that the reliability model can be effective retrieval the influence of maintenance forces scheduling on the reliability of <i>k</i>-out-of-<i>n</i> system, it can provide theoretical basis and practical reference for the reasonable arrangement of the number of repairman vacation and the optimal configuration of the number of system components.]]></description>
<pubDate>2023/6/7 0:00:00</pubDate>
<category><![CDATA[航天工程·数学与系统科学]]></category>
<author><![CDATA[YIN Dongliang, WU Jing, HUANG Xiaoying]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Dongliang, WU Jing, HUANG Xiaoying</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202303008]]></guid><cfi:id>1</cfi:id><cfi:read>true</cfi:read></item>
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