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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->专栏：全电无人飞行器技术]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Development status and technology challenges of high-altitude long-endurance solar-powered aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[HALE(high-altitude long-endurance) solar-powered aircrafts are the research frontiers, they can staying airborne for several months, and can form new application ability named "long-endurance+station-keeping". The three-stage development process of HALE solar-powered aircrafts was systematically summarized, including early exploration stage, rapid development stage and operational capability demonstration stage, and typical development plans aboard were introduced. Key technology challenges were analyzed, including aerodynamic configuration design, energy storage battery, high altitude propulsion, large scale structure and flight control, and the suggestions for research directions were proposed. All those can provide reference for innovation development of HALE solar-powered aircrafts.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[专栏：全电无人飞行器技术]]></category>
<author><![CDATA[YANG Xixiang,HOU Zhongxi,GUO Zheng]]></author>
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<atom:name>YANG Xixiang,HOU Zhongxi,GUO Zheng</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Near-field frequency domain imaging algorithm about the aircraft′s scattering characteristics diagnosis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The flexibility of UAV in structural style and material composition makes it have more space for stealth performance optimization than the manned aircraft, so it was urgent to carry out near-field imaging indoors or outdoors. Based on the imaging geometry model of aircraft turntable, a general signal model of near-field turntable imaging was established, and a near-field frequency-domain imaging algorithm for aircraft electromagnetic scattering feature diagnosis was proposed. Under the constraint of sub aperture imaging setting, the slant plane spectrum was approximately processed as the horizontal plane spectrum; the applicable conditions of the algorithm was analyzed, and simulation data around typical near-field imaging geometry and aircraft size was generated.The completes near-field imaging in the range of 0.6~35 GHz was performed. Good imaging results confirm the correctness of the theoretical analysis and the proposed algorithm.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[专栏：全电无人飞行器技术]]></category>
<author><![CDATA[JIA Gaowei,YIN Peng,SHAO Shuai]]></author>
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<atom:name>JIA Gaowei,YIN Peng,SHAO Shuai</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structural optimization for composite wings of tail-sitter electric aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the requirements of material delivery platform in the complex terrain area, the research on the structural design of the composite wing of the tail-sitter electric aircraft was carried out. Based on the load analysis, the structural configuration and lay out designs were studied, and the structural design scheme of the composite wing was proposed. The finite element model of the composite wing was developed and the static strength analyses under different operating conditions were completed. The deformation, structural stress, and Tsai-Wu failure factor distribution of the wing structure were obtained. The structural optimal analysis of the composite wing was performed on the basis of the stepwise optimization strategy with the layer thicknesses and angles as design variables. The optimal results show that the structural mass is reduced by 47.77% under the constraints of structural stiffness and strength, which can provide the important reference for the design and development of the tail-sitter electric aircraft structure.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[专栏：全电无人飞行器技术]]></category>
<author><![CDATA[MA Zhenyu,ZHANG Yijie,ZHANG Qi,DENG Xiaolong,YU Naihui]]></author>
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<atom:name>MA Zhenyu,ZHANG Yijie,ZHANG Qi,DENG Xiaolong,YU Naihui</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy logic control for hybrid electric propulsion energy management system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the energy management method for hybrid electric propulsion system was studied, an energy management strategy based on fuzzy logic control was presented. By setting the fuzzy membership function of VTOL(vertical take-off and landing) aircraft′s power requirement, internal-combustion-engine-generator′s output power, and the state of charge of battery, the output power of generator and battery were dynamically optimal allocated. So as to increase the fuel economy and aircraft range effectively. According to the model establishment, the energy system changes of 100 kg scale VTOL aircraft were simulated, and simulation results demonstrate that the algorithm was practical. Results indicate that energy management strategy based on fuzzy logic control can effectively improve the performance of hybrid electric propulsion system, during the 1.2 h flight, ICE(internal combustion engine) can run approximately 1 h with the lowest specific fuel consumption, and can improve the energy efficiency of hybrid electric propulsion system.The conduction provide design thoughts and analysis method for energy control and arrangement of hybrid electric propulsion system.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[专栏：全电无人飞行器技术]]></category>
<author><![CDATA[ZHU Bingjie,ZHU Yingtao,LI Jianqi]]></author>
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<atom:name>ZHU Bingjie,ZHU Yingtao,LI Jianqi</atom:name>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Scaled similarity analysis of aerodynamic characteristics and wind tunnel test for stratospheric airship]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The analysis and design method of the sky-ground scaled similarity of aerodynamic characteristics for stratospheric airship were described in detail. The similarity criteria for the rigid and flexible models to complete the wind tunnel tests were given. Two kind of scaled models and wind tunnel test were completed. By analyzing the wind tunnel experimental data for scaled models, it was found that the aerodynamic characteristics of the stratospheric airship under different inflatable internal pressures were basically same, but the rigid body model was obviously different. The aerodynamic drag coefficient under flexible characteristics was significantly higher than that of rigid body, and even twice as high as that under zero attack angle, which lead to the essential changes of the rolling aerodynamic torque characteristics, such as stability and divergence. It has important engineering application value for evaluating flexible aerodynamic characteristics of stratospheric airship, especially under low pressure state. And it overcomes the disadvantages of using rigid body aerodynamic characteristics data or engineering estimation method in the airship overall design of "dynamic-resistance balance".]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[专栏：全电无人飞行器技术]]></category>
<author><![CDATA[SHI Zhiguang,ZUO Zongyu,YANG Yujie]]></author>
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<atom:name>SHI Zhiguang,ZUO Zongyu,YANG Yujie</atom:name>
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