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• 长春光学精密机械与物... [8]
• 力学研究所 [3]
• 地理科学与资源研究所 [3]
• 高能物理研究所 [2]
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• 沈阳自动化研究所 [1]
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• OAI收割 [19]

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• 会议论文 [10]
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• 2023 [1]
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浏览/检索结果: 共19条，第1-10条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 Direct thrust test and asymmetric performance of porous ionic liquid electrospray thruster 期刊论文  OAI收割 CHINESE JOURNAL OF AERONAUTICS, 2023, 卷号: 36, 期号: 4, 页码: 120-133 作者:  Guo, Yuntao;  Sun, Wei;  Sun, Zhenning;  Wu, Zhiwen;  He JW(贺建武)   |  收藏  |  浏览/下载：27/0  |  提交时间：2023/06/15 Asymmetric performance  Direct thrust test  Ionic liquid electrospray thruster  Time of flight mass spec-trometry  Torsional thrust stand   Longitudinal Control for Balloon-Borne Launched Solar Powered UAVs in Near-Space 期刊论文  OAI收割 JOURNAL OF SYSTEMS SCIENCE & COMPLEXITY, 2022, 卷号: 35, 期号: 3, 页码: 802-819 作者:  Hu Yanpeng;  Guo Jin;  Meng Wenyue;  Liu Guanyu;  Xue Wenchao   |  收藏  |  浏览/下载：20/0  |  提交时间：2023/02/07 Aeroelastic model  balloon-borne flight test  flight dynamic model  longitudinal control  numerical simulation  solar powered UAV   On theory and methods for advanced detonation-driven hypervelocity shock tunnels 期刊论文  OAI收割 NATIONAL SCIENCE REVIEW, 2020, 卷号: 7, 期号: 7, 页码: 1198-1207 作者:  Jiang ZL(姜宗林);  Li JP(李进平);  Hu ZM(胡宗民);  Liu YF(刘云峰);  Yu HR(俞鸿儒)   |  收藏  |  浏览/下载：39/0  |  提交时间：2020/11/30 hypervelocity  shock tunnel  detonation driver  flight condition  tailored condition  test facilities   Modelling of XCO2 Surfaces Based on Flight Tests of TanSat Instruments 期刊论文  OAI收割 SENSORS, 2016, 卷号: 16, 期号: 11, 页码: 16 作者:  Zhang, Li Li;  Yue, Tian Xiang;  Wilson, John P.;  Wang, Ding Yi;  Zhao, Na   |  收藏  |  浏览/下载：37/0  |  提交时间：2019/09/26 TanSat  flight test  XCO2 retrieval  HASM  XCO2 simulation   Modelling of XCO2 Surfaces Based on Flight Tests of TanSat Instruments 期刊论文  OAI收割 SENSORS, 2016, 卷号: 16, 期号: 11, 页码: 16 作者:  Zhang, Li Li;  Yue, Tian Xiang;  Wilson, John P.;  Wang, Ding Yi;  Zhao, Na   |  收藏  |  浏览/下载：24/0  |  提交时间：2019/09/26 TanSat  flight test  XCO2 retrieval  HASM  XCO2 simulation   Modelling of XCO2 Surfaces Based on Flight Tests of TanSat Instruments 期刊论文  OAI收割 SENSORS, 2016, 卷号: 16, 期号: 11, 页码: 16 作者:  Zhang, Li Li;  Yue, Tian Xiang;  Wilson, John P.;  Wang, Ding Yi;  Zhao, Na   |  收藏  |  浏览/下载：11/0  |  提交时间：2019/09/26 TanSat  flight test  XCO2 retrieval  HASM  XCO2 simulation   Monte Carlo modeling of electron density in hypersonic rarefied gas flows 会议论文  OAI收割 the 29th International Symposium on Rarefied Gas Dynamics, Xi'an, China, July13-18, 2014 作者:  Fan J(樊菁);  Zhang YH(张羽淮);  Jiang JZ(蒋建政) 收藏  |  浏览/下载：38/0  |  提交时间：2015/01/21 hypersonic rarefied gas flow  electron density  DSMC  TSS  RAM-C II flight test   Aggressive Manuevering of Unmanned Helicopters: Learning from Human Based on Neural Networks 会议论文  OAI收割 2012 12th International Conference on Intelligent Autonomous System, Jeju Island, Korea, June 26-29, 2012 作者:  Song DL(宋大雷);  Wu C(吴冲);  Qi JT(齐俊桐);  Han JD(韩建达) 收藏  |  浏览/下载：32/0  |  提交时间：2012/12/28 neural network  unmanned helicopter  learning  flight test   A strong coupled CFD-CSD method on computational aeroelastity (EI CONFERENCE) 会议论文  OAI收割 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China Xi R.; Jia H. 收藏  |  浏览/下载：67/0  |  提交时间：2013/03/25 In this paper  a strong coupled CFD-CSD method is developed to simulate the aeroelastic phenomena. The CFD solver is based on the finite-volume algorithm for the Navier-Stokes equations on unstructured grid. The CSD solver solves the aeroelastic governing equations in the modal space. Their coupling is realized by a dual-time method. The spring-based smoothing method is adopted to deform and regenerate the aerodynamic grid. Two test cases are selected to validate the authors' method for static and dynamic aeroelastity .The results of the simulation for the static aeroelastic problems of a missile wing show that the Lift Coefficient and Drag Coefficient are severally 7% and 5% lower than those don't consider the elasticity of the wing. The results for the flutter boundary prediction of the AGARD 445.6 wing have been proved much closer to the experiment than using the DLM. This method can describe the effects of fluid viscosity more exactly for highly nonlinear transonic flight conditions. The calculation has proved reliable in the subsonic regime  but not accurate enough in the supersonic regime. 2011 IEEE.   Adaptive control at launching using three loop autopilot (EI CONFERENCE) 会议论文  OAI收割 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China 作者:  Zhang Y. 收藏  |  浏览/下载：25/0  |  提交时间：2013/03/25 In order to guarantee the precise initial flight trajectory  control the missile disturbance of large disturbance torque  three loop adaptive autopilot was researched. The characteristics of the projectile and three loop autopilot instruction formation characteristics were analysed. From equivalent pitching angle of lateral acceleration feedback loop  combined with the instruction of generalized error  autopilot structure was simplified  and three loop autopilot adaptive control law and stability were designed. The test data show that when disturbance torque was 600Nm  the attitude angle generalized error was -4.4. In the time lasted about 15s  late trajectory accuracy was within 1.0.Three loop autopilot adaptive control law was able to control the disturbance of initial trajectory and adapt to dynamic characteristics changes  control system stability. It was the initial trajectory accurate solution method of flight. 2011 IEEE.