全文获取类型
收费全文 | 107篇 |
免费 | 45篇 |
国内免费 | 45篇 |
专业分类
航空 | 129篇 |
航天技术 | 31篇 |
综合类 | 4篇 |
航天 | 33篇 |
出版年
2023年 | 7篇 |
2022年 | 6篇 |
2021年 | 15篇 |
2020年 | 7篇 |
2019年 | 8篇 |
2018年 | 9篇 |
2017年 | 11篇 |
2016年 | 8篇 |
2015年 | 6篇 |
2014年 | 10篇 |
2013年 | 7篇 |
2012年 | 5篇 |
2011年 | 7篇 |
2010年 | 5篇 |
2009年 | 5篇 |
2008年 | 3篇 |
2007年 | 4篇 |
2006年 | 8篇 |
2005年 | 7篇 |
2004年 | 1篇 |
2003年 | 3篇 |
2002年 | 2篇 |
2001年 | 2篇 |
2000年 | 2篇 |
1999年 | 5篇 |
1998年 | 10篇 |
1997年 | 5篇 |
1996年 | 4篇 |
1995年 | 7篇 |
1994年 | 14篇 |
1992年 | 2篇 |
1991年 | 1篇 |
1988年 | 1篇 |
排序方式: 共有197条查询结果,搜索用时 31 毫秒
161.
162.
163.
《中国航空学报》2020,33(1):64-72
The accuracy of the HB2 standard model attitude measurement has an important impact on the hypersonic wind tunnel data assessment. The limited size of the model and the existence of external vibrations make it challenging to obtain real-time reliable attitude measurement. To reduce the influence of attitude errors on test results, this paper proposes a Quaternion Nonlinear Complementary Filter (QNCF) attitude determination algorithm based on Microelectromechanical Inertial Measurement Unit (MEMS-IMU). Firstly, the threshold-based PI control strategy is adopted to eliminate noise effect according to the Acceleration Magnitude Detector (AMD). Then, the flexible quaternion method is updated to carry out attitude estimation which is operational and easy to be embedded in the Field Programmable Gate Array (FPGA). Finally, a high-precision three-axis turntable test and a hypersonic wind tunnel test are performed. The results show that the pitch-roll attitude errors are within 0.05° and 0.08° in the high-precision three-axis turntable test in a calculation time of 100 s respectively, and the attitude error is within 0.3° after the elastic angle correction in the hypersonic wind tunnel test. The proposed method can provide accurate real-time attitude reference for the analysis of the actual movement of the model, exhibiting certain engineering application value with robustness and simplicity. 相似文献
164.
《中国航空学报》2020,33(8):2123-2132
Well-designed airfoil is very important for high-performance rotor. This paper developed an efficient multi-objective and multi-constraint optimization design system for rotor airfoils based on RANS analysis, and verified the performance of the optimized airfoil. Using CRA09-A as the baseline rotor airfoil, the CRA09-B optimized rotor airfoil was designed successfully. Combined with the foundation of high-precision rotor airfoil stationary test technology, the CRA09-B and CRA09-A rotor airfoils were tested in the S3MA high-speed wind tunnel of ONERA. In order to correct the aerodynamic data, a single parameter linear wall pressure method is used to consider the tunnel effects. The results indicate that multi-objective and multi-constraint optimization design method developed in this study is reliable, and that CRA09-B optimized airfoil provides better stationary performance than CRA09-A airfoil in terms of maximum lift coefficient and lift-to-drag ratio. 相似文献
165.
《中国航空学报》2020,33(4):1272-1287
The paper deals with the design and experimental validation of the actuation mechanism control system for a morphing wing model. The experimental morphable wing model manufactured in this project is a full-size scale wing tip for a real aircraft equipped with an aileron. The morphing actuation of the model is based on a mechanism with four similar in house designed and manufactured actuators, positioned inside the wing on two parallel lines. Each of the four actuators used a BrushLess Direct Current (BLDC) electric motor integrated with a mechanical part performing the conversion of the angular displacements into linear displacements. The following have been chosen as successive steps in the design of the actuator control system: (A) Mathematical and software modelling of the actuator; (B) Design of the control system architecture and tuning using Internal Model Control (IMC) methodology; (C) Numerical simulation of the controlled actuator and its testing on bench and wind tunnel. The morphing wing experimental model is tested both at the laboratory level, with no airflow, to evaluate the components integration and the whole system functioning, but also in the wind tunnel, in the presence of airflow, to evaluate its behavior and the aerodynamic gain. 相似文献
166.
Bruno Mialon Alex Khrabrov Saloua Ben Khelil Andreas Huebner Andrea Da Ronch Ken Badcock Luca Cavagna Peter Eliasson Mengmeng Zhang Sergio Ricci Jean-Christophe Jouhaud Gilbert Rogé Stephan Hitzel Martin Lahuta 《Progress in Aerospace Sciences》2011,47(8):674-694
The dynamic derivatives are widely used in linear aerodynamic models in order to determine the flying qualities of an aircraft: the ability to predict them reliably, quickly and sufficiently early in the design process is vital in order to avoid late and costly component redesigns. This paper describes experimental and computational research dealing with the determination of dynamic derivatives carried out within the FP6 European project SimSAC. Numerical and experimental results are compared for two aircraft configurations: a generic civil transport aircraft, wing-fuselage-tail configuration called the DLR-F12 and a generic Transonic CRuiser, which is a canard configuration. Static and dynamic wind tunnel tests have been carried out for both configurations and are briefly described within this paper. The data generated for both the DLR-F12 and TCR configurations include force and pressure coefficients obtained during small amplitude pitch, roll and yaw oscillations while the data for the TCR configuration also include large amplitude oscillations, in order to investigate the dynamic effects on nonlinear aerodynamic characteristics. In addition, dynamic derivatives have been determined for both configurations with a large panel of tools, from linear aerodynamic (Vortex Lattice Methods) to CFD. This work confirms that an increase in fidelity level enables the dynamic derivatives to be calculated more accurately. Linear aerodynamics tools are shown to give satisfactory results but are very sensitive to the geometry/mesh input data. Although all the quasi-steady CFD approaches give comparable results (robustness) for steady dynamic derivatives, they do not allow the prediction of unsteady components for the dynamic derivatives (angular derivatives with respect to time): this can be done with either a fully unsteady approach i.e. with a time-marching scheme or with frequency domain solvers, both of which provide comparable results for the DLR-F12 test case. As far as the canard configuration is concerned, strong limitations for the linear aerodynamic tools are observed. A key aspect of this work are the acceleration techniques developed for CFD methods, which allow the computational time to be dramatically reduced while providing comparable results. 相似文献
167.
霍西恒王大伟李革萍李志茂 《民用飞机设计与研究》2013,(4):13-16,45
介绍了某型支线客机机翼防冰系统的性能验证思路,即通过采用2.5D试验模型验证三维防冰系统的性能j选取一个典型状态点分别进行了2.5D及三维模型的性能汁算分析,同时进行了相同状态点时2.5D模型的冰风洞试验结果分析,最后将2.5D模型计算结果与试验结果进行对比分析,修正3D模型的汁算结果,从而达到验证整个防冰系统性能的目的。 相似文献
168.
K. Issautier C. Perche S. Hoang C. Lacombe M. Maksimovic J.-L. Bougeret C. Salem 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2005,35(12):2141-2146
We present the solar wind plasma parameters obtained from the Wind spacecraft during more than nine years, encompassing almost the whole solar cycle 23. Since its launch in November 1994 Wind has frequently observed the in-ecliptic solar wind upstream of the Earth’s bow shock. The WIND/WAVES thermal noise receiver was specially designed to measure the in situ plasma thermal noise spectra, from which the electron density and temperature can be accurately determined. We present and discuss histograms of such measurements performed from 1994 to 2003. Using these large data sets, we study the density and core temperature variations with solar activity cycle and with different regimes of the solar wind. We confirm the anticorrelation of the electron density with the sunspot number, and obtain a positive correlation of the core temperature, with the sunspot number. 相似文献
169.
以陶瓷前驱体树脂为成膜物,以过渡金属氧化物和硼化物为填料,采用空气喷涂工艺在镍基高温合金和C/C基材上制备出了高温散热性能好、抗热震性好的高温高辐射涂层,并用DSC-TG、光学显微镜和风洞对涂层性能进行表征。结果表明:该涂层室温~827℃发射率达到0.85~0.92,827℃~室温抗热震循环20次后涂层不剥离、不脱落;该涂层在290 k W/m2冷壁热流、300 s时长的风洞考核条件下,可将镍基高温合金基材温度从686℃降到646℃,降温40℃。 相似文献
170.
Y. -M. Wang 《Space Science Reviews》1994,70(1-2):387-390
Empirical studies have shown that the solar wind speed at Earth is inversely correlated with the areal expansion rate of magnetic flux tubes near the Sun. Recent model calculations that include a self-consistent determination of the coronal temperature allow one to understand the physical basis of this relationship; they also suggest why the solar wind mass flux is relatively constant. 相似文献