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161.
将声发射动态无损检测技术引入试件疲劳试验中,通过对试验过程中声发射信号的分析,获取试件的初始裂纹数据.证明声发射技术可以发现试验中试件的初始裂纹,并对其破坏具有预警作用. 相似文献
162.
163.
根据三天线法的原理,提出了用三电缆线法来校正信号传输中由于电缆线的移动、弯曲或老化引起的电缆线传输特性的变化.该方法将三条电缆线两两组合成三对,进行三次连续的测量,从而得出电缆线的传输特性和校正因子,对测得的信号进行校正.该方法对传输信号而非反射信号的测量,克服了电缆线损耗引起的对交换反射计的使用限制. 相似文献
164.
A.S. Laxmiprasad V.L.N. Sridhar Raja Surya Menon Adwaita Goswami M.V.H. Rao K.A. Lohar 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
A miniaturized in situ laser induced breakdown spectroscope-LIBS is one of the two lunar rover payloads to be flown in India’s next lunar mission Chandrayaan-2, with an objective to carry-out a precise qualitative and quantitative elemental analyses of lunar regolith at the proximity of the landing region. As per the imposed mission constraints and the executed design optimization studies, a compact and light-weight LIBS prototype model is developed at our premises. This paper mainly concerns with the estimation of theoretical aspects; especially on evaluation of elemental ablation parameters and signal-to-noise ratio (SNR) calculations for the designed instrument. Theoretical estimations and simulations yielded an incident laser power density of the order of 5 × 1010 W/cm2 on the target surface at a defined lens-to-surface distance (LTSD) of 200 mm and revealed an SNR > 100 for most of the elements under consideration. This paper also addresses the impact of LTSD variation on detection capability. The estimation of plasma-temperatures was carried out utilizing the emission spectra obtained under high vacuum environments employing the LIBS laboratory model. Experimental investigations and the performed theoretical estimations asserted the successful operation of the configured LIBS instrument for in situ elemental analyses on lunar surface. 相似文献
165.
对铝合金平板上形成的超高速撞击(HVI)声发射(AE)信号S2模态的特征进行研究,分析其与损伤模式之间的关系。以3 mm厚5A06铝合金平板为研究对象,通过数值仿真获得不同撞击工况下的超高速撞击声发射信号,提取信号中的S2模态,并分析其幅值、能量、频谱等特征。结果表明,S2模态能量随传播距离呈指数衰减;分别随撞击弹丸直径和撞击速度的增加先下降后上升,且在弹丸直径与靶板厚度相近、临界撞击速度时最低。S2模态的中心频率随弹丸直径的增加而降低;随撞击速度的增加而增加;随传播距离的增加向1500 kHz移动。S2模态小波包系数呈凹性的频域范围分别随撞击速度和弹丸直径的增大变窄。在此基础上,当靶板形成穿孔损伤时,可根据S2模态的中心频率推测弹丸的直径;在传播距离和弹丸直径已知的前提下,可根据S2模态小波包系数呈凹性的频域范围推测撞击速度。 相似文献
166.
ZHANG Mana FU Zhenbob LIN Yuzhenb LI Jibaoa aAVIC Commercial Aircraft Engine Co. Ltd. Shanghai China bNational 《中国航空学报》2012,25(6):854-863
Air worthiness requirements of the aircraft engine emission bring new challenges to the combustor research and design. With the motivation to design high performance and clean combustor, computational fluid dynamics (CFD) is utilized as the powerful design approach. In this paper, Reynolds averaged Navier-Stokes (RANS) equations of reactive two-phase flow in an experimental low emission combustor is performed. The numerical approach uses an implicit compressible gas solver together with a Lagrangian liquid-phase tracking method and the extended coherent flamelet model for turbulence-combustion interaction. The NOx formation is modeled by the concept of post-processing, which resolves the NOx transport equation with the assumption of frozen temperature distribution. Both turbulence-combustion interaction model and NOx formation model are firstly evaluated by the comparison of experimental data published in open literature of a lean direct injection (LDI) combustor. The test rig studied in this paper is called low emission stirred swirl (LESS) combustor, which is a two-stage model combustor, fueled with liquid kerosene (RP-3) and designed by Beihang University (BUAA). The main stage of LESS combustor employs the principle of lean prevaporized and premixed (LPP) concept to reduce pollutant, and the pilot stage depends on a diffusion flame for flame stabili-zation. Detailed numerical results including species distribution, turbulence performance and burning performance are qualita-tively and quantitatively evaluated. Numerical prediction of NOx emission shows a good agreement with test data at both idle condition and full power condition of LESS combustor. Preliminary results of the flame structure are shown in this paper. The flame stabilization mechanism and NOx reduction effort are also discussed with in-depth analysis. 相似文献
167.
168.
I.V. Arkhangelskaja A.I. ArkhangelskyYu.D. Kotov P.A. KalmykovA.S. Glyanenko 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2009
The solar flare of January 20, 2005 (X7.1, 06:36–07:26 UT, maximum at 07:01 UT by the GOES soft X-ray data) was the most powerful one in January 2005 series. The AVS-F apparatus onboard CORONAS-F registered γ-emission during soft X-ray rising phase of this flare in two energy ranges of 0.1–20 MeV and 2–140 MeV. The highest γ-ray energy registered during this flare was ∼140 MeV. Six spectral features were registered in energy spectrum of this solar flare: annihilation + αα (0.4–0.6 MeV), 24Mg + 20Ne + 28Si + neutron capture (1.7–2.3 MeV), 21Ne + 22Ne + 16O + 12С (3.2–5.0 MeV), 16O (5.3–6.9 MeV), one from neutral pions decay (25–110 MeV) and one in energy band 15–21 MeV. Four of them contain typical for solar flares lines – annihilation, nuclear de-excitation and neutron capture at 1H. Spectral feature caused by neutral pions decay was registered during several flares too. Some spectral peculiarities in the region of 15–21 MeV were first observed in solar flare energy spectrum. 相似文献
169.
采用N-S方程求解了100 W微波等离子体推力器(MPT)选用不同推进工质时的性能参数;并采用直接蒙特卡洛模拟方法(DsMC)对MPT羽流进行了数值模拟.结果表明,几种工质的推力变化不大,氮气为23.6 mN,氮气为24.8mN,氩气为24.8 nuN;但比冲区别较大,氮气为565.2 s,氮气为243.7 8,氢气为180.2 s.羽流场中,密度、压强及温度沿轴向和径向均逐渐减小;轴向速度在轴线附近变化不大,采用氩气工质时,约1 700 m/s,在远离轴线区域,沿流动方向逐渐增大,沿径向逐渐减小;径向速度沿轴向变化不大,沿径向逐渐增大,并在接近流动区域边界时迅速减小. 相似文献
170.