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391.
混浊液内部的流动 ,由于微粒子之间的相互作用以及因浊度高不易进行内部观察 ,所以无论是分析还是可视化实验都相当困难 ,存在着许多未弄清的问题。通过采用折射率匹配 (Refractive IndexMatching)技术 ,使透明的微粒子与透明的溶媒的折射率近乎相同 ,做成一种透明的“混浊液” ,从而使混入其中的示踪粒子的运动轨迹能被摄像机捕捉到 ,并以微粒子的沉降和温度的干涉所引起的流动现象为焦点 ,利用图像速度测量法来处理分析所拍摄到的可视化图像 ,成功地获得了定量的混浊液内部的速度场 ,为进一步揭示混浊液内部自然对流的流动机理提供了实验依据。 相似文献
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393.
气动力对伞稳定下降阶段摆动的影响 总被引:1,自引:0,他引:1
为分析伞系统在稳定下降阶段运动稳定性,建立了5自由度的物伞模型,通过仿真发现具有不同气动力形式的物伞系统,其摆动情况有明显差异,并着重分析了气动力参数对物伞系统的摆动角度、频率的影响。 相似文献
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395.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(1):312-325
Spacecraft relative motion with inter-craft electromagnetic force has distinct advantages, and its invariant shapes that are convenient for formation keeping ensure some potential significant applications. However, the electromagnetic actuators affect both the relative trajectory and attitude motion, complicating related researches on issues of invariant shape design and formation control. In this paper, the formation keeping problem for an invariant three-craft triangular electromagnetic formation is investigated on the basis of a 6-DOF full nonlinear dynamic model. Moreover, a combined control scheme consisting of feed-forward and feed-back control components is proposed to handle the high nonlinearity, strong coupling, model uncertainties and external disturbances. The feed-forward component is obtained through desired invariant shape design which is complicated by the coupling and superposition effects of any two distinct magnetic dipoles, and the feed-back component is developed with a combination of linear feed-back controller by the LQR method and active disturbance rejection by the extended state observer. Finally, the numerical simulation is presented to verify the feasibility and validity of the proposed 6-DOF combined control scheme. 相似文献
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397.
《中国航空学报》2020,33(7):1991-2001
This paper presents a novel optimal Motion Cueing Algorithm (MCA) to control the rotations of a Human Centrifuge (HC) and achieve the best simulation of a SpaceCraft (SC) motion. Relations of the specific forces sensed by astronauts of the SC and the HC have been derived and linearized. A Linear Quadratic Regulator (LQR) controller is implemented for the problem which tends to minimize the error between the two sensed specific forces as well as control input in a cost function. It results in control inputs of the HC to generate its sensed specific force as close as possible to the one in the SC. The algorithm is implemented for both linearized and nonlinear portions of a US space shuttle mission trajectory as a verification using MATLAB. In longitudinal direction, the proposed MCA, works well when the acceleration is less than 2g in which the tracking error does not exceed 12%. In lateral direction the tracking is much better even in nonlinear region since the error remains less than 7% for tilting up to 50°. Finally, the effect of weight matrixes in the LQR cost function on overall weight and power of the HC motion system is discussed. 相似文献
398.
《中国航空学报》2020,33(7):2055-2069
It is extremely important to select appropriate feedrates for the stable machining of parts with ruled surface in modern aviation industrial applications. However, the current studies take too much time to achieve this goal. Therefore, this paper presents an efficient feedrate optimization method for constant peak cutting force in five-axis flank milling process. The solution method of the instantaneous undeformed chip thickness (IUCT) is proposed using least squares theory with the cutter entry angle and feedrate as variables. Based on this method, an explicit analytical expression of the peak cutting force for each cutting point is established. Furthermore, a feedrate scheduling method is developed to quickly solve the appropriate feedrate under constant peak cutting force. To verify the proposed IUCT model, the fitting IUCT is compared with the accuracy data at different feedrates. Additionally, some experiments of five-axis flank milling are conducted to demonstrate the effectiveness of the peak force model and the feedrate scheduling method. And the surface roughness before and after feedrate scheduling is detected. The results show that the proposed feedrate scheduling method can quickly adjust the feedrate and ensure constant peak force during machining. At the same time, the surface quality is kept at a high level. 相似文献
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400.
亚跨超风洞现代试验设计方法研究 总被引:2,自引:0,他引:2
开展了基于现代试验设计方法(MDOE)的亚跨超风洞试验研究,以八号标模尾翼为试验对象研究其气动特性,采用同时改变攻角-侧滑角的多变量方法,而不是传统的单变量(OFAT)方法进行试验。对自变量攻角和侧滑角进行试验设计(DOE),应用响应面法建模,用IV-最优方法对测量点分布进行设计。在FD-12亚跨超风洞完成了试验,并和传统的OFAT方法结果进行比较分析。结果表明:MDOE方法获得的数据和传统的OFAT方法的数据吻合很好;MDOE采集样点数减少了46%,吹风的时间比OFAT减少30%左右,提高了风洞试验效率,缩短了试验周期;MDOE试验方法可以给出设计空间内任意给定自变量对应的响应值及其置信区间。 相似文献