全文获取类型
收费全文 | 1088篇 |
免费 | 327篇 |
国内免费 | 252篇 |
专业分类
航空 | 1384篇 |
航天技术 | 59篇 |
综合类 | 199篇 |
航天 | 25篇 |
出版年
2024年 | 3篇 |
2023年 | 16篇 |
2022年 | 66篇 |
2021年 | 60篇 |
2020年 | 65篇 |
2019年 | 87篇 |
2018年 | 84篇 |
2017年 | 65篇 |
2016年 | 78篇 |
2015年 | 59篇 |
2014年 | 75篇 |
2013年 | 75篇 |
2012年 | 87篇 |
2011年 | 79篇 |
2010年 | 43篇 |
2009年 | 63篇 |
2008年 | 74篇 |
2007年 | 76篇 |
2006年 | 57篇 |
2005年 | 55篇 |
2004年 | 51篇 |
2003年 | 56篇 |
2002年 | 48篇 |
2001年 | 35篇 |
2000年 | 30篇 |
1999年 | 33篇 |
1998年 | 23篇 |
1997年 | 27篇 |
1996年 | 15篇 |
1995年 | 15篇 |
1994年 | 18篇 |
1993年 | 9篇 |
1992年 | 5篇 |
1991年 | 10篇 |
1990年 | 7篇 |
1989年 | 6篇 |
1988年 | 7篇 |
1987年 | 5篇 |
排序方式: 共有1667条查询结果,搜索用时 15 毫秒
61.
旋翼非定常气动载荷实验研究 总被引:2,自引:0,他引:2
对在4m直径旋翼/机身组合模型试验台上进行的非定常气动载荷试验结果进行了分析,试验完成了总距、周期变距突增对拉力和力矩的影响。本文还对试验结果和理论计算结果进行了对比分析,给出了分析结论。 相似文献
62.
从气动、动力学和结构设计三个方面介绍了直升机旋翼桨叶设计的一般要求,分析了桨叶扭转角、平面形状、浆尖形状等参数对直升机性能、旋翼气动特性和动力学特性的影响,并结合WZ-1无人驾驶直升机的使用要求对其旋翼桨叶进行了初步设计,给出了桨叶的构形和“共振图”。本文的设计和分析方法可用于指导其他直升机的旋翼桨叶设计。 相似文献
63.
《中国航空学报》2020,33(3):893-901
In this paper, the effect of different amount of protrusion on various parameters in rotor–stator system was experimentally studied by measuring CO2 concentration and pressure, in order to obtain the optimal protrusion amount. The parameters of different dimensionless sealing flow were measured under the condition that the annulus Reynolds number was 4.39 × 105 and the rotating Reynolds number was 1.05 × 106. The results show that the change of the amount of protrusions has little effect on the static pressure in the cavity, and the static pressure change near the sealing ring is almost negligible. But the total pressure and sealing efficiency increase first and then decrease with the increase of the amount of protrusion. The variation of power consumption is the same. A complex vortex structure will appear at the high radius region when the protrusion is installed. On the other hand, the protrusion can effectively reduce the minimum sealing flow of the rotor–stator cavity. Furthermore, considering the sealing efficiency and power consumption, the best range of the protrusion amount is about 36. The ratio near this range can optimally balance the alleviation of the gas ingestion and the reduction of the power consumption. 相似文献
64.
《中国航空学报》2020,33(6):1625-1641
The Tilt Quad Rotor (TQR) has complex dynamics characteristics, especially in conversion mode. It is difficult to build the dynamic model of the TQR and the environmental factors have a great influence on it. To solve the problem of control in conversion mode of TQR, this paper carries out the design of the controller based on improved Active Disturbance Rejection Control (ADRC). According to the characteristics of flight in conversion mode, Tracking Differentiator (TD) with explicit model is used to solve the problem of multiple integrals when the system is high-order system. Extended State Observer (ESO) with Radial Basis Function (RBF) neural network is used to estimate and compensate for internal and external uncertainties, and the adaptive sliding mode control in Nonlinear State Error Feedback (NLSEF) is used to improve the response speed of the controller and reduce the parameters which should be tuned. Through the flight control simulation of the TQR, the validity and rationality of the control system are verified. 相似文献
65.
An Equilibrium Multi-objective Optimization Model(EMOM) with self-regulated weighting factors has been proposed for the optimum design of non-circular clearance hole on the front flange of turbine disk. In the ‘‘equilibrium design", both the stress decrease around the hole and the least hole's profile variation are considered, which balances two ambivalent design goals. Specific discrete variables are applied to realize the standardization design in the optimization process, in which a Surrogate Genetic Coding Algorithm(SGCA) is introduced, and a special check module is used to get rid of repeated fitness evaluation of the samples. The method offers an equilibrium design for the non-circular clearance hole of the turbine disk with great accuracy and efficiency. 相似文献
66.
《中国航空学报》2020,33(8):2162-2175
The rim seal is used to prevent mainstream ingestion to the gap between the vane of a turbine and its blade. In this article, the dolphin lip with a hook configuration and a large seal cavity with hook structures are designed based on the high-pressure turbine datum single shark lip rim seal configuration. The sealing effect and parameters of the flow field are measured by an experiment method and a numerical simulation is used to explain the mechanism. For three configurations, the effect of the leakage slot vortex on the efficiency of the seal and the influence of leakage vortex, generated by the interaction between purge flow and mainstream flow, are discussed in depth. The result shows that the reverse vortex formed by the dolphin lip rim seal with hook structure will increase the sealing efficiency. The seal configuration with a large cavity improves sealing efficiency to a greater extent than the datum structure. At different purge flow rates and with unequal seal structures, the purge flow produces three types of leakage vortices in the passage. Besides, the seal configuration with dolphin lip produces a Kelvin-Helmholtz instability at the interface of the purge and the mainstream flows at a low purge flow rate to induce new leakage vortex branches in the passage of the blade. 相似文献
67.
68.
为了实现直升机旋翼转速在宽广范围内连续变化且涡轴发动机连续提供输出轴功率,采用1种扭矩序列转移控制方案来实现该传动链。通过2台涡轴发动机和2台多级变速器与旋翼协调工作,发动机依次连接或脱开旋翼,提供旋翼转速大范围内变化,并提供旋翼连续变化的功率。在扭矩转移过程中,针对发动机扭矩强扰动问题设计了鲁棒LMI控制器+ADRC扭矩前馈补偿控制器,最后基于直升机/发动机综合模型进行数值仿真,验证了扭矩转移方案的可行性。仿真结果表明:在转移过程中的扭矩强扰动对发动机动力涡轮转速的影响较小,旋翼转速可以实现较大范围内的快速平滑变化。 相似文献
69.
先进铝化物涂层制备技术进展 总被引:1,自引:0,他引:1
铝化物涂层是现役发动机热端部件高温氧化防护的主要手段。未来,高性能铝化物涂层仍是发展先进发动机所必需的技术。传统基于化学气相的制备方法不仅污染环境,腐蚀设备,效率低下,更重要的是难以有效制备高性能铝化物涂层。高效"绿色"化将是先进铝化物涂层制备技术的发展趋势。近年通过利用机械能辅助的策略获得了高效制备铝化物涂层的方法。另外,利用真空物理气相沉积加高温扩散的策略,"绿色"制备高性能铝化物涂层的研究也进展显著。结合上述两种策略,利用真空等离子辐照形成的离子撞击能,可高效、"绿色"地制备铝化物涂层,为高性能铝化物涂层的制备提供了一种新的有效途径。 相似文献
70.