全文获取类型
收费全文 | 311篇 |
免费 | 114篇 |
国内免费 | 78篇 |
专业分类
航空 | 171篇 |
航天技术 | 70篇 |
综合类 | 7篇 |
航天 | 255篇 |
出版年
2024年 | 3篇 |
2023年 | 14篇 |
2022年 | 36篇 |
2021年 | 27篇 |
2020年 | 33篇 |
2019年 | 24篇 |
2018年 | 19篇 |
2017年 | 11篇 |
2016年 | 14篇 |
2015年 | 9篇 |
2014年 | 19篇 |
2013年 | 28篇 |
2012年 | 20篇 |
2011年 | 26篇 |
2010年 | 15篇 |
2009年 | 9篇 |
2008年 | 16篇 |
2007年 | 31篇 |
2006年 | 13篇 |
2005年 | 17篇 |
2004年 | 9篇 |
2003年 | 9篇 |
2002年 | 10篇 |
2001年 | 9篇 |
2000年 | 6篇 |
1999年 | 12篇 |
1998年 | 12篇 |
1997年 | 16篇 |
1996年 | 5篇 |
1995年 | 5篇 |
1994年 | 4篇 |
1993年 | 4篇 |
1992年 | 4篇 |
1991年 | 8篇 |
1990年 | 2篇 |
1989年 | 2篇 |
1988年 | 2篇 |
排序方式: 共有503条查询结果,搜索用时 15 毫秒
261.
Aeromagnetic interference could not be compensated effectively if the precision of parameters which are solved by the aircraft magnetic field model is low. In order to improve the compensation effect under this condition, a method based on small signal model and least mean square(LMS) algorithm is proposed. According to the method, the initial values of adaptive filter's weight vector are calculated with the solved model parameters through small signal model at first,then the small amount of direction cosine and its derivative are set as the input of the filter, and the small amount of the interference is set as the filter's expected vector. After that, the aircraft magnetic interference is compensated by LMS algorithm. Finally, the method is verified by simulation and experiment. The result shows that the compensation effect can be improved obviously by the LMS algorithm when original solved parameters have low precision. The method can further improve the compensation effect even if the solved parameters have high precision. 相似文献
262.
A novel integrated guidance and autopilot design method is proposed for homing missiles based on the adaptive block dynamic surface control approach. The fully integrated guidance and autopilot model is established by combining the nonlinear missile dynamics with the nonlinear dynamics describing the pursuit situation of a missile and a target in the three-dimensional space. The integrated guidance and autopilot design problem is further converted to a state regulation problem of a time-varying nonlinear system with matched and unmatched uncertainties. A new and simple adaptive block dynamic surface control algorithm is proposed to address such a state regulation problem. The stability of the closed-loop system is proven based on the Lyapunov theory. The six degrees of freedom (6DOF) nonlinear numerical simulation results show that the proposed integrated guidance and autopilot algorithm can ensure the accuracy of target interception and the robust stability of the closed-loop system with respect to the uncertainties in the missile dynamics. 相似文献
263.
Gan Zhengtao Yu Gang Li Shaoxia He Xiuli Chen Ru Zheng Caiyun Ning Weijian 《中国航空学报》2016,(4):1018-1026
Laser heating technology is a type of potential and attractive space heat flux simulation technology, which is characterized by high heating rate, controlled spatial intensity distribution and rapid response. However, the controlled plant is nonlinear, time-varying and uncertainty when implementing the laser-based heat flux simulation. In this paper, a novel intelligent adaptive controller based on proportion–integration–differentiation(PID) type fuzzy logic is proposed to improve the performance of laser-based ground thermal test. The temperature range of thermal cycles is more than 200 K in many instances. In order to improve the adaptability of controller,output scaling factors are real time adjusted while the thermal test is underway. The initial values of scaling factors are optimized using a stochastic hybrid particle swarm optimization(H-PSO)algorithm. A validating system has been established in the laboratory. The performance of the proposed controller is evaluated through extensive experiments under different operating conditions(reference and load disturbance). The results show that the proposed adaptive controller performs remarkably better compared to the conventional PID(PID) controller and the conventional PID type fuzzy(F-PID) controller considering performance indicators of overshoot, settling time and steady state error for laser-based ground thermal test. It is a reliable tool for effective temperature control of laser-based ground thermal test. 相似文献
264.
依据航空噪声的频谱特性,提出将自适应滤波算法与改进的谱减法相级联的方法来增强语音。在强航空噪声背景下,处理后的语音不仅信噪比得到了很大提高,而且在有效抑制背景噪声和音乐噪声的同时,其清晰度和可懂度也得到了很大的改善。 相似文献
265.
266.
大型桁架式可展开航天结构在地面试验时,存在大挠度变形、精度低、泛用性差等结构特点,为提高地面试验有效性,提出了一种自适应多点悬挂重力补偿控制方法。首先,设计系统辨识算法和控制器算法,解决了多点耦合问题。其次,建立Simulink与Adams联合仿真平台,通过仿真分析选择算法参数,验证了算法的可行性。最后,以大型桁架式航天天线为对象,搭建重力补偿系统实验平台并进行实验验证。实验结果表明:控制系统在稳态环境和动态环境下均能快速收敛。稳态环境下,平均稳态误差为0.5503%;动态环境下,平均稳态误差0.526%。完成了航天结构天线的重力补偿,为多点重力补偿系统方案的实施提供建议和改进措施。 相似文献
267.
268.
269.
An adaptive optimal trajectory tracking controller is presented for the Solid-RocketPowered Vehicle(SRPV) with uncertain nonlinear non-affine dynamics in the framework of adaptive dynamic programming. First, considering that the ascent model of the SRPV is non-affine, a model-free Single Network Adaptive Critic(SNAC) method is developed based on the dynamic neural network and the traditional SNAC method. This developed model-free SNAC method overcomes the limitation of the traditional SNAC metho... 相似文献
270.
For different flight phases in an overall flight mission, different control and allocation preferences should be pursued considering lift, drag or maneuverability characteristics. The multi-objective flight control allocation problem for a multi-phase flight mission is studied. For an overall flight mission, different flight phases namely climbing, cruise, maneuver and gliding phases are defined. Firstly, a multi-objective control allocation problem considering drag, lift or control energy prefe... 相似文献