全文获取类型
收费全文 | 147篇 |
免费 | 31篇 |
国内免费 | 34篇 |
专业分类
航空 | 74篇 |
航天技术 | 25篇 |
综合类 | 3篇 |
航天 | 110篇 |
出版年
2023年 | 7篇 |
2022年 | 10篇 |
2021年 | 6篇 |
2020年 | 7篇 |
2019年 | 11篇 |
2018年 | 9篇 |
2017年 | 3篇 |
2016年 | 3篇 |
2015年 | 6篇 |
2014年 | 8篇 |
2013年 | 15篇 |
2012年 | 11篇 |
2011年 | 15篇 |
2010年 | 9篇 |
2009年 | 5篇 |
2008年 | 6篇 |
2007年 | 8篇 |
2006年 | 7篇 |
2005年 | 9篇 |
2004年 | 5篇 |
2003年 | 8篇 |
2002年 | 3篇 |
2001年 | 5篇 |
2000年 | 5篇 |
1999年 | 8篇 |
1998年 | 4篇 |
1997年 | 4篇 |
1996年 | 2篇 |
1995年 | 6篇 |
1994年 | 1篇 |
1993年 | 1篇 |
1992年 | 1篇 |
1991年 | 3篇 |
1990年 | 1篇 |
排序方式: 共有212条查询结果,搜索用时 31 毫秒
21.
22.
未来复杂航天器低频模态密集,其敏感载荷要求很高的指向精度和稳定度,只对航天器本体姿态控制很难满足要求.本文采用Stewart超静平台对敏感载荷进行6自由度主动隔振,建立了非线性动力学模型,并根据线性模型设计了多变量鲁棒控制器,采用DK迭代算法求解.频域分析可得Stewart平台对3~800Hz的扰动主动隔振大于25dB,仿真证明Stewart平台对10Hz谐波扰动隔振性能优于40dB,对白噪声随机扰动隔振性能优于30dB,有效抑制了微小扰动,起到了6自由度超静隔振平台作用. 相似文献
23.
24.
Robust adaptive fault-tolerant control of a tandem coaxial ducted fan aircraft with actuator saturation 总被引:1,自引:0,他引:1
This paper is concerned with the robust adaptive fault-tolerant control of a tandem coaxial ducted fan aircraft under system uncertainty, mismatched disturbance, and actuator saturation. For the proposed aircraft, comprehensive controllability analysis is performed to evaluate the controllability of each state as well as the margin to reject mismatched disturbance without any knowledge of the controller. Mismatched disturbance attenuation is ensured through a structured H-infinity controller tuned by a non-smooth optimization algorithm. Embedded with the H-infinity controller, an adaptive control law is proposed in order to mitigate matched system uncertainty and actuator fault. Input saturation is also considered by the modified reference model. Numerical simulation of the novel ducted fan aircraft is provided to illustrate the effectiveness of the proposed method. The simulation results reveal that the proposed adaptive controller achieves better transient response and more robust performance than classic Model Reference Adaptive Control (MRAC) method, even with serious actuator saturation. 相似文献
25.
26.
针对高超声速飞行器动力学模型强耦合、非对称时变迎角限制、气动参数高度不确定以及跟踪误差收敛速率要求高等问题,设计了一种考虑非对称时变迎角限制的高超声速飞行器固定时间非奇异切换控制策略。为了解决非对称时变迎角限制问题,首先限制迎角虚拟控制器的幅值并设计固定时间误差补偿系统补偿迎角虚拟控制器饱和带来的不利影响,然后设计了一种新的光滑切换的非对称时变障碍函数限制迎角跟踪误差,从而使迎角满足非对称时变限制。光滑切换技术以及固定时间收敛技术也应用于其他虚拟控制律和实际控制律的设计中,以避免奇异值问题并且保证闭环系统的固定时间稳定。此外,设计了一种固定时间稳定的鲁棒补偿器用以补偿系统不确定性带来的不利影响。严格的数学推导证明了本文方法的正确性,仿真结果验证了本文方法的有效性和优越性。 相似文献
27.
Aeroelastic two-level optimization for preliminary design of wing structures considering robust constraints 总被引:1,自引:0,他引:1
An aeroelastic two-level optimization methodology for preliminary design of wing struc- tures is presented, in which the parameters for structural layout and sizes are taken as design vari- ables in the first-level optimization, and robust constraints in conjunction with conventional aeroelastic constraints are considered in the second-level optimization. A low-order panel method is used for aerodynamic analysis in the first-level optimization, and a high-order panel method is employed in the second-level optimization. It is concluded that the design of the abovementioned structural parameters of a wing can be improved using the present method with high efficiency. An improvement is seen in aeroelastic performance of the wing obtained with the present method when compared to the initial wing. Since these optimized structures are obtained after consideration of aerodynamic and structural uncertainties, they are well suited to encounter these uncertainties when they occur in reality. 相似文献
28.
主要研究了频率域鲁棒稳定性分析的新方法及其在收音机横侧控制系统中的应用。为了提高计算效率,基于Nyquist判据,提出了对数和鲁棒稳定性的新判据,为了简化多变量频率域鲁棒性分析和设计方法,进一步提出了递Nyquist阵对占优势判别式,使计算量大大减少,所提出的鲁棒性新判据在飞机横侧向控制中的应用表明,该方法可以得到讼人满意的结果。 相似文献
29.
30.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(1):297-311
This paper investigates a novel finite-time attitude control method for the postcapture spacecraft with an unknown captured space target in the presence of input faults and quantization. First, a quasi fixed-time convergent performance function is developed to quantitatively characterize the attitude tracking performance. Then, a backstepping prescribed performance attitude controller is devised via using integral barrier Lyapunov function. Compared with the existing works, the fractional state feedback and discontinuous controller is directly avoided to achieve the fixed-time convergence rate. Namely, the proposed fixed-time controller is easily achieved online. Finally, two groups of illustrative examples are organized to validate the effectiveness and robustness of the proposed control method. 相似文献