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51.
根据强5飞机以往型号的颤振计算结果,对强5E型飞机的两种外挂状态(全机+2×LS-500J激光弹。全机+2×LS-500J激光弹+2×4001副油箱)作了颤振特性分析。 相似文献
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For flight control systems with time-varying delay, an H1 output tracking controller is proposed. The controller is designed for the discrete-time state-space model of general aircraft to reduce the ef... 相似文献
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For flight control systems with time-varying delay, an H∞ output tracking controller is proposed. The controller is designed for the discrete-time state-space model of general aircraft to reduce the effects of uncertainties of the mathematical model, external disturbances, and bounded time-varying delay. It is assumed that the feedback-control loop is closed by the communication network, and the network-based control architecture induces time-delays in the feedback information. Suppose that the time delay has both an upper bound and a lower bound. By using the Lyapu- nov-Krasovskii function and the linear matrix inequality (LMI), the delay-dependent stability criterion is derived for the time-delay system. Based on the criterion, a state-feedback H∞ output tracking controller for systems with norm-bounded uncertainties and time-varying delay is presented. The control scheme is applied to the high incidence research model (HIRM), which shows the effectiveness of the proposed approach. 相似文献
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I.F. Shaikhislamov V.M. AntonovYu.P. Zakharov E.L. BoyarintsevA.V. Melekhov V.G. PosukhA.G. Ponomarenko 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Magnetosphere with a size comparable to the ion kinetic scales is investigated by means of laboratory experiment, analytical analysis and Hall MHD simulation. In experiment a specific magnetic field was observed which is non-coplanar to dipole field, does not change sign at dipole moment inversion and could be generated only via the quadratic Hall term. Magnetopause position and plasma stand off distance were found to be profoundly different between the experimental regimes with small and large ion inertia length. In the previous studies of a mini-magnetosphere by kinetic codes such novel features were observed as absence of the bow shock and plasma stopping at the Stoermer particle limit instead of the pressure balance distance. Proposed analytical model explains these features by Hall currents which tend to cancel magnetic field convection by ions. Performed numerical simulation shows a good agreement with experiment and analytical model. It gives detailed spatial structure of the Hall field and reveals that while ions penetrate deep inside mini-magnetosphere electrons overflow around it along magnetopause boundary. 相似文献
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多刚体卫星转动惯量在轨辨识 《空间控制技术与应用》2015,41(6):31
惯量辨识需要精确的动力学特性,针对动力学特性不可忽略太阳电池阵转动这一状况,提出一种惯量辨识方法,用于卫星本体惯量和太阳电池阵惯量的联合辨识.在建立多刚体姿态动力学基础上,针对辨识变量的耦合特性,推导带约束的优化辨识模型,再利用约束最小二乘算法求解.最后通过仿真计算验证了辨识方法的可行性. 相似文献
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以大气层内导弹逆轨拦截高速机动目标为背景,本文运用最优控制和双曲正切函数设计带角度约束的三维最优制导律。分别假设导弹弹道倾角和弹道偏角保持瞬时恒定,将三维制导分解为两个相互垂直平面内的二维制导。考虑导弹速度时变的情况,建立带角度约束的制导方程。设计一种双曲正切函数的变种,并将其设为脱靶量和角度约束的权重系数,根据极小值原理推导了最优制导律的解析表达式。双曲正切函数变种的引入,使得制导律对脱靶量和角度约束的要求是逐渐增强的,可以解决传统最优制导律初始段过载指令过大的问题。仿真结果表明了该制导律的有效性。 相似文献
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针对存在不确定非线性动态和外部时变干扰的多无人机系统的时变编队问题,提出了基于扩张状态观测器(ESO)的抗扰编队控制方法。首先建立了分布式ESO来估计多无人机系统的不确定性,基于ESO的输出提出了抗扰编队控制律,并提出一套算法来对控制律进行参数选定。然后,通过分析得到基于该控制律下,多无人机系统实现抗扰时变编队所需要的充要条件,并最终严格证明了在满足编队充要条件和基于提出的控制律下,多无人机系统可以稳定实现抗扰时变编队。最后仿真结果表明理论方法的有效性。 相似文献