全文获取类型
收费全文 | 890篇 |
免费 | 229篇 |
国内免费 | 278篇 |
专业分类
航空 | 583篇 |
航天技术 | 292篇 |
综合类 | 58篇 |
航天 | 464篇 |
出版年
2024年 | 10篇 |
2023年 | 32篇 |
2022年 | 51篇 |
2021年 | 61篇 |
2020年 | 68篇 |
2019年 | 53篇 |
2018年 | 75篇 |
2017年 | 48篇 |
2016年 | 53篇 |
2015年 | 77篇 |
2014年 | 85篇 |
2013年 | 66篇 |
2012年 | 87篇 |
2011年 | 93篇 |
2010年 | 64篇 |
2009年 | 51篇 |
2008年 | 49篇 |
2007年 | 66篇 |
2006年 | 43篇 |
2005年 | 26篇 |
2004年 | 32篇 |
2003年 | 25篇 |
2002年 | 17篇 |
2001年 | 27篇 |
2000年 | 21篇 |
1999年 | 18篇 |
1998年 | 21篇 |
1997年 | 21篇 |
1996年 | 8篇 |
1995年 | 11篇 |
1994年 | 10篇 |
1993年 | 3篇 |
1992年 | 4篇 |
1991年 | 2篇 |
1990年 | 7篇 |
1989年 | 7篇 |
1988年 | 5篇 |
排序方式: 共有1397条查询结果,搜索用时 78 毫秒
431.
《中国航空学报》2020,33(7):2024-2042
Designing a stable and robust flight control system for an Unmanned Aerial Vehicle (UAV) is an arduous task. This paper addresses the trajectory tracking control problem of a Ducted Fan UAV (DFUAV) using offset-free Model Predictive Control (MPC) technique in the presence of various uncertainties and external disturbances. The designed strategy aims to ensure adequate flight robustness and stability while overcoming the effects of time delays, parametric uncertainties, and disturbances. The six degrees of freedom DFUAV model is divided into three flight modes based on its airspeed, namely the hover, transition, and cruise mode. The Dryden wind turbulence is applied to the DFUAV in the linear and angular velocity component. Moreover, different uncertainties such as parametric, time delays in state and input, are introduced in translational and rotational components. From the previous work, the Linear Quadratic Tracker with Integrator (LQTI) is used for comparison to corroborate the performance of the designed controller. Simulations are computed to investigate the control performance for the aforementioned modes and different flight phases including the autonomous flight to validate the performance of the designed strategy. Finally, discussions are provided to demonstrate the effectiveness of the given methodology. 相似文献
432.
433.
针对高超声速飞行器俯冲段精确打击任务需求,提出了一种能够同时满足落速与落角约束的轨迹规划方法。建立了两段式轨迹规划策略,第一段采用参数化控制剖面调节飞行速度,第二段采用传统偏置比例导引律实现落角控制。将控制剖面的参数设计分解为多参数优化与单参数搜索两个问题:通过离线求解可行初始位置范围最大的多参数优化问题,提高控制剖面对初始偏差的适应性;通过在线求解带罚函数的单参数搜索问题,得到落速偏差最小的俯冲轨迹。结合高超声速飞行器模型,对所提出的俯冲轨迹规划方法进行了仿真。结果表明,该方法能够得到满足落速与落角约束的俯冲轨迹,具有较好的求解效率,且对初始状态偏差具有较强的鲁棒性。 相似文献
434.
针对接收机跟踪卫星导航信号时可能发生的各类故障,利用卡尔曼滤波器的残差观测量进行滤波,通常可以在不借助冗余观测量的情况下快速检测和隔离故障。建立软件接收机平台,利用卡尔曼滤波器进行导航信号的矢量跟踪,在跟踪环中模拟故障的发生并依靠残差序列滤波的方法检测并排除错误观测量。实验表明,在算法模拟的短时较大幅度干扰下,完好性监测方法可以快速检测并排除错误观测量对环路跟踪的影响,且无需冗余观测量。 相似文献
435.
模糊C均值算法在机载PD雷达杂波跟踪中的应用 总被引:4,自引:0,他引:4
介绍一种适用于机载PD雷达的杂波跟踪技术,结合机载PD雷达杂波分布特征和模糊C均值算法的特点,将模糊C均值算法用于杂波跟踪,给出了相应的算法流程,并提出了一种确定初始模糊隶属度的方法,经仿真数据验证,取得了满意的结果。 相似文献
436.
喷嘴为执行机构的空间飞行器基于误差四元数的非线性姿态跟踪控制 总被引:5,自引:0,他引:5
研究带喷嘴空间飞行器在姿态跟踪机动时的多轴耦合非线性姿态控制问题。姿态运动学和动力学用误差四元数描述。通过线性变换将误差四元数动力学方程转换成 4个摄动双积分系统 ,并基于此摄动双积分系统设计了开关控制器。由误差四元数及其导数构成的抛物型开关函数决定了控制器中的逻辑。文章考虑了最短的姿态捕获路径、外部干扰抑制、和不确定参数补偿问题。控制器允许力矩矩阵为非对称 ,从而使喷气执行机构的安装有更好的灵活性。由于不需要目标的加速度反馈 ,控制器可用于对机动目标的跟踪。用相平面方法分析了闭环系统的鲁棒稳定性。仿真结果验证了控制方案的可行性 相似文献
437.
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
438.
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
439.
440.
Weiyong Yi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2012
GOCE is the first satellite with a gravitational gradiometer (SGG). This allows to determine a gravity field model with high spatial resolution and high accuracy. Four of the six independent components of the gravitational gradient tensors (GGT) are measured with high accuracy in the so-called measurement band (MB) from 5 to 100 mHz by the GOCE gradiometer. Based on more than 1 year of GOCE measurements, two gravity field models have been derived. Here, we introduce a strategy for spherical harmonic analysis (SHA) from GOCE measurements, with a bandpass filter applied to the SGG data, combined with orbit analysis based on the integral equation approach, and additional constraints (or stabilization) in the polar areas where no observation is available due to the orbit geometry. In addition, we combined the GOCE SGG part with a set of GRACE normal equations. This improves the accuracy of the gravity field in the long-wavelength parts, due to the complementarity of GOCE and GRACE. Comparison with other models and with external data shows that our results are rather close to the GPS-levelling data in well-selected test regions, with an uncertainty of 4–7 cm, for truncation at degree 200. 相似文献