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961.
针对火星返回上升器由于环境等因素造成的推力器故障导致的姿态控制系统失稳而难以安全返回的严重问题,提出基于模型预测的动态容错控制再分配方法。根据推力器动态特性建立上升器推力分配模型,对模型参数误差进行实时估计从而修正分配模型,根据模型预测自适应推力再分配方法实施容错控制。同时,将推力器输出限制作为优化求解器的约束,并将推力器故障模型作为优化求解的约束域,实现最小化分配误差和最小化燃料消耗意义下的最优推力再分配。计算机仿真表明了该方法的可行性和实用性,获得了满意的结果,它能使推力器输出推力误差降低60%以上,姿态控制系统能在故障状态下3~5 s快速镇定。 相似文献
962.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(1):439-455
Inter-spacecraft electrostatic force (Coulomb force) is desirable for close formation flying control because of its propellant-less and free contaminate characteristics attributed to the propellant exhaust emission. This paper presents robust optimal sliding mode control to deal with the problem of thruster saturation in tracking the formation trajectory for Coulomb spacecraft formation flying. The robust controller design is based on optimal control theory as a linear quadratic system, and it is augmented with an integral sliding mode control technique. The stability of the closed-loop system is guaranteed using the second Lyapunov method. The developed controller outperforms the existing ones, because it has a higher degree of fine-tuning to cope with the uncertainty. Numerical simulations are employed to confirm the efficiency of the developed controller. 相似文献
963.
基于飞行-推力一体化思想提出了一种针对搭载超燃冲压发动机的吸气式高超声速飞行器速度通道的状态/输入约束自适应鲁棒保性能安全控制方案。首先根据超燃冲压发动机的机理分析与计算流体动力模型数据,建立了安全子系统与性能子系统面向控制的仿射非线性模型。之后基于障碍Lyapunov理论与动态面设计方法设计了一套安全子系统状态约束控制器,从理论上保证了飞行器在跟踪指令的全过程中,发动机相关状态不会触碰安全边界,并结合自适应技术与辅助系统提高了该控制系统的鲁棒性。针对性能子系统设计了一套鲁棒自抗扰控制器,达到“保证安全的前提下不折损性能”的目的。仿真结果表明所设计的控制系统可以在保障安全的同时达到预想的性能,并显著放宽了超燃冲压发动机对飞行器飞行姿态的约束,保证了高超声速飞行器的机动灵活性。 相似文献
964.
《中国航空学报》2022,35(8):221-235
Aimed at the problem of instability in engine control caused by vector deflection in experiment of turbofan engines with Axisymmetric Vectoring Exhaust Nozzle (AVEN), a vector deflection stability control method of aero-engine based on Linear Active Disturbance Rejection Control (LADRC) is proposed. Firstly, based on CFD numerical simulation, aerodynamic performance model of AVEN is established, and the aerodynamic load change rule of the nozzle throat area actuator during vector deflection is revealed. Subsequently, the integrated model of AVEN/turbofan engine is established by Simulink/AMESim co-simulation. Finally, the nozzle throat area control loop based on LADRC is designed. The simulation results show that the integrated model can reflect the influence of vector deflection on the stability of the control system. The accuracy comparison between the fan rotor speed and the test data during vector deflection is larger than 1%, indicating a high degree of confidence. Compared with the conventional PID control, the designed LADRC control loop reduces the speed of the low-pressure rotor during vector deflection by 70%, which effectively improves the control stability of the vector deflection. Meanwhile, the fuel flow ratechange during the vector deflection process is smaller and more economical, which provides an important reference for engineering applications. 相似文献
965.
《中国航空学报》2023,36(4):354-365
The problem of decreasing stability margins in L1 adaptive control systems is discussed and an out-of-loop L1 adaptive control scheme based on Lyapunov’s stability theorem is proposed. This scheme enhances the effectiveness of the adaptation, which ensures that the system has sufficient stability margins to achieve the desired performance under parametric uncertainty, additional delays, and actuator faults. The stability of the developed control system is demonstrated through a series of simulations. Compared with an existing control scheme, the constant adjustment of the stability margins by the proposed adaptive scheme allows their range to be extended by a factor of 4–5, bringing the stability margin close to that of variable gain PD control with adaptively scheduled gains. The engineered practicability of adaptive technology is verified. A series of flight tests verify the practicability of the designed adaptive technology. The results of these tests demonstrate the enhanced performance of the proposed control scheme with nonlinear parameter estimations under insufficient stability margins and validate its robustness in the event of actuator failures. 相似文献
966.
967.
968.
Liu ZHANG Yong HUANG Zhenglong ZHU Lihua GAO Fuzheng CHEN Fuzhang WU Meng HE 《中国航空学报》2023,36(6):52-62
Circulation Control(CC) realizes rudderless flight control by driving compressed air jet to generate a virtual rudder surface, which significantly improves low detectability. The layout plan of combined control rudder surface is proposed based on the tailless flying wing aircraft. The closed-loop jet actuator system and stepless rudder surface switching control strategy are used to quantitatively study the control characteristics of circulation actuator for pitch and roll attitude through 3-DOF ... 相似文献
969.
固体姿轨控发动机通过伺服机构控制喉栓位移实现推力矢量调节。为实现推力精确调控,需拟合大量地面试验数据,得出发动机喉栓位移与推力矢量间的数学模型。提出了一种面向喉栓式固体轨控发动机喉栓运动时序实验设计方法,实现了单次试验中不同燃烧室理论压强及喉栓位移组合最大覆盖,为最低试验成本下精准构建喉栓位移与推力输出模型提供训练样本。以四阀固体轨控发动机作为对象,基于零维内弹道实现燃气发生器压强求解。采用Φ p ![]()
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准则评估喉栓位置组合遍历性,并对其进行优化,获得合理的喉栓运动方案。算例结果证明实验设计后方案在整个运动周期内几乎遍历各种组合状态,较实验设计前Φ p ![]()
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值提升近40%,验证了本文实验设计方法在时序工程问题中的优良性能。采用实验设计方法可提高固体姿轨控发动机地面试车数据利用效率。 相似文献
970.