全文获取类型
收费全文 | 542篇 |
免费 | 139篇 |
国内免费 | 58篇 |
专业分类
航空 | 355篇 |
航天技术 | 79篇 |
综合类 | 24篇 |
航天 | 281篇 |
出版年
2023年 | 6篇 |
2022年 | 22篇 |
2021年 | 19篇 |
2020年 | 23篇 |
2019年 | 12篇 |
2018年 | 16篇 |
2017年 | 7篇 |
2016年 | 17篇 |
2015年 | 15篇 |
2014年 | 32篇 |
2013年 | 40篇 |
2012年 | 28篇 |
2011年 | 35篇 |
2010年 | 27篇 |
2009年 | 11篇 |
2008年 | 15篇 |
2007年 | 41篇 |
2006年 | 30篇 |
2005年 | 43篇 |
2004年 | 27篇 |
2003年 | 20篇 |
2002年 | 23篇 |
2001年 | 18篇 |
2000年 | 22篇 |
1999年 | 31篇 |
1998年 | 22篇 |
1997年 | 19篇 |
1996年 | 23篇 |
1995年 | 27篇 |
1994年 | 12篇 |
1993年 | 11篇 |
1992年 | 9篇 |
1991年 | 17篇 |
1990年 | 5篇 |
1989年 | 8篇 |
1988年 | 3篇 |
1987年 | 3篇 |
排序方式: 共有739条查询结果,搜索用时 31 毫秒
451.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2020,65(11):2662-2673
The Newton-Kantorovich/Radau pseudospectral method is implemented in a homotopy scheme to solve the rigid spacecraft time-optimal three-axis reorientation problem. First, the reorientation differential equations associated with the current homotopic variable are linearized about the nominal (previous homotopic variable) solution. Then, the Radau pseudospectral method is used to solve the resulting linearized differential equations. By successively updating the nominal solution with the Newton-Kantorovich approach, the linearized solving procedure is iterated to achieve high-order precision. Because no numerical integration is needed and only linear algebraic equations are solved, the proposed method is computationally efficient. Finally, performance of the proposed method is illustrated through numerical examples. 相似文献
452.
关于探测器定点在共线平动点附近的控制问题 总被引:6,自引:0,他引:6
对探测器定点在共线平动点附近的轨道控制提出了一种小推力方案,针对日-地(月)系的具体背景给出了数值模拟结果,并对其进行了相应的分析. 相似文献
453.
Liang Sun 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(7):2229-2238
A saturated fault-tolerant attitude tracking controller for disturbed rigid spacecraft is derived using nonlinear state feedback control method. The proposed controller achieves the constraints of control inputs by directly using the bounded function instead of the traditional saturation compensator technique, and the active tolerance to the partial loss of actuator effectiveness is also achieved by directly using the known bounds of the actuator faults in the controller. Specifically, compared with the traditional saturated control methods, a continuously bounded nonlinear function in the proposed controller is used to guarantee that the actuator outputs are smoothly bounded under the prescribed constraints. Based on some properties of the attitude tracking dynamics, the proposed controller can ensure the attitude tracking errors converge to small neighborhoods of zero via stability analysis in the Lyapunov framework. Simulation results are presented to illustrate the effectiveness of the control scheme. 相似文献
454.
Thomas S. Richardson Cormac McFarlane Askin Isikveren Ken Badcock Andrea Da Ronch 《Progress in Aerospace Sciences》2011,47(8):647-659
One of the main drivers behind the SimSAC project and the CEASIOM software is to bring stability analysis and control system design earlier into the aircraft conceptual design process. Within this paper two very different aircraft are considered, a conventional T-tail based on the existing EA500 Very Light Jet and the second, a novel Z-wing configuration known as the GAV or general aviation vehicle. The first aircraft serves as a baseline comparison for the second, and the cruise case is considered as a benchmark for identifying potential drag reductions and aircraft stability characteristics. CEASIOM, the Computerised Environment for Aircraft Synthesis and Integrated Optimisation Methods, is used to generate aerodynamic data sets for both aircraft, create trim conditions and the associated linear models for classical stability analysis. The open-loop Z-wing configuration is shown to display both highly unstable and coupled modes before a multivariable Stability Augmentation System (SAS) is applied both to decouple and stabilise the aircraft. Within this paper, these two aircraft provide a test case with which to demonstrate the capabilities of the CEASIOM environment and the tools which have been developed during the SimSAC project. This new software suite is shown to allow conceptual development of unconventional novel configurations from mass properties through adaptive-fidelity aerodynamics to linear analysis and control system design. 相似文献
455.
为解决直流电机速度控制问题,采用增量式PI控制方法,设计了无刷直流电机速度控制器。对模拟调节器进行了离散化处理,每隔10ms用编码器测速一次,并进行适当的软件滤波,用计算出速度差作为控制量,用离散的差分方程代替连续的微分方程,用软件实现了PI控制算法。搭建了基于STM32的实验平台,给出了P和I参数整定方法,并通过大量实验得到了合适的P和I的系数,验证了该增量式PI控制方法的正确性。研究结果表明:该PI控制算法能够实现对速度的恒定控制,响应速度快、抗干扰能力强。为PID控制提供了实验的方法和步骤。 相似文献
456.
457.
458.
459.
短周期运动飞行品质的几种判据 总被引:3,自引:3,他引:0
飞机纵向短周期运动是影响其飞行品质的关键因素,根据国外近年来所进行的研究,综合,发纳出六种适用于小迎角飞行的短周期飞行品质标准,基于等效系统的控制期望参数(CAP)等准则依然适用,并作了增补;对于不能用低阶系统等效的飞机提出了诸发带宽准则等相应判据,这六种准则各有其侧重点和适用范围,较全面地反映了飞机短周期运动特性,共同完成对飞行品质的评判和预估。 相似文献
460.
Dominik Quantius Daniel Schubert Volker Maiwald Rosa París Lopéz Jens Hauslage Wolfgang Seboldt Ondrej Doule Irene Lia Schlacht Stephen Ransom 《Acta Astronautica》2014
An effective and self-sustainable artificial habitat design is essential for human spaceflight and expansion of mankind into orbit or towards other celestial bodies. There are two approaches that need to be implemented in future sustainable habitats: the use of re-cycling technologies in order to gain experience in closed-loop processes and the primary production of resource materials using In Situ Resource Utilisation (ISRU) principles. Various products will be provided and, where applicable, recycled in such a system taking into account basic human factors requirements such as crew work load capacity, safety and well-being, namely: 相似文献