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161.
为解决工程中直接使用基于C-W方程的双脉冲法和拉格朗日乘子法时远距离导引精度低,以及分段导引过程复杂和可靠性降低等问题,设计了一种新的冲量计算方法。基于原方法适时引入当前状态和误差信息,继承了拉格朗日法运算简单的优点,并将原开环控制改为闭环控制。仿真结果表明,该法提高了导引精度,同时还充分利用多冲量法的特性实现了更大交会时间范围的燃料最优。 相似文献
162.
传统制导拦截模型可用一组方程来描述,由于该方程是耦合的,对其进行制导律的设计时,往往假定导弹在瞄准线方向不可控,但这样必然产生较大的模型误差。文中将传统制导方程进行变换得到其状态空间形式,根据导弹和目标各自加速度沿瞄准线(LOS)方向及其垂直方向的分量之间的物理关系对状态方程降维,然后通过引入有界参数变量,得到含有控制不确定性和外部干扰的描述形式,进而按照不确定系统变结构控制原理设计了制导律。由于制导律设计时考虑了导弹法向加速度分量的相关性、不同状态对拦截模型不确定性影响和外部干扰,所以具有强鲁棒特性.仿真结果表明这种制导律在合理参数选取下其抗目标机动能力强、脱靶量小、过载要求低、无控制抖动问题。
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165.
Optimal guidance based on receding horizon control for low-thrust transfer to libration point orbits
Haijun Peng Qiang Gao Zhigang Wu Wanxie Zhong 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
This paper addresses the design and computation of a guidance law for a transfer mission from an orbit near the Earth to a halo orbit around the libration point L2 in the Sun–Earth system. The guidance law, which is designed based on receding horizon control and compensates for launch velocity errors that are introduced by inaccuracies of the launch vehicle, is solved using the generating function method. During the design of the closed-loop guidance law, the entire transfer mission, which is considered a nonlinear optimal control problem, is evaluated to obtain a nominal reference trajectory. Using the launch velocity errors and the uncertainty of the model, a spacecraft controlled by the proposed guidance law tracks the reference trajectory. Furthermore, the original Riccati differential equation in the receding horizon control algorithm is replaced by an equivalent convenient form of the Riccati differential equation that is based on the generating function. The high-efficiency solution of the equivalent equation avoids the online direct integration of the original Riccati differential equation, which significantly increases the computational efficiency for the receding horizon control problem. Numerical simulations using a nonlinear bicircular four-body model demonstrate the capabilities of the proposed receding horizon guidance law for the transfer mission. In addition, the generating function method improves the computational efficiency by at least one order of magnitude over the backward sweep method in solving the receding horizon control problem. 相似文献
166.
Collaborative Navigation in an Unfamiliar Environment with People Having Different Spatial Aptitudes
This study addressed the issue of collaborative navigation by examining the types of information communicated in the processes of direction giving and receiving between people who guided each other simultaneously to a destination over the cell phone in a novel environment. When paired with a partner whose sense of direction differed greatly from their own, people found the collaboration difficult and took a longer time to verbally direct the partner to the destination. Landmarks that people used in giving navigational instructions differed depending on sense of direction. People with a good sense of direction adjusted route directions to their partners' wayfinding ability. Results from a detailed qualitative analysis of participants' verbal protocols and implications for personalized navigation tools are discussed. 相似文献
167.
Abstract This paper addresses changes of spatial granularity in route directions in relation to information needs in multimodal traveling. We outline a model of variability in granularity and apply this model to empirical data. Results reveal that linguistic route directions produced by humans as well as automatically generated web-based services provide the most crucial route elements in hierarchically structured ways that reflect the salient structure imposed by multimodal traveling. However, although the web-based information is impressively comprehensive, human route directions exhibit more flexibility regarding switches of place-related granularity, and they provide more detailed information at complex locations or decision points. 相似文献
168.
Abstract The nature of route learning in terms of the memorizing of landmarks was investigated. In Experiment 1, participants memorized landmarks while being guided through a computer-simulated hallway (dynamic, with spatial context), or while viewing the landmarks one by one in front of a black background (static, without context). Two more conditions completed the 2 × 2 design. One condition preserved the dynamic landmark viewing properties (observers approached each object, passed it, turned to the next object, and so on), but the background was black (dynamic, without context). In the other condition the observer saw a stationary display of each object within a hallway, but did not approach the object (static, with context). Serial recall was much better after viewing the landmarks in the dynamic presentation format with spatial context than in the other conditions. Experiment 2 showed that the superior performance in the dynamic condition with context was abolished when all hallway segments were equally long. This implies that metric information is a component of route knowledge at a very early stage, which is incompatible with the dominant framework, but is compatible with the alternative framework for spatial microgenesis. 相似文献
169.
Stability analysis of explicit guidance laws for space launch vehicles with varying thrust integrals
Eun-Jung Song Sang-bum ChoChang-Su Park Woong-Rae RohMiok Joh 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
In this study, a stability analysis of the explicit guidance laws for space launch vehicles is performed with consideration of varying thrust integrals. Among various forms of explicit guidance, linear tangent guidance in its general form is selected and six different acceleration profiles are considered for this numerical experiment. A linear system modeling which includes all of the significant dynamic elements of a space launcher is performed to analyze the effect of the characteristics of thrust integrals on stability margins. Numerical results show that in an aspect of guidance stability, it is advantageous to have thrust integrals derived from increasing acceleration profiles, such as constant thrust case, which may be considered in the development of propulsion systems. Finally, time-domain simulation with the original nonlinear models is performed to verify the approach and the result shows that the nonlinear dynamics of the system is conserved well in the linear model. 相似文献
170.