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排序方式: 共有250条查询结果,搜索用时 15 毫秒
总被引:2,自引:1,他引:2 针对高超声速飞行器再入制导问题,提出了一种基于轨迹线性化控制(TLC)方法的轨迹跟踪制导律.利用再入飞行器动力学固有时间尺度分离的特点,通过外环路和内环路的设计分别对高度和速度进行控制.轨迹倾角被用作外环路的虚拟控制量来控制高度;倾侧角和迎角用于在内环路跟踪轨迹倾角指令和速度.在反馈回路通过设计线性时变控制器对误差动态进行镇定.反馈增益可在线计算并能符号化地表示为参考轨迹的函数,从而避免了增益插值调度和可能需要的模式切换.大量仿真结果表明:TLC可以实现轨迹的精确跟踪且控制参数对不同参考轨迹的依赖性很小;TLC与基于轨迹在线生成的制导方法的结合可以显著提高再入制导的自主性和适应性. 相似文献
32.
火星进入过程中的故障和外部干扰不可避免地降低了火星进入制导和控制算法的性能。利用反步法设计了一种对转动惯量信息变化不敏感的火星进入姿态容错控制算法。首先,将虚拟控制律的微分量视作干扰量,利用自适应技术对其进行补偿,避免了传统反步法微分爆炸的缺陷。同时,控制设计过程中显式地引入了饱和函数,保证了在存在输入饱和的情况下,控制律仍然能使得探测器姿态保持稳定。最后,以“火星科学实验室”探测器为模型进行了数值仿真验证,结果表明该控制律在存在输入饱和约束、转动惯量不确定性、执行机构部分失效甚至完全失效的工况下,仍然能够完成对姿态的精准跟踪。 相似文献
33.
城市供水调度系统的现状与发展 总被引:4,自引:0,他引:4
简述国内城市供水调度系统的应用现状,指出在实际应用中存在的问题和解决的途径。并介绍了系统几年来的发展及今后的趋势。 相似文献
34.
35.
基于金星探测机械展开式进入飞行器技术述评 总被引:2,自引:0,他引:2
传统的金星进入飞行器存在弹道系数高、热流密度高、过载大等缺点,对热防护系统和设备的要求比较严苛。针对金星探测的任务需求,美国提出了一种基于机械展开式结构的金星进入飞行器,该飞行器发射时处于折叠状态,进入时展开形成较大的气动面,可以显著地降低弹道系数、热流密度、过载等。文章介绍了该飞行器的结构组成和展开过程,对机械展开式进入飞行器的研究现状进行了介绍,重点对比了机械展开式进入飞行器与传统形式的不同,通过对构型、工作流程、效果的对比,可以看出机械展开式进入飞行器在金星探测上具有很大的优越性,最后对其优势进行了总结,并提出了未来需要研究的问题。 相似文献
36.
为了研究冰冻天体表面撞击坑的形成与演化,开展了水冰的超高速撞击成坑实验。使用二级轻气炮发射1.0 mm直径的球形弹丸,以3 km/s、5 km/s和7 km/s速度对圆柱状冰块进行撞击。弹丸材料包括聚碳酸酯和不锈钢两种,冰块温度为253 K。实验观察到了不同弹丸和不同速度条件下,冰块中撞击坑的形貌特征。对撞击坑直径、深度和剖面形状进行了测量,并与文献中铝弹丸对水冰的撞击坑进行了比较分析。获得了水冰撞击坑特征随撞击参数的变化规律,结果表明:撞击坑直径和深度的主导机制不同,坑深主要由弹丸侵彻作用形成,而坑径主要由冰块的剥落所致;坑深比坑径具有更强的对于弹丸密度的依赖性,高密度弹丸撞击坑直径具有比低密度弹丸更强的对于撞击速度的依赖性;撞击坑体积与撞击能量成正比,高密度弹丸形成的撞击坑直径表现出“能量缩比”行为,而低密度弹丸形成的撞击坑直径表现出“动量缩比”行为。 相似文献
37.
During the conceptual design of a re-entry vehicle, the vehicle shape and geometry can be varied and its impact on performance can be evaluated. In this study, the shape optimization of two classes of vehicles has been studied: a capsule and a winged vehicle. Their aerodynamic characteristics were analyzed using local-inclination methods, automatically selected per vehicle segment. Entry trajectories down to Mach 3 were calculated assuming trimmed conditions. For the winged vehicle, which has both a body flap and elevons, a guidance algorithm to track a reference heat-rate was used. Multi-objective particle swarm optimization was used to optimize the shape using objectives related to mass, volume and range. The optimizations show a large variation in vehicle performance over the explored parameter space. Areas of very strong non-linearity are observed in the direct neighborhood of the two-dimensional Pareto fronts. This indicates the need for robust exploration of the influence of vehicle shapes on system performance during engineering trade-offs, which are performed during conceptual design. A number of important aspects of the influence of vehicle behavior on the Pareto fronts are observed and discussed. There is a nearly complete convergence to narrow-wing solutions for the winged vehicle. Also, it is found that imposing pitch-stability for the winged vehicle at all angles of attack results in vehicle shapes which require upward control surface deflections during the majority of the entry. 相似文献
38.
Chao Wu Jun Yang Shihua Li Qi Li Lei Guo 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2018,61(9):2457-2471
Facing the complex aerodynamic environment of Mars atmosphere, a composite atmospheric entry trajectory tracking strategy is investigated in this paper. External disturbances, initial states uncertainties and aerodynamic parameters uncertainties are the main problems. The composite strategy is designed to solve these problems and improve the accuracy of Mars atmospheric entry. This strategy includes a model predictive control for optimized trajectory tracking performance, as well as a disturbance observer based feedforward compensation for external disturbances and uncertainties attenuation. 500-run Monte Carlo simulations show that the proposed composite control scheme achieves more precise Mars atmospheric entry (3.8?km parachute deployment point distribution error) than the baseline control scheme (8.4?km) and integral control scheme (5.8?km). 相似文献
39.
Conceptual study of Mars Aeroflyby Sample Collection (MASC) is conducted as a part of the next Mars exploration mission currently entertained in Japan Aerospace Exploration Agency. In the mission scenario, an atmospheric entry vehicle is flown into the Martian atmosphere, collects the Martian dust particles as well as atmospheric gases during the guided hypersonic flight, exits the Martian atmosphere, and is inserted into a parking orbit from which a return system departs for the earth to deliver the dust and gas samples. In order to accomplish a controlled flight and a successful orbit insertion, aeroassist orbit transfer technologies are introduced into the guidance and control system. System analysis is conducted to assess the feasibility and to make a conceptual design, finding that the MASC system is feasible at the minimum system mass of 600 kg approximately. The aerogel, which is one of the candidates for the dust sample collector, is assessed by arcjet heating tests to examine its behavior when exposed to high-temperature gases, as well as by particle impingement tests to evaluate its dust capturing capability. 相似文献
40.
A.A. de Almeida R. Boczko G.C. Sanzovo D. Trevisan Sanzovo 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2009
We developed a general method for determination of water production rates from groundbased visual observations and applied it to Comet Hale–Bopp. Our main objective is to extend the method to include total visual magnitude observations obtained with CCD detector and V filter in the analysis of total visual magnitudes. We compare the CCD V-broadband careful observations of Liller [Liller, W. Pre-perihelion CCD photometry of Comet 1995 O1 (Hale-Bopp). Planet. Space Sci. 45, 1505–1513, 1997; Liller, W. CCD photometry of Comet C/1995 O1 (Hale-Bopp): 1995–2000. Int. Comet Quart. 23(3), 93–97, 2001] with the total visual magnitude observations from experienced international observers found in the International Comet Quarterly (ICQ) archive. A data set of ∼400 CCD observations covering about the same 6 years time span of the ∼12,000 ICQ selected total visual magnitude observations were used in the analysis. A least-square method applied to the water production rates, yields power laws as a function of the heliocentric distances for the pre- and post-perihelion phases. The average dimension of the nucleus as well as its effective active area is determined and compared with values published in the literature. 相似文献