共查询到19条相似文献,搜索用时 156 毫秒
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基于逆控制和模糊逻辑的直升机飞控系统设计 总被引:1,自引:0,他引:1
提出了一种基于模型的逆控制技术与基于规则的模糊控制技术相结合的直升机飞控系统设计方法,以解决当直升机数学模型不确定时飞控系统的设计问题,并设计了相应的逆控制器及模糊控制器。仿真结果表明,所设计的飞控系统具有良好的动态响应、较强的鲁棒性及满意的解耦效果,在直升机飞行控制系统的设计中有一定应用价值。 相似文献
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回顾了直升机机动飞行逆仿真技术国内外发展概况,借鉴国内外的研究成果,针对逆仿真核心技术的发展现状进行了分析和讨论,在此基础上,对直升机机动飞行逆仿真技术的进一步发展趋势进行了分析。 相似文献
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基于UKF的共轴式无人直升机模型辨识 总被引:1,自引:0,他引:1
建立了共轴式无人直升机系统非线性模型,并针对其非线性强,不同飞行模态下气动参数差异等问题,将无迹卡尔曼滤波(UKF)引入共轴式直升机系统非线性模型辨识,不但避免了直升机线性模型仅仅适用于悬停模态的局限性,同时为直升机系统在线自适应控制提供了基础条件,使得共轴式无人直升机自主全包线飞行成为可能.以北京航空航天大学FH-1共轴式无人直升机为例进行了仿真辨识实验.实验结果表明基于该方法的共轴式直升机在线非线性模型辨识不依赖于参数初值的选取,模型参数能在10s内收敛,各状态量辨识精度达到80%以上,明显高于传统的预报误差法(PEM),具有一定的实用性. 相似文献
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直升机悬停状态全耦合飞行动力学模型辨识方法 总被引:4,自引:0,他引:4
提出了一种基于集员辨识理论的直升机全耦合飞行动力学模型参数辨识方法.该方法针对直升机飞行动力学模型耦合强,难以得到辨识模型和待辨识参数之间显式函数关系的特点,推导并建立了状态空间微分方程形式模型集员辨识的间接辨识算法.通过引入广义噪声的概念以及对其边界的灵活设定,实现了对辨识参数众多、耦合严重且灵敏度差异大的复杂模型的... 相似文献
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直升机全量飞行动力学数值仿真模型及其实现 总被引:1,自引:0,他引:1
论述了一种通用的直升机飞行动力学全量数值仿真模型及其实现,该模型有6个机体自由度和3个旋翼自由度。以旋翼系统的仿真为重点,将直升机旋翼的气动力和力矩通过沿半径和方位角的解析积方求得,并计入了旋翼挥舞动力学的影响。仿真模型以某型直升机为算例,并加入了增稳系统,对仿真模型飞行特性进行了初步的验证,结果表明,所述模型思路是正确的。 相似文献
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一种无人直升机飞行力学模型辨识方法研究 总被引:2,自引:0,他引:2
研究了一种无人直升机飞行力学模型辨识方法.将状态子空间辨识法和误差预报辨识法这两种不同机理的辨识方法相结合,用于无人直升机飞行力学模型的辨识.通过仿真计算,成功地辨识得到了悬停状态下算例无人直升机的高阶飞行力学模型.结果表明:提出的辨识方法具备状态子空间辨识法和误差预报辨识法各自的优点,不会出现经典辨识算法中寻优过程中出现的局部极小现象以及迭代带来的收敛性问题. 相似文献
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某型无人直升机飞控系统仿真研究 总被引:1,自引:0,他引:1
介绍了某型无人直升机飞行控制系统半实物仿真系统的组成、原理和实现方法。在仿真系统中,采用Windows平台实现了无人直升机飞行动力学模型的实时解算,解决了在多任务平台上进行实时仿真的关键问题。通过对某型无人直升机飞行控制系统半实物仿真结果的分析和研究,确定了无人直升机飞行控制规律,并整定了控制参数。 相似文献
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直升机机动飞行的逆模拟 总被引:1,自引:0,他引:1
本文给出了一种直升机机动飞行的逆模拟方法以计算跟随预定飞行轨迹的驾驶员操纵,根据这一方法可以确定为完成直升机机动飞行所需的驾驶员操纵输入及直长机的飞行速度、角速度和的变化历程。直同飞行动力学模型没有作任何线化假设,其中考虑了旋翼入流的时滞效应、前行桨叶的压缩性物后行桨叶的失速特性及旋翼桨叶的非定常挥舞运动,引入了旋翼尾迹对直升机机身、尾翼和尾桨的气动干扰。最后以黑鹰直升机为例计算了鱼跃越障机动飞行 相似文献
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直升飞机动力学逆问题是已知运动的控制规律,对直升机机动飞行和现代飞行控制律设计有重要意义。根据直升机飞行动力学逆问题研究的现状,概述现代飞行动力学逆问题的研究内容及进展,重点分析直升机逆仿真技术的特点,讨论直升机最佳机动控制与非线性控制律设计的途径与方法,展示直升机逆问题研究的前景以及存在的问题,供直升机设计和飞行动力学研究人员参考。 相似文献
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Wang Wei Xia Pinqi 《中国航空学报》2007,20(6):501-510
The methodology for adaptive control of helicopter ground resonance with magnetorheological (MR) damper is presented. The adaptive inverse control method is used to control the output damping force of MR damper and the range of the damping force is given. Through the adaptive inverse control, the damping force of MR damper is fit to a desired damping force. With the background of applying MR damper to control of helicopter ground resonance, a model of loss force and an adaptive arithmetic for stabilization of the coupled rotor/fuselage system are presented. The simulation shows that the controller presented in this paper can stabilize the rotor/fuselage coupling system quickly and control the helicopter ground resonance effectively. 相似文献
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《Progress in Aerospace Sciences》2006,42(3):174-210
The technique of inverse simulation is finding application in many and varied fields. As the name implies this technique is used to calculate the control action required to achieve a specified system response. The field of aircraft flight dynamics is particularly suited to this form of simulation as the question of what control actions must the pilot (or automatic flight control system) take for the aircraft to fly along a particular trajectory (a landing approach, for example) is often asked. This paper looks specifically at the application of inverse simulation in flight dynamics. The aim is not only to give an overview of the various techniques and applications but also to provide guidance to potential users of the technique on several of the physical and numerical features often observed in the results. An extensive review of the methodologies used within the family of inverse simulations is presented followed by a formal treatment of the theoretical development of inverse simulation as an established technique. A case study involving the inverse simulation of a helicopter flying a slalom manoeuvre is presented to demonstrate the application of inverse simulation in a flight dynamics analysis. An important feature of the use of inverse simulation is that it is necessary to define the output response required—in the case of flight dynamics the required flight path has to be modelled. Some of the methods used are documented, and their validity discussed. The paper also gives an insight into the types of problem which can be addressed by inverse simulation by detailing some of the many applications to which it has been put in the past. These include studies of rotorcraft handling qualities, performance and design, and pilot modelling as well as model validation. An important element of this paper is the formal, theoretical analysis of some of the numerical and physical features exhibited by inverse simulation which should aid potential users to interpret their results. The work presented in this paper shows a clear evolution of inverse simulation from its initial days when the mathematical models used were relatively simple into a mature analytical technique able to incorporate state of the art mathematical models and be applied to real flight dynamics problems. 相似文献