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过失速大机动飞机的飞行控制律设计 总被引:1,自引:0,他引:1
对新一代带推力矢量的战斗机在大迎角过失速机动下的飞行控制律进行设计,并进行了机动指令飞行仿真。引进推力矢量技术,建立带推力矢量的飞机模型方程;采用奇异摄动理论,将控制回路分为两个快慢(内外)回路,对每个回路分别用动态逆方法进行飞行控制律设计;并采用结构奇异值μ综合和分析的方法对快(内)回路设计了鲁棒控制器;最后所设计的控制律进行了机动指令飞行仿真,仿真结果表明设计的过失速机动控制律良好。 相似文献
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无人直升机具有悬停、小速度全向机动、大速度前飞等飞行能力,其飞行包线范围大,对飞行控制律设计的要求很高。无人直升机在进行自动航线飞行时,不仅涉及的飞行模态多,而且需要满足复杂的飞行航线需求。根据无人直升机复杂的航线飞行特点,对其航线飞行过程进行区域划分,针对不同划分区域,采用工程上常用的PID控制方法和衰减软化技术,设计了高度控制器、纵向位置控制器、横向位置控制器、协调转弯控制器和控制器问的切换算法,并进行典型航线飞行的数字仿真。仿真结果显示,无人直升机飞行航迹与设定航线的重合性较好,模态切换稳定平滑,从而验证了无人直升机自动航线飞行控制律设计的正确性,为后续工程应用奠定基础。 相似文献
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《中国航空学报》2021,34(2):396-406
In this paper a nonlinear control method is proposed for the tracking control of hypersonic flight vehicles. The designed control laws do not utilize the measured flight path angle due to its inferior accuracy in practical engineering. For this, an estimated flight path angle is designed via the measurements of the altitude and velocity. A tracking differentiator is designed for constructing nonlinear disturbance observer which is used to estimate the model uncertainties including the parameter indeterminacies and external disturbances in the channels of velocity and pitch rate. A robust high-order differentiator is introduced to avoid the employment of the measured flight path angle and estimate the lumped disturbance in dynamics of flight path angle. Meanwhile, the possible saturation of the control inputs is considered and compensated by the auxiliary states. The boundness of closed-loop signals is proved through the Lyapunov theory. Comparative simulations are carried out and the results demonstrate the effectiveness of the proposed method. 相似文献
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针对传统UAV编队控制律显式考虑约束能力不强的不足,基于预测控制方法和虚拟结构控制策略,设计了一种分布式编队控制律。该控制律能显式地考虑各种约束,每个UAV仅需要滚动求解有限时域优化问题得到自身控制输入,提出了一种简单的代价惩罚的方法实现障碍规避,并将优先级策略引入UAV之间避碰中。仿真结果表明,所设计的编队控制律具有... 相似文献
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Guidance problems with flight time constraints are considered in this article. A new virtual leader scheme is used for design of guidance laws with time constraints. The core idea of this scheme is to adopt a virtual leader for real missiles to convert a guidance problem with time constraints to a nonlinear tracking problem, thereby making it possible to settle the problem with a variety of control methods. A novel time-constrained guidance (TCG) law, which can control the flight time of missiles to a prescribed time, is designed by using the virtual leader scheme and stability method. The TCG law is a combination of the well-known proportional navigation guidance(PNG) law and the feedback of flight time error. What's more, this law is free of singularities and hence yields better performances in comparison with optimal guidance laws with time constraints. Nonlinear simulations demonstrate the effectiveness of the proposed law. 相似文献
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针对含有不确定干扰项的吸气式高超声速飞行器模型,分别设计了基于反馈线性化的速度控制器和基于反步法的航迹控制器,以实现对速度和航迹角参考信号的稳定跟踪。通过指令滤波器得到俯仰角的实际跟踪指令及其一阶、二阶微分信号,可直接设计升降舵控制指令,在解决了虚拟控制量求导"复杂性爆炸"问题的同时,减少了反推计算步数,从而达到提高系统动态性能和优化控制器结构的目的。基于LaSalle不变集原理和Lyapunov理论设计的自适应更新律保证了系统的稳定性。仿真结果表明,所设计的控制器在飞行器存在不确定干扰的情况下仍能满足对参考信号跟踪性能的要求。 相似文献
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在进行大包线飞行控制律设计中,需将飞行包线分为几个区域,针对各个区域设计线性控制律,采用多个线性控制律来近似替代所需的非线性控制律,本文中线性控制律采用PID控制结构,若用传统PID控制律参数整定方法,工作烦琐、设计时间长,而且控制效果不是很好,提出运用遗传算法优化控制律参数,并针对遗传算法局部寻优能力差、收敛速度差、易早熟等缺点,对其进行了几点改进,为提高鲁棒性,对其适应函数进行了设计,针对某机型某个区域的俯仰控制进行了PID控制律设计仿真,利用改进的遗传算法对其参数进行优化,结果表明,该方法在23代就能得到最优控制参数,而且使系统动态性能有了较明显的提高。 相似文献
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航迹控制回路是无人机自动控制飞行中的重要环节,它涉及无人机的姿态、航向和飞行状态等重要参数的变化。根据飞行控制的基本控制律实现了无人机在复杂航迹条件下的安全飞行控制,模拟出无人机在自动控制下的航迹、盘旋和着陆等的飞行任务。采用面向对象方法设计了基于堆栈的通用化的航线管理类。并分析了无人机在手动操作切换到自动控制方式时寻找航迹点飞行中可能出现的问题,提出了相应的解决方案。 相似文献
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拖曳系统的飞行性能是评价拖曳系统可行性的一项基本内容,而要求解拖曳系统的飞行性能,则必须解决拖曳系统中运载器的航迹控制问题。在飞行器“准平衡”的假设下,研究了拖曳系统在铅垂面和水平面内飞行时运载器的航迹控制律,并进行了仿真计算。计算结果表明,所采用的控制律可以实现运载器跟随拖曳飞机的飞行航迹。 相似文献
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The Flight Research Laboratory at Princeton University is engaged in an experimental program to investigate a variety of approaches to digital control by actual flight test. Experimentation is being conducted with Princeton's 6-DOF variableresponse research aircraft (VRA), which is equipped for direct side-force control, direct-lift control, feedback of all motion variables, and multiple-pilot command modes. VRA avionics have been augmented by a microprocessor digital flight control system (Micro-DFCS), which uses off-the-shelf computer components capable of operating in parallel or in series with the existing variable-response system. The digital control laws operate in conjunction either with the "bare airframe" dynamics of the VRA or with the dynamics of a simulated aircraft, provided by the existing variable-response system. The initial flight control computer program CAS-1 provides three longitudinal control options: direct (unaugmented) command, pitch rate command, and normal acceleration command. The latter two options are "Type 0" systems designed by linear-quadratic control theory. Future Micro-DFCS software will provide a variety of increasingly complex control options, including "Type 1," logic, gain scheduling, coupled 3-axis control, and "CCV" command modes. 相似文献
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《中国航空学报》2022,35(12):144-155
To overcome the drawbacks such as large wing deformations, poor performance encountering gusts, limits in taking off and landing, inconvenience of transportation of High-Altitude Long-Endurance (HALE) Unmanned Aerial Vehicles (UAVs), a new conceptual aircraft called wingtip-docked Multi-Body Aircraft (MBA) has attracted lots of attentions. Aiming to investigate the feasibility of this concept, two UAV models were designed, manufactured and connected by a wingtip-docking mechanism, which only allows the relative roll motion between the two aircraft. The trim solution of the two connected aircraft is firstly obtained by solving the developed nonlinear flight dynamic equations, followed by the stability analysis based on the linearized model. The results show that the connected aircraft is inherently unstable and cannot fly without a reasonable flight control system. A set of Proportional-Integral-Derivative (PID) control laws was then developed and implemented in the two experimental aircraft. The success of the flight tests show that the flight control can effectively eliminate the unstable motion and the wingtip-docked MBA is controllable and feasible. 相似文献
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弹性飞机阵风减缓研究 总被引:1,自引:0,他引:1
阵风响应减缓可有效抑制飞机由于离散突风和紊流引起的附加过载。以某民机为研究对象,基于飞机结构动力学方程和非定常空气动力学模型,建立弹性飞机在突风作用和控制面偏转联合激励下的开环气动弹性方程。引入坐标变换,建立飞机刚体模态对应的广义坐标与飞行动力学运动变量之间的关系,从而实现气动弹性方程与飞行动力学方程的融合。并以副翼和升降舵为突风减缓控制面。采用俯仰角速率,翼尖加速度和质心加速度作为反馈信号,针对连续突风和离散突风,分别设计相应的控制律。仿真结果表明,减缓系统对翼尖过载、翼根弯矩具有较好的抑制能力。 相似文献
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直升机全包线协调转弯控制律设计及仿真 总被引:1,自引:0,他引:1
提出了一种应用多目标遗传算法设计直升机全包线协调转弯控制律参数的方法.将侧向过载和倾斜角稳态误差的设计要求转换为不等式约束,并以所有设计包线总体性能Pareto最优作为总目标,以各设计包线性能最优作为子目标,再应用多目标遗传算法自动搜索最优伞包线协调转弯控制律参数.最后,设计了某型直升机协调转弯控制律参数,仿真结果表明... 相似文献