共查询到20条相似文献，搜索用时 15 毫秒
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针对民航飞机的飞控系统高可靠性设计要求,研究基于专家系统的故障诊断与健康评估方法,构建了健康监控系统的功能结构和实现流程,实现综合前期、实时、长期统计信息的数据库和基于故障树的专家系统知识库,最后基于CPCI总线开发出一套适合于客机的飞控健康监控验证系统。 相似文献
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为了解决连续退火线硅钢带钢生产中的带材跑偏问题。简述了带材自动纠偏系统控制必须满足要求,详细分析纠偏控制系统整体方案。对影响纠偏控制因素,提出了解决方案。并根据现场生产实践要求,在液压回路方面,分析设计采用自动和手动相结合的液压传动方案,可满足自动纠偏和手动调试以及故障的处理。 相似文献
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飞行仿真系统为民机设计动态验证提供了重要的支持,本文以一般民用客机为研究背景,从民用飞机飞行仿真系统的模型分类、飞行仿真系统模型的通用建模规范、飞行仿真系统模型的组成及其互联关系等方面进行了研究。 相似文献
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A320系列飞机是AIRBUS公司研发的单通道电传操控民用客机,它是世界上第一种采用电传操纵及侧杆驾驶的民用客机。该飞机的电子设备舱存放大量与飞行相关的控制计算机,当飞机在飞行过程中各计算机会产生大量的热量,严重影响航空运行安全。本文深入研究电子舱通风的工作原理,并总结分析航线维护过程中电子舱通风系统故障产生原因与排故思路。 相似文献
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李福山 《科技成果管理与研究》2010,(2):58-60
针对目前油田抽油机井生产实际工作中存在的问题,结合抽油机井的工作状况,开发研制了抽油机井实时监测控制系统,该系统可实现人工智能控制,能够自动控制,自动适应负载的变化,实现无人看守;设计了GSM／GPRS方式的远程无线监控功能,实现数字化、网络化、集约化、可视化管理,实现遥控、防盗与故障报警等功能。经过几年来的试验与应用,取得了较好的效果,各项技术指标均达到了要求。 相似文献
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从理想环境下的需求工程出发,以需求的变更控制、可追踪性、编写能力和语言、属性等几个方面着重论述了民用客机需求的工程化过程和方法。提出了民用客机需求工程的一些广泛被使用的技术,探讨了可追踪性的建立和意义,并建议使用需求工程来高效低成本地生产飞机产品。 相似文献
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Chih-Chin Wen 《Journal of The Franklin Institute》2008,345(8):926-941
The design of an adaptive sliding mode control (SMC) scheme is proposed in this paper for stabilizing a class of dynamic systems with matched and mismatched perturbations. Two methods for designing a novel sliding surface function are introduced first. By utilizing a pseudocontrol input in the sliding surface function, one cannot only suppress the mismatched perturbations in the sliding mode, but also obtain the property of asymptotical stability. Then a sliding mode controller is designed to drive the controlled systems to the designated sliding surface in a finite time. Adaptive mechanism is also embedded in the controller as well as in the sliding surface function designed from the second method to overcome the perturbations, so that the informations of upper bound of perturbations are not required. An application of flight control and experimental results of controlling a servomotor are also given for demonstrating the applicability of the proposed control scheme. 相似文献
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针对大飞机无损检测智能化的需求,研发一种大飞机蒙皮结构健康检测真空吸附爬壁机器人.设计了一种基于PTR8000模块的用于爬壁机器人的无线通信系统.首先介绍了机器人的总体设计;然后介绍了无线系统的硬件原理框图和接口设计,建立了爬壁机器人无线通讯系统的硬件平台;设计了爬壁机器人的无线通讯软件;最后进行了收发通讯和性能指标的... 相似文献
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《Journal of The Franklin Institute》2021,358(18):9698-9720
To achieve the flight mode transfer of the tilt-rotor aircraft, this paper develops a smooth switching method for an weighted L2 robust asynchronously switched system. Considering the asynchronous phenomenon that exists in the switching control of the tilt-rotor aircraft, first, a sufficient condition for the existence of the sub-controller is derived, which guarantees the exponential stability and weighted L2 performance. Besides, the on-line system and the off-line system are separately employed to realize the continuity of the control input signals, which further improve the transient performance and smoothness of the asynchronously switched system. The simulations on the tilt-rotor aircraft verify the effectiveness and applicability of the proposed method. 相似文献
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Yishi Liu Xiwang Dong Zhang Ren Jonathan Cooper 《Journal of The Franklin Institute》2019,356(7):3849-3868
In this paper, a constrained control scheme based on model reference adaptive control is investigated for the longitudinal motion of a commercial aircraft with actuator faults and saturation nonlinearities. Actuator faults and constraints are both important factors adversely affecting the stability and performance of flight control systems. An adaptive adjustment law based on Lyapunov function is utilized to adjust the fault-tolerant control law. Both additive and multiplicative faults are considered in the designed controller to deal with the three types of actuator faults: locked in place, loss of effectiveness, and bias. Moreover, different techniques are implemented in the basic and fault-tolerant controller to anti-windup. Proofs for the stability of the two modified controllers which improve the performance of control system operating in the presence of actuator faults and saturations are proposed. Finally, a numerical example of the anti-windup fault-tolerant controller for a commercial aircraft is demonstrated. The stability and performance improvements can be accrued with the presented fault-tolerant control scheme. 相似文献
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Chien-Chun Kung 《Journal of The Franklin Institute》2008,345(8):851-876
In this paper, an analytic solution of nonlinear H∞ robust controller is first proposed and used in a complete six degree-of-freedom nonlinear equations of motion of flight vehicle system with mass and moment inertia uncertainties. A special Lyapunov function with mass and moment inertia uncertainties is considered to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). The HJPDI is solved analytically, resulting in a nonlinear H∞ robust controller with simple proportional feedback structure. Next, the control surface inverse algorithm (CSIA) is introduced to determine the angles of control surface deflection from the nonlinear H∞ control command. The ranges of prefilter and loss ratio that guarantee stability and robustness of nonlinear H∞ flight control system implemented by CSIA are derived. Real aerodynamic data, engine data and actuator system of F-16 aircraft are carried out in numerical simulations to verify the proposed scheme. The results show that the responses still keep good convergence for large initial perturbation and the robust stability with mass and moment inertia uncertainties in the permissible ranges of the prefilter and loss ratio for which this design guarantees stability give same conclusion. 相似文献
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Quadrotor vehicle control via sliding mode controller driven by sliding mode disturbance observer 总被引：1，自引：0，他引：1
Lénaïck Besnard Yuri B. Shtessel Brian Landrum 《Journal of The Franklin Institute》2012,349(2):658-684
Over the last decade, considerable interest has been shown from industry, government and academia to the design of Vertical Take-Off and Landing (VTOL) autonomous aerial vehicles. This paper uses the recently developed sliding mode control driven by sliding mode disturbance observer (SMC-SMDO) approach to design a robust flight controller for a small quadrotor vehicle. This technique allows for a continuous control robust to external disturbance and model uncertainties to be computed without the use of high control gain or extensive computational power. The robustness of the control to unknown external disturbances also leads to a reduction of the design cost as less pre-flight analyses are required. The multiple-loop, multiple time-scale SMC-SMDO flight controller is designed to provide robust position and attitude control of the vehicle while relying only on knowledge of the limits of the disturbances. Extensive simulations of a 6 DOF computer model demonstrate the robustness of the control when faced with external disturbances (including wind, collision and actuator failure) as well as model uncertainties. 相似文献
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对民用飞机飞控系统的半实物仿真过程中所采用的硬件接口系统的功能、架构、组成等进行了设计和研究,并提供了硬件采购清单,该方案可以为各种半实物仿真实验系统提供高效、灵活的接口管理方案。 相似文献
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The backstepping technique is one of the tools which provides control Lyapunov functions (CLFs) and, therefore, control laws for automatic systems. In this paper, the backstepping design for position and force nonlinear electrohydraulic servos is investigated. Three control laws ensuring the asymptotic stability of references tracking are obtained by constructing CLFs on the errors concerning the state variables and theirs desired values. The possibility of converting a position servo into a force servo, with only minimal hard modification, is proved. An approach based on partitioning the state system into two subsystems—a first one stable, and a second one taken as framework of control synthesis by backstepping technique—was developed and used. Using as reference point a flight controls hydromechanical servo, numerical simulations were reported from viewpoint of servo time constant performance. Certain conjectures, concerning the behaviour of systems mathematical models, in connection with mathematical methodologies of control synthesis operating on them, are finally stressed. 相似文献
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《Journal of The Franklin Institute》2022,359(12):6267-6285
In this paper, the prescribed performance trajectory tracking problem of quadrotor aircraft with six degrees of freedom is addressed. Firstly, for the sake of facilitating the construction of controller, the aircraft is decomposed into position loop and attitude loop through time scale decomposition method. A fixed-time sliding mode controller is proposed to guarantee the convergence time of the aircraft system regardless of initial states. After that, to enhance security of control system, the hyperbolic tangent performance function is designed as performance index function to maintain the error within a prescribed range. Then, the event-triggered strategy is adopted to attitude subsystem which can significantly save communication resources, and the stability of control system is analyzed by Lyapunov method. In addition, the Zeno phenomenon is avoided which can be proved by ensuring the two consecutive trigger events have a positive lower limit. Finally, the validity of the constructed controller is confirmed by simulation results. 相似文献
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Jafar Zarei Allahyar Montazeri Mohmmad Reza Jahed Motlagh Javad Poshtan 《Journal of The Franklin Institute》2007,344(5):577-594
In this paper two robust controllers for a multivariable vertical short take-off and landing (VSTOL) aircraft system are designed and compared. The aim of these controllers is to achieve robust stability margins and good performance in step response of the system. LQG/LTR method is a systematic design approach based on shaping and recovering open-loop singular values while mixed-sensitivity H∞ method is established by defining appropriate weighting functions to achieve good performance and robustness. Comparison of the two controllers show that LQG method requires rate feedback to increase damping of closed-loop system, while H∞ controller by only proper choose the weighting functions, meets the same performance for step response. Output robustness of both controllers is good but H∞ controller has poor input stability margin. The net controller order of H∞ is higher than the LQG/LTR method and the control effort of them is in the acceptable range. 相似文献