滚转机动飞行对纵横航向操纵要求

本文讨论了高机动性飞机滚转机动飞行对纵横航向操纵效能的要求,并以J-7飞机为算例进行了验证.计算结果表明,高机动性飞机作滚转机动飞行时,除了一般考虑稳定性要求外,还应考察本文提出的纵横航向操纵力矩要求及滚转机动飞行对航向稳定性的要求.     

基于线性规划的多操纵面重构控制研究

为实现多操纵面飞机的重构控制,提高飞机飞行的安全性能,提出了一种基于线性规划的多操纵面重构控制策略.针对操纵面卡死、松浮、损伤等典型故障情况,推导了相应的重构分配器,通过基于线性规划的直接分配方法来实现在操纵面故障下的重构控制.仿真结果表明,该控制策略能有效处理典型操纵面故障,发生故障时仍能快速跟踪控制指令,保证较好的...     

飞行传感器的故障检测与识别

 飞行传感器是飞行控制和导航系统中的薄弱环节,它们的故障率一般是比较高的。为了提高系统的可靠性,对传感器的故障应能实时地检测和识别,并重构传感器所测量的信号(修正)。为此,在系统中常采用传感器的硬件余度和解析余度。本文介绍了飞行传感器硬件余度和解析余度的原理以及几种实用的余度方案,对解析余度中的统计决策原理和故障检测的鲁棒性问题也作了简单介绍。     

大型客机电传飞控系统余度配置研究

大型客机电传飞控系统采用余度配置是提高飞机安全性与任务可靠性的重要方法之一。大型客机通过余度配置降低系统部件发生故障后对飞行性能和整个系统飞机安全性的影响,从而提高了飞控系统的安全可靠性。本文通过对波音和空客飞机电传飞控系统余度配置等主要设计环节的对比分析,阐述了大型客机电传飞控系统在余度设计与配置方面的关键技术点和方法,为大型客机电传飞控系统的余度设计提供技术支持。     

飞机操纵面故障研究及其补偿重构

进行了自修复飞行控制系统各操纵面的单独／组合故障分类，研究了不同种类，不同组合，不同程度的故障下的飞机特性，分析了各种故障的影响；针对不同的故障模式分别进行了控制律重构设计并对飞机重构后的稳定性及操纵品质进行了仿真研究。结果表明，在非极端故障下，现有操纵面权限范围内，可以保证稳定飞行并具有可接受的操纵品质。     

民用飞机偏航控制系统设计策略研究

偏航控制系统是保证飞机安全飞行的关键系统,其性能优劣不仅直接影响飞机的操纵品质和性能,失效状态下还会危及飞机的飞行安全,方向舵作为偏航控制主要操纵面,其权限管理、余度配置以及稳定能力的设计都需要高的可靠性和安全性;如果使用闭环控制回路,设计措施来避免系统与飞机弹性模态之间的不良耦合是必须的。     

机载大屏幕显示器的余度设计及余度管理

余度技术是系统或设备获得高可靠性的设计方法之一。为了显著提高系统的任务可靠性,当系统发生故障时,余度系统能够自动完成系统重构,继续正常工作,从而提高了飞机的任务可靠性和安全性。本文从余度设计的概念出发,通过对余度等级、结构、数目及层次等几个方面对余度设计进行分析,结合某大屏幕显示器余度设计,给出了余度设计的基本方法,提出了一种余度管理方案,该设计思想也可用于其它机载设备中。     

差动平尾和方向舵辅助滚转的横航向数学模型研究

为了解决高速飞行时副翼效率不足的问题 ,现代战斗机在横航向操纵中广泛采用了差动平尾和方向舵辅助滚转 ,这样适用于常规操纵飞机的横航向运动方程已不能应用于此类飞机。本文重新推导了针对此类飞机的横航向运动方程和传递函数 ,并对模型进行了验证。可以为飞行品质分析、飞行模拟和空战仿真提供可用的数学模型。     

飞控系统余度信号奇异故障处理策略研究

飞机机翼、操纵面的对称性设计,决定了飞控系统传感器、计算机和舵机等部件在飞机上分布式对称安装并选择偶数n 余度的体系架构。余度部件生产关系的平衡分工,不同厂家设计、制造的差异,不可避免地出现“两派对立”的偶数分离和“互不认可”的奇异故障。本文提出了中位数表决、变化量记忆、余度重构等基础理论,给出了极端信号大概率故障判据,研究论证了这些基础理论和判据的科学原理。为四余度信号“2∶2 不确定故障、1∶1∶1∶1 多故障”、三余度信号1∶1∶1 多故障和二余度信号1∶1 故障,提供了有效的表决监控方案。     

70°迎角定常飞行数值仿真

建立了带俯仰－偏航－滚转推力矢量高性能战斗机的非线性数学模型,利用该模型和Ｆ－１６飞机的气动数据,针对典型的大迎角定常飞行过失速机动的特点,结合逆方法和试凑法获得了各个操纵面的操纵规律,对其进行了数值仿真。结果表明,带俯仰－偏航－滚转推力矢量控制下,该飞机在过载为１,７０°迎角定常飞行时具有较好的操纵性和稳定性。     

Reconfigurable Flight Control Design for Combat Flying Wing with Multiple Control Surfaces

With control using redundant multiple control surface arrangement and large-deflection drag rudders,a combat flying wing has a higher probability for control surface failures.Therefore,its flight control system must be able to reconfigure after such failures.Considering three types of typical control surface failures(lock-in-place(LIP),loss-of-effectiveness(LOE) and float),flight control reconfiguration characteristic and capability of such aircraft types are analyzed.Because of the control surface redundancy,the aircraft using the dynamic inversion flight control law already has a control allocation block.In this paper,its flight control configuration during the above failures is achieved by modifying this block.It is shown that such a reconfigurable flight control design is valid,through numerical simulations of flight attitude control task.Results indicate that,in the circumstances of control surface failures with limited degree and the degradation of the flying quality level,a combat flying wing adopting this flight control reconfiguration approach based on control allocation could guarantee its flight safety and perform some flight combat missions.     

A two-stage approach for managing actuators redundancy and its application to fault tolerant flight control

In safety-critical systems such as transportation aircraft, redundancy of actuators is introduced to improve fault tolerance. How to make the best use of remaining actuators to allow the system to continue achieving a desired operation in the presence of some actuators failures is the main subject of this paper. Considering that many dynamical systems, including flight dynamics of a transportation aircraft, can be expressed as an input affine nonlinear system, a new state representation is adopted here where the output dynamics are related with virtual inputs associated with the intended operation. This representation, as well as the distribution matrix associated with the effectiveness of the remaining operational actuators, allows us to define different levels of fault tolerant governability with respect to actuators’ failures. Then, a two-stage control approach is developed, leading first to the inversion of the output dynamics to get nominal values for the virtual inputs and then to the solution of a linear quadratic(LQ) problem to compute the solicitation of each operational actuator. The proposed approach is applied to the control of a transportation aircraft which performs a stabilized roll maneuver while a partial failure appears. Two fault scenarios are considered and the resulting performance of the proposed approach is displayed and discussed.     

Reconstructed Flight Control Sensor Signals Via Luenberger Observers

The feasibility of providing flight control systems with software-managed redundancy is investigated. It is shown that sufficient information can be extracted from aircraft attitude sensors to allow analytic reconstruction of the stability augmentation system (SAS) sensor signals in the event of SAS sensor failures. The sensor signal reconstruction is performed in a deterministic setting by using a Luenberger observer. A simple and efficient design procedure is presented based on Gopinath's [1] work. As an illustrative example, the proposed sensor signal reconstruction technique is exercised on the L-1011 aircraft lateral axis rigid body simulation. It is shown that with an accurate airframe model perfect reconstruction is feasible. In addition, it is also shown via simulation results that with imperfect knowledge of the airframe model (based on standard wind tunnel data), the proposed reconstruction is accurate enough to have a negligible impact on the overall aircraft performance.     

商用涡扇发动机推力控制故障处置功能解析

针对运输类飞机对动力装置必须确认任何单一失效或故障及可能的失效组合都不会危及飞机安全飞行的适航要求,经工程研究和飞机运营经验证明,原有的通过安全性分析以及申请豁免来表明设计符合性的验证方法存在不足,为了保障飞机飞行的安全性,可增加推力控制故障处置(TCMA)系统。以B787飞机配装的GEnx发动机TCMA系统为研究对象,采用系统工程的方法研究和分析了该系统的安全性需求来源、符合性验证方法及其演进、TCM事件危害、TCMA系统架构和系统功能,其中包括事件侦测、处置逻辑、激活功能监控与内部自检BIT等功能。分析结果表明:TCMA系统是1个集成的智能控制系统,在TCM事件发生后无需飞机机组人员干预,能够自动处置并保障飞机的飞行安全。     

关于桶滚动态特点的分析

桶滚是近代空战中重要的战术机动动作之一,飞行员能否熟练掌握桶滚的操纵方法,是取得空战胜利和保障飞行安全的基础。针对飞行训练中,桶滚操纵动作不易准确掌握,后段易出现偏差等特点。从桶滚的运动方程入手,根据其战术意义及飞机机动性能特点,分析与研究桶滚的动态特点及其影响因素,总结出桶滚的运动特点及操作规律。最终,为飞行员正确掌握桶滚的操纵方法,提高飞行员对飞机空中状态变化的掌控和识别能力,提升技战术水平,有效地保障飞行安全提供可靠的理论依据。     

基于多模型的飞控系统自适应重构技术研究

针对飞控系统执行器故障引起参数大范围跳变的问题,提出了一种基于多模型的自适应重构控制方法。建立了执行器故障参数模型,根据故障的特征模型设计一系列并行的辨识模型,采用固定模型与自适应模型相结合的方式,依据转换标准选择与当前飞机状态最匹配的辨识模型所对应的控制器。通过对某型飞机侧向控制系统进行仿真,表明在执行器严重受损的情况下,飞机仍能保持良好的性能。     

MD-11 automatic flight system

The overall architecture and redundancy of the highly integrated MD-11 automatic flight system for commercial aircraft are summarized, and the application of the flight control computer capabilities to each of the system functions is detailed. The automatic flight system interface with other primary systems and subsystems is described     

Conceptual design and flight test of two wingtip-docked multi-body aircraft

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.     

飞机的模型参考容错控制

 本文针对飞机内部元件或控制元件的故障,用检测滤波器理论设计了相应的故障检测器和故障参数估计器,并用Lyapunov稳定性理论设计了模型参考自适应容错控制律,从而保证了在内部故障情况下飞行控制系统的稳定性。