共查询到19条相似文献,搜索用时 156 毫秒
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在飞机显示器的水平导航区域上需要为飞行员实时显示最新的航线信息,航线中的每个航路点均有不同的转弯方式,目前国内正在研发的飞机采用旁切转弯和飞越转弯两种方式,若错过了预计的转弯起始点,则需要重新进行航线解算,这被定义为超调转弯,给出三类转弯航线的解算方法。 相似文献
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随着社会经济的发展,重庆作为西南重镇,民航事业取得了迅猛发展。同时,江北机场周边军航活动也越来越频繁。在军民航活动密度越来越大的情况下,为了保证飞行安全,在军航活动期间民航飞机往往要求严格沿航路、航线中心飞行以避让军事飞行。而空客飞机因其飞行特点,经常出现因转弯不当而偏离航路,引起军民航冲突的情况。下面就对此问题进行相关探讨。 相似文献
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通过分析水平面内的最快转弯和最小半径转弯,研究了现代战斗机的最优过失速机动和高速机动。利用最优控制理论,讨论和分析了最优倾侧角控制和推力控制规律。典型示例飞机的数值仿真计算结果表明,最优高速转弯轨迹是B、C和S等各段子弧的相应组合,它与发动机推力、飞行高度、端点马赫数、过载和空气动力约束等相关;提高发动机推力亦可减小最优转弯时间。 相似文献
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通过对比分析波音737-300和A321机型的前轮转弯控制原理,阐述机械-液压控制和电传控制两种前轮转弯方式的优缺点,为分析转弯机构出现的疑难故障提供了理论基础. 相似文献
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张学军 《海军航空工程学院学报》2006,21(2):234-236, 240
阐明了转弯飞行是直升机的基本机动科目,现有的运动学问题研究仅从性能的角度出发,分析转弯过程中的过载、转弯半径等,忽略了转弯过程中的迎角、侧滑角、姿态和角速度等运动参数的变化,因而不能合理地预测转弯过程中旋翼的真实能力、直升机的机动性能及飞行轨迹。文中着重介绍了一种直升机稳定转弯时的运动学分析方法,该方法建立了不同稳定转弯条件下,速度、迎角、侧滑角与过载系数、姿态、角速度之间的关系,定量分析了不同稳定转弯条件对直升机角速度和姿态的影响。 相似文献
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收敛转弯是目前国外普遍采用的试飞驾驶方法,通过与以往采用的试飞驾驶方法进行比较,说明收敛转弯方法的优越性,并阐述了收敛转弯的操纵要领,注意事项,安全措施及其适用范围。理论和实践证明,收敛转弯是一种较好的试飞驾驶方法,在试飞中有广泛的用途,值得推广。 相似文献
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基于MFCS直升机协调转弯模态设计 总被引:1,自引:0,他引:1
为了消除直升机的侧滑,在已设计完成的具有优良操纵特性的直升机显模型跟踪控制系统(MFCS)基础上,开发了协调转弯模态;按照直升机协调转弯基本要求,开发了基于 MFCS协调转弯模态控制律,给出了结构配置及系统参数设计方法。经仿真表明,所开发的直升机协调转弯模态具有优良的特性。 相似文献
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载人航天器显示仪表展望 总被引:3,自引:0,他引:3
根据90年代的先进技术展望载人航天器显示仪表的未来发展。在简单回顾现有航天器仪表之后,介绍90年代有代表性的先进的波音777飞机座舱仪表。接着讨论彩色液晶平板显示仪、大屏幕显示仪与玻璃座舱等90年代的先进技术,并提出由计算机统一管理的带自然语言输出的仪表,以发挥航天员听觉的作用和减轻航天员的视觉负担。 相似文献
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高均立 《西安航空技术高等专科学校学报》2011,29(3):55-57
本系统采用单片机AT89S52作为控制核心,设计并制作一个基于16×32点阵LED模块显示屏。该点阵可以实现扫描微亮和显示点亮两种工作模式,能够通过自制光笔检测在点阵处于扫描微亮状态时获取其行列坐标信息,并能通过数码管显示出来,同时能依据功能要求控制检测点处LED的亮灭,在屏幕上实现"点亮、划亮、反显、整屏擦除"等书写显示功能,通过按键可以实现不同功能之间的切换。 相似文献
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A. V. Efremov M. S. Tyaglik A. S. Tyaglik V. V. Aleksandrov 《Russian Aeronautics (Iz VUZ)》2016,59(2):183-189
In this paper, we propose to compensate the time delay in the vehicle response by a display that demonstrates the vector of predictive velocity projected on the surface located on a preliminary defined distance from the operator’s eyes. The effectiveness of the approach is demonstrated for the tasks of lunar rover docking and control. 相似文献
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平视显示器的机上安装研究 总被引:1,自引:0,他引:1
由CRT中心点发出与平显光轴线平行并通过驾驶员眼点的光线是平显的零位瞄准线。平显的炮口十字线不宜称为零位瞄准线。平显的零位瞄准线被要求相对于飞机机身水平线下沉一定角度安装。平显的构造-安装方程表述了平显构造参量与安装参量间的关系。当平显在飞机上的安装要求确定后,平显的构造被方程所限定;当平显的构造确定后,平显在飞机上的安装被方程所限定。》 相似文献
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《中国航空学报》2023,36(8):313-330
Multi-Optical Theodolite Tracking systems (MOTTs) can stealthily extract the target’s status information from bearings only through non-contact measurement. The constrained MOTTs are partially compatible, yet many existing research works and results are based on the known model, ignoring its discrimination with the target maneuvering behavior pattern. To compensate for these mismatches, this paper develops a Measurement-driven Gauss-Hermite Particle Filter (MGHPF), which elegantly fuses the spatiotemporal constraints and its soft form to perform MOTT missions. Specifically, the target dynamic model and tracking algorithm are based on the target behavior pattern with the adaptive turn rate, fully exploiting the spatial epipolar geometry characteristics for each intersection measurement by a minimax strategy. Then, the center of the feasible area is approximated via the analytic coordinate transformation, and the latent samples are updated via the deterministic Gauss-Hermite integral method with the target’s predictive turn rate. Simultaneously, the effects of truncation correction and compensation feedback from the current measurement and historical estimation data are adaptively incorporated into the PF’s importance distribution to cover the mixture likelihood. Besides, an effective causality-invariant updating rule is provided to estimate the parameters of these soft spatiotemporal constrained MOTTs with convergence guarantees. Simulated and measured results show good agreement; compared with the state-of-the-art Multi-Model Rao-Blackwell Particle Filter (MMRBPF), the proposed MGHPF improves the filtering accuracy by 7.4%-34.7% and significantly reduces the computational load. 相似文献
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Dynamic simulation of aerial towed decoy system based on tension recurrence algorithm 总被引:1,自引:0,他引:1
《中国航空学报》2016,(6):1484-1495
Dynamic model of aerial towed decoy system is established and simulations are performed to research the dynamic characteristics of the system. Firstly, Kinetic equations based on spinor are built, where the cable is discretized into a number of rigid segments while the decoy is modeled as a rigid body hinged on the cable. Then tension recurrence algorithm is developed to improve computational efficiency, which makes it possible to predict the dynamic response of aerial towed decoy system rapidly and accurately. Subsequently, the efficiency and validity of this algorithm are verified by comparison with Kane's function and further validated by wind tunnel tests.Simulation results indicate that the distance between the towing point and the decoy's center of gravity is suggested to be 5%–20% of the length of decoy body to ensure the stability of system.In up-risen maneuver process, the value of angular velocity is recommended to be less than0.10 rad/s to protect the cable from the aircraft exhaust jet. During the turning movement of aircraft, the cable's extent of stretching outwards is proportional to the aircraft's angular velocity.Meanwhile, the decoy, aircraft and missile form a triangle, which promotes the decoy's performance. 相似文献
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In this paper, we introduce a concept of coordinated turn that means the application of the lifting force being perpendicular to the UAV velocity vector and parallel to the surface on which the exact point target is located. Analytical solutions of the corresponding differential equations of the coordinated turn are derived. 相似文献