共查询到20条相似文献,搜索用时 31 毫秒
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跑道作为机场的关键设施,是飞机着陆和减速滑行的区域,通过视觉定位方法计算飞机相对跑道的位置,可以作为辅助飞机快速平稳着陆的一种思路。视觉传感器所需成本较低,对安装环境要求不高,本文旨在设计一个仅靠视觉传感器对飞机进行定位的辅助着陆系统,运用目标检测和视觉定位两个模型,计算飞机相对跑道的位置。首先搭建出等比例微缩的机场跑道模型,视觉传感器产生运动模拟飞机飞行路径,目标检测模型通过机载视觉传感器获取的图像识别出跑道区域,随后视觉定位模型提取图像中跑道区域特征点,计算飞机相对跑道的位置。分别对目标检测和视觉定位两部分的实现原理及难点进行阐述,尝试将目标检测和视觉定位结合起来实现飞机降落时的定位,描述辅助着陆系统设计的整体思路。 相似文献
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All weather tactical aircraft recovery and high sortie generation rates from forward, possibly battle damaged landing areas will reqire autonomous landing guidance systems which are independent of ground-based cooperative aids. A recently completed study has examined the operational requirements and assessed current and near term technology for an answer to this need. The Landing Systems Requirements/Synthesis Study has defined the Pilot/vehicle Interface and imaging sensor suite required, based on the concept of augmenting pilot forward vision with sensor imagery and guidance symbology on a HUD during low visibility landings. Image processing technology was also assessed for potential enhancement of the information presented to the pilot. This paper summarizes the final report of the Study, which is in publication. 相似文献
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The small aircraft transportation system (SATS) concept envisions doorstop to destination transportation in a safe and timely manner. Data communications are a key component in achieving the aviation-related operational performance improvements that are sought. However, data communication doesn't start when you get into the aircraft; it starts back at the location where the flight is planned. In fact, data communications support the pilot in all phases of the flight: flight planning, pre-flight, departure, en route, transition, approach, landing, and rollout as well as for a missed approach. The Internet is being used to perform flight planning activities, and the mobile communications available today support Internet access en route to the departure airfield. On-board the aircraft, data communications provide surveillance and air traffic control (ATC) support to the pilot. The location of other aircraft is available to the pilot and ATC system through automatic dependent surveillance-broadcast (ADS-B) and traffic information service-broadcast (TIS-B) applications that transmit the location of other aircraft in the vicinity. Other aircraft locations are used to forecast potential conflicts and, thus, enhance flight safety. As the aircraft nears a SATS-equipped airfield, the pilot uses data link messages to request a landing sequence. The airport management module (AMM) provides a landing sequence assignment to the aircraft. As the pilot maneuvers the aircraft for a landing, he/she is using data-linked surveillance data to determine the location of other aircraft and maintain a safe separation distance between aircraft even in a low visibility environment. 相似文献
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Augmented flight dynamics model for pilot workload evaluation in tilt-rotor aircraft optimal landing procedure after one engine failure 总被引:1,自引:0,他引:1
An augmented flight dynamics model is developed to extend the existing flight dynamics model of tilt-rotor aircraft for optimal landing procedure analysis in the event of one engine failure.Compared with the existing flight dynamics model, the augmented model involves with more pilot control information in cockpit and is validated against the flight test data. Based on the augmented flight dynamics model, the optimal landing procedure of XV-15 tilt-rotor aircraft after one engine failure is formulated into a Nonlinear Optimal Control Problem(NOCP), solved by collocation and numerical optimization method. The time histories of pilot controls in cockpit during the optimal landing procedure are obtained for the evaluation of pilot workload. An evaluation method which can synthetically quantify the pilot workload in time and frequency domains is proposed with metrics of aggressiveness and cutoff frequencies of pilot controls. The scale of the pilot workload is compared with those of the shipboard landing procedures, bob-up/bob-down and dash/quickstop maneuvers of UH-60 helicopter. The results show that the aggressiveness of pilot collective and longitudinal controls for the tilt-rotor aircraft optimal landing procedure after one engine failure are higher than those for UH-60 helicopter shipboard landing procedures up to the condition of sea state 4, while the pilot cutoff frequency of collective control is lower than that of the bob-up/bob-down maneuver but the pilot cutoff frequency of longitudinal control is higher than that of the dash/quick-stop maneuver. The evaluated pilot workload level is between Cooper–Harper HQR Level 2 and Level 3. 相似文献
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The cockpit design in the new JAS39 Gripen combat aircraft is based on an electronic computer-controlled display system. This display system EP 17, has four areas of presentation: one Head-Up Display (HUD) and three Multi-Function Displays (MFD). The HUD is equipped with a diffraction optics combiner which gives the display high visibility within a large field-of-view, and with minimal visual interference to the outside world. The Multi-Function Displays in the front panel are a Flight Data Display showing flight and system data, a Horizontal Situation Display that superimposes tactical information on a digital map and a Multi-Sensor Display with, primarily, radar information. This system is supported by a Display Processor comprising computers, graphic generators, sensor information processors and a digital map memory. It also includes an integrated video recording system for recording analog and digital sensor video, bus data and voice 相似文献
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针对雾霾天气对舰载机目视着舰安全性的影响难以量化的问题,利用激光雷达在近海的能见度观测数据,反演海上雾霾天气下飞行员目视着舰的斜程能见度的状况,提出 1种基于能见度指标的目视着舰风险评估方法,将舰载机着舰过程中飞行员频繁的目测压力,转变为舰上数据测量、风险评估和应对措施等程序化工作,将定性的安全分析转变为定量的风险评估和安全指导,谋求在现有着舰控制模式下有效降低飞行员着舰压力,提升指挥引导效率,为低能见度下舰载机目视着舰训练提供理论依据和实践指导。 相似文献
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A simplified practical approach to determining the effects of weather on the transmission of radiation at visible, infrared (IR), and millimetre (mm) wavelengths, with particular reference to the aircraft landing problem, is outlined. Passive landing systems are studied. Landing categories related to visibility are defined. An extinction coefficient used to relate the effect of the atmosphere on the radiation detected by the human eye (or an imaging sensor onboard the aircraft) to the landing category and the calculation of this coefficient are discussed. The approach makes use of data from openly available literature. Results have been found useful in indicating the effects of adverse weather on imaging sensor performance for an enhanced vision aircraft-mounted landing system. As an example of the technique, the method of determining the extinction coefficients in fog for infrared radiation is outlined 相似文献
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武光梁远东李畅 《民用飞机设计与研究》2014,(3):44-47
由于平视显示器(HUD)、视景增强系统(EVS)以及合成视景系统(SVS)优秀的情景显示能力,HUD与EVS、SVS结合使用将显著提高飞行机组情景识别以及态势感知能力。同时,HUD与自动着陆系统结合使用可降低着陆和起飞时的最低天气标准。随着机组情景识别能力的提高,必须提出高效的试飞方法来验证情景识别系统的适航符合性,在分析EVS、SVS与HUD结合使用的基础上,提出综合的优化的民用飞机机组情景识别系统试飞方法以及基于任务的符合性判据。 相似文献
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Vertical guidance for an instrument approach to landing during conditions of reduced visibility is a crucial element with respect to safety of flight. It is noteworthy that this vertical component-to be most useful and safe-must desirably provide the pilot with no more than several feet of uncertainty. Unfortunately, with GPS the vertical portion of the position information supplied the pilot by GPS signals is the least precise because of geometries involved. Augmentation for enhancement of accuracy is quite important and the assertion is that it is necessary for totally safe vertical guidance. Evidence from approximately 60 years of experience with electronic landing systems serving the public is that there has been no aircraft accident due to a defective vertical guidance signal. Visibilities as low as 600 feet horizontally can exist at certain airports and landings can still be accomplished. These landings, while not common, are being accomplished flawlessly by contemporary aircraft and equipment. Many aspects of the contemporary UHF glide slope have been studied during its half-century of use. This paper reports on advances, some of them quite recent, that make it realistic to claim that a glide slope can be sited for Category I operation at any runway that meets the physical requirements for this type of operation. For the UHF glide slope, siting imperfections are accommodated by using one of five available types of contemporary glide slope systems or derivatives thereof. This paper reviews how accommodations are achieved in practical cases. Results from earlier tests are identified which show hybridizing of UHF glide slopes and GPS can be used to provide good approach guidance to aircraft making fully automatic approaches to touchdown 相似文献
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以刚体系动力学理论为基础,建立飞机、起落架六自由度全量非线性方程,根据有侧风时着陆过程中驾驶员的操纵特点,提出比较符合实际情况的操纵逻辑,以及用3个单轴操纵的驾驶员模型,通过采用分时采集、分时处理飞行状态信息和分时操纵的方式,将它们有机地综合成~个同时做三轴操纵时的驾驶员模型。最后,对所建立的人-机闭环系统模型编制了相应的仿真软件,并对某验证机进行了着陆品质分析,其结果与试飞情况比较吻合。 相似文献
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朱志胜 《民用飞机设计与研究》2014,(2):88-92
飞机着陆灯与机场助航灯光系统为民用飞机夜航起飞、着陆提供照明,两者都十分重要。民航法规CCAR121部要求飞机必须装有至少两个着陆灯,而AC-97-FS-2011-01则要求民用机场必须配备助航灯光系统。分析了着陆灯与助航灯光两者在夜航着陆过程中的作用,并阐述两者的相互关系。 相似文献
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舰载飞机着舰过程的参数适配特性对于着舰安全性有着重要的影响.基于着舰安全准则,研究了无风和平静海况下驾驶员视野、着舰下沉速率和拦阻距离对舰载飞机参数适配特性的影响,给出了一定初始状态下舰载飞机的着舰质量和着舰速度的适配包线,分析了影响最大着舰质量的因素并对适配包线的扩展方法进行了研究.结果表明,适配包线由最小着舰速度和最大着舰速度封闭而成.其中,最小着舰速度主要由驾驶员视野准则决定;对于最大着舰速度,当着舰质量较小时主要由着舰下沉速率准则决定,当着舰质量较大时主要由拦阻距离准则决定;最大着舰质量由拦阻系统性能和驾驶员视野共同决定.通过增大拦阻力、改善飞机的低速气动特性可以有效扩展适配包线范围,增加许用的最大着舰质量,但下滑角大小的改变对其影响不大. 相似文献
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In this paper, the accuracy, integrity and continuity of function requirements for automatic landing systems using satellite navigation systems are discussed. Such a landing system is the integrated navigation and landing system (INLS) developed by Deutsche Aerospace (DASA/Ulm, Germany). The system concepts of the INLS are presented. It is shown how an INLS, based on system integration of a satellite navigation system (e.g., GPS) in realtime differential mode with an inertial measurement unit (IMU) in the accuracy class of an attitude and heading reference system (AHRS), can meet the requirements: the results given are mainly devoted to the accuracy issues. Using Kalman filter techniques, an in-flight calibration of the IMU is performed. The advantage of system integration, especially in dynamic flight conditions and during phases of flight with satellite masking, is explained. The accuracy, integrity and continuity of function of the INLS were proven by means of flight tests in a commuter aircraft using a laser tracker as a reference. These flight tests have shown that the short-term accuracy (<60 seconds) of the AHRS used within the INLS has been improved from low cost sensor quality to the accuracy of a high quality laser inertial navigation system (LNIS). With the presented INLS, a landing at any airfield, not equipped with conventional Instrument Landing System (ILS) or Microwave Landing System (MLS), is possible by using a very cost effective system. The INLS is a high accuracy navigation and landing system designed to be used instead of conventional landing systems at small airfields and to fill operational gaps of conventional navigation and landing systems in cruise and approach on large airports 相似文献