飞行仪表相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
121	一种航空驾驶仪表实时仿真模拟系统	CN201410100469.2	2014-03-18	CN103886783B	2016-04-27	张毅; 吴伟
一种航空驾驶仪表实时仿真模拟系统，利用飞行仪表模拟驱动控制系统驱动姿态仪、转弯侧滑仪和航向指示器，分别指示航空器飞行的俯仰角度、倾斜角度、转弯方向、转弯快慢、侧滑方向、侧滑程度、飞行的方向和飞行方向变化的角度；利用全静压模拟驱动控制系统驱动空速表、高度表和升降速度表，分别指示航空器的飞行速度、飞行高度和上升或下降的垂直速度；利用发动机指示仪表模拟驱动控制系统驱动发动机转速表、油量表、滑油温度表、滑油压力表和燃油压力表，分别指示发动机转速、发动机油量、发动机滑油温度、发动机滑油压力和发动机燃油压力；该系统能够实时仿真模拟航空驾驶仪表的工作参数，同时性能稳定可靠、操作简单、使用维护方便，满足航空教学实训要求。
122	一种全空域姿态反馈系统	CN201810906552.7	2018-08-10	CN108992934A	2018-12-14	刘丰; 厉翔龙; 杨晶; 陆元桃
本申请实施例提供了一种全空域姿态反馈系统。所述全空域姿态反馈系统包括：显示器，所述显示器固定设置在所述遥控器本体上，用于显示飞行仪表盘模拟界面；遥控器本体，所述遥控器本体上设置有用于接收用户遥控指令的遥控外设；震动马达，所述震动马达收容在所述遥控器本体内，用于形成所述遥控器主体的震动；声音播放设备，所述声音播放设备设置在所述遥控器本体上，用于输出音频信号；控制电路，所述控制电路收容在所述遥控器本体内，分别与所述显示器、震动马达、灯组以及声音播放设备连接；所述控制电路用于根据航模飞行器的运行状态，相应的控制所述显示器、震动马达以及声音播放设备，向用户反馈对应的姿态信息。
123	布帘式飞机暗舱飞行罩	CN200620113209.X	2006-04-28	CN2898990Y	2007-05-09	郑香根; 李桂芳; 蔡娟
本实用新型涉及一种用于飞机飞行仪表训练时使用的布帘式飞机暗舱飞行罩。导轨骨架与座舱前风挡骨架的弧形相对应，其上开闭合型槽口，连接件的一端卡入骨架的槽口中；连接件的下端挂接布帘，锁座和连接座分别焊接在导轨骨架的两端并与飞机座舱前风挡弧形框固定。本实用新型能有效地阻断飞机前风挡透明区域的舱外环境视线；在起飞、着陆时进行收合而不影响飞行员正前方视野；便于快速装卸；应急弹射离机时，与穿盖弹射相配备，且不需任何附加动作；同时也不会对飞行员产生额外的弹射过载而造成损伤。
124	一种航空机载三维合成视景模组	CN201821254366.1	2018-08-03	CN208589056U	2019-03-08	邹健; 殷军; 李磊
一种航空机载三维合成视景模组，包括3U显控机箱，以及CPCI 3U图形处理板、LVDS图形扩展板、429数据通信板、电源板和母板。CPCI 3U图形处理板卡包括采用板载设计的高性能低功耗处理器、内存、硬盘；429数据通信板包括数字处理器、可编程逻辑器件和ARINC429驱动芯片；LVDS扩展板包括电源模块、LVDS输入接口、4×LVDS信号扩展模块、4×LVDS信号增强模块以及十路LVDS输出接口；电源板包括电源隔离模块、电源转换模块；母板包括芯片组和两个PCIe总线连接器。融合处理生成二维矢量或三维合成视景地图，接收惯性导航部件的总线数据，实时向显示控制分系统和飞行仪表系统输出航图信息。
125	Apparatus and methods for providing a flight display in an aircraft	US10350124	2003-01-24	US07268702B2	2007-09-11	Bassam H. Chamas; Joseph S. Nalbach; Ryuichi Yokota
Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.
126	虚拟驾驶飞行系统	CN201620651702.0	2016-06-27	CN206162928U	2017-05-10	鲁传龙; 梁琪; 张鑫
本实用新型涉及一种虚拟驾驶飞行系统，设有底座，所述底座上设有电动六自由度运动平台，所述电动六自由度运动平台上装有仿真飞机外壳，所述仿真飞机外壳内设有飞行座舱平台，所述飞行座舱平台前部装有飞行仪表装置，所述飞行座舱平台旁边设有油门杆、摇杆、脚跺，所述仿真飞机外壳前部装有多块液晶显示屏，所述多块液晶显示屏通过通讯采集卡与主电路板控制连接，所述主电路板采用1G显存工业驱动器主板。本实用新型适可以模拟飞行器上下、左右、前后、俯仰、偏航、滚转六个方向的位置、速度、加速度、角度、角速度、角加速度等位姿，精度高、响应快，动感效果好，同时能提供额外的真实的交互式运动感受。
127	APPARATUS AND METHODS FOR PROVIDING A FLIGHT DISPLAY IN AN AIRCRAFT	PCT/US2003/001947	2003-01-24	WO2003062754A1	2003-07-31	CHAMAS, Bassam, H.; NALBACH, Joseph, S.; YOKOTA, Ryuichi
Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.
128	Apparatus and methods for providing a flight display in an aircraft	US10350124	2003-01-24	US20030179109A1	2003-09-25	Bassam H. Chamas; Joseph S. Nalbach; Ryuichi Yokota
Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.
129	Universal aircraft panel with a dynamically symmetrical series of displays for the directional and rate flight instruments	US09428452	1999-10-28	US06255964B1	2001-07-03	Gordon H. Steele, Jr.
An integrated and dynamic symmetrical display of flight instruments for universal use in aircraft, wherein key instruments indicating with respect to aircraft direction are specifically arrayed with respect to key instruments indicating aircraft rate, wherein flight under instrument flight rules may be more easily learned, undertaken, and practiced with greater safety and ease of pilot workload, as compared with asymmetrical and random conventional flight instrument displays. Specifically, directional instruments are positioned in an aligned row above similarly arranged aircraft rate instruments for quick, reliable pilot scan and information utilization.
130	Apparatus for displaying detected wires to an aircraft flight crew	US09895042	2001-06-29	US20020033808A1	2002-03-21	Richard P. Krulis
The pilot or crew of an aircraft is alerted to the danger presented by wires in the vicinity of the aircraft by a flight instrument which includes a plurality of wire detected display elements, advantageously arranged as bars on the face of the flight instrument, and which display elements are color coded according to the level of danger presented to the aircraft by the detected wires.
131	HVAC DEVICE WITH FOOTWELL OUTLET	US13474864	2012-05-18	US20120291986A1	2012-11-22	Gerald Richter
A heating, ventilating, and air conditioning device includes a footwell outlet, where the footwell outlet is positioned such that the accompanying air channel can preferably run at the front wall in direction of the tunnel. A design of the HVAC device is suitable for compact dashboard structures. In particular, the HVAC device enables the use of a flying dashboard architecture.
132	Apparatus for displaying detected wires to an aircraft flight crew	US09895042	2001-06-29	US06771257B2	2004-08-03	Richard P. Krulis
The pilot or crew of an aircraft is alerted to the danger presented by wires in the vicinity of the aircraft by a flight instrument which includes a plurality of wire detected display elements, advantageously arranged as bars on the face of the flight instrument, and which display elements are color coded according to the level of danger presented to the aircraft by the detected wires.
133	Altitude tape for aircraft displays	US851585	1992-03-16	US5250947A	1993-10-05	James K. Worden; John C. Todd; Gerald B. Jones, Jr.
A moving altitude tape for a flight instrument display adapted to provide intuitive visual cues for determining deviation from a desired altitude. A window incorporates a digital altitude readout and a pointer index which is aligned with calibration marks on the altitude tape. In use the tape exhibits a motion in accordance with deviations in altitude of the aircraft and displays a vernier indication of such deviations with respect to the reference index. The tape further includes indicia associated with the reference index for defining predetermined increments of altitude deviation in accordance with commonly commanded altitudes, and a further pointer indicative of actual altitude deviation from a preset altitude.
134	電性絕緣膜以及形成彼之方法 ELECTRICALLY INSULATING FILM AND METHOD THEREFOR	TW097105566	2008-02-18	TW200846452A	2008-12-01	薩波那布萊克柏恩 BLACKBURN, SAPNA; 史考特費雪 FISHER, SCOTT MICHAEL; 昆恩宏拉達羅 HONGLADAROM, KWAN; 羅勃荷森 HOSSAN, ROBERT
一種不含鹵素電性絕緣膜係從一種包括特定量之聚(芳醚)、烯基芳族化合物和共軛二烯所成的經氫化嵌段共聚物、及磷酸三芳酯的組成物所製備。該電性絕緣膜可藉由擠壓及/或壓延方法而製備。該電性絕緣膜之用途包括(例如)電源外殼之遮蔽應用、印刷電路板絕緣、飛機飛行儀表板和顯示器之背光、辦公設備絕緣、電腦架間隔及電視和監視器絕緣。
135	Flugsimulator und Verfahren zur Simulation von Flugzuständen	EP97109001	1997-06-04	EP0814449A1	1997-12-29	SCHULZE STEFAN
Der Flugsimulator besteht aus einer Kabine, in der ein Flugzeugcockpit mit allen zur Steuerung eines Flugzeuges erforderlichen Instrumenten und Bedienungsorganen eingebaut ist und aus einem Computer zur Simulation einer Vielzahl von Flugzeugzuständen, die von den Instrumenten angezeigt werden, wobei der Flugsimulator von einer Vielzahl von Lautsprechern umgeben ist, die mit einem Tongenerator verbunden sind, der vom Computer ansteuerbar ist, so daß die Lautstärke eines jeden Lautsprechers einzeln einstellbar ist.
136	PROCÉDÉ DE DIAGNOSTIC IN SITU D'UN INSTRUMENT DE BORD AVIONIQUE ET INSTRUMENT DE BORD PERMETTANT DE METTRE EN ŒUVRE LE PROCÉDÉ SELON L'INVENTION	PCT/EP2008/062856	2008-09-25	WO2009043800A2	2009-04-09	PAPINEAU, Jérôme
La présente invention concerne un procédé de diagnostic d'un instrument de bord d'un aéronef piloté par un pilote et éventuellement un copilote, l'instrument de bord recevant des signaux secondaires d'au moins un capteur. Selon l'invention, le procédé de diagnostic comprend les étapes suivantes : déclencher (41 ) un enregistrement des signaux secondaires sur commande du pilote ou du copilote lorsqu'il constate une défaillance de l'instrument de bord; récupérer (42) les signaux enregistrés sans déposer l'instrument de bord; déterminer (43), à partir des signaux récupérés, la présence ou non d'une défaillance de l'instrument de bord et, le cas échéant, diagnostiquer la défaillance de l'instrument de bord. L'invention s'applique notamment pour réduire les durées de dépannages et remonter à la cause source de la défaillance sans déposer l'instrument de secours.
137	Aircraft sensor anticipator system	US12429362	2009-04-24	US08209069B1	2012-06-26	Frank A. McLoughlin; Xi Li
An apparatus and method for estimating future pitch and roll angles of an aircraft to compensate for a time delay caused by a flight instrumentation system calculating the aircraft's pitch and roll. The apparatus may output signals to an aircraft autopilot system. The apparatus may comprise various inputs and outputs, at least one compensation module, and at least one addition module. The compensation module may multiply a gain value by the pitch rate of the aircraft and by the roll rate of the aircraft to determine a pitch compensation amount and a roll compensation amount. Then the pitch compensation amount may be added to the pitch of the aircraft, and the roll compensation amount may be added to the roll of the aircraft to solve for a compensated pitch and a compensated roll to send to the autopilot system.
138	PROCEDE D'AFFICHAGE DE DONNEES POUR LA GESTION DU VOL D'UN AERONEF, PRODUIT PROGRAMME D'ORDINATEUR ET SYSTEME ASSOCIES	PCT/EP2017/059045	2017-04-14	WO2017178640A1	2017-10-19	PERRIN, Jean-Cédric; BARAILLER, Fany; LE ROUX, Yannick; CAZAUX, Patrick
L'invention concerne un procédé d'affichage de données pour la gestion du vol d'un aéronef comprenant les étapes consistant à recevoir la sélection d'un objet sur un écran d'affichage présent dans le cockpit de l'aéronef; déterminer une ou plusieurs commandes de vol associées à l'objet sélectionné; sélectionner au moins une commande de vol parmi lesdites une ou plusieurs commandes de vol déterminées; générer un panneau d'affichage comprenant une pluralité de volets d'affichage, un des volets affichant des données associées à l'objet sélectionné et un autre volet affichant la commande de vol sélectionnée. Des développements décrivent la mise à jour du panneau en fonction d'une révision du plan de vol, l'affichage d'attributs d'une commande de vol, des modifications d'affichage conditionnelles, des modalités de déploiement ou de repliement des volets d'affichage, la prise en compte de la densité visuelle d'affichage, l'utilisation de règles d'affichage, notamment en fonction du contexte de vol.
139	COMBINED STANDBY INSTRUMENTS FOR AIRCRAFT	PCT/FR1999/002418	1999-10-08	WO00022382A1	2000-04-20
The invention concerns standby instruments to assist piloting of an aircraft designed to supply, with high operating safety, indications concerning the aircraft pressure altitude, calibrated airspeed and attitude (roll and pitch angles), in order to serve both as reference for controlling the proper functioning of the main flight instruments and as standby in case of faulty functioning. More particularly, the invention concerns combined standby instruments comprising an electronics part providing it with computing power. It consists in forecasting, in said combined instruments which operate exclusively on the basis of total pressure, static and inertial pressure measurements coming from their own sensors, a correction of the static pressure measurement error caused by the aircraft aerodynamic angle of attack worked out solely from data already available to said standby instruments, in order to improve accuracy of pressure altitude without, however, increasing costs or reducing the safety of said combined standby instruments.
140	EP0883791A4 -	EP96920571	1996-05-30	EP0883791A4	1998-12-16
An interferometer comprising a base (12) forming an interior, and first and second optical members (14 and 16) located in the interior of the base. The interferometer further comprises a first retainer assembly (20) connecting the first optical member to the base, translation means (24) for moving the second optical member (16) relative the first optical member (14), to vary the distance between the first and second optical members, and a second retainer assembly (22) connecting the second optical member to the translation means (24). The preferred mechanical configuration and design features of the interferometer produce a very durable instrument that can rapidly scan and accurately filter light across a wide bandwidth. This uniquely designed instrument combines high speed switching, high resolution, wide bandwidth, and adjustable damping capabilities in a durable flight capable instrument.

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