| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | METHOD AND APPARATUS FOR TRACKING THE POSITION AND VELOCITY OF AIRBORNE INSTRUMENTATION. | EP93919927 | 1993-08-06 | EP0664008A4 | 1997-08-20 | MACDORAN PETER F; CALL DAVID B; GOLD KENNETH L; SCHREINER WILLIAM S; ZIEL FRED A |
| A method and system for tracking the position of at least one moving object, such as an airborne meteorological instrument (20) from a ground processing station by intercepting wideband spread spectrum signals transmitted from a plurality of satellites in which the code sequence of the signals is not known, comprises a receiver circuit in the moving object which compresses the wideband signals received into a narrow band, removes any frequency bias with a reference oscillator (12) having a frequency offset value, forms a narrow analog baseband (9) and transmits (14) to the processing station at which spectral lines are produced and compared with synthetic spectrum values to determine the identity of each satellite, the reference oscillator frequency offset value is estimated, and the location and velocity of the moving object is determined. | ||||||
| 82 | Flight instrument displaying a variable rotational speed of a main rotor of an aircraft | US14607162 | 2015-01-28 | US09409655B1 | 2016-08-09 | Jean-Baptiste Vallart; Patrick Hellio; Patricia Gauthier; Setareh Taheri |
| A flight instrument that displays the rotational speed of a main rotor of a rotary-wing aircraft, with the flight instrument including display means, a first indicator of a setpoint for the rotational speed of the main rotor, a second indicator of the first current value of the rotational speed of the main rotor, and third and fourth indicators of the limit values of the rotational speed. The setpoint for the rotational speed of the main rotor is variable and the first indicator is stationary on the display means, with the second, third and fourth indicators being movable in relation to the first indicator. | ||||||
| 83 | Edit area algorithm for navigation display of an electronic flight instrument system | US594672 | 1990-10-09 | US5041982A | 1991-08-20 | Vijayakumar Rathnam |
| In the navigation display of the electronic flight instrument system, the arc mode and Rose Nav mode of a navigation display require computation of parameters for a greater surface (modified Edit) area than the Edit area for each display scale. When the icons representing selected navigational features are included on the navigation display, the retrieved and stored icons can be positioned external to the viewable Edit area. Because access to a dictionary defining the position of the icons is sequential and because the display buffer storage unit from which the screen display is created has a limited capacity, the arc or Rose Nav display can include features in the non-viewable modified Edit area while not including important features in the Edit area. An algorithm is described that determines when a feature with which an icon is associated is in the Edit area and selects the data associated with those features in the Edit area to be stored in the display buffer storage unit. Data associated with features only in the modified Edit area are not stored in the display buffer storage unit. In the arc display mode and the Rose Nav display mode, the display screen can be continuously updated requiring the algorithm to operate with a dynamically changing display. | ||||||
| 84 | SYSTEM AND METHOD FOR ATTITUDE CONTROL OF A FLIGHT VEHICLE USING PITCH-OVER THRUSTERS | EP07863325.2 | 2007-03-06 | EP1991825A2 | 2008-11-19 | BRINKERHOFF, Robert; MAHNKEN, Michael; LOEHR, Richard; COOK, James; CAVALLERI, Robert |
| A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch- over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability. | ||||||
| 85 | SYSTEM FOR ATTITUDE CONTROL OF A FLIGHT VEHICLE USING PITCH-OVER THRUSTERS | EP07863325.2 | 2007-03-06 | EP1991825B1 | 2013-04-24 | BRINKERHOFF, Robert; MAHNKEN, Michael; LOEHR, Richard; COOK, James; CAVALLERI, Robert |
| 86 | 电脑显示器的无人直升机飞行仪表界面 | CN201830122328.X | 2018-03-29 | CN304986364S | 2019-01-08 | 贾伟力; 张妍 |
| 1．本外观设计产品的名称：电脑显示器的无人直升机飞行仪表界面。 2．本外观设计产品的用途：本外观设计产品用于显示运行程序及通讯。 3．本外观设计产品的设计要点：显示的图形及用户界面内容。 4．最能表明本外观设计设计要点的图片或照片：主视图。 5．省略视图：后视图、左视图、右视图、俯视图和仰视图不涉及设计要点，故省略。 6．请求保护的外观设计主视图为软件界面整体布局图及显示元素，变化状态图1为数据正常状态显示，变化状态图2为数据异常状态显示，表示油门变距超限以及报警灯及报警内容等。 参考图1为布局内容及标示，参考图2为展示图中标号2的放大布局图，参考图3为展示图中标号3的放大布局图，参考图4为展示图中标号4的放大布局图。 | ||||||
| 87 | EINRICHTUNG UND VERFAHREN ZUM VERSETZEN EINES FLUGGERÄTES, INSBESONDERE EINES HELIKOPTERS, AN BORD EINES SCHIFFES | PCT/EP2016/000541 | 2016-03-31 | WO2016155883A1 | 2016-10-06 | JONUSCHEIT, Ulf |
Die Erfindung betrifft eine Einrichtung und ein Verfahren zum Versetzen eines Fluggerätes (1), insbesondere eines Helikopters, an Bord eines Schiffes mittels wenigstens drei Zugseilen (4, 5, 6). Zum Fluggerät (1) ausgelegte Enden der Zugseile (4, 5, 6) werden mittels wenigstens drei jeweils einem der Zugseile (4, 5, 6) zugeordneten Winden (9, 10, 19) gespannt. Die Winden (9, 10, 19) weisen drehbar gelagerte Trommeln (11, 12, 21) zum Wickeln der Zugseile (4, 5, 6) und Elektromotoren (13, 14, 18), insbesondere Servomotoren, zum Antrieb der Trommeln (11, 12, 21) auf. Dadurch ist eine kostengünstige und reaktionsschnell zu betreibende Alternative zu herkömmlichen Einrichtungen mit hydraulischen Systemen zum Versetzen von Fluggeräten (1) geschaffen. |
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| 88 | METHOD FOR CONTROLLING AN AIRCRAFT IN THE FORM OF A MULTICOPTER AND CORRESPONDING CONTROL SYSTEM | PCT/EP2013060267 | 2013-05-17 | WO2013174751A3 | 2014-01-16 | WOLF STEPHAN; RUF THOMAS |
| A method and a system are proposed for controlling an aircraft in the form of a multicopter which has a plurality of redundant rotors (4), preferably arranged in a common rotor plane, in order, on the one hand, to generate lift, and, on the other hand, also propulsion by inclining the at least one rotor plane, wherein the regulation of the position and the control of the multicopter are carried out by changing rotor rotational speeds as a function of pilot control instructions. The system is characterized in that the rotors (4) are connected to one another in terms of data technology via a failsafe network (8), and they communicate their respective operating state, in particular their rotor rotational speed, in the network (8), and in that the network contains a first multiplicity of redundant sensors which determine control-relevant data and make it available in the network, in particular inclination, acceleration, rotational speed and/or position in all three spatial axes of the multicopter. | ||||||
| 89 | VERFAHREN ZUM STEUERN EINES FLUGGERÄTS IN FORM EINES MULTICOPTERS UND ENTSPRECHENDES STEUERUNGSSYSTEM | PCT/EP2013/060267 | 2013-05-17 | WO2013174751A2 | 2013-11-28 | WOLF, Stephan; RUF, Thomas |
Vorgeschlagen wird ein Verfahren und ein System zum Steuern eines Fluggeräts in Form eines Multicopters, welcher mehrere, vorzugsweise in einer gemeinsamen Rotorebene angeordnete, redundante Rotoren (4) aufweist, um einerseits Auftrieb und andererseits durch Neigung der wenigstens einen Rotorebene auch Vortrieb zu erzeugen, wobei Lageregelung und Steuerung des Multicopters durch Veränderungen von Rotordrehzahlen in Abhängigkeit von Piloten-Steuerbefehlen erfolgen, welches dadurch gekennzeichnet ist, dass die Rotoren (4) über ein ausfallsicheres Netzwerk (8) miteinander datentechnisch verbunden sind und ihren jeweiligen Betriebszustand, insbesondere ihre Rotordrehzahi, in dem Netzwerk (8) kommunizieren; in dem Netzwerk eine erste Mehrzahl an redundanten Sensoren enthalten sind, die steuerungsrelevante Daten ermitteln und in dem Netzwerk bereitstellen, insbesondere Neigung, Beschleunigung, Drehrate und/oder Position in allen drei Raumachsen des Multicopters; weiterhin in dem Netzwerk eine zweite Mehrzahl an Reglern enthalten sind, die autonom und dezentral anhand der Sensordaten, und vorzugsweise außerdem anhand der Rotor-Betriebszustände, jeweils ein Regelsignal für jeweils wenigstens einen Rotor bestimmen und in dem Netzwerk bereitstellen; die Rotoren mittels der Regelsignale so geregelt werden, dass ein Flugverhalten des Multicopters im Wesentlichen der Vorgabe durch den Piloten-Steuerbefehl entspricht. |
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| 90 | Method for controlling navigation of an aircraft, and interactive flight instrument panel to implement said method | US498428 | 1995-07-05 | US5758297A | 1998-05-26 | Philippe Gaultier |
| A method for preparing and controlling navigation of an aircraft uses a processor equipped with memories, a screen and keys. It comprises the steps of preparing the route to be followed by an aircraft by loading into the memory data pertaining to a route, defining parameters characterizing the environment in which the navigation will take place, and displaying during navigation a couple of way points including the last point through which the aircraft has passed and the next way point, the segment joining these two points together, and information required to control navigation between these two points. The invention enables the pilot to prepare his navigation without taking measurement readings and performing calculations. | ||||||
| 91 | Apparatus and method for displaying energy management circles on displays for electronic flight instrument systems | US522281 | 1990-05-11 | US5258756A | 1993-11-02 | Lyal H. Bauer; Scott F. Bauler |
| An improved method and apparatus for drawing energy management circles on electronic flight instrument system displays which includes a microprocessor for making several initial inquiries regarding the orientation of the circle with respect to the display and issuing write or don't write commands for each point on the circle without the need for individually analyzing each point as to whether it is located on the display screen. | ||||||
| 92 | METHOD AND APPARATUS FOR TRANSPORTING A LARGE INFORMATION OR ADVERTISING MEDIUM BY MEANS OF A REMOTE-CONTROLLABLE SMALL FLYING VEHICLE, AND ASSOCIATED INFORMATION OR ADVERTISING MEDIUM | PCT/EP2014078751 | 2014-12-19 | WO2015091954A3 | 2015-09-24 | KABBANI ZIAD |
| The invention relates to a method for transporting at least one information or advertising medium (1) by means of a remote-controllable, helicopter-type small flying vehicle (2). In said method, the information or advertising medium (1) is held substantially in a predefined shape (3) substantially underneath the small flying vehicle (2). The invention further relates to an apparatus (15) for transporting at least one information or advertising medium as well as to an information or advertising medium (1). | ||||||
| 93 | VERFAHREN UND VORRICHTUNG ZUM TRANSPORT EINER GROSSFLÄCHIGEN INFORMATIONS- ODER WERBEFLÄCHE MITTELS EINES FERNSTEUERBAREN KLEINFLUGGERÄTES UND ZUGEHÖRIGE INFORMATIONS- ODER WERBEFLÄCHE | PCT/EP2014/078751 | 2014-12-19 | WO2015091954A2 | 2015-06-25 | KABBANI, Ziad |
Die Erfindung betrifft ein Verfahren zum Transport mindestens einer Informations- oder Werbefläche (1) mittels eines fernsteuerbaren, hubschrauberähnlichen Kleinfluggerätes (2), wobei die Informations- oder Werbefläche (1) im Wesentlichen unterhalb des Kleinfluggerätes (2) im Wesentlichen in einer vorgegebenen Form (3) gehalten wird. Die Erfindung betrifft weiter eine Vorrichtung (15) zum Transport mindestens einer Informations- oder Werbefläche sowie eine Informations- oder Werbefläche (1). |
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| 94 | 一种飞机地面试验用信号交联测控系统 | CN201810342715.3 | 2018-04-16 | CN108646705A | 2018-10-12 | 鹿凡超; 周冰; 毛绍婧 |
| 一种飞机地面试验用信号交联测控系统，包含一个信号交联箱、总线监控/仿真设备和地面电源、飞机的飞行仪表和自动驾驶仪，在信号交联箱的前面板上分布有多个断连端子，每个断连端子对应飞行仪表或自动驾驶仪的一个信号，在信号交联箱的后面板上设有地面电源输入接口、飞行仪表和自动驾驶仪的信号接口、外围机载设备信号接口，上述的断连端子为一个三通的连接器，断连端子前端接口可与外部总线监控/仿真设备连接，断连端子后端有两个接口，其中一个接口与信号交联箱的后面板上对应的飞行仪表和自动驾驶仪信号接口连接，断连端子后端的另一个接口与信号交联箱的后面板上对应的外围机载设备信号接口连接，信号交联箱的前面板上还设有多个二位开关，该二位开关用于控制飞行仪表和自动驾驶仪的上电以及离散量的输入。 | ||||||
| 95 | ADS-B防撞算法测试方法及系统 | CN202111450122.7 | 2021-11-30 | CN114137943B | 2024-04-02 | 吴俊; 姜锋; 龙泓宇 |
| 本发明公开了一种ADS‑B防撞算法测试系统及方法，系统的控制模块用于向飞行仪表仿真模块和目标机模拟装置发送场景启动指令；目标机模拟装置用于根据场景启动指令运行预存的目标机场景产生目标机信息并向ADS‑B防撞设备；飞行仪表仿真模块根据接收到的场景启动指令运行预存的本机场景，获得本机位置信息，并发送给待测ADS‑B防撞设备接收并显示防撞告警信息和目标机信息；待测ADS‑B防撞设备接收本机位置信息和目标机信息，运行待测ADS‑B防撞算法产生告警信息，并将告警信息和目标机信息发送给飞行仪表仿真模块。本发明实现了预存场景的自动化调用测试、告警信息和目标机信息的可视化，成本低，实现方便。 | ||||||
| 96 | 一种航空应急仪表及其系统初始对准方法和组合导航算法 | CN200910210347.8 | 2009-10-30 | CN102050226A | 2011-05-11 | 谢莉莉; 游学; 朱强; 郭秋芬; 李旭东; 杨勇; 郭双红; 岳步江; 向伟荣; 姜洪雷 |
| 一种航空应急仪表，包括：大气压力测量单元，惯性测量单元，双天线GPS卫星接收机，与卫星信号接收天线连接，图形显示单元，二次电源电路，综合处理计算单元，所述综合处理计算单元接收来自各传感器的信息，通过传感器信息融合算法，计算出指示空速、气压高度、姿态、航向、经纬度等导航参数，并将计算结果发送给高密度液晶图形显示单元；根据本发明提供的一种航空应急仪表够提供指示空速、气压高度、姿态(俯仰角、横滚角)、航向、经纬度等导航信息，既可以作为正常状态下飞行员操控主飞行仪表的信息参考又可以在主飞行仪表发生故障时作为应急备用仪表，当主飞行仪表完全丧失功能时，仍可依靠该仪表提供的导航信息指引飞行员驾驶飞机安全返航。 | ||||||
| 97 | ADS-B防撞算法测试方法及系统 | CN202111450122.7 | 2021-11-30 | CN114137943A | 2022-03-04 | 吴俊; 姜锋; 龙泓宇 |
| 本发明公开了一种ADS‑B防撞算法测试系统及方法，系统的控制模块用于向飞行仪表仿真模块和目标机模拟装置发送场景启动指令；目标机模拟装置用于根据场景启动指令运行预存的目标机场景产生目标机信息并向ADS‑B防撞设备；飞行仪表仿真模块根据接收到的场景启动指令运行预存的本机场景，获得本机位置信息，并发送给待测ADS‑B防撞设备接收并显示防撞告警信息和目标机信息；待测ADS‑B防撞设备接收本机位置信息和目标机信息，运行待测ADS‑B防撞算法产生告警信息，并将告警信息和目标机信息发送给飞行仪表仿真模块。本发明实现了预存场景的自动化调用测试、告警信息和目标机信息的可视化，成本低，实现方便。 | ||||||
| 98 | 一种飞机的飞行指引系统及改进方法 | CN201810647424.5 | 2018-06-22 | CN108646785B | 2020-12-29 | 张恒瑞; 任泉儒; 李武杰 |
| 一种飞机飞行指引系统，含有飞行控制计算机、电子飞行仪表和状态选择板，通过离散量信号将飞机的襟翼位置信号输入飞行控制计算机，通过数字总线信号将起落架载荷信号输入飞行控制计算机；飞行控制计算机将接收到的飞行参数信息、襟翼位置信号以及起落架载荷信号结合内置逻辑和飞行员由状态选择板选择的飞行模式，解算出合适的飞行指引信息，并将该飞行指引信息输出给电子飞行仪表供飞行员读取。 | ||||||
| 99 | 一种飞行器海面高、低空巡航预选高度基准切换方法 | CN201910553604.1 | 2019-06-24 | CN110262551A | 2019-09-20 | 王骞; 刘中平; 马韬; 刘俊杰; 梁凤霞; 马静坡; 周甄; 李君君; 任准; 李莹 |
| 本发明属于航空技术领域，涉及一种飞行器海面高、低空巡航预选高度基准切换方法。本方法首先设置飞行器预选值高度数值；之后电子飞行仪表系统判断预选高度值与HK的关系，确定高度基准，HK是切换高度常数，根据无线电高度有效精度来确定；最后电子飞行仪表系统处理机将高度基准和预选高度数值发送给自动驾驶仪和显示器。本方法利用不同高度基准的优势，克服将标准大气高度作为单一高度基准源，在海面低空测高精度不足的问题，提高了飞行器海面高、低空巡航的高度控制可靠性。 | ||||||
| 100 | 一种飞机的飞行指引系统及改进方法 | CN201810647424.5 | 2018-06-22 | CN108646785A | 2018-10-12 | 张恒瑞; 任泉儒; 李武杰 |
| 一种飞机飞行指引系统，含有飞行控制计算机、电子飞行仪表和状态选择板，通过离散量信号将飞机的襟翼位置信号输入飞行控制计算机，通过数字总线信号将起落架载荷信号输入飞行控制计算机；飞行控制计算机将接收到的飞行参数信息、襟翼位置信号以及起落架载荷信号结合内置逻辑和飞行员由状态选择板选择的飞行模式，解算出合适的飞行指引信息，并将该飞行指引信息输出给电子飞行仪表供飞行员读取。 | ||||||
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