| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 321 | 便携式飞机机翼智能检测装置 | CN201520942393.8 | 2015-11-23 | CN205150267U | 2016-04-13 | 王浩; 张鹏; 王涛; 唐杰 |
| 一种便携式飞机机翼智能检测装置。其包括底座、多根驱动轮支柱、多个橡胶轮、两台步进电机、两个气缸、两个气动吸盘、四个电磁换向阀、气泵、橡胶减振底座、两个转动轴固定件、两个转向连接件、齿条、齿轮、伺服电机、闪光灯组件、两个红外温度传感器、红外记录仪探头、高分辨率摄像头和控制装置。本实用新型优点：可大大提高检测效率，同时避免人为原因所导致的误检或漏检，可降低机务维护人员的劳动强度，提高检测精度；本系统体积较小，便于移动携带，也可将机翼的检测结果无线传输到手提电脑中记录和保存，通过分析可显著降低维护成本，提升飞行安全水平。 | ||||||
| 322 | 항공기의 기체수명 관리를 위한 비행 데이터 처리방법 | KR1019980063120 | 1998-12-31 | KR1020000046440A | 2000-07-25 | 안동규 |
| PURPOSE: A flight data process method is provided to proffer the data processing way for a managing a life span of an airplane body to raise the confidence of the data. CONSTITUTION: Binary flight data are entered from a flight load recorder, and a mission type is inputted. The inputted binary data are converted to the text engineering unit data by a parsing process. The text engineering unit data are rearranged in the time order and synchronized. By filtering gaps of the synchronized text engineering unit data, omitted data are supplemented. The over load are detected by analyzing the filtered engineering unit data. | ||||||
| 323 | 항공기의 기체 수명 관리를 위한 비행 데이터분석방법 | KR1019980063113 | 1998-12-31 | KR1020000046433A | 2000-07-25 | 안동규 |
| PURPOSE: A flight data analyzing method is provided to manage the life span of an airplane body by preprocessing the flight data calculated from a flight load recorder(FLDR) and analyzing the flight data for each airplane accumulatively. CONSTITUTION: A preprocessed engineering unit data file is inputted. Worked time for a specific airplane is analyzed from the inputted data file. An accumulative frequency of the load spectrum is analyzed from the inputted data file. A stress spectrum is created by inputting a stress delivering function. An accumulative frequency of the stress spectrum for the specific airplane is analyzed by using the created stress spectrum. A crack growth for the specific airplane is calculated by using the created stress spectrum. A damage index and a consolidatory inspecting time is calculated from the crack growth. | ||||||
| 324 | Acoustic command link to retrieve submerged flight data | US12800632 | 2010-05-19 | US08005584B1 | 2011-08-23 | Owen E. Flynn |
| Presently the only way to obtain the flight data from an open ocean crash site is to physically retrieve the flight data recorder. Retrieving a flight data recorder from the sea floor is extremely complex and expensive, requiring remotely operated robotic devices to locate and then to physically bring a piece of wreckage to the surface. In some cases water depth may preclude any retrieval. In these cases the flight data recorder will not be recovered and the cause of the crash will never be known. What is needed, however, is not the flight data recorder but the flight data. The invention provides a safe, convenient and economical way to retrieve flight data from a submerged flight data recorder without having to physically retrieve the recorder hardware. | ||||||
| 325 | FLIGHT RECORDER | EP11724001.0 | 2011-05-26 | EP2580123A1 | 2013-04-17 | KIDD, Nicholas; CHAMBERLAIN, Paul |
| The present invention describes a flight recorder for an aircraft with an instrument display panel for displaying aircraft status data to a pilot. The flight recorder comprises one or more sensors that monitor one or more flight conditions of the aircraft, a camera unit for providing image data and a data storage unit for storing the aircraft status data and image data from the camera. The flight recorder additionally comprises a control unit for monitoring the flight condition data supplied by the sensors. | ||||||
| 326 | DIGITAL RECORDING AND REPLAY SYSTEM FOR AN AIRCRAFT AND METHOD FOR REPRODUCTION OF ONBOARD INSTRUMENTATION OF AN AIRCRAFT | PCT/EP2010/068999 | 2010-12-06 | WO2011067419A1 | 2011-06-09 | O'CONNOR, Daniel; CERVIA, Bruno; MILNS, Robert; GIBSON, Paul |
Digital recording and replay system (100) for an aircraft, comprising a Mission Computer (MC) with an Operational Flight Program (OFP) for generating instrument data (ID) for onboard instruments of the aircraft; a Mission Data Recorder (MDR) connected to said Mission Computer (MC) for recording said instrument data (ID); and a Mission Debriefing System (MDS);wherein the Mission Debriefing System (MDS) is configured to reproduce the onboard instruments of the aircraft based on instrument data (ID) retrieved from the Mission Data Recorder (MDR). Method for reproduction of onboard instrumentation of an aircraft, comprising the steps of connecting a Mission Data Recorder (MDR) to a Mission Computer (MC) of an aircraft having an Operational Flight Program (OFP) for generating instrument data (ID) for onboard instruments; recording instrument data (ID); providing a Mission Debrief System (MDS) and causing it to reproduce the onboard instruments of the aircraft based on instrument data (ID) retrieved from the Mission Data Recorder (MDR). |
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| 327 | Analog voltage memory unit for power suspension compensation | JP15939275 | 1975-12-26 | JPS5280764A | 1977-07-06 | MINAMI SHIYUNJI |
| PURPOSE: The input signal is memorized even at power source cutoff such as in the case of power suspension. Thus, the data can be memorized before occurrence of unexpected accident, being suitably applied for flight recorder of airplane or automatic measurement instruments, etc. COPYRIGHT: (C)1977,JPO&Japio | ||||||
| 328 | ULTRASOUND/INFRASOUND SIGNAL IDENTIFICATION DEVICE | PCT/PL2016/000127 | 2016-11-15 | WO2017086814A1 | 2017-05-26 | JANOSZEK, Zbigniew |
The object of the invention is an ultrasound/infrasound signal identification device used to detect the locations of flight recorders called "black boxes" which are in the aquatic environment, both in fresh and salt waters, as a result of a crash. The ultrasound/infrasound signal identification device is undetachably connected to the flight recorder and it is in the form of a skeleton-based (7) shell-like solid with the outer shape of a polyhedron (1) or a sphere (2) which walls (3) or surface (3') are fitted with membranes (4), whereas the skeleton (7) of the shell-like solid is formed by reinforcing bars (5) undetachably joined to the walls (3) or surface (3'), and there are minimum two through holes (8) in at least one wail (3) or surface (3') or in the edge joining adjacent walls (3). |
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| 329 | Fahrtschreiber für Kraftfahrzeuge | EP80101132.1 | 1980-03-06 | EP0016994A1 | 1980-10-15 | Kuhn, Peter, Dr.; Zimmermann, Hans |
©7 Anordnung eines Fahrtschreibers im Armaturenbrett eines Kraftfahrzeuges. Fahrtschreiber mit einem Gehäuse und einem mit diesem gelenkig verbundenen Deckel, an dem frontseitig eine im wesentlichen rechteckförmige Frontplatte ausgebildet ist und dessen Schwenkachse in einem nicht unwesentlichen Abstand von dessen Frontfläche, und zwar parallel zu einem der Kantenpaare der Frontfläche angeordnet sind, sind nur dann «versenkt» in einem Armaturenbrett einbaubar, wenn der Armaturenbrettausschnitt größer ist als die Frontfläche des Fahrtschreibers. Der erforderliche Eintauchspalt für den aufschwenkenden Deckel muß in diesem Falle durch eine geeignete Blende abgedeckt werden. Eine solche Blende (19), die hinsichtlich ihrer äußeren Form und Oberflächengestaltung als ein Element des Armaturenbretts ausgebildet sein kann, wird vorzugsweise mittels Rast-, Steck- oder Schraubverbindungen (20) lösbar mit dem Deckel (9) des Fahrtschreibers (3) verbunden, so daß dieser wahlweise «aufgesetzt» oder «versenkt» einbaufähig ist. |
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| 330 | AIRCRAFT FLIGHT DATA ACQUISITION AND TRANSMISSION SYSTEM | EP99935996.1 | 1999-07-29 | EP1101177B2 | 2017-02-15 | GRABOWSKY, John, F.; STEVENS, David, Ray |
| 331 | Aircraft flight data acquisition and transmission system | EP03078940.8 | 1999-07-29 | EP1414192A2 | 2004-04-28 | Grabowsky, John F.; Stevens, David Ray |
An aircraft data transmission system (10) used with an aircraft (12) having a data acquisition unit. The system includes a communications unit located in the aircraft (12) and in communication with the data acquisition unit. The system also includes a cellular infrastructure (14) in communication with the data communications unit after the aircraft (12) has landed. The system further includes a data transceiver means in communication with the cellular infrastructure (14). |
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| 332 | Flight recording floating device | JP14984692 | 1992-05-18 | JPH05319400A | 1993-12-03 | KAWAMURA MASANORI; NARUSE OSAMU; YAMASHITA SHIGERU |
| PURPOSE: To provide a small flight recorder floating device capable of causing a large and heavy flight recorder to be afloat. CONSTITUTION: This device is equipped with a flight recorder 2, a submerged detecting section 5 for detecting water, a gas supply section 4 actuated upon the detection of water with the section 5, and an air bag 6 inflated with gas fed from the section 4. When the flight recorder 2 is submerged, the section 5 detects water and drives the section 4, thereby inflating the air bag 6. As a result, the flight recorder 2 becomes afloat. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 333 | Flight data monitoring and validation | US13721505 | 2012-12-20 | US09346557B2 | 2016-05-24 | Dave Jesse; Chris Jesse; Anne Seldon; Nadim Rahman; Farshad Fahimi |
| A computer-implemented flight data monitoring method is provided for monitoring flight data, for example flight data obtained by a flight data recorder or quick access recorder on an aircraft. The method comprises receiving input flight data, performing flight data validation on the input flight data to generate validated flight data, and performing flight data analysis on the validated flight data to detect at least one predetermined type of flight event. The events may be useful for generating an aircraft safety report, for example. By validating the data before performing the analysis, the number of events which are falsely detected based on invalid or unreliable data can be reduced. | ||||||
| 334 | FLIGHT DATA MONITORING AND VALIDATION | US13721505 | 2012-12-20 | US20130274964A1 | 2013-10-17 | Dave Jesse; Chris Jesse; Anne Seldon; Nadim Rahman; Farshad Fahimi |
| A computer-implemented flight data monitoring method is provided for monitoring flight data, for example flight data obtained by a flight data recorder or quick access recorder on an aircraft. The method comprises receiving input flight data, performing flight data validation on the input flight data to generate validated flight data, and performing flight data analysis on the validated flight data to detect at least one predetermined type of flight event. The events may be useful for generating an aircraft safety report, for example. By validating the data before performing the analysis, the number of events which are falsely detected based on invalid or unreliable data can be reduced. | ||||||
| 335 | 无人飞行器（F08） | CN201830422530.4 | 2018-08-02 | CN304962214S | 2018-12-25 | 高建民 |
| 1．本外观设计产品的名称：无人飞行器（F08）。 2．本外观设计产品的用途：本外观设计产品用于飞行、航拍、行车记录仪功能等。 3．本外观设计产品的设计要点：在于产品的整体外形设计。 4．最能表明本外观设计设计要点的图片或照片：立体图。 | ||||||
| 336 | LOCATOR BEACON DISPOSED INTERNAL TO AN ENCLOSURE OF A FLIGHT DATA RECORDER AND METHOD THEREFOR | PCT/US2009053733 | 2009-08-13 | WO2010027620A2 | 2010-03-11 | WINTERHALTER MICHAEL C; BERECZ ENDRE |
| A flight data recorder includes an enclosure and electronic interface within the enclosure. The electronic interface is coupled for receiving data. A crash survivable memory unit is disposed within the enclosure. The crash survivable memory unit includes a memory module electrically coupled to the electronic interface for storing the data. A locator beacon is disposed within the enclosure or within the crash survivable memory unit. The locator beacon is an acoustic resonator which emits ultrasonic pulses. A battery is disposed within the enclosure or within the crash survivable memory unit for providing operating power to the locator beacon. The battery is rechargeable. The battery status is stored in the memory module. A beacon control circuit is disposed within the enclosure or within the crash survivable memory unit for monitoring the battery. A beacon activation device detects a crash event and notifies the beacon control circuit to activate the locator beacon. | ||||||
| 337 | FAIL SAFE AIRCRAFT MONITORING AND TRACKING | US14486350 | 2014-09-15 | US20160075443A1 | 2016-03-17 | Thomas R. Schmutz; Eduardo M. Carro; Ayaz Nemat; Sean P. Reilly |
| Flight data recorder receives from an aircraft a data stream specifying values for flight data parameters while an aircraft is in flight. The flight data recorder stores the values in a crash survivable non-volatile memory unit of the flight data recorder. The flight data recorder determines an occurrence during flight of an exception condition based on an evaluation of at least one exception parameter. Responsive to determining the occurrence of the exception condition, the flight data recorder wirelessly communicates selected aircraft data to a remote location external of the aircraft using a wireless transmitter under the exclusive control of the flight data recorder. | ||||||
| 338 | Fault-tolerant solid-state flight recorder | EP92305494.4 | 1992-06-16 | EP0528518A2 | 1993-02-24 | Yokote, Timothy Alan; Upton, Eric Lawrence; Enyedy, Arthur Gustav; Stockton, Grant Joseph |
A fault-tolerant solid-state flight data recorder providing reliable, high-speed storage of flight data. The flight data recorder employs a distributed, modular architecture in which an array of controller/memory modules is arranged in parallel controller/memory chains and the memory in the individual controller/memory modules is partitioned into submodules. This distributed architecture allows failed controller/memory modules or failed memory submodules to be bypassed, thus providing fault tolerance for both controller and memory functions. The modular architecture allows the number of controller/memory modules to be easily configured to accommodate any required storage size, while the number of parallel controller/memory chains can be configured to accommodate any required data rate. |
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| 339 | Flugkörper | EP89111648.5 | 1989-06-27 | EP0348880A1 | 1990-01-03 | Baumann, Gerd |
Ein beispielsweise mit einem Zeitzünder versehener Flugkörper enthält einen Mikroprozessor (10), dem bestimmte relevante Signale zugeführt werden und der aufgrund dieser Signale bestimmte Steuerfunktionen auslöst. Gleichzeitig schreibt dieser Mikroprozessor (10) für den Flug und die Funktion des Zünders relevante Daten in einen Speicher EEPROM-(18), der diese Daten unverlierbar speichert. Nach einem Aufschlag bzw. einer Zerlegung des Flugkörpers kann dieser Speicher (18) geborgen werden und nach Art eines Flugschreibers kann die in ihm enthaltene Information für die Analyse der Fehlfunktion bzw. Funktion des in dem Flugkörper enthaltenen Zünders verwendet werden. |
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| 340 | Fault allowable data recorder | JP17693292 | 1992-07-03 | JPH06290064A | 1994-10-18 | TEIMOSHII AREN YOTOKE; ERITSUKU ROORENSU ATSUPUTON; AASAA GUSUTAFU ENIIDEI; GURANTO JIYOSEFU SUTOTSUKUTON |
| PURPOSE: To provide a fault allowable semiconductor flight data recorder which provides reliable high-speed storage of flight data. CONSTITUTION: The flight data recorder employs decentralized modular architecture which has an array of controller/memory modules 24 arranged in a parallel controller/memory chain 14 and also has the individual controller/memory modules 24 sectioned into submodules. This decentralized architecture can by- pass a controller/memory module 24 which gets out of order or a memory submodule which gets out of order, and consequently a controller function and a memory function are allowed to get out of order. Further, the modular architecture can easily be constituted that the number of the controller/memory modules 24 can be adapted to arbitrary necessary storage size and the number of parallel controller/memory chains 14 can be adapted to an arbitrary necessary data speed. COPYRIGHT: (C)1994,JPO | ||||||
