| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | EP85904698.0 | 1985-07-10 | EP0190345A1 | 1986-08-13 | BATEMAN, Charles, D.; GLOVER, J.H.; MULLER, Hans, R. |
| Les performances d'un système d'avertissement de la proximité du sol peuvent être améliorées, surtout dans des cas où les performances de l'avion lui-même ont été dégradées par un facteur tel que le cisaillement du vent, en étendant les enveloppes d'avertissement en Mode 1 (24) et Mode 3 (32) jusqu'à cinq pieds du sol. D'autres améliorations des performances d'avertissement peuvent être obtenues en contrôlant l'angle de trajectoire de vol (46) lorsque l'avion se trouve près du sol. Les avertissements sont fondés sur un réseau logique (28) qui utilise l'altitude radio (12), la vitesse barométrique d'altitude (14), la vitesse (50) de l'avion, la marge de décrochage (82), et une source (10) de signaux représentant l'angle d'attaque, l'accélération verticale, et la phase de vol de l'avion. Un avertissement (30) est ainsi donné pour faire tanguer l'avion sauf lorsque la marge de décrochage est inférieure à une valeur prédéterminée. | ||||||
| 42 | Fireplace including a safety proximity warning system | EP12154796.2 | 2012-02-09 | EP2498004A2 | 2012-09-12 | Vendramini, Antonio; Balladore, Giovanni |
The present invention relates to a fireplace (1) in which a flame (3) can be lightened, said fireplace including a warning system, said system comprising: a proximity sensor (5) to detect the presence of object within an active volume, said volume surrounding at least a portion of the fireplace, an alarm device (6) to emit an alarm signal, a clock (9) to calculate a time elapsed since the switching off of the fireplace, and a processing unit (8) receiving as input data from the clock (8) and the proximity sensor (5), and outputting command signals to the alarm device (6). The alarm device (6) is activated by the processing unit (8) to generate an alarm signal when an object is detected by the proximity sensor (5) as entering said active volume and the fireplace (1) has been switched off since no later than a first pre-defined time interval. In addition, the invention relates to a method for warning when an object that enters the active volume of a fireplace.
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| 43 | GROUND PROXIMITY APPROACH WARNING SYSTEM WITHOUT LANDING FLAP INPUT | EP88904766.0 | 1988-04-05 | EP0309578A1 | 1989-04-05 | BATEMAN, Charles, D.; GROVE, Michael, M. |
| Dispositif avertisseur de proximité du sol susceptible de reconnaître à quel moment un avion est en phase d'approche finale d'un aéroport, sans l'utilisation d'une entrée de signaux de volet d'intrados. Les données relatives aux aéroports (16) ainsi qu'à la topographie environnante sont reproduites par une forme géométrique simple, telle qu'un cône tronqué inversé (4), et stockées à bord de l'appareil. Le dispositif utilise des données relatives à la navigation (12, 14) afin de déterminer la distance de l'avion à partir de la représentation géométrique. Après avoir déterminé que l'appareil, se situe à l'intérieur de la zone définie par la représentation géographique, le dispositif fournit une enveloppe de validation (46) indiquant que l'avion est en phase d'approche finale, afin de valider plusieurs dispositifs avertisseurs de proximité du sol. Un dispositif permettant de modifier l'enveloppe de validation (46) en fonction de l'alignement de l'appareil avec une piste donnée (50), est également décrit. | ||||||
| 44 | GROUND PROXIMITY WARNING SYSTEM AND METHOD HAVING A REDUCED SET OF INPUT PARAMETERS | EP00937508.0 | 2000-03-24 | EP1163534A2 | 2001-12-19 | BATEMAN, C., Don; JOHNSON, Steven, C. |
| The ground proximity warning system and method provide a number of alerts based upon a substantially reduced list of input parameters relative to a conventional ground proximity warning system and method. The ground proximity warning system and method generally constructs alert envelopes and generates alerts if the upcoming terrain or other obstacles pierce the alert envelopes. The ground proximity warning system and method can also generate alerts if the aircraft has an excessive descent rate at a relatively low altitude and if the aircraft descends immediately following takeoff in a similar fashion to Mode 1 and Mode 3 alerts. Further, the ground proximity warning system and method can provide altitude call outs at predefined altitudes above a target runway and can provide alerts if the aircraft appears to be landing short of a runway. The ground proximity warning system and method are capable of providing the various warnings based upon only a pressure altitude, GPS signals and, in some embodiments, the external air temperature. Thus, the ground proximity warning system and method can be independent of a radio altimeter, an ADC, a glideslope receiver and signals indicative of the configuration of the landing gear and flaps. | ||||||
| 45 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | EP86905565.7 | 1986-08-25 | EP0233941B1 | 1994-10-19 | BATEMAN, Charles, D.; GLOVER, John, H.; MULLER, Hans, R. |
| Performance of an aircraft ground proximity warning system can be improved, especially where the performance of the aircraft itself has been degraded by a factor such as wind shear, by extending excessive descent rate (24) and negative climb after takeoff (32) warning enveloppes down to within five feet of the ground. Additional immprovements in warning performance can be made by monitoring flight path angle (100) when the aircraft is close to the ground, and by monitoring computed altitude rate (16), phase of flight (208, 236), glide slope deviation (110), angle of attack (10) and stall margin (82). | ||||||
| 46 | GROUND PROXIMITY APPROACH WARNING SYSTEM WITHOUT LANDING FLAP INPUT | EP88904766.8 | 1988-04-05 | EP0309578B1 | 1994-07-27 | BATEMAN, Charles, D.; GROVE, Michael, M. |
| A ground proximity warning system is disclosed which can recognize when an aircraft is on a final approach to an airport without utilizing a landing flap signal input. Airports (16) together with the surrounding terrain topography are modeled by a simple geometric shape, such as, an inverted truncated cone (4), and stored on-board the aircraft. The system uses navigational data (12, 14) to determine the distance of the aircraft from the geometric model. Once the aircraft is determined to be within the area defined by the geometric model, the system provides an enabling envelope (46) indicative that the aircraft is on a final approach for enabling various ground proximity warning systems. Also disclosed is a system for altering the enabling envelope (46) as a function of the aircraft's alignment with particular runway (50). | ||||||
| 47 | SYSTEM AND METHOD FOR USING AIRPORT INFORMATION | EP03768785.2 | 2003-11-10 | EP1563473A2 | 2005-08-17 | CONNER, Kevin, J.; JOHNSON, Steven, C.; ISHIHARA, Yasuo |
| A method, system, and computer program product for using airport information based on the flying environment are provided. When a helicopter is determined to be approaching a runway, ground proximity warning envelopes are automatically reduced to prevent unwanted, or nuisance, terrain alerts. On the other hand, when a helicopter is flown near a runway without intent to land or when a helicopter is taking off, ground proximity warning envelopes may remain unchanged. As a result, nuisance alerts are reduced when a helicopter is approaching a runway for landing and ground proximity warnings may remain in effect to maximize protection when a helicopter is flying near a runway without an intent to land or is taking off from a runway. | ||||||
| 48 | METHOD AND SYSTEM OF REDUCING THE NUMBER OF NUISANCE TERRAIN ALERTS PRODUCED BY A GROUND PROXIMITY WARNING SYSTEM WHEN APPROACHING A RUNWAY | EP03768785.2 | 2003-11-10 | EP1563473B1 | 2008-07-02 | CONNER, Kevin, J.; JOHNSON, Steven, C.; ISHIHARA, Yasuo |
| 49 | SYSTEMS AND METHOD FOR WIRELESSLY AND SECURELY UPDATING A TERRAIN AWARENESS WARNING SYSTEM DATABASE | EP15196868.2 | 2015-11-27 | EP3029654A1 | 2016-06-08 | CECCOM, Christophe |
Systems and methods for updating a terrain awareness and warning system (TAWS) database are disclosed. The systems request, by way of the first wireless communications device communicating by way of an avionics data transfer protocol, an update to the TAWS database, where the request is based upon flight path data, and receive and accept, by way of the first wireless communications device and by way of the avionics data transfer protocol and in response to the request, the update to the TAWS database.
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| 50 | Ground proximity warning system geographic area determination | US560073 | 1983-12-09 | US4675823A | 1987-06-23 | Lyle J. Noland, deceased |
| A ground proximity warning system utilizes geographic position data to alter the warning criteria as is required by the terrain features of particular geographic areas. To determine whether the aircraft is within a particular geographic area, the world is subdivided into latitude bands that are in turn subdivided into non-overlapping zones by predetermined lines of longitude, with the position of each zone being defined by the latitude and longitude coordinates of one of its corners. The zones are further defined by regions which may overlap other zones. The regions are limited in size, and their positions are also defined by the locations of one of their corners. The regions are further subdivided into one or more geographic areas that are defined by their shapes and locations within the region. Inputs from the navigational system of the aircraft are used successively to determine whether the aircraft is in a particular latitude band, zone, region and area, and adjustments to the warning criteria are made to optimize the performance of the warning system for the area in which the aircraft is flying. A "snapshot" is made over known territory to verify the validity of the barometric altitude signal before any modification to the warning criteria is made. | ||||||
| 51 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | EP86905565 | 1986-08-25 | EP0233941A4 | 1991-04-17 | BATEMAN, CHARLES, D.; GLOVER, JOHN, H.; MULLER, HANS, R. |
| Performance of an aircraft ground proximity warning system can be improved, especially where the performance of the aircraft itself has been degraded by a factor such as wind shear, by extending excessive descent rate (24) and negative climb after takeoff (32) warning enveloppes down to within five feet of the ground. Additional immprovements in warning performance can be made by monitoring flight path angle (100) when the aircraft is close to the ground, and by monitoring computed altitude rate (16), phase of flight (208, 236), glide slope deviation (110), angle of attack (10) and stall margin (82). | ||||||
| 52 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | EP85904698.9 | 1985-07-10 | EP0190345B1 | 1991-02-20 | BATEMAN, Charles, D.; GLOVER, J.H.; MULLER, Hans, R. |
| Performance of an aircraft ground proximity warning system can be improved, especially where the performance of the aircraft itself has been degraded by a factor such as wind shear, by extending Mode 1 (24) and Mode 3 (32) warning envelopes down to within five feet of the ground. Additional improvements in warning performance can be made by monitoring flight path angle (46) when the aircraft is close to the ground. Warnings are based on a logic network (28) which uses radio altitude (12), barometric altitude rate (14), airspeed (50), stall margin (82), and a source (10) of signals representative of the angle of attack, vertical acceleration, and phase of flight of the aircraft, whereby a warning (30) is provided that the aircraft should pitch up except when the stall margin is below a predetermined value. | ||||||
| 53 | Embedded Ground Proximity Warning System for Helicopters | US12471607 | 2009-05-26 | US20100305784A1 | 2010-12-02 | Thomas E. Anderson; Thomas D. Anderson |
| A system for warning a pilot of a helicopter of a flight-into-terrain hazard includes a signal processing component that determines helicopter flight conditions by fusing data obtained from multiple flight condition data sources, a protection component that communicates with the signal processing component, determines whether a potential controlled flight-into-terrain hazard exists by computing predicted recovery trajectories based upon flight conditions and characteristics of the helicopter and decides upon a recovery trajectory, and a pilot interface component that provides a directive to the pilot to indicate the decided-upon recovery trajectory if multiple predicted recovery trajectories indicate a terrain impact will occur. | ||||||
| 54 | Method and system for providing ground proximity warnings | US09924894 | 2001-08-08 | US06452511B1 | 2002-09-17 | Wallace E. Kelly; Serdar Uckun |
| A conditional TAWS algorithm system and method for providing advanced warnings of potential CFIT situation which could result from predictable errant course changes. | ||||||
| 55 | A COMPUTERISED TRACKING AND PROXIMITY WARNING METHOD AND SYSTEM FOR PERSONNEL, PLANT AND EQUIPMENT OPERATING BOTH ABOVE AND BELOW THE GROUND OR THEIR MOVEMENT THEREBETWEEN | EP14900569.6 | 2014-09-10 | EP3186985A1 | 2017-07-05 | JONES, Jeanette |
| A computerized safety tracking and proximity warning method and system for personnel, plant and equipment operating both above and below the ground and moving therebetween comprising a computer adapted to receive wireless position information from transponders carried or worn by personnel, and affixed to plant or equipment via one or more wireless communication protocols to provide a seamless visual display of their relative positions whether above or below ground level or moving therebetween, and wherein an alarm is triggered to alert an operator or worker if the locations of the personnel and plant or equipment are within a predetermined and unsafe distance of each other. | ||||||
| 56 | Systems and methods for reducing nuisance alerts for helicopter enhanced ground proximity warning systems | EP07110841.9 | 2007-06-22 | EP1870676A2 | 2007-12-26 | ISHIHARA, Yasuo; BATEMAN, Charles, Donald. |
Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.
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| 57 | Systems and methods for reducing nuisance alerts for helicopter enhanced ground proximity warning systems | EP07110841.9 | 2007-06-22 | EP1870676B1 | 2011-07-20 | Ishihara, Yasuo; Bateman, Charles, Donald. |
| 58 | DETECTING A LOW PERFORMANCE TAKEOFF CONDITION FOR AIRCRAFT FOR USE WITH GROUND PROXIMITY WARNING SYSTEMS | EP01985949.5 | 2001-07-23 | EP1303737A2 | 2003-04-23 | JOHNSON, Steven |
| The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current clinb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second componnet that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach). | ||||||
| 59 | DETECTING A LOW PERFORMANCE TAKEOFF CONDITION FOR AIRCRAFT FOR USE WITH GROUND PROXIMITY WARNING SYSTEMS | EP01985949.5 | 2001-07-23 | EP1303737B1 | 2008-02-20 | JOHNSON, Steven |
| The present invention includes a system, method and computer program product for reducing nuisance warnings during low performance takeoff conditions. The system includes a first component that determines aircraft current clinb rate and potential climb rate based on aircraft vertical speed data and velocity information and a second componnet that adds the determined current climb rate and potential climb rate. The system also includes a third component that disables alerts, if the sum of the current climb rate and potential climb rate differ from a predetermined climb rate by a threshold amount and if the aircraft is supposed to be in a maximum thrust condition (e.g. takeoff, missed approach). | ||||||
| 60 | Aircraft ground proximity warning system with speed compensation | US606037 | 1975-08-20 | US3958218A | 1976-05-18 | Charles Donald Bateman |
| By using air speed as an input to a ground proximity warning system that includes: a signal representative of the time rate of change of the aircraft altitude with respect to ground; circuitry for limiting the amplitude of this signal; a signal that represents a time rate of change of the aircraft's barometric altitude; and circuitry for combining the amplitude limited signal, representing the time rate of change of the aircraft with respect to ground, with a signal that represents the aircraft's altitude over ground; the effective warning time is extended by increasing the allowable amplitude, of the signal representing rate of change of the aircraft with respect to the ground, in response to the speed of the aircraft. | ||||||
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