| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | PCT/US1986001749 | 1986-08-25 | WO1987001356A1 | 1987-03-12 | SUNDSTRAND DATA CONTROL, INC.; 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). | ||||||
| 22 | GROUND PROXIMITY WARNING SYSTEM AND METHOD HAVING A REDUCED SET OF INPUT PARAMETERS | PCT/US2000/007976 | 2000-03-24 | WO00057202A2 | 2000-09-28 | |
| 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. | ||||||
| 23 | GROUND PROXIMITY APPROACH WARNING SYSTEM WITHOUT LANDING FLAP INPUT | PCT/US1988001102 | 1988-04-05 | WO1988008182A1 | 1988-10-20 | SUNDSTRAND DATA CONTROL, INC.; 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). | ||||||
| 24 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | PCT/US1985001315 | 1985-07-10 | WO1986001022A1 | 1986-02-13 | SUNDSTRAND DATA CONTROL, INC.; 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. | ||||||
| 25 | 無人飛行機の接近検出装置及び接近警報システム | JP2014212536 | 2014-10-17 | JP6079744B2 | 2017-02-15 | 樋口 智朗 |
| 26 | ROTARY WING AIRCRAFT PROXIMITY WARNING SYSTEM WITH A GEOGRAPHICALLY BASED AVOIDANCE SYSTEM | PCT/US2007086331 | 2007-12-04 | WO2008147460A2 | 2008-12-04 | MATUSKA DAVID G; ANTTILA DONALD S; KRONAUER BRAD J |
| A proximity warning system which controls a transmission power output of the proximity sensor suite in response to an aircraft position being within a predefined minimum threshold of at least one sensitive area. | ||||||
| 27 | APPARATUS, METHOD AND COMPUTER PROGRAM PRODUCT FOR HELICOPTER GROUND PROXIMITY WARNING SYSTEM | PCT/US2001/017228 | 2001-05-25 | WO01090694A2 | 2001-11-29 | |
| An apparatus, method and computer program product has a first terrain awareness mode and a second terrain awareness mode selectable by the pilot. | ||||||
| 28 | GROUND PROXIMITY WARNING SYSTEM AND METHOD | EP03814370.7 | 2003-12-22 | EP1588228A2 | 2005-10-26 | REYNOLDS, Zachary; RIDENOUR, Richard; STONE, Cyro; ROWLAN, Stacey |
| Methods and systems are disclosed for preventing aircraft collisions with forward looking terrain avoidance (FLTA) functionality based on a terrain avoidance profile used to evaluate potential terrain threats based on the projected flight path of an aircraft in flight, and a clear terrain profile to determine whether the terrain threat has been cleared. If the terrain avoidance profile conflicts with terrain, a collision threat may exist whereby the pilot is notified and a terrain avoidance maneuver is executed. During the terrain avoidance maneuver the clear terrain profile extends in a direction substantially parallel with the horizon at or near the present altitude of the aircraft to check whether it is safe to return to the previous flight path angle or otherwise end the terrain-avoiding maneuver. When the clear terrain profile no longer conflicts with the terrain threat, a terrain clear indicator is then issued to the pilot. | ||||||
| 29 | PITCH ANGLE ALERTING DEVICE FOR GROUND PROXIMITY WARNING SYSTEM (EGPWS) | PCT/US2002/010369 | 2002-04-01 | WO2003008908A1 | 2003-01-30 | BATEMAN, Peter |
A ground proximity warning system including a pitch angle alerting device, the pitch angle alerting device including warning logic having an input that is structured to receive a signal that is representative of the indicated pitch angle of the aircraft, the warning logic being structured to determine a difference between a pitch angle signal received on the input and a predetermined threshold, the warning logic being structured also to output a signal representative of the difference between the two signals; and an advisory indication generator coupled to accept the output of the warning logic, the advisory indication generator being structured to generate an advisory indication signal as a function of the difference between the two signals. |
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| 30 | VARIABLE ENHANCED GROUND PROXIMITY WARNING SYSTEM LOOK-AHEAD OFFSET AND SUB-OFFSET | PCT/US2001/023738 | 2001-07-27 | WO2002059705A1 | 2002-08-01 | JOHNSON, Steve; ISHIHARA, Yasuo; CONNER, Kevin |
The present invention includes a system, method and computer program product for reducing nuisance warnings during low altitude flight conditions and in the presence of low position uncertainty. The system includes a first component that determines whether the aircraft is in a low altitude flight condition and a second component that determines the position, positional uncertainty, and the heading. The system also includes a third component that attenuates and refines the look-ahead envelope in accord with the determined condition of flight and positional uncertainty. |
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| 31 | APPARATUS, METHOD AND COMPUTER PROGRAM PRODUCT FOR HELICOPTER GROUND PROXIMITY WARNING SYSTEM | PCT/US0117228 | 2001-05-25 | WO0190694A3 | 2002-04-18 | ISHIHARA YASUO; CONNER KEVIN |
| An apparatus, method and computer program product has a first terrain awareness mode and a second terrain awareness mode selectable by the pilot. | ||||||
| 32 | SYSTEM AND METHOD FOR GROUND PROXIMITY WARNING WITH ENHANCED OBSTACLE DEPICTION | PCT/US2006/014453 | 2006-04-17 | WO2006115884A1 | 2006-11-02 | KHATWA, Ratan |
Systems and methods for displaying ground obstructions on a visual display are disclosed. In an embodiment, a ground proximity warning system includes at least one aircraft sensor system operable to acquire aircraft data and a ground proximity warning computer coupled to the aircraft sensor system to process the aircraft data that generates ground proximity warning data corresponding to a sensed ground obstruction. An indicating system including a visual display device then presents an image of a visual symbol corresponding to the sensed ground obstruction. At least one of the computer and the visual display device is controllable to selectively display the visual symbol. |
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| 33 | System and method for real-time data logging of enhanced ground proximity warning system | JP2011173791 | 2011-08-09 | JP2012035838A | 2012-02-23 | CONNER KEVIN J; OSTROM GARY A; BATEMAN C DON |
| PROBLEM TO BE SOLVED: To provide a system and a method for real-time data logging of an enhanced ground proximity warning system.SOLUTION: The system and method perform efficient, inexpensive data logging of aircraft sensor data. An example system 20 on board an aircraft 18 includes: a plurality of data sources 34 that provide sensor data associated with a plurality of avionic components; a line replaceable processing unit 24 that is in signal communication with the plurality of data sources via one or more databuses 32; a wireless router 26 connected to the line replaceable processing unit via a data cable; and a portable data unit 28 in wireless data communication with the wireless router. The wireless router receives at least a portion of the sensor data from the line replaceable processing unit and sends the received sensor data to the portable data unit. | ||||||
| 34 | GROUND PROXIMITY WARNING SYSTEM TERRAIN CLASSIFICATION SYSTEM | EP87905070 | 1987-07-15 | EP0274525A4 | 1991-05-15 | BATEMAN, CHARLES, D. |
| 35 | Sytstems and methods for selectively altering a ground proximity message | EP07103498.7 | 2007-03-05 | EP1832850B1 | 2015-12-02 | Ishihara, Yasuo; Johnson, Steve C. |
| 36 | APPARATUS, METHOD AND COMPUTER PROGRAM PRODUCT FOR HELICOPTER ENHANCED GROUND PROXIMITY WARNING SYSTEM | PCT/US0117105 | 2001-05-25 | WO0190693A3 | 2002-04-18 | ISHIHARA YASUO |
| An apparatus, method and computer program product for alerting rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft. | ||||||
| 37 | APPARATUS, METHOD AND COMPUTER PROGRAM PRODUCT FOR HELICOPTER ENHANCED GROUND PROXIMITY WARNING SYSTEM | PCT/US2001/017105 | 2001-05-25 | WO01090693A2 | 2001-11-29 | |
| An apparatus, method and computer program product for alerting rotary wing aircraft of potentially hazardous proximity to terrain also reduces nuisance warnings and provides a terrain display consistent with the unique performance capabilities of such aircraft. | ||||||
| 38 | GROUND PROXIMITY WARNING SYSTEM AND METHOD HAVING A REDUCED SET OF INPUT PARAMETERS | EP00937508.0 | 2000-03-24 | EP1163534B1 | 2009-09-23 | 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. | ||||||
| 39 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE | EP86905565.0 | 1986-08-25 | EP0233941A1 | 1987-09-02 | BATEMAN, Charles, D.; GLOVER, John, H.; MULLER, Hans, R. |
| On améliore l'efficacité d'un système d'avertissement de proximité du sol pour un aéronef, en particulier lorsque le comportement de l'aéronef lui-même s'est détérioré en raison, par exemple, d'un gradient vertical de vent, en portant les limites d'alarme relatives à une vitesse de descente excessive (24) et à une montée négative après décollage (32) à cinq pieds du sol. Des améliorations supplémentaires peuvent être apportées à l'efficacité du système d'alarme en contrôlant l'angle de trajectoire de vol (100) lorsque l'aéronef est proche du sol, et en contrôlant la vitesse de changement d'altitude calculée par ordinateur (16), la phase de vol (208, 236), la déviation de pente radiogoniométrique (110), l'angle d'attaque (10) et la marge de décrochage (82). | ||||||
| 40 | GROUND PROXIMITY WARNING SYSTEM FOR USE WITH AIRCRAFT HAVING DEGRADED PERFORMANCE. | EP85904698 | 1985-07-10 | EP0190345A4 | 1987-01-20 | 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. | ||||||
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