近地警告系统相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
41	GROUND PROXIMITY WARNING SYSTEM AND METHOD HAVING A REDUCED SET OF INPUT PARAMETERS	PCT/US0007976	2000-03-24	WO0057202A3	2001-01-18	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.
42	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).
43	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.
44	Positioning and ground proximity warning method and system thereof for vehicle	US241164	1999-02-01	US6157891A	2000-12-05	Ching-Fang Lin
A positioning and ground proximity warning method for vehicle includes the steps of outputting global positioning system signals to an integrated positioning/ground proximity warning system processor; outputting an inertial navigation solution to an integrated positioning/ground proximity warning processor; measuring air pressure, and computing barometric measurements which is output to the integrated positioning/ground proximity warning processor; measuring time delay between transmission and reception a radio signal from a terrain surface, and computing radio altitude measurement which is output to the integrated positioning/ground proximity warning processor; accessing a terrain database for obtaining current vehicle position and surrounding terrain height data which is output to the integrated positioning/ground proximity warning processor; and receiving the position, velocity and time information or said pseudorange and delta range measurements of said global positioning system, the inertial navigation solution, the radio altitude measurement, the radio altitude measurement, and the current vehicle position and surrounding terrain height data, and computing optimal positioning solution data and optimal ground proximity warning solution data.
45	Ground proximity warning system having modified terrain closure rate warning on glide slope approach	US512208	1983-07-08	US4684948A	1987-08-04	Charles D. Bateman
An aircraft ground proximity warning system having an excessive terrain closure warning mode and a below glide slope warning mode monitors the glide slope signal and modifies the terrain closure warning envelope to accept a lesser terrain clearance when the aircraft is within the glide slope beam.
46	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.
47	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).
48	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.
49	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).
50	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.
51	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.
52	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.

53	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.
54	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.
55	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.
56	Ground proximity warning system utilizing radio and barometric altimeter combination	US3715718D	1970-08-11	US3715718A	1973-02-06	ASTENGO R
A ground proximity warning system for an aircraft which produces a warning signal when the rate of descent of the aircraft exceeds a limiting value determined by the aircraft altitude. The rate of descent of the aircraft is calculated from a combination of measurements of the altitude of the aircraft above ground and the barometric altitude of the aircraft. A signal representing the rate of change of the altitude of the aircraft above ground is limited, to minimize false warnings as a result of surface irregularities. The barometric portion of the system is disabled during take-off run and the initial portion of the aircraft climb-out to avoid a false warning resulting from an increased barometric pressure condition during this maneuver. The limits on the aircraft altitude rate signal are modified in accordance with the flight mode of the aircraft, to reduce the sensitivity of the warning system during the final stage of a landing approach. The warning system provides an alarm to the pilot which is an audio tone modulated at a low frequency repetition rate. A soft warning is actuated when the sink rate of the aircraft exceeds a desired level for the altitude at which the aircraft is operating. If the aircraft is also below a limiting altitude, a hard warn signal is provided. The repetition rate of the warning signal, while in a soft warn condition, is a function of the difference between the altitude of the aircraft and the altitude at which the sink rate would be proper. A complementary filter with which the altitude rate signals are combined, includes an operational amplifier connected in an unloading amplifier configuration with a resistive circuit connecting one input signal with the amplifier and a capacitive circuit connecting the other input signal with the amplifier, the resistive and capacitive input circuits forming a low pass filter for the first signal and a high pass filter for the second signal.
57	METHOD OF ALERT CALCULATION FOR AN AIRCRAFT GROUND PROXIMITY WARNING SYSTEM	US12900747	2010-10-08	US20110251741A1	2011-10-13	Stéphane FLEURY; Laurent FLOTTE; Nicolas MARTY; Erick RAKOTOARISOA
The invention relates to a method of alert calculation for an aircraft obstruction proximity warning system including a step for detecting a hazardous flight situation capable of triggering an alert as a function of a data signal representing the change in height below the aircraft, including, prior to the step of detection, a step for converting the data signal representing the change in height as a function of information representative of the vertical profile of the obstructions below the aircraft.
58	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).
59	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).
60	SYSTEM AND METHOD FOR GROUND PROXIMITY WARNING WITH ENHANCED OBSTACLE DEPICTION	US10907934	2005-04-21	US20060238402A1	2006-10-26	Ratan Khatwa
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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