AIRCRAFT ENGINE HEALTH MONITORING SYSTEM AND METHOD

Abstract

A system and method are provided that monitors ground level ambient air in an airport ground environment while aircraft equipped with electric taxi drive systems and ground level visual monitoring assemblies are driven with the electric taxi drive systems during ground travel. Monitoring assemblies with detection elements having configurations similar to pitot tubes modified with a sensor array are provided to generate data about components in the ground level ambient air identified to adversely affect aircraft engine health. The detection elements may be cooperatively mounted with the ground level visual monitoring assemblies. Ambient air flow is directed into the detection elements to contact the sensor array during electric taxi drive system-powered ground travel. Real time data related to the identified components generated by the sensor array is processed and analyzed, engine health is monitored, and a predictive scheduled of engine maintenance may be developed from the analyzed real time data.

Claims

1. An on-aircraft system that monitors ground level ambient air in an aircraft ground travel environment and provides real time data during aircraft ground travel for components in the ground level ambient air identified to adversely affect aircraft engine health to improve the monitoring of aircraft engine health, comprising: a. an aircraft equipped with landing gear wheel-mounted electric taxi drive systems operable to power aircraft ground movement and drive said aircraft on a ground surface in said ground travel environment; b. one or more ground level visual assemblies operable to provide a view of said aircraft's ground level environment mounted on or adjacent to a ground facing surface of said aircraft; c. at least one detection element mounted cooperatively with at least one of said one or more ground level visual assemblies in fluid contact with said ground level ambient air in said aircraft's ground level environment and configured to direct a flow of said ground level ambient air through said detection element to sensor means for generating real time data about said components in said flow of ground level ambient air identified to adversely affect aircraft engine health; and d. a processor in data transmission connection with said sensor means operable to receive and analyze said real time data generated by said sensor means and to communicate said analyzed real time data relating to said components identified to adversely affect aircraft engine health in said flow of ground level ambient air.

2. The system of claim 1, wherein each said detection element comprises an intake end open to said flow of ground level ambient air, a sensor end supporting said sensor means, and a channel in fluid communication between said intake end and said sensor end configured to direct said flow of ground level ambient air from said intake end to said sensor end to contact said sensor means, said sensor means being programmed to detect said components in said flow of ground level ambient air identified to adversely affect aircraft engine health and to generate said real time data transmitted to said processor.

3. The system of claim 2, wherein said sensor means comprises a sensor array comprising a single sensor programmed to generate said real time data for a single identified component in said ground level ambient air or a sensor array comprising multiple sensors, each of said multiple sensors being programmed to generate real time data for a different one of multiple components identified in said ground level ambient air.

4. The system of claim 3, wherein said detection element further comprises one or more transmission wires connecting said single sensor or said sensor array to a power source and to said processor.

5. The system of claim 1, wherein each of said one or more ground level visual assemblies comprises an aerodynamic frame mounted on said aircraft ground facing surface to form an enclosed space, a housing within said frame supporting a visual information-providing device positioned within said housing and said frame to obtain said view of said aircraft's ground level environment, and said detection element is supported by said frame in said fluid contact with said flow of ground level ambient air and said sensor means is located within said enclosed space.

6. The system of claim 5, wherein said visual information-providing device comprises a camera, a video camera, or a scanning LiDAR device.

7. The system of claim 4, wherein each of said ground level visual assemblies and said cooperatively mounted detection elements share a common power and signal transmission wire connected to said power source and to said processor.

8. The system of claim 2, wherein said detection element has a linear configuration between said intake end and said sensor end, and said channel provides a linear flow of said ground level ambient air along a linear path from said intake end to said sensor end to contact said sensor means.

9. The system of claim 2, wherein said detection element has a right angle configuration between said intake end and said sensor end, with a linear intake section and a sensor portion oriented perpendicularly to said linear intake portion, and said channel being configured to direct a linear flow of said ground level ambient air into said intake end and along a linear path through said intake portion and to direct a right angle flow of said ground level ambient air from said intake portion along a right angle path through said sensor portion to contact said sensor means mounted in said sensor portion.

10. The system of claim 1, wherein said identified components in said flow of ground level ambient air comprise at least sand, dust, particles from FOD, corrosion-producing chemicals, deposit-producing chemicals, and moisture.

11. A method that monitors ground level ambient air of an aircraft's ground level environment during ground travel, generates real time data for components detected in the ground level ambient air identified to adversely affect engine health, and uses the real time data to improve aircraft engine health, comprising: a. providing an aircraft equipped with landing gear wheel-mounted electric taxi drive systems operable to drive the aircraft during ground travel and mounting on or adjacent to a ground-facing surface of the equipped aircraft one or more ground level visual assemblies operable to provide a view of the aircraft's ground level environment during ground travel for transmission to a cockpit of the aircraft; b. providing at least one detection element cooperatively mounted with at least one of the ground level visual assemblies in fluid contact with the ground level ambient air in the aircraft's ground level environment during ground travel and configured to direct a flow of the ground level ambient air through the detection element to sensor means for generating real time data about components in the ground level ambient air identified to adversely affect aircraft engine health of the aircraft, and positioning the detection element with an intake end directing a flow of the ground level ambient air to the sensor means as the aircraft is driven with the electric taxi drive systems; and c. transmitting the generated real time data from the sensor to a processor programmed to analyze the transmitted information and determine parameters of the identified components, and communicating information relating to the determined parameters to an engine maintenance service provider or compiling the information relating to the determined parameters in a historical health record of the aircraft's engines.

12. The method of claim 11, wherein the sensor means comprises a sensor array programmed to detect aircraft environment meteorological and ground level ambient air composition information, and further comprising determining aircraft environment meteorological information and ground level ambient air composition information to be identified in real time as the aircraft is driven on the ground with the electric taxi drive systems, generating the real time meteorological and ground level ambient air composition information by the sensor array, transmitting the generated real time information to the processor, and analyzing aircraft engine health based on the generated aircraft environment meteorological and ground level ambient air composition information.

13. The method of claim 12, further comprising developing a schedule of predictive maintenance for engines on the equipped aircraft based on the analyzed aircraft engine health and the generated real time aircraft environment meteorological and ground level ambient air composition information.

14. The method of claim 11, further comprising communicating information relating to the determined parameters to an engine maintenance service provide and developing a schedule of predictive maintenance for engines on the equipped aircraft based on the communicated information.

15. The method of claim 11, further comprising compiling the information relating to the determined parameters in a historical health record of engines on the equipped aircraft and developing a schedule of predictive maintenance for the engines on the equipped aircraft based on the historical health record.

16. An on-aircraft system for monitoring ground level ambient air in an aircraft ground travel environment and providing real time data during aircraft ground travel about components in the ground level ambient air identified to adversely affect aircraft engine health to improve the monitoring of aircraft engine health, comprising: a. an aircraft equipped with landing gear wheel-mounted electric taxi drive systems operable to power aircraft ground movement and drive said aircraft on the ground in said ground travel environment; b. one or more monitoring assemblies comprising a detection element and sensor means for generating real time data about said components in ground level ambient air identified to adversely affect aircraft engine health mounted on said equipped aircraft with said detection element in fluid contact with said ground level ambient air in said aircraft's ground level environment and oriented to direct a flow of said ground level ambient air through said monitoring assembly to said sensor means during electric taxi drive system-powered aircraft ground travel; and c. a processor in data transmission connection with said sensor means operable to receive and analyze said real time data generated by said sensor means and to communicate or store said analyzed real time data about said components identified to adversely affect aircraft engine health in said flow of ground level ambient air.

17. The system of claim 16, wherein said sensor means comprises a sensor array comprising a single sensor programmed to generate said real time data for a single identified component in said ground level ambient air or a sensor array comprising multiple sensors, each of said multiple sensors being programmed to generate real time data for a different one of multiple components identified in said ground level ambient air.

18. The system of claim 17, wherein said detection element comprises an intake end in fluid contact with said ground level ambient air in said aircraft's ground level environment and oriented to direct a flow of said ground level ambient air through a channel in said monitoring assembly to said sensor array.

19. The system of claim 18, wherein said channel has a linear configuration and is oriented to direct said flow of ground level ambient air from said intake end to said sensor array along a linear path.

20. The system of claim 18, wherein said channel has a right angle configuration with a linear portion aligned with said flow of ground level ambient air and a right angle portion perpendicular to said linear portion and is oriented to direct said flow of ground level ambient air from said intake end along a linear path through said linear portion and through said right angle portion along a path at a right angle to said linear portion to said sensor array located in said right angle portion.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0013] FIG. 1 illustrates a front and side perspective view of an aircraft equipped with electric taxi drive systems and with the ground level visual monitoring assemblies and the detection elements of the present invention;

[0014] FIG. 2 is a schematic illustration of one embodiment of an aircraft ground level visual monitoring assembly with a detection element supporting a sensor array cooperatively mounted with the ground level visual monitoring assembly in an orientation that directs a flow of ambient air to the sensor array in accordance with the present invention; and

[0015] FIG. 3 is a schematic illustration of another embodiment of a detection element configured to intake a flow of ambient air and direct the ambient airflow to contact a sensor array and monitor the ambient air in an airport ground environment to detect and identify substances and materials known to adversely affect aircraft engine health in accordance with the system and method of the present invention.

DESCRIPTION OF THE INVENTION

[0016] Aircraft currently move into, out of, and within airport ramp environments that may be congested with other aircraft, ground service vehicles, and equipment. The ambient air in this congested ground level environment may be the source of environmental conditions, substances, and materials that may adversely impact aircraft engine health. At the present time, airport ramp areas and aircraft engines are monitored to determine levels of engine exhaust gases and combustion products so that engine operation may be adjusted to reduce engine emissions and improve air quality. Ambient air in an airport ramp area, however, is not currently monitored with an on-aircraft system that detects the presence of and determines concentrations and other information for identified substances and materials in the ambient air known to adversely affect aircraft engine health. The present invention provides an on-aircraft system and a method that monitors ambient air to detect and determine concentrations and other relevant information relating to such identified substances and materials. This system and method may be used on aircraft that are equipped with landing gear wheel-mounted electric taxi drive systems to power ground travel that may also be equipped with ground level visual monitoring assemblies operative to provide visual information about the aircraft's adjacent ground level environment as the aircraft is driven on the ground in the ramp area and elsewhere with the electric taxi drive systems.

[0017] “Electric taxi drive systems” and “electric taxi systems,” as used herein, refer to pilot-controllable landing gear wheel-mounted drive systems used to drive aircraft independently of and without reliance on operation of aircraft main engines and tugs or external tow vehicles. Electric taxi drive systems may include landing gear wheel-mounted electric drive motors, gear or roller traction drive systems, clutches, and other components activatable to power landing gear wheels and drive the aircraft during ground travel in response to pilot control. An example of one electric taxi drive system developed by Applicant to drive an aircraft during ground travel without reliance on operation of the aircraft's main engines or attachment to tugs is described in commonly owned U.S. Pat. No. 10,308,352, the disclosure of which is fully incorporated herein in its entirety by reference. Other drive systems using drive motors that are not electric, including, for example, hydraulic or pneumatic drive motors, may also drive aircraft in connection with the system and method for monitoring the ambient air in the airport ground environment of the present invention and are contemplated to be included within the terms “electric taxi drive systems.” An electric taxi drive system may be mounted completed within a volume defined by walls of a landing gear wheel in one or more nose or main landing gear wheels. In a preferred embodiment, electric taxi drive systems are mounted completely within defined wheel wall volumes in both nose landing gear wheels and are controlled by a pilot or flight crew from the aircraft cockpit with controls designed to operate the electric taxi drive system, power the nose landing gear wheels, and drive the aircraft during ground travel without reliance on the aircraft's main engines and external assistance from tugs. During electric taxi drive system-powered ground travel, aircraft engines are not operating, and adverse effects on aircraft engine health produced by engine ingestion of FOD may be avoided.

[0018] The terms “ramp” or “ramp area” are used herein to refer to the airside area at an airport that is intended to accommodate aircraft for the loading and unloading of passengers, mail, cargo, fueling, parking, or maintenance and is synonymous with the term “apron,” which is also used to identify this area at an airport.

[0019] “Ground level visual monitoring assemblies,” as used herein, provide visual information about an aircraft's adjacent ground level environment as the aircraft is driven on the ground with the electric taxi drive systems and may include camera assemblies specifically designed for aircraft use. Camera assemblies may be used alone or with other visual information-providing devices, for example LiDAR (light detection and ranging) or LADAR (laser detection and ranging) devices that may provide a three-dimensional field of view of a designated target area. Alternatively, a visual information-providing device other than a camera may be used alone in the ground level visual monitoring assemblies. Other visual information-providing devices, such as radar and the like, may also be used in the ground level visual monitoring assemblies. “LiDAR” as used herein is also intended to encompass “LIDAR,” “LADAR,” radar, and other visual information-providing devices. Applicant's commonly owned U.S. Pat. No. 10,964,221, issued 30 March 2021, the disclosure of which is fully incorporated herein in its entirety by reference, describes such devices in connection with an aircraft collision avoidance system.

[0020] Referring to the Drawings, which are not drawn to scale, FIG. 1 illustrates, from a front and side perspective, an aircraft 10 equipped with the ambient air and engine health monitoring system of the present invention. The aircraft 10 has a nose landing gear 12 with a pair of tire-supporting wheels 14 and a pair of main landing gears 16, each with a pair of tire-supporting wheels 18; the aircraft is shown on a ground surface 20 in an airport ramp area. The aircraft 10 is equipped with pilot-controllable electric taxi drive systems that power aircraft ground movement without reliance on operating engines and tow vehicles. Each electric taxi drive system may include a pair of electric drive motors 22 mounted completely within the wheel volume in each nose landing gear wheel 14 shown on aircraft 10. One or more electric taxi drive systems (not shown) may also or alternatively be mounted within one or more of the main landing gear wheels 18. The electric taxi drive system is controlled by a pilot or the crew of the aircraft from the aircraft cockpit 32 to drive an arriving aircraft into the ramp area, maneuver the aircraft within the ramp area into a parking location, and drive a departing aircraft forward or in reverse out of the ramp area.

[0021] The nose landing gear 12 and the main landing gears 16 on the aircraft 10 are the retractable type of landing gears that are stowed in fuselage or wing wheel well compartments (not shown) while in the aircraft 10 is in flight. This removes the landing gears 12, 16 out of the aircraft's slipstream so that they maintain the aircraft's aerodynamic profile and do not cause parasitic drag during flight. Doors 24, which can be clearly seen on the nose landing gear 12, and are not seen, but are also present, on the main landing gears 16, open to allow the nose and main landing gears to extend upon landing so that tires (14, 18) on the tire-supporting wheels may contact the ground surface 20. To maintain the aircraft's aerodynamic profile, the landing gears are retracted after takeoff, and the doors are closed during flight.

[0022] The pilot and crew driving the aircraft 10 on the ground with the electric taxi drive system have a relatively limited view and cannot see all of the aircraft's exterior or all of the ramp area environment surrounding the aircraft from the cockpit 32. The aircraft may be equipped with a number of ground level visual monitoring assemblies, indicated schematically at 26, 28, and 30 on aircraft 10, to enable the pilot and crew to see portions of the aircraft's ground level exterior that are not visible from the cockpit 32. The ground level visual monitoring assemblies of the present invention may use cameras, including video cameras, and/or LiDAR visual information-providing devices, which may be scanning devices. A ground level visual monitoring assembly 26 may be positioned just aft of the wheel well of the nose landing gear 12, and/or another ground level visual monitoring assembly 28 may be positioned just aft of the main landing gears on the exterior of the aircraft fuselage. An additional location for a ground level visual monitoring assembly 30 may be under the aircraft tailskid; the tailskid is not clearly visible in FIG. 1. The ground level visual monitoring assemblies 26, 28, and 30 may be connected by wiring and/or other suitable connections to a source of power (not shown) and to a processor 34, shown schematically on aircraft 10. Ground level visual monitoring assemblies may also be positioned in other suitable locations on the exterior of aircraft 10.

[0023] Any structures on the aircraft fuselage exterior in the foregoing locations may be located in the aircraft slipstream, which requires the configurations of the ground level visual monitoring assemblies 26, 28, and 30 to be aerodynamic and not interfere with aircraft's slipstream. Another approach is to design the ground level visual monitoring assemblies 26, 28, and 30 with supporting structure that makes them extendible from and retractable into the fuselage so that they may be extended to function only during electric taxi drive system-powered aircraft ground movement and retracted during flight. An aerodynamically configured fairing or like structure (not shown) may be provided to cover the ground level visual monitoring assembly locations on the fuselage exterior during flight. The ground level visual monitoring assemblies may also be designed to be pop-down or pop-out devices that extend from the fuselage exterior when in use and are pulled back into the interior when not is use or when the aircraft is in flight.

[0024] FIG. 2 shows one embodiment of a ground level visual monitoring assembly 40 that has been modified for use with the engine health monitoring system of the present invention. The ground level visual monitoring assembly 40 is intended to be mounted on the external surface of the underside of an aircraft fuselage, such as where the ground level visual monitoring assemblies 26, 28, and 30 are shown in FIG. 1. A frame 42, which has an aerodynamic form, is attached to the aircraft fuselage skin 44 with suitable attachment devices (not shown). This embodiment may be permanently positioned to extend from the aircraft surface. Other aerodynamic forms besides the one shown may be used. This embodiment may additionally be modified so that the frame 42 pivots between the position exterior to the aircraft fuselage shown and a position inside the fuselage interior. As noted above, in an additional embodiment, the ground level visual monitoring assemblies 26, 28, and 30 may have a “pop-out” or “pop-down” configuration that extends from and retracts into the aircraft fuselage interior. An exterior form of the frame 42 that is less aerodynamic than that shown may be covered with an aerodynamic fairing or the like.

[0025] A housing 46 may be provided to support a camera, a video camera, a scanning LiDAR device, and/or another visual information-providing device 48 within the frame 42. Depending on the device, a housing 46 may not be required. A section of the frame 42, indicated by the bracket 47, may be formed of a transparent material to enable the camera, LiDAR device, or other visual information-providing device to remain protected within the frame 42 and still “see” the area to be visualized. The housing 46 and visual information-providing device 48 in FIG. 2 are schematic representations. Both may have different shapes and/or configurations than that shown. A separate housing may not be needed for some visual information-providing devices.

[0026] FIG. 2 shows one embodiment of a single detection element 50 mounted through the frame 42 so that an ambient air intake end 52 protrudes through the frame 42 to be in contact with the flow of ambient air surrounding the aircraft 10, represented by arrow a, around the ground level visual monitoring assembly. An opposite sensor end 54 of the detection element 50 supports a sensor array 55 that may include a single sensor or multiple sensors programmed to detect one or more identified substances or materials in the ambient air. The identified substances or materials to be detected are preferably those substances and materials whose presence in the ambient air is known to adversely affect aircraft engine health. Power and signal wires 56 may extend from the sensor end 54 of the detection element 50 and may join with wires 58 from the camera, LiDAR device, or other visual information-providing device 48, for example to connect with a processor, such as processor 34 in FIG. 1. Alternatively, a common power and signal wire (not shown) may be provided for both the detection element 50 and the visual information-providing device 48. Additional locations for the detection element 50 may also be appropriate, depending on the configuration of the frame 42. The intake end 52 of the detection element 50 must be positioned so that ambient air flows into the detection element while the aircraft is moving. As noted, the arrow a represents the direction of the flow of ambient air into the intake end of the detection element 50.

[0027] As the aircraft 10 is driven on the ground with the electric taxi drive systems, ambient air surrounding and contacting the aircraft flows into the intake end 52 of the detection element 50 and is directed to the sensor end 54 to contact the sensor array 55. The sensor array is programmed to detect, in real time, the presence and other desired information related to any of the identified substances or materials in the flow of ambient air in the detection element. The system may be programmed to detect concentrations of identified substances and materials, as well as any other information that may relate to effects of the identified substances and materials on engine health.

[0028] One or more of the ground level visual monitoring assemblies 26, 28, and 30 may be modified to support one or more detection elements 50 so that real time data from information produced by the sensor array 55 may be transmitted to and generated by the processor 34. It is contemplated that at least the ground level visual monitoring assembly 26 located closest to the aircraft nose will be modified to support a detection element 50. Although only a single detection element 50 is shown, multiple detection elements may be provided in a single ground level visual monitoring assembly.

[0029] It is also contemplated that detection elements 50 may be modified to be mounted in locations on the aircraft other than in the cooperative mounting with a ground visual monitoring assembly as shown in FIG. 2. Advantageously, mounting a detection element within a ground level visual monitoring assembly 40, as shown in FIG. 2, provides a protected environment for the detection element sensor end 54 and the sensor array 55, as well any power and wire transmission connections.

[0030] It is further contemplated that the numbers of different sensors in the sensor array 55 may be varied, depending in part on the number of detection elements 50 used. As noted, the sensor array may have a single sensor or multiple sensors. If only one or a small number of detection elements are used, the sensor array may have multiple sensors, while if a large number of detection elements are used, each detection element may have a single sensor in the sensor arrays.

[0031] The detection element may be a pitot type tube that has been modified to mount an array of sensors within an end of the pitot type tube. FIG. 3 illustrates schematically one kind of pitot tube 60 that may be modified to form a second embodiment of a detection element useful in the engine health monitoring system and method of the present invention. In this embodiment, ambient air flow, represented by arrows a, enters a channel 63 through an opening 61 in the detection element intake end 62. The airflow is directed to contact a sensor array 65 in a sensor end 64 of the detection element 60. The detection element 60 may have a different configuration from that of detection element 50. A power and/or transmission wire 66 is provided and may, like the wire 56 in detection element 50, be a common power and signal wire for the detection element 60 and a camera, LiDAR device, or other visual information-providing device. Other designs of pitot type tubes that can direct a flow of the ambient air produced as an aircraft is driven on the ground with electric taxi drive systems into the tube to contact a sensor array and that can be mounted in a ground level visual monitoring assembly or on an aircraft exterior surface as shown and described herein may also be modified to function as a detection element in accordance with the present invention.

[0032] The ambient airflow directed into the detection element (50, 60) to contact the sensor array (55, 65) may be analyzed to produce a range of information relating potential effects on engine health. As noted above, the presence of identified substances and materials in the ambient air known to adversely affect aircraft engine health may be detected by the array of sensors, and specific individual sensors that detect specific ones of the identified substances and materials may be included in the array of sensors. Such substances and materials may include, for example, sand, dust, and particles from FOD, as well as corrosion-producing chemicals and deposit-producing chemicals. These substances, which may be present in ramp ambient air, may cause deterioration of engine performance over time. Physical distortion of engine parts may be caused by the cumulative effects of FOD, corrosion, erosion, and deposit build-up. It is contemplated that the ambient airflow will be analyzed for concentrations of selected ones of these substances and materials that have been established to produce the foregoing adverse effects. Ambient airflow may also be analyzed for air quality and for differences from standard meteorological conditions. Optimal engine operating parameters may be affected by barometric pressure, air moisture content, air temperature, and other environmental conditions. It is contemplated that sensors that detect these conditions in real time may be included in the array of sensors.

[0033] The real time data produced by the array of sensors (55, 65) may be transmitted to a processor, such as processor 34. The processor uses suitable analytical algorithms to process and analyze the real time data from the array of sensors and to generate information relating to the ambient air, for example to detect the presence of FOD and other substances and materials in the ambient air that will, over time, produce physical distortion of engine components and/or to determine the real time meteorological conditions that might adversely affect engine performance. The analyzed real time data obtained may be matched with other aircraft data, including that from the aircraft GPS, from time stamps, and from engine thrust. All of this, and other, aircraft environmental and matched data may be used to improve engine health monitoring and to develop schedules for engine predictive maintenance.

[0034] The engine health monitoring system and method of the present invention can enable airlines and maintenance, repair, and overhaul providers to collect and analyze unique environmental data in real time while an aircraft is being driven on the ground with the electric taxi drive systems. A history of diagnostic data may be produced for an aircraft that will facilitate the development of a schedule of predictive engine maintenance. When a history of diagnostic data, such as that possible with the system and method of the present invention, is available, and engine health monitoring and predictive maintenance are implemented, instances of unscheduled aircraft groundings and time out of service may be significantly minimized and potentially eliminated.

[0035] In accordance with the present method of monitoring engine health, an aircraft equipped with electric taxi drive systems for ground movement and with ground level visual monitoring assemblies is additionally equipped with detection elements, as described and shown in connection with FIGS. 2 and 3, that may be supported by modified ground level visual monitoring assemblies or mounted separately on the aircraft. Aircraft environmental meteorological information and ambient air composition information to be detected is identified, and sensors capable of detecting the identified information are provided in an array of sensors in one or more detection elements. The aircraft is driven with the electric taxi systems during ground travel, and a flow of ambient air is produced by the moving aircraft. This flow of ambient air is directed into the detection element and flows through the detection element to contact the array of sensors in real time as the aircraft moves. Information from the array of sensors is transmitted in real time to a processor, where the information is processed using analytical algorithms appropriate for the sensed information and analyzed to generate desired data. The desired data may include, for example, qualitative identification of substances and materials known to affect engine health in the ambient air, as well as quantitative information relating to concentrations of these substances and materials. Comparisons of airflow quality and differences from standard meteorological conditions may also be included in the desired data. The desired data obtained may be stored to produce a historical record for the aircraft. The data may also or alternatively be communicated to a maintenance, repair, and overhaul provider, if appropriate, and/or to others with responsibility for monitoring and maintaining engine health. Further, a schedule of predictive maintenance for the aircraft may be developed from historical or current data.

[0036] While the present invention has been described with respect to preferred embodiments, this is not intended to be limiting, and other arrangements and structures that perform the required functions are contemplated to be within the scope of the present invention.

INDUSTRIAL APPLICABILITY

[0037] The aircraft engine health monitoring system and method of the present invention will find its primary applicability in improving the generation and collection of data from ambient ground level air relating to aircraft engine health and in developing schedules of predictive maintenance from the data to avoid and minimize unscheduled engine maintenance and time out of service of the monitored aircraft.