COLLISION AVOIDANCE SYSTEM

Abstract

A collision avoidance system for aircraft. A light fixture assembly includes a housing with a base and a clear dome over the base. The base including an aircraft attachment element that allows for drop-in replacement of original light housings. An aircraft light is within the housing, as well as an ultrasonic sensor. The sensor is tied to a warning indicator configured to issue an alert when the light fixture approaches an obstacle. The installation provides a permanent replacement for wing lights or taillights, whereby the proximity sensors are always on the aircraft, and do not need to be added once landed.

Claims

1. A collision avoidance system for aircraft comprising: a plurality of ultrasonic sensors positioned around the aircraft and configured to be integrally fixed to the aircraft; and a warning indicator when the aircraft approaches an obstacle.

2. The collision avoidance system of claim 1, wherein the ultrasonic sensors comprise ultrasonic transducers.

3. The collision avoidance system of claim 1, wherein the ultrasonic sensors comprise a 0.1 m to 20 m detection range, with 1 cm resolution.

4. The collision avoidance system of claim 1, wherein the warning indicator comprises an audio piezo module.

5. The collision avoidance system of claim 1, wherein the warning indicator comprises a smart phone app wirelessly paired with the system.

6. The collision avoidance system of claim 1, wherein the warning indicator comprises a flashing mode for a taxi light.

7. The collision avoidance system of claim 1, further comprising a three-position cockpit switch, comprising an enabled mode, a disabled mode, and a standby mode.

8. The collision avoidance system of claim 1, further comprising an electronic control unit enclosed in a housing, wherein the electronic control unit is connected to the plurality of ultrasonic sensors and the warning indicator.

9. The collision avoidance system of claim 1, wherein each of the plurality of ultrasonic sensors is integrated within a corresponding wingtip light or taillight fixture of the aircraft.

10. The collision avoidance system of claim 1, wherein the plurality of ultrasonic sensors detect a proximity of a landing strip during landing and ground obstacles during ground movement.

11. The collision avoidance system of claim 1, further comprising a secondary battery power supply configured to power the system in a passive operation state when the aircraft is not operating.

12. A collision avoidance system for aircraft comprising: a light fixture assembly comprising a housing including a base and a clear dome over the base, the base including an aircraft attachment element; an aircraft light within the housing, an ultrasonic sensor within the housing; and a warning indicator in combination with the ultrasonic sensor, and configured to issue an alert when the light fixture approaches an obstacle.

13. The collision avoidance system of claim 12, wherein the aircraft light is selected from a navigation light, a position light, a taxi light, an anti-collision light, or a landing light.

14. The collision avoidance system of claim 12, wherein the light fixture assembly is a drop-in replacement for an original equipment light assembly.

15. The collision avoidance system of claim 12, wherein the light fixture is a wingtip light or a taillight.

16. The collision avoidance system of claim 12, further comprising a secondary battery power supply configured to power the system in a passive operation state when the aircraft is not operating.

17. The collision avoidance system of claim 12, further comprising an electronic control unit enclosed in a housing, wherein the electronic control unit is wired or wirelessly connected to the ultrasonic sensor and the warning indicator.

18. The collision avoidance system of claim 17, further comprising a three-position cockpit switch connected to the electronic control unit, the cockpit switch comprising an enabled mode, a disabled mode, and a standby mode.

19. The collision avoidance system of claim 17, further comprising engine sensors connected to the electronic control unit.

20. The collision avoidance system of claim 12, wherein the warning indicator comprises at least two of: an audio piezo module mounted in the aircraft cowling, a smart phone app wirelessly paired with the system, and a flashing taxi light.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above-mentioned and other features and objects of this invention will be better understood from the following detailed description taken in conjunction with the drawings wherein:

[0021] FIG. 1 shows a perspective view of a system according to a preferred embodiment of this invention;

[0022] FIG. 2 shows a system block diagram according to a preferred embodiment of this invention;

[0023] FIGS. 3A-3B show an electronic control unit according to a preferred embodiment of this invention;

[0024] FIGS. 4A-4B show an ultrasonic sensing module according to a preferred embodiment of this invention;

[0025] FIG. 5 shows a schematic view of a use case of the subject system according to a preferred embodiment of this invention;

[0026] FIG. 6 shows a schematic view of a use case of the subject system according to a preferred embodiment of this invention;

[0027] FIG. 7 shows a schematic view of a use case of the subject system according to a preferred embodiment of this invention;

[0028] FIG. 8 shows a schematic view of a use case of the subject system according to a preferred embodiment of this invention;

[0029] FIG. 9 shows a wing end installation site according to one embodiment of this invention;

[0030] FIG. 10 shows a wing end system assembly according to one embodiment of this invention; and

[0031] FIG. 11 shows a wing end system assembly site according to one embodiment of this invention.

DESCRIPTION OF PREFERRED EMBODIMENTS

[0032] FIG. 1 shows a schematic of a subject collision avoidance system. In a preferred embodiment ultrasonic sensors 20 are installed in the wingtips 22 and/or the tail 24 of the aircraft 26, as shown. The illustrated sensors 20 are adaptable for tail plus wingtip obstruction (or collision) avoidance warnings and will sound alerts in the cockpit, externally on the aircraft, to ground personnel, and/or to mobile devices. The sensors 20 are connected by communication bus system 32 to an electronic control unit (ECU) 30. The ECU 30 can be connected also to cockpit controls, as well as other sensors for the aircraft, such as engine sensors.

[0033] Preferably, the ultrasonic sensors are remote ultrasonic (above 50 KHz) transducers, utilizing time-of-flight algorithms. The sensors are preferably similar sensors to auto blind-spot detection systems adapted to aircraft use. Preferred sensors include a 0.1 m-20 m detection range with 1 cm resolution.

[0034] FIG. 2 shows a system block diagram according to a preferred embodiment of this invention, such as for the implementation in FIG. 1. ECU 30 is connected to three sensor modules 20 (two wing, one tail). The ECU 30 desirably includes connector terminal, such as serial consoles 32, for efficient plug-in installation of the various components. The ECU 30 is connected to warning indicators 40 and 42. Active warning interfaces may include an audio (piezo) module 40 preferably mounted in or under an aircraft cowling and/or taxi or other light integration 42 (e.g., flashing). The ECU 30 further includes or connects to a Bluetooth antenna 46, for pairing to a smart phone app 48 or tow tug device. The ECU 30 further includes a connection to a cockpit switch 50. The system may include an Enable/Disable/Standby (3-position) switch, preferably within the cockpit but can be located as needed. In addition, the system may include a battery standby mode to allow the sensors to operate when the aircraft is powered off, thereby allowing the sensors to warn when another object is too close to the parked aircraft.

[0035] FIG. 3A shows an electronic control unit (ECU) 130 according to a preferred embodiment of this invention. The ECU 130 includes an outer housing 134 enclosing the operational circuitry, such as shown in FIG. 3B. The ECU 130 is preferably located within the host aircraft, and connectable to the system components by the housing serial connector consoles 132, such as shown in FIGS. 1 and 2. FIG. 3B schematically shows the ECU 130, according to one embodiment of this invention. A microcontroller 160 communicates with the sensors though sensor interfaces 162, and relays 164 for the warning indicators, as well as the Bluetooth module 166 and a cockpit switch interface 168.

[0036] FIGS. 4A-4B show an ultrasonic sensing module 220 according to a preferred embodiment of this invention. The module 220 includes a ‘system on a chip’ (SoC) 222 connected to an ultrasonic transducer 224. One example of a suitable module is the Ultrasonic Sensor Signal Processor with Integrated Microcontroller, model number PGA450-Q1, available from Texas Instruments (Dallas, Tex.). Multiple modules may be located on the aircraft to detect potential collisions with wings, tail and/or fuselage. The sensors are preferably enabled to sense proximity of ground obstacles, including other aircraft, during taxi and/or towing. The sensors preferably include wide enough range to provide protection for wing tips; wing leading edges; the top of the rudder; the rudder leading edge; and/or the tail section.

[0037] The subject system is additionally configurable by the user/owner and capable of owner configuration to modify: increase/decrease warning zone; audible tone; light flashing sequence; and/or direction of sensors.

[0038] FIG. 5 shows one use case of the subject system which is while the aircraft is taxiing. The subject system is capable of providing an audible warning during taxiing via a wireless or wired connection to a cabin speaker when proximity to a ground obstacle is detected within the warning zone. An example of the audible waring might be, “Warning: Ground Obstacle Detected, Left Wing Tip.” An onboard power system enables an active state during ground operation.

[0039] FIG. 6 show another use case of the subject system during towing. During towing, a ground crew or the owner/operator can make use of the system's proximity detection through the use of a mobile app that provides visual and audible warnings to detected objects. In addition, visual warning can be provided by flashing the aircraft light where the risk is detected.

[0040] FIG. 7 shows yet another use case of the subject system while parked. While parked, the system preferably operates in a passive state until another object such as another taxiing aircraft or ground vehicle is detected. Once detected it could provide a low light flashing indication to make the aircraft more visible to the incoming object.

[0041] FIG. 8 shows yet another use case of the subject system during landing. By integrating proximity sensors with a 100 m range, and then orienting them downwards, the capability of having an inexpensive radar altimeter becomes possible. While it is unlikely that this use would be certified for lower minimum approaches, it will still provide additional data to the pilot and enhance safety, especially when operating around unfamiliar airports.

[0042] The subject sensors are preferably integrated and/or integrateable with existing light assemblies, such as those shown in FIGS. 9-11. The integrated light assembly/proximity sensor is preferably a drop-in replacement for existing lighting assemblies without the need to add any additional wiring or structure. Adapters may be used where necessary to expand available market without the need of new product design. To facilitate use on aircraft the subject system is built to FAA TSO to minimize certification costs and/or be capable of installation using field approval processes.

[0043] Referring to FIG. 9, a light fixture assembly 300 includes a housing 302 with a base 304 and a clear dome 306 over the base 304. The base 304 includes suitable aircraft attachment elements, which correspond to the OEM attachments of the lighting assemblies for the aircraft. Within the domed housing 302 is an aircraft light 310, such as matching/replacing the original OEM light, and an ultrasonic sensor 312 according to this invention, such as described above.

[0044] FIG. 10 shows a light fixture assembly 400 that includes an adapter base 404 for an OEM light fixture 402. The adapter base 402 further includes a sensor 412. The adapter base with sensor allows the existing light fixture to be reused.

[0045] FIG. 11 shows a similar light fixture assembly 500 without the adapter, instead having the sensor 512 integrated with the base 504. The sensor 512 can also be integrated under the clear dome 506 with light 510 for further protection.

[0046] The subject system is preferably wireless capable and may include integrated wireless communication capability in either Bluetooth or WiFi for easy communication with mobile devices or other wireless devices.

[0047] The subject sensors preferably have a range of no less than 100 m. Sensors are accurate to within no less than 6 inches but ideally be accurate to within 1 inch. Sensors are active during ground operation through use of onboard aircraft battery supply. Sensors are preferably capable of being active during passive states through use of integrated battery for warning indications for other nearby moving aircraft or equipment.

[0048] The subject system thereby provides warnings of proximity to objects through audio and/or visual means. The system provides visual warning indications such as flashing lights with increased frequency for nearest proximity. A mobile app may also provide visual cues for proximity to object and warning indications. Audible warnings are provided through an integrated speaker and/or a mobile application with audible warning. The speaker may be a wireless speaker provided in cabin and/or on ground equipment. Audio panel integration may be an additional installation option.

[0049] As discussed above, the system, such as the ECU, can be integrated or otherwise combined with other potential bolt-on hardware and/or services. In one exemplary embodiment a real-time external weather sensor is tied to the system. This is a sensor that could be installed externally to the aircraft that would provide real time weather information at flight altitudes. When coupled with a wireless connection to a mobile application, Pilot reports (PIREPS) could be submitted automatically when certain conditions are observed. The data collected could also be licensed for use by other interested parties.

[0050] In aircraft that are not equipped with modern avionics systems, wireless engine sensors can be installed to track key operating information, such as run time, cycles, and flight hours. This data could then be used with the mobile application to assist operators in keeping track of their operational use of the aircraft and can provide notifications regarding required periodic maintenance and inspections. In addition to the data being tracked, automated delivery of required materials such as oil and oil filters could be automatically shipped to the user. As the maintenance actions are performed the app could be updated to keep track of the critical maintenance actions for proof of airworthiness. This application could also provide a single source for maintaining all other documentation required for flight, such as digital copies of pilot's certificates and medicals.

[0051] Lastly, the subject system may be adaptable to other vehicles and industries including nautical, trucking, shipping, warehouse, and others.

[0052] While in the foregoing specification this invention has been described in relation to certain preferred embodiments thereof, and many details have been set forth for purpose of illustration, it will be apparent to those skilled in the art that the device and placard are susceptible to additional embodiments and that certain of the details described herein can be varied considerably without departing from the basic principles of the invention.