System and method of preventing aircraft wingtip ground incursion

• US 20050007257A1
• Filed: 07/30/2004
• Published: 01/13/2005
• Est. Priority Date: 05/11/2000
• Status: Abandoned Application

• Current Assignee: Rodger H. Rast
• Original Assignee: Rodger H. Rast
• Inventors: Rast, Rodger H.
• Application Number:
  US10/909,106
• Publication Number:
  US 20050007257A1
• Time in Patent Office: Days
• US Class Current: 340/815.450
• CPC Class Codes: B64D 47/04 the lighting devices being primarily intended to illuminate the way ahead
• CPC Class Codes: G02B 27/017 Head mounted
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/065 Navigation or guidance aids, e.g. for taxiing or rolling

Abstract

An apparatus and method for tracking aircraft wingtip position during taxi operations to prevent wingtip ground incursion. A patterned illumination source is attached proximal the wingtips to project a readily discernable target pattern in the direction of taxi travel. At least a portion of the target pattern is reflected off of any obstructions that lie in the straight-line direction of travel, such that the pilot can maneuver to avoid striking the obstruction. By way of example, the patterned illumination source comprises a laser module positioned with the navigation and/or strobe light of the aircraft. The device may be retrofitted to existing aircraft without additional wiring with the control of activation being selectable via power cycling of existing aircraft lighting controls. One aspect of the invention provides a tip tracking module bulb that may be retrofitted into existing light sockets to simplify system installation.

Claims

1. An illumination bulb module, comprising:

a housing adapted for receiving power from a bulb receptacle into which it is inserted;

at least one solid state light emitting element joined to said housing and adapted to generate a partial or fully omni directional lighting pattern; and

a laser diode illumination source within said housing, adapted for directing a narrow beam of illumination in a predetermined direction.

2. A bulb as recited in claim 1, wherein said partial or fully omni directional lighting pattern is configured to be equivalent to a conventional illumination element.

3. A bulb as recited in claim 1, wherein a plurality of solid state light emitting elements is joined to said housing.

4. A bulb as recited in claim 1, wherein said solid state light emitting elements comprise light emitting diodes (LEDs).

5. A bulb as recited in claim 1, wherein said illumination bulb is configured for connection within an aircraft navigation or strobe lighting circuit.

6. A bulb as recited in claim 1, wherein said lighting system is an automotive, truck, motorcycle, or boat lighting system.

7. A bulb as recited in claim 1, further comprising a controller circuit within said housing, said controller circuit adapted for controlling the power applied to said laser diode element.

8. A bulb as recited in claim 7, wherein said controller circuit is further configured for controlling power application to said solid state light emitting element.

9. A bulb as recited in claim 7, wherein said controller circuit controls the duration that said laser diode illumination element is activated.

10. A light beacon apparatus for increasing aircraft recognition during flight comprising:

a housing having transparent portions and configured for attachment to an aircraft;

a power connection from said housing to receive power from an aircraft to which said housing is connected;

a laser light source retained in said housing;

a power supply receiving power from said power connection for regulating the current applied to the laser element in said laser light source;

at least one substantially non-directional light source configured to generate a flashed or rotating light output in response to power received from said power connection; and

means for directing the laser or its output light beam in a circular pattern about a substantially horizontal plane.

11. An apparatus as recited in claim 10, wherein said housing is configured for replacement of conventional light beacons.

12. An apparatus as recited in claim 10, wherein said means for directing said laser comprises a motorized stage for rotating the laser in a circular pattern.

13. An apparatus as recited in claim 10, wherein said means for directing said laser output beam comprises a motorized stage for rotating a mirror or lens for directing the laser output in a circular pattern.

14. An apparatus as recited in claim 10, wherein said substantially non-directional light source comprises a plurality of LEDs coupled to a flashing circuit.

15. An apparatus as recited in claim 10, wherein said substantially non-directional light source comprises a plurality of LEDs coupled to a rotating platform or directed to reflect from a rotating mirror assembly.

16. An apparatus for registering aircraft loading as an aircraft taxies, comprising:

a plurality of weight sensors configured for application to a taxiway and oriented at multiple different angles in relation to a given compass direction; and

means for generating aircraft loading information in response to the output signals from said plurality of weight sensors.

17. An apparatus as recited in claim 16, wherein said means for generating aircraft loading information comprises a computer element and programming configured for determining the weight applied at each landing gear to the taxiway, and the distribution of the weight between the landing gears.

18. An apparatus as recited in claim 16:

further comprising a display configured for being mounted in view of the pilot;

wherein said display is configured for displaying the registered total weight and weight distribution of the aircraft.

19. An apparatus as recited in claim 17:

further comprising a wind sensor configured for generating a signal in response to wind speed and direction for receipt by said controller; and

wherein said controller is configured for eliminating wind contributions to the measurement of loading.

20. An apparatus as recited in claim 16, wherein said multiple orientation of said sensors comprises a moving platform containing multiple sensors to register at least front to back weight distribution and/or side to side weight distribution and a movable platform configured for being rotated after all the wheels of an aircraft are moved into a position on the movable platform.

21. An apparatus for dropping aircraft power in response to airspeed, comprising:

a means for sensing airspeed;

a circuit for generating an over speed signal in response to the fast approach, or exceeding, of the aircraft V_NE airspeed; and

means for dropping aircraft power in response to receipt of said over speed signal.

22. An apparatus as recited in claim 21, further comprising means for preventing said apparatus from subsequently dropping aircraft power for a period of time after it is restored by the pilot.

23. An apparatus as recited in claim 21, wherein said apparatus is integrated within an autopilot system that remains active when the autopilot has not been selected for performing aircraft control functions according to an autopilot flight plan.

24. An apparatus as recited in claim 23, wherein said functions are integrated as programming within said autopilot system.

25. An apparatus as recited in claim 21, wherein said means for dropping aircraft power comprises an actuator which unlocks the throttle setting wherein a bias force moves the throttle to a lower setting.

26. An apparatus as recited in claim 21, wherein said means of sensing airspeed comprises a separate electronic airspeed sensing element, an aircraft airspeed sensor which generates an electrical output, or an electronic sensor which converts available airspeed information in an air pressure form or movement form into an electrical signal output.

27. An apparatus for automatically determining aircraft loading factors, comprising:

a strain sensor configured for mounting on each of the landing gear or wheels of an aircraft;

said strain sensors configured for registering the force applied to each of said landing gear from attached tire assemblies; and

means for determining aircraft loading in response to signals received from said strain sensors.

28. An apparatus as recited in claim 27, further comprising means for detecting wind direction and speed coupled to said means for determining aircraft loading.

29. An apparatus as recited in claim 27, wherein aircraft loading determination comprise displaying information relating to total load and the distribution of forces between the various landing gear.

30. An apparatus as recited in claim 27, further comprising means for computing a center of gravity for an aircraft based on said aircraft loading registered by said apparatus.

31. An apparatus as recited in claim 27, wherein said strain sensors communicated to said means for determining aircraft loading via a wireless communication link.

32. An apparatus as recited in claim 27, further comprising a display configured for outputting said aircraft loading information.

33. An apparatus as recited in claim 32, wherein said aircraft loading information is output in a graphical form.