Method and apparatus for determining weight and center of gravity of a vehicle

• US 4,639,872 A
• Filed: 02/10/1984
• Issued: 01/27/1987
• Est. Priority Date: 02/10/1984
• Status: Expired due to Term

• Current Assignee: Aldis Consultants, Inc.
• Original Assignee: Aldis Consultants, Inc.
• Inventors: Watson, David, Marrone, Joseph, McHale, Charles J.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US06/578,874
• Time in Patent Office: 1,082 Days
• Field of Search: 364/427, 364/463, 364/466, 364/567, 73/65, 177/25, 235/61 T
• US Class Current: 701/124
• CPC Class Codes: G01G 19/07 for weighing aircraft
• CPC Class Codes: G01M 1/125 of aircraft

Abstract

An apparatus for use in determining the weight and the location of the center of gravity of a vehicle, particularly an aircraft prior to its taking off, comprising in combination at least one load-measuring device secured in a roadway and adapted for contacting load-supporting members of the vehicle when such is moved thereover; computer means linked to the load-measuring devices and adapted to receive data therefrom; means for relaying to the operator of the vehicle data computed by the computer means, and sensor means linked to the computer means, the sensor means adapted to read characteristics of the vehicle as it observes the same and alert the computer, programmed for such characteristics. Also disclosed are methods based on use of the disclosed apparatus.

Claims

1. An apparatus for use in determining the respective weight and center of gravity of different types of aircraft rapidly prior to their successively taking off, each aircraft including at least a pair of laterally spaced main undercarriage wheels and a tail or nose wheel longitudinally spaced from said main under-carriage wheels with the lateral spacing between the main undercarriage wheels as well as the longitudinal spacing between the nose or tail wheels and the main undercarriage wheels varying substantially from one type of aircraft to another, said apparatus comprising in combination:

(a) a plurality of load measuring devices secured to a roadway in spaced relation one to another and integrally forming part of said roadway, ones of said devices each comprising an elongated aircraft wheel supporting platform extending transversely of said roadway for respectively receiving and supporting the respective varyingly spaced main undercarriage wheels of said different types of aircraft as said aircraft are moved along a common path of travel upon said roadway, said path extending in a direction generally normal to the length of each platform, a further one of said devices comprising an aircraft wheel supporting platform positioned in said path of travel for receiving and supporting the respective nose or tail wheel of said different types of aircraft as said aircraft are moved along said common path of travel;

(b) aircraft weight readout means linked to said load measuring devices for displaying load data measured thereby upon said platforms receiving and supporting thereon said respective aircraft nose or tail and main undercarriage wheels; and

(c) computer means operatively connected in the link between said load measuring devices and said aircraft weight readout means, for use in computing the respective center of gravity of said different types of aircraft following successive arrival of the wheels thereof on said platforms, said computing of said centerof gravity of each respective aircraft utilizing data entered into said computer means, said data comprising nose or tail wheel to main undercarriage wheel spacing and the loads measured by said load measuring devices, whereby following said computing, center of gravity data for the aircraft may be is displayed on said readout means.

2. An apparatus as defined in claim 1, wherein each of said aircraft wheel supporting platforms extends lengthwise of said roadway a distance sufficient to ensure recordal by each load measuring device of the load applied by the respective aircraft wheel as it rolls over each platform at a selected speed, thereby to provide successive dynamic weighing of said aircraft.

3. An apparatus as defined in claim 2, wherein said distance is sufficient to ensure that the nose or tail and main undercarriage wheels of the respective different aircraft are simultaneously received and supported for weight recordal by said respective wheel supporting platforms, thereby to provide successive static weighing of said aircraft.

4. An apparatus as defined in claim 1, wherein said readout means is located exteriorly of said aircraft.

5. An apparatus as defined in claim 1, wherein said readout means is located interiorly of said aircraft.

6. An apparatus as defined in claim 1, wherein said computer means is located exteriorly of said aircraft.

7. An apparatus as defined in claim 1, wherein said computer means is located interiorly of said aircraft.

8. An apparatus as defined in claim 1, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated when a signal therefrom is intercepted by a transponder on said aircraft.

9. An apparatus as defined in claim 1, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated by a signal transmitted from said aircraft.

10. An apparatus as defined in claim 1, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated by a signal transmitted from said aircraft, said signal being transmitted to said sensor means via a transponder means on said aircraft.

11. An apparatus as defined in claim 1, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated by a signal transmitted from said aircraft, said signal being transmitted to said sensor means via a transponder means on said aircraft in response to a signal emitted thereto by said sensor means.

12. An apparatus as defined in claim 1, including wind speed and wind direction measuring means operatively linked to said computer means for entering therein wind speed and wind direction data, permitting said computed weight and center of gravity data to possibly be adjusted for such environmental factors.

13. An apparatus as defined in claim 1, including a humidity measuring means operatively linked to said computer means for entering therein humidity data, permitting said computed weight and center of gravity data to possibly be adjusted for such environmental factor.

14. An apparatus as defined in claim 1, including an ambient temperature measuring means operatively linked to said computer means for entering therein ambient temperature data, thereby permitting said computed weight and center of gravity data to possibly be adjusted for such environmental factor.

15. An apparatus as defined in claim 1, including controller/interrogator means linked to said computer means for respectively entering therein aircraft travel speed as said aircraft rolls along said roadway toward said load measuring devices and unique identity data of said aircraft as said aircraft approaches said load measuring devices, said controller/interrogator means being activated for operation upon interface with means on said aircraft, whereby said computer means is accessed for characteristics of said uniquely identified aircraft which is utilized by said computer means for computing said weight and center of gravity data.

16. An apparatus as defined in claim 1, wherein said platforms extend in elongated manner to define a T-like shaped configuration.

17. A method for determining the location of the center of gravity of an aircraft, prior to its taking off, said aircraft including a nose or tail wheel and at least a pair of laterally spaced main undercarriage wheels, said method comprising the steps of:

(a) moving the aircraft upon said wheels along a path of travel upon a roadway lengthwise thereof in preparation for take-off, which path of travel is common with other aircraft using said roadway for take-off, said other aircraft having nose or tail wheels whose spacing with respect to their main undercarriage wheels varies substantially as does the lateral spacing of the main undercarriage wheels one to another;

(b) maintaining said movement along said path of travel, including passing the wheels of the aircraft over a load measuring means secured to and forming part of said aircraft roadway, said load measuring means comprising a single elongated platform extending transversely of said roadway for contact by all the wheels of said aircraft, as well as those of said other aircraft, as said wheels are received and supported upon said platform for registering the loads carried thereby;

(c) registering said loads and entering registered loads data into a computer means linked to said load measuring means;

(d) computing the location of the center of gravity of said aircraft utilizing said entered loads data and wheel spacing data of said aircraft also entered into said computer means; and

(e) displaying said computed location of center of gravity on a readout means.

18. A method according to claim 17, including the step of pre-programming said computer means, said pre-programming step including entering said wheel spacing data of the aircraft into said computer means along with those of said other aircraft, and selectively accessing said wheel spacing data to carry out said computing of said location of center of gravity.

19. A method for determining the location of the center of gravity of an aircraft, prior to its taking off, said aircraft including a nose or tail wheel and at least a pair of laterally spaced main undercarriage wheels, said method comprising the steps of:

(a) moving the aircraft upon said wheels along a path of travel upon a roadway lengthwise thereof in preparation for take-off, which path of travel is common with other aircraft using said roadway for take-off, said other aircraft having nose or tail wheels whose spacing with respect to their main undercarriage wheels varies substantially as does the lateral spacing of the main undercarriage wheels one to another;

(b) maintaining said movement along said path of travel including passing the wheels of the aircraft over a load measuring means secured to and forming part of said aircraft roadway, said load measuring means being elongated to extend tranversely of said roadway for contact by all the wheels of said aircraft as well as of said other aircraft, as said wheels are received and supported upon said load measuring means for registering the loads carried thereby;

(c) registering said loads and entering registered loads data into a computer means linked to said load measuring means;

(d) computing the location of the center of gravity of said aircraft utilizing said entered loads data and wheel spacing data of said aircraft also entered into said computer means; and

(e) displaying said computed location of center of gravity on a readout means.

20. A method for determining the center of gravity and the static weight of aircraft respectively one after another while each in turn is parked prior to preparation for take-off, said aircraft including a nose or tail wheel and at least a pair of laterally spaced main undercarriage wheels providing a three-point support for the aircraft and wherein the spacing between said nose or tail wheels and the main undercarriage wheels may vary substantially from one aircraft to another, and wherein the lateral spacing between said main undercarriage wheels may vary substantially from one aircraft to another, said method comprising the steps of:

(a) moving a first one of said aircraft upon its wheels along a path of travel upon a roadway therefor, said path of travel being in common with that of other different aircraft using said roadway;

(b) maintaining said movement of said first of said aircraft along said path of travel, including placing and parking the respective wheels thereof upon respective load measuring devices positioned in spaced relation one to another and forming part of said roadway for registering the respective loads carried by said respective wheels, said load measuring devices secured to said roadway and each including an aircraft wheel supporting platform whose top surface area is sufficient to receive and support the respective wheels of said respective aircraft as they pass along said common path of travel;

(c) registering said respective wheel loads as said aircraft wheels rest upon said platform;

(d) computing with a computer means the center of gravity of said first one of said aircraft, said computing utilizing at least the load data registered in step (c) and nose or tail wheel to main undercarriage wheel spacing data pertaining to said aircraft;

(e) moving said first one of said aircraft to remove the wheels thereof from said platforms;

(f) moving a second one of said aircraft upon its wheels along said path of travel upon said roadway;

(g) maintaining said movement of said second one of said aircraft along said path of travel and while maintaining said load measuring devices in position in said spaced relation one to another, placing and parking the respective wheels of said second one of said aircraft upon said respective wheel supporting platforms for registering the respective wheel loads of said second one of said aircraft;

(h) registering said respective wheel loads of said second one of said aircraft as the wheels thereof rest upon said platforms; and

(i) computing with a computer means the center of gravity of said second one of said aircraft, said computing utilizing at least the load data registered in step (h) and nose or tail wheel to main undercarriage wheel spacing data pertaining to said second one of said aircraft.

21. A method according to claim 20, wherein said step (d) is performed during or subsequent to performing step (e).

22. A method according to claim 20, including the step of utilizing for said computing steps (d) and (i) at least one environmental factor, thereby permitting said loads registered in steps (c) or (h), or in both steps (c) and (h), to be adjusted to provide a more accurate determination of said center of gravity.

23. A method according to claim 21, including the step of utilizing for said computing steps (d) and (i) at least one environmental factor, thereby permitting said loads registered in steps (c) or (h), or in both steps (c) and (h), to be adjusted to provide a more accurate determination of said center of gravity.

24. An apparatus for use in determining the respective dynamic weight and center of gravity of different types of aircraft rapidly prior to their successively taking off, each aircraft including at least a pair of laterally spaced main undercarriage wheels and a tail or nose wheel longitudinally spaced from said main undercarrige wheels with the lateral spacing between the main undercarriage wheels as well as the longitudinal spacing between the nose or tail wheels and the main undercarriage wheels varying substantially from one type of aircraft to another, said apparatus comprising in combination:

(a) a single load measuring device secured to a roadway and including an elongated aircraft wheel supporting platform extending transversely of said roadway for successively receiving and supporting the respective nose or tail wheel and varying spaced main undercarriage wheels of said different types of aircraft as said aircraft are moved along a common path of travel upon said roadway, said path extending in a direction generally normal to the length of said platform;

(b) aircraft weight readout means linked to said load measuring device for displaying load data measured thereby upon said platform receiving and supporting thereon said respective aircraft nose or tail and main undercarriage wheels; and

(c) computer means operatively connected in the link between said load measuring device and said aircraft weight readout means for computing the respective center of gravity of said different aircraft following successive arrival of the wheels thereof on said platform, said computing of the respective center of gravity of each aircraft utilizing data entered into said computer means, said data comprising nose or tail wheel to main undercarriage wheel spacing and the loads measured by said load measuring device, whereby following said computing, center of gravity data for the aircraft is displayed on said readout means.

25. An apparatus as defined in claim 24, wherein said readout means is located exteriorly of said aircraft.

26. An apparatus as defined in claim 24, wherein said readout means is located interiorly of said aircraft.

27. An apparatus as defined in claim 24, wherein said computer means is located exteriorly of said aircraft.

28. An apparatus as defined in claim 24, wherein said computer means is located interiorly of said aircraft.

29. An apparatus as defined in claim 24, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated when a signal therefrom is intercepted by a transponder on said aircraft.

30. An apparatus as defined in claim 24, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated by a signal transmitted from said aircraft.

31. An apparatus as defined in claim 24, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated by a signal transmitted from said aircraft, said signal being transmitted to said sensor means via a transponder means on said aircraft.

32. An apparatus as defined in claim 24, wherein at least part of the operation of said computer means is activated or controlled by a sensor means operatively linked to said computer means, said sensor means being activated by a signal transmitted from said aircraft, said signal being transmitted to said sensor means via a transponder means on said aircraft, in response to a signal emitted thereto by said sensor means.

33. An apparatus as defined in claim 24, including wind speed and wind direction measuring means operatively linked to said computer means for entering therein wind speed and wind direction data, permitting said computed weight and center of gravity data to possibly be adjusted for such environmental factors.

34. An apparatus as defined in claim 24, including humidity measuring means operatively linked to said computer means for entering therein humidity data, permitting said computed weight and center of gravity data to possibly be adjusted for such environmental factor.

35. An apparatus as defined in claim 24, including an ambient temperature measuring means operatively linked to said computer means for entering therein ambient temperature data, thereby permitting said computed weight and center of gravity data to possibly be adjusted for such environmental factor.

36. An apparatus as defined in claim 24, including controller/interrogator means linked to said computer means for respectively entering therein aircraft travel speed as said aircraft moves along said roadway toward said load measuring device and unique identity data of said aircraft as said aircraft approaches said load measuring device, said controller/interrogator means being activated for operation upon interface with means on said aircraft, whereby said computer means is accessed for characteristics of said uniquely identified aircraft which is utilized by said computer means for computing said weight and center of gravity data.