Weighing system and methods of operating such weighing system

• US 8,452,525 B2
• Filed: 09/22/2011
• Issued: 05/28/2013
• Est. Priority Date: 11/09/2010
• Status: Active Grant

• Current Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Original Assignee: Eurocopter Deutschland Gesellschaft Mit Beschrã¤Nkter Haftung (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Sendlinger, Johann, Wahnfried, Markus
• Primary Examiner(s): Trammell, James
• Assistant Examiner(s): MELTON, TODD M
• Application Number:
  US13/239,451
• Publication Number:
  US 20120116660A1
• Time in Patent Office: 614 Days
• Field of Search: 701/124, 244/108
• US Class Current: 701/124
• CPC Class Codes: G01G 19/07 for weighing aircraft
• CPC Class Codes: G01M 1/125 of aircraft

Abstract

A weighing system for detecting total weight, including optional external loads, and monitoring of center of gravity of a helicopter (2), comprising a fuselage (1), a landing gear (4), mounted to the fuselage (1) by flanges (10-13) and weighing cells (41-44). The weighing cells (41-44) are integral with the flanges (10-13) between the fuselage (1) and the landing gear (4). Attachment means are provided at the landing gear (4) for external loads (39, 40).

Claims

1. A weighing system for detecting total weight, including optional external loads, and monitoring of center of gravity of a helicopter, comprising:

a fuselage of the helicopter,

a landing gear, mounted to the fuselage by flanges,

weighing cells integrated into said flanges,

a control unit for calculations of the center of gravity and total weight of the helicopter, and

connection means from said weighing cells to the control unit for transfer of weights detected by said weighing cells;

wherein each of said flanges has two fork type projections separated from and facing each other; and

wherein attachment means for an external lifting gear are provided at the landing gear for any external loads.

2. The system according to claim 1, wherein the control unit is provided with data storage means for calculations of the center of gravity and total weight of the helicopter and communication means for transfer of data resulting from said calculations in the control unit to at least one display in the helicopter'"'"'s cockpit.

3. The system according to claim 1, wherein the landing gear is a skid type landing gear comprising two struts with two flanges between fuselage and each strut and/or one strut with one flange.

4. The system according to claim 1, wherein each of the flanges comprises an essentially annular aluminium casing and each of said casings is fixed onto the respective bow shaped strut with a respective damping element inside of said two fork type projections.

5. The system according to claim 1, wherein the control unit comprises a data amplifier, a data processor with software and a data storage.

6. The system according to claim 1, wherein the control unit comprises at least one first interface for the connection means from said weighing cells and at least one second interface for a communication means to at least one display.

7. The system according to claim 1, wherein the at least one display comprises input means.

8. The system according to claim 1, wherein the control unit comprises at least one external data interface.

9. The system according to claim 1, wherein the control unit comprises at least one interface towards a helicopter'"'"'s maintenance system.

10. The system according to claim 1, wherein the weighing cells comprise strain gauges.

11. The system according to claim 1, wherein a load hook is provided, said load hook being mounted to the landing gear by means of a system of bars and/or ropes, the weight of said load hook being detectable by said weighing cells.

12. A method to operate the system according to claim 1, wherein detecting the net weight of the helicopter by means of the weighing cells, transmitting said detected net weight via at least one first interface for the connection means from said weighing cells to the control unit, storing said detected net weight in a data storage of said control unit, presenting said detected net weight via communication means in a display and setting a reference point via an input means at the display via at least one second interface for the communication means in said control unit, fuelling, detecting, transmitting and storing the fuel weight the same way as the net weight of the helicopter by subtracting by means of a data processor of said control unit the net weight of the helicopter from the transmitted weight signal after fuelling and setting another reference point via the input means at the display.

13. The method according to claim 12, wherein summing up the detected loads and storing the sum in the data storage of the control unit.

14. The method according to claim 12, wherein calculating by means of the data processor of the control unit the center of gravity of the helicopter from said detected weights at said weighing cells.

15. The method according to the preamble of claim 12, wherein taking off with the helicopter, taking up any external lifting gear attached to its landing gear, detecting, transmitting and storing the weight of the external lifting gear the same way as the net weight of the helicopter by subtracting by means of the data processor the known net weight of the landing gear of the helicopter from the transmitted weight signal, setting a reference point via the input means, taking up an external load by means of the external lifting gear and detecting, transmitting and storing the external load weight the same way as the net weight of the helicopter by subtracting by means of the data processor the known net weight of the landing gear and the detected weight of the external lifting gear from the weight signal transmitted after take off and after the external load is clear from the ground.

16. A weighing system for detecting total weight, including optional external loads, and monitoring of center of gravity of a helicopter, comprising:

a series of flanges for mounting a landing gear to a fuselage of the helicopter, wherein each flange is connected to the fuselage using a pair of fork like projections spaced apart and facing one another, each flange having;

an annular damping element surrounding a strut of the landing gear,

a annular casing surrounding the damping element and having a pair of flattened areas defining a pair of borings, and

an integral weighing cell,

wherein the flattened areas of the casing mate with an inside surface of the pair of fork like projections and a pair of bolts extend through the boring in the casing and a groove in the fork like projection such that the landing gear is mounted to the fuselage;

external lifting gear for external loads, the external lifting gear connected to the struts of the landing gear adjacent to the series of flanges; and

a control unit in communication with the weighing cells and configured to calculate a center of gravity and a total weight during flight of the helicopter based on a signal from the weighing cells, the total weight during flight being the sum of a weight detected before take off and a weight detected after take off and when clear of ground.