Systems and methods for lifting body vibration control

• US 10,507,920 B2
• Filed: 05/16/2016
• Issued: 12/17/2019
• Est. Priority Date: 05/18/2015
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Waltner, Peter J., Herter, John R.
• Primary Examiner(s): Badawi, Medhat
• Application Number:
  US15/155,652
• Publication Number:
  US 20160340039A1
• Time in Patent Office: 1,310 Days
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: F16F 15/027 comprising control arrangements F16F15/0237 takes precedence
• CPC Class Codes: F16F 2230/183 fluid actuated
• CPC Class Codes: F16F 9/067 Partitions of the piston type, e.g. sliding pistons

Abstract

An external cargo damping system includes lifting gear and a damping assembly. The lifting gear has a lifting body attachment end and an opposed external cargo end, and defines a load path that extends between the lifting body attachment and external cargo ends of the lifting gear. The damping assembly is connected in series with the lifting gear and is disposed along the load path to damp vibratory force transmitted between the lifting gear lifting body attachment and lifting gear ends.

Claims

1. An external cargo system for a rotary wing aircraft, comprising:

lifting gear having rotary wing aircraft and external cargo ends; and

a damping assembly which is tunable to one or more frequencies of the rotary wing aircraft and which is connected in series with the lifting gear, wherein the lifting gear and the damping assembly define a damped load path extending through the rotary wing aircraft and external cargo ends of the lifting gear to reduce vibrational force transmitted along the load path between an external load suspended from a rotary wing aircraft and the rotary wing aircraft, and wherein the lifting gear is configured to connect the damping assembly to the external load,

the damping assembly comprising;

a housing defining an aperture;

a sliding piston extending through the housing aperture and slidably disposed within an interior of the housing; and

a floating piston slidably disposed within an interior of the sliding piston, wherein the floating piston separates a variable volume first chamber and a constant volume chamber defined within an interior of the damping assembly.

2. The external cargo system as recited in claim 1, wherein the

damping assembly is connected (a) between the lifting gear rotary wing aircraft end and the rotary wing aircraft, (b) between the lifting gear rotary wing aircraft end and the external cargo end, or (c) between the lifting gear external load end and the external load suspended from the rotary wing aircraft.

3. The external cargo system as recited in claim 1, wherein a surface of the floating piston opposite the housing bounds the first chamber.

4. The external cargo system as recited in claim 1, further comprising an orifice plate fixed to the sliding piston and in fluid communication with the second chamber.

5. The external cargo system as recited in claim 1, wherein a face of the floating piston facing the housing bounds the second chamber.

6. The external cargo system as recited in claim 1, further comprising a lifting gear coupling connected to an end of the sliding piston opposite the housing.

7. The external cargo system as recited in claim 1, further comprising a load path coupling connected to an end of the sliding piston facing the housing.

8. The external cargo system as recited in claim 1, further comprising a compressible fluid port connected to the sliding piston and in selective fluid communication with the first chamber, wherein the compressible fluid port is connected to a rotary wing aircraft compressor module.

9. The external cargo system as recited in claim 1, further comprising an incompressible fluid port connected to the housing and in selective fluid communication with the second chamber, wherein the incompressible fluid port is connected to a hydraulic system.

10. The external cargo system as recited in claim 1, wherein the housing is (a) disposed with a floor portion of a rotary wing aircraft airframe, (b) suspended below a rotary wing aircraft airframe, or (c) suspended from a ceiling portion of a rotary wing aircraft airframe.

11. A rotary wing aircraft, comprising an airframe and the external cargo system according to claim 1.