Helicopter supported material transfer assembly

• US 4,826,109 A
• Filed: 07/11/1988
• Issued: 05/02/1989
• Est. Priority Date: 07/11/1988
• Status: Expired due to Fees

• Current Assignee: Mark D. Camus
• Original Assignee: Mark D. Camus
• Inventors: Camus, Mark D.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US07/217,624
• Time in Patent Office: 295 Days
• Field of Search: 244/137.4, 244/136, 244/17.11, 244/31, 244/33, 244/1 TD, 414/624, 414/625, 414/626, 37/183 R, 294/68.23
• US Class Current: 244/137.4
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface

Abstract

A material handling assembly primarily in the form of a clamshell structure being hyraulically activated and used in combination with a helicopter for the support of the clamshell structure and its operation thereof between a closed and an open position. The height and actual positioning of the clamshell relative to any applicable types of materials being handled or transferred is regulated by the height and positioning of the helicopter.

Claims

1. A material handling assembly used in combination with a helicopter for the support, positioning and operation thereof, said assembly comprising:

a. a clamshell device having an activating means attached thereto for the opening and closing of said clamshell,

b. a suspension assembly having an elongated configuration and connected to and supporting said clamshell at one distal end of said suspension assembly, an opposite end of said suspension assembly secured to said helicopter,

c. control means mounted on said helicopter and interconnected to said clamshell and said activating means thereof for regulating operation of said clamshell,

d. said control means and said activating means being hydraulically structured and fluid activated and connected in fluid communication to one another by a fluid conduit assembly, and

e. said fluid conduit assembly extending along the length of said suspension means and removably connected at one end thereof to said helicopter.

2. An assembly as in claim 1 wherein said control means comprises a fluid reservoir connected to said activating means via said fluid conduit assembly and a pump means interconnected in fluid communication with both said fluid reservoir and said activating means for forcing fluid flow therebetween along said fluid conduit assembly, a drive motor drivingly connected to said pump means and electrically powered by an electric generator of said helicopter.

3. An assembly as in claim 2 wherein said control means further comprises a switch assembly mounted on said helicopter at a flight control area accessible to personnel occupying the helicopter.

4. An assembly as in claim 3 further comprising a control valve means connected in fluid communication between said fluid reservoir and said activating means for regulating fluid flow therebetween, said switch assembly connected to said control valve means and cooperatively structured therewith to activate said control valve means and regulate flow of fluid therethrough.

5. An assembly as in claim 4 wherein said activating means comprises a hydraulic piston and cylinder assembly secured to said clamshell in operative engagement with a hinge assembly thereon, said hinge assembly positionable between an open and a closed position.

6. An assembly as in claim 1 further comprising a connection assembly structured to releasably connect said suspension means to said helicopter.

7. An assembly as in claim 1 further comprising a quick release coupling disposed to define an interconnection between said control means and said fluid conduit assembly.

8. An assembly as in claim 7 wherein said quick release coupling is structured to allow fluid flow therebetween and define a removable interconnection between a correspondingly positioned end of said fluid conduit assembly and said control means.