Aeronautics and astronautics – Aircraft structure – Passenger or cargo loading or discharging
Reexamination Certificate
2002-05-28
2004-03-23
Barefoot, Galen L. (Department: 3644)
Aeronautics and astronautics
Aircraft structure
Passenger or cargo loading or discharging
C244S137300, C244S0010TD
Reexamination Certificate
active
06708926
ABSTRACT:
BACKGROUND OF THE INVENTION
The present invention relates to a system and a method for more efficiently deploying and retrieving large external loads from an aircraft, such as a helicopter.
Currently, the U.S. Navy and the Japanese Maritime Self Defense force deploy and retrieve airborne mine counter measures (AMCM) equipment using a system
10
such as that shown in FIG.
1
. The system
10
includes a tow boom
12
, a winch
14
, a davit
16
, a cradle
18
, a modified aircraft ramp
20
capable of moving from an up and closed position to a 90 degree (vertically down) open position, and an aperture guard
19
. Airborne mine counter measure deployment and retrieval operations are performed as follows. The tow boom
12
is moved from its center line stowed position to a side stow position. The winch cable
22
is unwound from the winch
14
aft to the davit sheave
24
. The davit sheave cable retainer is opened and the cable
22
is laid on the sheave
24
and locked in place by closing the davit cable retainer. The cable
22
is then run to and attached to the towed body
28
. The towed body
28
is unstrapped from its transport cradle
18
. The davit
16
is rotated aft from its stowed forward position while the winch
14
is then activated, lifting the towed body
28
from its cradle
18
. At the same time, the ramp
20
is lowered to further increase the clearance between the cradle
18
and the towed body
28
. Continuous rotation aft of the davit
16
is maintained as the ramp
20
is now also lowered until the towed body
28
fully clears the ramp
20
and the cradle
18
. The towed body
28
is then further lowered until it enters the water by a synchronous operation of the winch
14
and the davit
16
. A tow ball is secured to the tow cable
22
. The tow boom
12
is rotated to the aircraft center line and lowered over the tow cable
22
and the tow ball. The tow cable
22
is played off the winch
14
to trap the tow ball in the tow hook
34
. A guillotine is placed over the tow cable
22
and secured to the aft facing end of the tow boom tow hook
34
. The aircraft is now ready to begin tow operations. Towed body retrieval is the reverse of this procedure, with the additional crew task of using a manually held pole to stabilize and correct the attitude of the towed body
28
as it approaches the aircraft.
This prior art system is very inefficient and can have a large weight impact on the basic aircraft. This prior art system also is very labor intensive and has high risk tasks associated with it. Still further, this prior art system requires extensive fuselage modifications.
SUMMARY OF THE INVENTION
Accordingly, it is an object of the present invention to provide a system and a method for deploying and retrieving large external loads from an aircraft such as a helicopter.
It is a further object of the present invention to provide a system and a method as above which is simpler to use.
It is still a further object of the present invention to provide a system as above which is self-contained and modular in nature.
It is yet a further object of the present invention to provide a deployment and retrieval system which can be integrated into an existing aircraft structure with minimum structural modifications.
The foregoing objects are attained by the deployment and retrieval system and method of the present invention.
In accordance with the present invention, a system for deploying and retrieving an external load from an aircraft, such as a helicopter, broadly comprises a support frame, a winch connected to the support frame, a tow cable wound around the winch, which tow cable is connected to the external load, and a support structure connected to the support frame. The support structure is axially movable relative to the support frame for moving the external load so as to aid in deploying the load or aid in controlling the center of gravity of the aircraft.
Further, in accordance with the present invention, a method for deploying and retrieving an external load from an aircraft broadly comprises the steps of providing a self contained modular deployment and retrieval system which includes a support frame, a winch connected to the support frame, and an axially movable support structure connected to the support frame for supporting a sheave, passing a tow cable on the winch over the sheave and connecting an end of the tow cable to the external load, and moving the support structure relative to the support frame from a retracted position to a deployed position so that the external load passes through an opening in the aircraft.
Other details of the modular integrated self contained cargo deployment and retrieval system of the present invention, as well as other objects and advantages attendant thereto, are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
REFERENCES:
patent: 3782319 (1974-01-01), Hale
patent: 4298176 (1981-11-01), Kendall
patent: 4598882 (1986-07-01), Opdahl
patent: 4890751 (1990-01-01), Opdahl
patent: 5137193 (1992-08-01), McDonald
patent: 5260820 (1993-11-01), Bull et al.
patent: 6056236 (2000-05-01), Weimer et al.
Bachman & LaPointe P.C.
Barefoot Galen L.
Sikorsky Aircraft Corporation
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