U.S. patent application number 10/945602 was filed with the patent office on 2006-03-23 for in-flight refueling system, damping device and method for preventing oscillations in in-flight refueling system components.
This patent application is currently assigned to The Boeing Company. Invention is credited to Stephen M. Stecko, John F. Takacs.
Application Number | 20060060710 10/945602 |
Document ID | / |
Family ID | 35221483 |
Filed Date | 2006-03-23 |
United States Patent
Application |
20060060710 |
Kind Code |
A1 |
Takacs; John F. ; et
al. |
March 23, 2006 |
IN-FLIGHT REFUELING SYSTEM, DAMPING DEVICE AND METHOD FOR
PREVENTING OSCILLATIONS IN IN-FLIGHT REFUELING SYSTEM
COMPONENTS
Abstract
An in-flight refueling system, damping device and method are
provided for enhancing the stability of an elongate hose extending
from a tanker aircraft during an in-flight refueling operation. The
various embodiments of the system, device, and method provide a
passive, integrated damping device that may generate electrical
energy from changes in disposition of the elongate hose and then
using the electrical energy generated to impart mechanical damping
forces to a portion of the elongate hose. Thus, the embodiments may
minimize the occurrence of oscillations in the elongate hose as it
extends from the tanker aircraft during an in-flight refueling
operation.
Inventors: |
Takacs; John F.; (Long
Beach, CA) ; Stecko; Stephen M.; (Fullerton,
CA) |
Correspondence
Address: |
ALSTON & BIRD LLP;BANK OF AMERICA PLAZA
101 SOUTH TRYON STREET, SUITE 4000
CHARLOTTE
NC
28280-4000
US
|
Assignee: |
The Boeing Company
|
Family ID: |
35221483 |
Appl. No.: |
10/945602 |
Filed: |
September 21, 2004 |
Current U.S.
Class: |
244/135A |
Current CPC
Class: |
B64D 39/00 20130101 |
Class at
Publication: |
244/135.00A |
International
Class: |
B64D 39/00 20060101
B64D039/00 |
Claims
1. An in-flight refueling system comprising: a tanker aircraft; an
elongate hose having a first end carried by the tanker aircraft and
an opposing second end configured to extend from the tanker
aircraft; and a damping device operably engaged with a portion of
the elongate hose and capable of stiffening in response to a change
in disposition of the portion of the elongate hose, thereby
resisting the change in disposition of the portion of the elongate
hose in response to a force exerted thereon.
2. An in-flight refueling system according to claim 1, wherein the
damping device comprises a transducer capable of generating
electrical energy in response to the change in disposition, the
damping device further comprising a stiffening element capable of
converting the generated electrical energy into a damping force to
be exerted on the portion of the elongate hose so as to resist the
change in disposition of the portion of the elongate hose.
3. An in-flight refueling system according to claim 1, wherein the
damping device comprises material selected from the group
consisting of: piezoelectric material; piezoelectric fiber;
polyvinylidene fluoride (PVDF); and combinations thereof,
4. An in-flight refueling system according to claim 1, wherein the
damping device is integrated into the elongate hose.
5. An in-flight refueling system according to claim 2, further
comprising a controller device operably engaged with the damping
device, the controller device being capable of storing the
generated electrical energy and transmitting the generated
electrical energy to the damping device such that the damping
device is capable of exerting the damping force on the portion of
the elongate hose.
6. An in-flight refueling system adapted to be carried by a tanker
aircraft, comprising: an elongate hose having a first end carried
by the tanker aircraft and an opposing second end configured to
extend from the tanker aircraft; and a damping device operably
engaged with a portion of the elongate hose and capable of
stiffening in response to a change in disposition of the portion of
the elongate hose, thereby resisting the change in disposition of
the portion of the elongate hose in response to a force exerted
thereon.
7. An in-flight refueling system according to claim 6, wherein the
damping device comprises a transducer capable of generating
electrical energy in response to the change in disposition, the
damping device further comprising a stiffening element capable of
converting the generated electrical energy into a damping force to
be exerted on the portion of the elongate hose so as to resist the
change in disposition of the portion of the elongate hose.
8. An in-flight refueling system according to claim 6, wherein the
damping device comprises material selected from the group
consisting of: piezoelectric material; piezoelectric fiber;
polyvinylidene fluoride (PVDF); and combinations thereof.
9. An in-flight refueling system according to claim 6, wherein the
damping device is integrated into the elongate hose.
10. An in-flight refueling system according to claim 7, further
comprising a controller device operably engaged with the damping
device, the controller device being capable of storing the
generated electrical energy and transmitting the generated
electrical energy to the damping device such that the damping
device is capable of exerting the damping force on the portion of
the elongate hose.
11. A damping device adapted to be operably engaged with a portion
of an elongate hose, the elongate hose having a first end carried
by a tanker aircraft and an opposing second end configured to
extend from the tanker aircraft, the damping device being
configured to be capable of stiffening in response to a change in
disposition of the portion of the elongate hose, thereby resisting
the change in disposition of the portion of the elongate hose in
response to a force exerted thereon.
12. A damping device according to claim 11, wherein the damping
device comprises a transducer capable of generating electrical
energy in response to the change in disposition, the damping device
further comprising a stiffening element capable of converting the
generated electrical energy into a damping force to be exerted on
the portion of the elongate hose so as to resist the change in
disposition of the portion of the elongate hose.
13. A damping device according to claim 11, comprising a material
selected from the group consisting of: piezoelectric material;
piezoelectric fiber; polyvinylidene fluoride (PVDF); and
combinations thereof.
14. A damping device according to claim 11, wherein the damping
device is integrated into the elongate hose.
15. A damping device according to claim 12, further comprising: a
piezoelectric transducer; a controller device operably engaged with
the piezoelectric transducer, the controller device being
configured to be capable of storing the generated electrical energy
and transmitting the generated electrical energy to the
piezoelectric transducer such that the piezoelectric transducer is
capable of exerting the damping force on the portion of the
elongate hose.
16. A method for facilitating the stabilization of an elongate hose
having a first end carried by a tanker aircraft and an opposing
second end configured to extend from the tanker aircraft, the
method comprising: detecting a change in disposition of a portion
of the elongate hose; and stiffening the portion of the elongate
hose in response to the detected change in disposition of the
portion of the elongate hose, thereby resisting the change in
disposition of the portion of the elongate hose in response to a
force exerted thereon.
17. A method according to claim 16, wherein detecting the change in
disposition comprises generating electrical energy from the change
in disposition of the portion of the elongate hose and wherein
stiffening the portion of the elongate hose comprises converting
the generated electrical energy into a damping force to be exerted
on the portion of the elongate hose so as to resist the change in
disposition of the portion of the elongate hose.
18. A method according to claim 17, further comprising storing the
generated electrical energy from the change in disposition.
Description
FIELD OF THE INVENTION
[0001] The present invention relates generally to in-flight
refueling of a manned or unmanned aircraft using a probe and drogue
in-flight refueling system, and specifically, providing a damping
device having the capability of resisting changes in the
disposition of an elongate hose trailing from a tanker aircraft as
part of an in-flight refueling operation so as to prevent
oscillatory motion or other changes in disposition of the elongate
hose. More particularly the present invention relates to an
integrated, passive damping device operably engaged with the
elongate hose so as to stabilize the elongate hose as it is
extended from a tanker aircraft as part of an in-flight refueling
operation.
BACKGROUND OF THE INVENTION
[0002] In-flight refueling (or air-to-air refueling) is an
important method for extending the range of both manned and
unmanned aircraft traveling long distances over areas having no
feasible landing or refueling points. Although in-flight refueling
is a relatively common operation, especially for military aircraft,
the passage of large amounts of fuel between a first aircraft (the
tanker aircraft, for instance) and a second aircraft (the receiver
aircraft, for instance) during an in-flight refueling operation may
create a potentially dangerous situation, especially if components
of the in-flight refueling system are allowed to move or oscillate
in an uncontrolled manner. In addition, the close proximity of the
first aircraft and the second aircraft during an in-flight
refueling operation may create the danger of a mid-air collision
between the aircraft. Such a danger may be increased if a component
of an in-flight refueling system extending from the first aircraft
is allowed to oscillate or move in an erratic manner relative to
the first aircraft.
[0003] One conventional system for in-flight refueling is the probe
and drogue in-flight refueling system wherein the first aircraft
may extend an elongate flexible hose having an end attached to a
drogue such that the second aircraft, having a refueling probe
extending therefrom, may engage the drogue while in flight in order
to initiate the transfer of fuel. An operator of the second
aircraft is responsible for maneuvering the second aircraft such
that the refueling probe extending therefrom may enter and engage
the drogue. According to some conventional probe and drogue
in-flight refueling systems, the engagement of the refueling probe
with the drogue is accomplished as the second aircraft carefully
accelerates with respect to the trailing drogue. The drogue may
include, for instance, a catch mechanism for securing the refueling
probe within the drogue so that the refueling probe may be securely
fastened within the drogue during the transfer of fuel. The catch
mechanism may also include a fuel valve that may be opened when the
probe is secured within the drogue. Thus, fuel may be pumped from
the first aircraft into the elongate hose and down to the fuel
valve disposed in the drogue so as to pressurize the elongate hose
prior to the engagement of the probe carried by the second
aircraft.
[0004] The elongate hose extending from the first aircraft may
trail directly aft and below a fuselage of the first aircraft, or,
in some instances, it may trail directly aft and below a refueling
pod that may be carried by the first aircraft on, for instance, a
wing hardpoint. In both of these cases, the elongate hose may be
exposed to high wind speeds as it is trailed behind the first
aircraft. For instance, the first aircraft may travel at speeds
between about 180 and 400 knots during a conventional in-flight
refueling operation. During an in-flight refueling operation using
a probe and drogue in-flight refueling system, the elongate hose
may trail aft and below the first aircraft in a stable arc such
that the drogue operably engaged with the end of the elongate hose
may be held in a relatively stable position relative to the first
aircraft. In such cases, an operator of the second aircraft may
position the second aircraft such that a refueling probe extending
therefrom may engage the relatively stable drogue.
[0005] As in all mechanical systems, however, the elongate hose and
attached drogue may experience oscillatory vibrations in response
to applied forces (such as for instance, wind forces, or the impact
force encountered as the second aircraft engages the drogue). In
some cases, the elongate hose (and attached drogue) may begin to
oscillate uncontrollably (at for instance, a resonance frequency)
with respect to the first aircraft such that the drogue may move in
an erratic pattern with respect to the first aircraft such that it
may become difficult for an operator of the second aircraft to
maneuver the second aircraft such that the refueling probe
extending therefrom may be engaged with the drogue. In such cases,
the elongate hose, may, for instance, rise into an upward arc
relative to the first aircraft and/or oscillate relative to the
first aircraft. Such motion may not only make the in-flight
refueling operation difficult but also endanger both the first and
second aircraft if the motion becomes extreme. In addition, if the
second aircraft engages the drogue at a relatively high closure
rate, slack may be introduced in the elongate hose and a traveling
wave (such as a sinusoid or "sine" wave) may be propagated in the
elongate hose that may travel from the drogue to the tanker
aircraft (or the in-flight refueling system pod carried thereby).
The safety of the crews that may operate the first and second
aircraft may be in danger if the elongate hose and attached drogue
begin to impact the control surfaces, in-flight refueling system
pod, or other structural components of the first or second
aircraft.
[0006] In such cases, conventional probe and drogue in-flight
refueling systems may provide an elongate hose retraction system
disposed, for instance, in the fuselage of the first aircraft, for
stabilizing the hose with respect to the first aircraft. More
particularly, the retraction system may act to take up excess slack
in the elongate hose in order to shorten the extension of the
elongate hose in an attempt to dampen the oscillation of the
elongate hose. If such a retraction system is used, however, the
elongate hose may be drawn away from the second aircraft such that
the in-flight refueling operation must be restarted wherein the
first aircraft must re-extend the elongate hose and the second
aircraft must re-position itself relative to the elongate hose and
drogue attached to an end thereof. Additionally, simply taking up
slack in the hose may not ensure that the oscillations in the
elongate hose will not reappear when the elongate hose is
re-extended. Additionally, suspending the in-flight refueling
operation in order to retract and re-extend the elongate hose may
be disadvantageous especially in cases wherein the second aircraft
is carrying only a minimal amount of fuel and is therefore in need
of an expeditious in-flight refueling contact.
[0007] Conventional probe and drogue in-flight refueling systems
may also provide a guillotine system for cutting and jettisoning
the elongate hose should oscillations or movement of the elongate
hose and attached drogue become erratic enough so as to endanger
the operators and/or other crew of either the first or second
aircraft. However, it is undesirable to jettison the elongate hose
and attached drogue as the first aircraft must cease in-flight
refueling operations and return to an airfield for costly and
complex repairs to the in-flight refueling system.
[0008] Therefore, there exists a need for an in-flight refueling
system and method for damping oscillations and preventing changes
in disposition that may occur in probe and drogue in-flight
refueling system components, such as for instance, an elongate hose
trailing aft and below a first aircraft (serving as, for instance,
a tanker aircraft). More particularly, there exists a need for a
passive, integrated damping device that may selectively and/or
responsively add rigidity to the elongate hose in order to dampen
oscillations in the elongate hose to enhance the stability of a
portion of the elongate hose as it is trailed below and aft of the
tanker aircraft as part of an in-flight refueling operation.
[0009] Thus, it would be advantageous to provide an alternative
in-flight refueling system, damping device, and method for damping
oscillations or changes in the disposition of the elongate hose and
attached drogue that may occur during an in-flight refueling
operation. Also, it would be advantageous to provide a device for
damping oscillation of the elongate hose and attached drogue that
is passive and may be integrated into the elongate hose and other
in-flight refueling system components.
SUMMARY OF THE INVENTION
[0010] The embodiments of the present invention satisfy the needs
listed above and provide other advantages as described below. The
in-flight refueling system, according to one embodiment, includes a
tanker aircraft, an elongate hose having a first end carried by the
tanker aircraft and an opposing second end configured to extend
from the tanker aircraft, and a damping device operably engaged
with a portion of the elongate hose and capable of stiffening in
response to a change in disposition of the elongate hose (such as
an oscillation or vibration), thereby resisting the change in
disposition of the elongate hose and stabilizing the elongate hose
such that the elongate hose may be more easily engaged by a second
aircraft as part of an in-flight refueling operation.
[0011] According to other embodiments, the damping device of the
present invention may further comprise a transducer capable of
generating electrical energy in response to the change in
disposition. Furthermore, the damping device may further comprise a
stiffening element capable of converting the generated electrical
energy into a damping force to be exerted on the portion of the
elongate hose so as to resist the change in disposition of the
portion of the elongate hose. The damping device may comprise
materials selected for their ability to generate electrical energy
in response to vibration, oscillation, or other changes in
disposition such as piezoelectric materials, polyvinylidene
fluoride (PVDF); and other materials suitable for generating
electrical energy that may be used to subsequently energize the
damping device to produce a damping force that may act to stiffen
the damping device and/or resist changes in disposition of the
elongate hose. In some embodiments, the damping device may be
integrated directly into the materials of the elongate hose. The
in-flight refueling system according to some embodiments of the
present invention, may also further comprise a controller device
capable of storing the electrical energy generated by the materials
of the damping device and transmitting the generated electrical
energy back into the damping device such that the damping device is
capable of exerting the damping force on the elongate hose in a
controlled manner.
[0012] The embodiments of the present invention also provide a
method for facilitating the stabilization of an elongate hose
having a first end carried by a tanker aircraft and an opposing
second end configured to extend from the tanker aircraft. For
instance, according to some embodiments, the method comprises the
steps of detecting a change in disposition of a portion of the
elongate hose and stiffening the portion of the elongate hose in
response to the detected change in disposition so as to resist the
change in disposition of the portion of the elongate hose in
response to the exerted force. According to other embodiments of
the method of the present invention, the detecting step may
comprise generating electrical energy from the change in
disposition of the portion of the elongate hose and the stiffening
step may comprise converting the generated electrical energy into a
damping force to be exerted on the portion of the elongate hose so
as to resist the change in disposition of the portion of the
elongate hose.
[0013] Thus the various embodiments of the in-flight refueling
system, damping device, and method of the present invention provide
many advantages that may include, but are not limited to: providing
an in-flight refueling system that may resist changes in the
disposition of an end of the elongate hose trailing from a tanker
aircraft during an in-flight refueling operation, providing a
damping device that is capable of stiffening in response to the
application of electrical energy that it generates in response to a
change in disposition of the elongate hose and thereby passively
prevent oscillations that may occur in the elongate hose due to
wind or other aerodynamic forces exerted on the elongate hose and a
drogue attached thereto, and providing a damping device that may be
passively integrated into existing in-flight refueling systems
without adding large amounts of weight or the need for additional
power to be provided for its operation.
[0014] These advantages and others that will be evident to those
skilled in the art are provided in the in-flight refueling system,
damping device, and method of the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Having thus described the invention in general terms,
reference will now be made to the accompanying drawings, which are
not necessarily drawn to scale, and wherein:
[0016] FIG. 1 shows a side view of a tanker aircraft and an
elongate hose and attached drogue extending therefrom and including
a damping device according to one embodiment of the present
invention; and
[0017] FIG. 2 shows a schematic close-up of several damping devices
and associated control circuits operably engaged with a portion of
an elongate hose according to one embodiment of the present
invention.
DETAILED DESCRIPTION OF THE INVENTION
[0018] The present inventions now will be described more fully
hereinafter with reference to the accompanying drawings, in which
some, but not all embodiments of the invention are shown. Indeed,
these inventions may be embodied in many different forms and should
not be construed as limited to the embodiments set forth herein;
rather, these embodiments are provided so that this disclosure will
satisfy applicable legal requirements. Like numbers refer to like
elements throughout.
[0019] FIG. 1 shows an in-flight refueling system according to one
embodiment of the present invention including a tanker aircraft 110
and an elongate hose 114 extending therefrom. The elongate hose 114
comprises a first end (not shown) that is carried by the tanker
aircraft 110 and may be operably engaged with a fuel reservoir
located within a fuselage, wing structure, or other internal
compartment within the tanker aircraft 110. In some embodiments,
the first end of the elongate hose 114 may further be operably
engaged with a refueling pod (not shown) that may be configured to
be carried by a hardpoint located, for instance, on a portion of a
wing of the tanker aircraft 110. Furthermore, the elongate hose 114
may be configured to be capable of being taken up from an extended
position and rolled up on, for instance, a rotating drum assembly
that may be disposed within a fuselage of the tanker aircraft 110
or within a refueling pod carried on a wing hardpoint of the tanker
aircraft 110. Also shown in FIG. 1 is the second end of the
elongate hose 114 extending aft and below the tanker aircraft 110
and operably engaged with a drogue 118. The elongate hose 114 and
drogue 118 attached thereto are thus positioned so as to be capable
of being engaged by, for instance, a refueling probe 125, carried
by a second aircraft 120 which may approach the tanker aircraft 110
from the aft and below as part of an in-flight refueling
operation.
[0020] FIG. 1 also shows a plurality of damping devices 130
according to one embodiment of the present invention, operably
engaged with the elongate hose 114. In the depicted embodiment, the
damping devices 130 are shown integrated with a surface of the
elongate hose 114 along the length of the elongate hose that is
extending from the tanker aircraft 110. In such embodiments, the
damping devices 130 may be configured to be capable of stiffening
in response to changes in disposition of the elongate hose 114.
Thus, the elongate hose 114 may more effectively resist
oscillations and/or changes in disposition when subjected to
external forces such as, for instance, aerodynamic forces, wind
forces, or impact forces resulting from the engagement of the
refueling receptacle 125 of a second aircraft 120 with the drogue
118. Furthermore, the damping devices 130 may act to stiffen and/or
actuate so as to dampen and/or resist a change in disposition of
the second end of the elongate hose 114 in response to an
aerodynamic force (such as wind, wind shears, jet wash, or other
disturbances that may be encountered when the elongate hose 114 is
extended from the tanker aircraft 110 during the course of an
in-flight refueling operation). The stiffened damping device 130
may also aid in stabilizing the position of the elongate hose 114
(and the drogue 118 attached thereto) by creating additional
inertia in the elongate hose 114 such that the aerodynamic
disturbances produced in the area ahead of a second aircraft 120
(known in some instances as a "bow wave") may be less likely to
push the elongate hose 114 and drogue 118 forward as the second
aircraft 120 approaches the tanker aircraft 110 as part of an
in-flight refueling operation.
[0021] The damping devices 130 may be capable of operably engaging
the elongate hose 114 in a variety of dispositions such as, for
instance, attached above, below, or on one or more sides of the
elongate hose 114. In addition, a single damping device 130 or
multiple damping devices 130 may be disposed at one or more
positions along the length of the elongate hose 114 so as to
distribute the stiffening capability to such positions when the
damping device 130 is subjected to the changes in disposition that
may cause the damping device 130 to stiffen. Furthermore (as shown
in FIG. 2), a single damping device 130 or multiple damping devices
130 may be disposed at one or more positions about the radially
outward surface of the elongate hose 114 so as to distribute the
stiffening capability to such positions when the damping device 130
is subjected to changes in disposition. One skilled in the art will
appreciate that the damping devices 130 may also be disposed on or
within the elongate hose 114 in various configurations both
integrated within the elongate hose 114 and/or disposed on the
surface of the elongate hose 114 so as to more completely
distribute the stiffening capability when the damping device 130 is
subjected to the changes in disposition.
[0022] As shown in FIG. 2, the damping device 130 may comprise a
transducer, disposed lengthwise along a surface (or integrated
within the materials) of a portion the elongate hose 114. According
to embodiments of the present invention, the transducer is capable
of generating electrical energy in response to the change in
disposition of the elongate hose 114 (such as, for instance, a
traveling wave, vibration, or oscillation). The damping device 130
may further comprise a stiffening element capable of converting the
generated electrical energy into a damping force to be exerted on
the portion of the elongate hose 114 so as to resist the change in
disposition of the portion of the elongate hose 114. According to
some embodiments, the damping device 130 may comprise one or more
piezoelectric materials, such as for instance, piezoelectric
fibers, piezoelectric crystal or polyvinylidene fluoride (PVDF)
that may act as transducers suitable for both generating electrical
energy (in the form of, for instance, a time-varying electrical
signal) in response to the change in disposition of the elongate
hose 114 as well as stiffening elements suitable for altering their
mechanical properties (stiffening, for example) in response to an
input that may be provided by either an external controller 150
(see FIG. 1), or a control circuit 135 that may be operably engaged
with or in electrical communication with, the damping device 130.
In some embodiments, the piezoelectric materials may be integrated
into a composite structural material such as a sheath configured to
substantially surround the elongate hose 114 and thereby distribute
both the sensing and actuation capability of the piezoelectric
materials about the surface of the elongate hose 114.
[0023] In some embodiments of the damping device 130 comprising
piezoelectric materials, the piezoelectric materials may serve as a
transducer configured to generate electrical energy (in the form of
a time-varying electrical signal, for instance) in response to and
corresponding to a change in the disposition of the elongate hose
114. Such a time-varying electrical signal may then be transmitted
(via a wire 140 or wireless connection) to a control circuit 135
(such as a timer circuit, clock circuit, inverter circuit, or
similar control circuit) that may be configured to alter the signal
(such as by imparting a phase shift to the signal). The control
circuit 135 may be further configured to send the altered signal
back to the damping device 130 (and the piezoelectric material
therein) so as to induce motion in the piezoelectric material. The
resulting motion induced in the piezoelectric material may be
substantially out of phase with the change in disposition of the
elongate hose 114 such that an oscillatory change in disposition of
the elongate hose 114 may be cancelled and/or damped by the induced
motion of the piezoelectric materials. In such embodiments, a
single piezoelectric crystal disposed within the damping device 130
may serve both as a transducer and a stiffening element such that
it may: detect the change in disposition of the elongate hose 114;
produce an electrical signal that may be sent to and altered by a
control circuit 135 operably engaged with the damping device 130;
and receive the altered electrical signal from the control circuit
135 and either stiffening or imparting a motion that is out of
phase with the change in disposition so as to effectively dampen
the change in disposition of the portion of the elongate hose 114.
In other embodiments, the piezoelectric material disposed within
the damping device may be segmented so as to contain a transducer
portion configured to produce an electrical signal in response to a
change in disposition of the elongate hose 114 as well as a
stiffening portion configured to stiffen in response to either the
electrical signal produced by the transducer portion (acting in
substantially real time) or the altered electrical signal that may
be transmitted by a control circuit 135 operably engaged with the
damping device 130.
[0024] According to other embodiments of the damping device 130,
the control circuit 135 may be configured to transmit a
substantially non-time-varying electrical signal to the
piezoelectric material (or other stiffening element) so as to
induce the piezoelectric material to stiffen substantially in
response to the signal. In such embodiments, the portion of the
elongate hose 114 with which the damping device 130 may be operably
engaged may be substantially more resistant to changes in
disposition due to the increased stiffness introduced into the
elongate hose 114 by the damping device 130. Furthermore, as the
change in disposition of the portion of the elongate hose 114
ceases, the control circuit 135 may be configured to cease the
generation of the signal such that the piezoelectric material
disposed in the damping device 130 may substantially relax such
that the elongate hose 114 may again attain flexibility so as to be
capable of being flattened, rolled, and/or taken up by a hose
take-up system (such as a roller drum) that may be carried by the
tanker aircraft 110 or carried by a refueling pod configured to be
carried by the tanker aircraft 110.
[0025] In some embodiments of the present invention, multiple
damping devices 130 may be operably engaged with the elongate hose
114 along its length and at various radial positions about an
exterior surface of the elongate hose 114 (as shown in FIG. 2). In
such embodiments, the damping devices 130 may be in communication
with each other via, for instance, electrical connections that may
be established via wire 140 or wireless techniques. In such
embodiments, the damping devices 130 may be configured to transmit
and receive data related to detected changes in disposition of
portions of the elongate hose 114 that may be in the form of
electrical signals generated by the piezoelectric materials that
may be disposed within the damping devices 130. For example, in
some embodiments, a change in disposition of the elongate hose 114
may be detected by a damping device 130 (and a corresponding
control circuit 135 (as shown generally in FIG. 2) operably engaged
with a portion of the elongate hose 114 located near the drogue
118. The change in disposition detected by the damping device 130
may be used to generate an electrical signal (via, for instance,
the piezoelectric material disposed therein) that may be
transmitted, via wire 140 or wireless techniques to a second
damping device 130 (and corresponding control circuit 135 operably
engaged with another portion of the elongate hose 114 (such as a
portion located nearer the tanker aircraft 110). Thus, the
electrical signal may be generated by a first damping device 130
and transmitted to a second damping device 130 such that a change
in disposition (such as a traveling wave) of the elongate hose 114
may be detected at one point along the length of the elongate hose
114 and substantially damped and/or minimized by a damping device
130 operably engaged with a different portion of the elongate hose
114. In such embodiments, relatively sudden changes in disposition
of the elongate hose 114 (such as impact forces imparted on the
drogue 118 as a second aircraft 120 engages the drogue 118) that
may produce, for instance, a fast-moving traveling wave in the
elongate hose 114, may be detected immediately and substantially
damped before the traveling wave (and the resulting slack that may
be developed thereby) is capable of striking (and possibly
damaging) a fuselage of the tanker aircraft 110.
[0026] The embodiments of the present invention may thus provide a
damping device 130 that requires little or no external power supply
in order to operate since the transducer (such as a piezoelectric
material) may be configured to produce electrical energy (such as a
time-varying electrical signal) in response to a change in
disposition of the portion of the elongate hose 114 with which it
may be operably engaged. As described above, the electrical energy
may then be transferred to a control circuit 135 in communication
with the transducer that may be energized by the electrical energy
and configured to alter the electrical energy such that the altered
electrical energy may then be sent back to the transducer disposed
in the damping device 130 so as to dampen and/or counteract the
change in disposition of the portion of the elongate hose 114 with
which the damping device 130 may be operably engaged. Thus, in some
embodiments, the damping device 130 may be configured so as to
require little or no external power supply from, for instance, the
electrical systems of the tanker aircraft 110.
[0027] According to other embodiments of the present invention, a
controller device 150 may be operably engaged with the damping
device 130 (or multiple damping devices 130 (as shown generally in
FIG. 1). The controller device 150 may be in communication with the
damping device 130 via a wire 140 or other wireless connection and
may be capable of storing the generated electrical energy (produced
by, for instance, the piezoelectric material disposed within a
damping device 130) and selectively transmitting the generated
electrical energy to one or more damping devices 130 such that the
damping devices 130 may be further capable of exerting the damping
force on a portion of the elongate hose 114 that may be
experiencing a change in disposition such as an oscillation. The
controller device 150 may be carried within a fuselage of the
tanker aircraft 110 near the aft end of the tanker aircraft 110 as
shown generally in FIG. 1 or in some embodiments, the controller
device 150 may be carried within the fuselage of the tanker
aircraft 110 at a remote aerial refueling operator (RARO) station
located near the flight deck of the tanker aircraft (i.e. near the
forward end of the fuselage). The controller device 150 may be
connected to a power supply (such as a generator or battery)
carried by the tanker aircraft 110 and may also be in communication
with one or more control circuits 135 so as to coordinate the
transmission of electrical signals to various damping devices 130
that may be operably engaged with the elongate hose 114 so as to
dampen and/or minimize a change in disposition (such as an
oscillation and/or traveling wave) that may travel from one end of
the elongate hose 114 to another as described in more detail above.
In some embodiments, the controller device 150 may comprise a
computer device and/or other control circuitry such that the
controller device 150 may more effectively coordinate the
stiffening and/or actuation of the damping device 130 with which it
may be in communication. The controller 150 may also comprise a
user interface (such as a terminal and/or display) such that an
operator of the in-flight refueling system carried by the tanker
aircraft 110 may monitor the operation of the damping device 130
and/or override the functions of the damping device 110 in some
cases. For instance, the operator may wish to disengage and/or
cease operation of the damping device 130 as the elongate hose 114
is being taken up (by, for instance, a roller drum) into a fuselage
of the tanker aircraft 110 as the changes in disposition of the
elongate hose 114 as it is rolled and/or retracted may activate the
damping device 130, causing it to stiffen and/or actuate during the
take-up of the elongate hose 114.
[0028] In some embodiments, the controller device 150 may also
comprise a storage device (such as a capacitor, battery device, or
other electronic component) capable of storing the generated
electrical energy (produced by, for instance, the piezoelectric
material disposed within a damping device 130) and selectively
transmitting the generated electrical energy to one or more damping
devices 130 such that the damping devices 130 may be further
capable of exerting the damping force on a portion of the elongate
hose 114 that may be experiencing a change in disposition (such as
an oscillation). In such embodiments, the controller device 150 may
be capable of switching the damping device 130 to a passive mode
(such that the transducers disposed within the damping device 130
may be capable of generating electrical energy from a change in
disposition, but may not immediately transmit the energy for the
purpose of stiffening and/or actuating the damping device 130 as
described above). In such embodiments, while the damping device 130
is in a passive mode, the controller device 150 may be capable of
storing electrical energy that may be generated by the
piezoelectric material (or other transducers) disposed in the
damping device 130 as the elongate hose 114 is either extended or
retracted. Thus, at least some portion of the energy required to
actuate the elongate hose 114 take-up mechanism (such as, for
instance, an automated drum roller) may be converted from
mechanical changes in disposition to electrical energy that may
later be used to power the damping device 130 as described in
detail above.
[0029] Referring again to FIGS. 1 and 2, a method for facilitating
the stabilization of an elongate hose 114 having a first end
carried by a tanker aircraft 110 and an opposing second end
(operably engaged with a drogue 118) configured to extend from the
tanker aircraft 110 is described. According to some embodiments,
the method may comprise the steps of: detecting a change in
disposition of a portion of the elongate hose 114 (via, for
instance, a damping device 130 comprising a piezoelectric
material); and stiffening the portion of the elongate hose 114 in
response to the detected change in disposition of the portion of
the elongate hose, thereby resisting the change in disposition of
the portion of the elongate hose 114 in response to a force exerted
on the elongate hose 114. According to some embodiments, the
stiffening step may occur via the actuation of piezoelectric
materials provided as part of a damping device 130 that may be
operably engaged with the portion of the elongate hose 114 (as
described in more detail above).
[0030] According to some other embodiments, the detecting step may
further comprise generating electrical energy (via for instance the
damping device 130 and transducers included therein) from the
change in disposition of the portion of the elongate hose 114. In
addition, the stiffening step may further comprise converting the
generated electrical energy into a damping force to be exerted on
the portion of the elongate hose 114 (via a damping device 130) so
as to resist the change in disposition of the portion of the
elongate hose 114. In other embodiments of the present invention,
the method may further comprise the step of storing the generated
electrical energy from the change in disposition of the elongate
hose 114 such that the electrical energy may be selectively
transmitted to the damping device 130 when necessary to dampen
and/or counteract a change in the disposition of a portion of the
elongate hose 114 with which the damping device 130 may be operably
engaged.
[0031] Many modifications and other embodiments of the invention
will come to mind to one skilled in the art to which this invention
pertains having the benefit of the teachings presented in the
foregoing descriptions and the associated drawings. Therefore, it
is to be understood that the invention is not to be limited to the
specific embodiments disclosed and that modifications and other
embodiments are intended to be included within the scope of the
appended claims. Although specific terms are employed herein, they
are used in a generic and descriptive sense only and not for
purposes of limitation.
* * * * *