U.S. patent application number 15/752491 was filed with the patent office on 2018-08-23 for loader for aircraft.
This patent application is currently assigned to JOHN BEAN TECHNOLOGIES CORPORATION. The applicant listed for this patent is JOHN BEAN TECHNOLOGIES CORPORATION. Invention is credited to Mark James RODENKIRCH.
Application Number | 20180237160 15/752491 |
Document ID | / |
Family ID | 54008030 |
Filed Date | 2018-08-23 |
United States Patent
Application |
20180237160 |
Kind Code |
A1 |
RODENKIRCH; Mark James |
August 23, 2018 |
LOADER FOR AIRCRAFT
Abstract
An aircraft loader (54) includes an upper loading platform (50)
and an underlying frame (52) with the frame utilizing the bogey
suspension system (60), as well as carrying auxiliary lift system
(400) at the rearward end thereof for assisting in the initial
lifting of the platform relative to the frame. Powered roller
assemblies (100,110,120, and 130), composed of hollow drive shafts,
may be conveniently assembled and disassembled from the underside
of loading platform (50). A plurality of upwardly convex-shaped
static slider elements (200) facilitate unidirectional movement of
loads on the platform (50). At the forward end of the platform, a
guard or side rail (316) is rotatable from a retracted position
within the confines of a control platform (68) to a forwardly
directed position toward the fuselage of the aircraft. The side
rail (316) is shaped to resemble the exterior cross-sectional shape
of the fuselage, thereby to close the gap between the forward end
of the loading platform and the fuselage, for the protection of
loader personnel.
Inventors: |
RODENKIRCH; Mark James;
(Groveland, FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
JOHN BEAN TECHNOLOGIES CORPORATION |
Chicago |
IL |
US |
|
|
Assignee: |
JOHN BEAN TECHNOLOGIES
CORPORATION
Chicago
IL
|
Family ID: |
54008030 |
Appl. No.: |
15/752491 |
Filed: |
August 17, 2015 |
PCT Filed: |
August 17, 2015 |
PCT NO: |
PCT/US2015/045508 |
371 Date: |
February 13, 2018 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B65G 39/04 20130101;
B65G 69/22 20130101; B65G 2814/0398 20130101; B64F 1/32
20130101 |
International
Class: |
B64F 1/32 20060101
B64F001/32; B65G 39/04 20060101 B65G039/04 |
Claims
1-19. (canceled)
20. An aircraft loader for transferring loads into and out of an
aircraft, comprising: (a) a ground-engaging frame; (b) a loading
platform adapted to raise and lower relative to the frame; (c)
wherein the loading platform comprises an upper deck having a top
surface; and (d) a plurality of static upwardly convex cargo slider
elements disposed on the upper deck of the loading platform to
project above the upper deck to support loads carried by the
loading platform and facilitate movement of the loads about the
loading platform.
21. The aircraft loader of claim 20, wherein the upwardly convex
cargo slider elements comprise an upper surface disposed
substantially parallel to the top surface of the upper deck of the
loading deck to define a bearing surface for bearing against loads
being transferred.
22. The aircraft loader of claim 20, wherein the cargo slider
elements are in the shape selected from the group including a
truncated dome, a truncated dome with a base, a truncated cone, and
a truncated cone with a base.
23. The aircraft loader of claim 22, wherein the radius of
curvature of the truncated dome-shaped cargo slider elements is in
the range of about 1 inch to about 5 inches.
24. The aircraft loader according to claim 20, further comprising:
wheels to support the frame; and a suspension system acting between
the wheels and the frame, the suspension system comprising a
suspension link connected between the wheels and the frame.
25. The aircraft loader according to claim 24, wherein the
suspension system further comprises a shock absorber acting between
the suspension link and the frame to absorb shock loads imposed on
the aircraft loader during travel of the aircraft loader.
26. The aircraft loader according to claim 24, wherein the
suspension system further comprises a fluid cylinder acting on the
frame to adjust the elevation of the frame relative to the
ground.
27. An aircraft loader for transferring loads into and out of an
aircraft, comprising: (a) a ground-engaging frame; (b) a loading
platform adapted to raise and lower relative to the frame; (c)
wherein the loading platform comprises an upper deck having a top
surface; (d) wherein the loading platform comprises side portions
and a forward end portion, the forward end portion positionable
adjacent an aircraft fuselage when the aircraft loader is in use;
and (e) further comprising a retractable side guardrail located
along a side portion of the loading platform, the side guardrail
rotatable between a stowed position and an extended position,
wherein the side guardrail extends forwardly relative to the
loading platform, the side guardrail when in extended position is
shaped to correspond to the exterior circumferential shape of the
aircraft fuselage below the water line of the aircraft
fuselage.
28. The aircraft loader of claim 27, wherein the side guardrail
extends downwardly and forwardly relative to the loading platform
to simulate the exterior circumferential shape of the aircraft
fuselage adjacent the side guardrail.
29. The aircraft loader of claim 28: further comprising a walkway
disposed laterally of and along the loading platform, the walkway
having a forward end portion extending forwardly relative to the
aircraft fuselage when the aircraft loader is in use; further
comprising a forward guardrail extending upwardly from the walkway
and transversely to the forward end portion of the walkway to block
the forward end of the walkway; and wherein the side guardrail is
rotatable between a stowed position parallel to the end guardrail
and an extended position disposed transversely to the end guardrail
and disposed forwardly relative to the loading platform.
30. The aircraft loader of claim 29, wherein the forward end
guardrail comprises: a lower section attached to the walkway; and
an upper section extending upwardly from the lower section and
canted rearwardly in the upward direction relative to the forward
end of the walkway.
31. The aircraft loader of claim 29, wherein the rotatable side
guardrail comprises: a shorter upper arm; a longer lower arm; and a
downward section extending between the shorter upper arm and the
longer lower arm.
32. The aircraft loader according to claim 27, further comprising:
wheels to support the frame; and a suspension system acting between
the wheels and the frame, the suspension system comprising a
suspension link connected between the wheels and the frame.
33. The aircraft loader according to claim 32, wherein the
suspension system further comprises a shock absorber acting between
the suspension link and the frame to absorb shock loads imposed on
the aircraft loader during travel of the aircraft loader.
34. The aircraft loader according to claim 32, wherein the
suspension system further comprises a fluid cylinder action on the
frame to adjust the elevation of the frame relative to the
ground.
35. An aircraft loader for transferring loads into and out of an
aircraft, comprising: (a) a ground-engaging frame; (b) a loading
platform adapted to raise and lower relative to the frame; (c)
wheels to support the frame; and (d) a suspension system acting
between the wheels and the frame, the suspension system comprising:
(i) a suspension link pivotally connected between the wheels and
the frame; and (ii) a shock absorber interposed between the
suspension link and the frame to absorb shock loads imposed on the
aircraft loader during travel of the aircraft loader.
36. The aircraft loader according to claim 35, wherein the shock
absorber comprises a snubber positioned between the suspension
system and the frame to absorb shock loads transmitted from the
wheel to the shock absorber.
37. The aircraft loader according to claim 36, wherein the snubber
is composed of a compressible elastomeric material.
38. The aircraft loader according to claim 35, wherein the
suspension link comprises a swing arm assembly pivotally mounted to
the frame and axled to the wheels.
39. The aircraft loader according to claim 38: wherein the
suspension link is pivotally mounted to the frame; and further
comprising a linear actuator is connected between the suspension
link and the frame to control the nominal position of the
suspension link relative to the frame, thereby to adjust the
elevation of the frame relative to the ground.
40. The aircraft loader according to claim 39, wherein the linear
actuator comprises a fluid cylinder connected between the swing arm
assembly and the frame to adjust the elevation of the frame
relative to the ground.
Description
BACKGROUND
[0001] The present invention pertains to loader systems for loading
and unloading cargo and other loads from aircraft. Aircraft loaders
may include a loading platform (also "cargo platform" or "lift
platform") that is coupled to an underlying frame by a pair of
scissors arms. Hydraulic cylinders may typically act between
connection locations on the scissors arm and the underlying frame.
Although this arrangement is simple and locates the lift cylinders
below the loading platform so that the top conveying surface of the
loading platform is unobstructed, when the platform is fully
lowered and the scissors arms are folded down, this causes the lift
cylinders to be lowered into a substantially horizontal position.
In such position, the lift cylinders, being horizontally disposed,
do not have the capacity to impose a significant lifting force on
the scissors. This may be addressed by utilizing vertical mounted,
relatively short, helper cylinders. The helper cylinders act
between the frame and the loading platform to provide a relatively
high pushing force against the loading platform when the loading
platform is in fully lowered position. However, such helper
cylinders either have a relatively short total stroke or are of
multi-stage construction, which are relatively expensive.
[0002] Typical aircraft loaders must be moved from place to place
about an airport. Sometimes the loaders must be driven over
relatively long distances at high speeds and over rough surfaces.
Because in a typical aircraft loader the support wheels are mounted
to the loader frame with solid axis, there is no suspension system
between the wheels and the loader frame. As a consequence,
significant shock loads are imposed on the loader frame during the
travel of the loader about an airport. Moreover, the loader driver
can experience discomfort during the aircraft loader travel.
[0003] Aircraft cargo is typically transported in containers or on
pallets, referred to as Unit Load Devices (ULDs). During the
loading and unloading processes, the ULDs are conveyed over the
surface of the loading platform. The ULDs are moved longitudinally
along the platform, laterally of the platform, and/or rotated
relative to the platform so as to position the ULDs in correct
location and orientation relative to the cargo hold opening and
also relative to ground equipment used to place the ULDs on the
loader or receive the ULDs. Various types of powered conveying
systems are used to move the ULDs forward, backward, laterally, or
rotationally. In this regard, powered rollers may be mounted
beneath the upper surface of the loading platform. Such rollers may
consist of several rolling elements mounted on a drive shaft
extending laterally across the platform. In lieu of a simple
roller, other types of rollers may be used; for example, a
HELIROLL.RTM. multi-directional roller, manufactured by Applicant's
assignee. The HELIROLL.RTM. multi-directional roller is able to
move a container, pallet, or other load in multiple directions
depending on the operation of the roller. Such rollers are also
mounted spaced apart from each other or along a transverse support
and driven shaft. Heretofore, loading platforms were not able to
accommodate different types of rollers very easily. Moreover,
changing from one type of roller to another was a difficult and
costly process.
[0004] The conveying surfaces of aircraft loaders, in addition to
being equipped with powered elements noted above, typically also
include non-powered elements; for example, free rollers, casters
and/or ball mats. Free rollers have a single conveying axis,
whereas casters and ball mats allow conveyance in 360 degrees. A
caster is typically a free-swiveling wheel mounted "upside down,"
with the wheel disposed upwardly to support the ULD for
multi-directional conveyance. However, casters can skew the ULD as
the caster swivels into the desired direction. Also, casters are
quite tall, which can interfere with the structural elements
supporting the conveying surface and may limit spacing of the
casters about the cargo platform. In addition, because the swivel
wheel needs to rotate about a vertical axis, casters require a
relatively large opening in the conveying surface, which creates a
potential catch point for ULDs, as well as a hazard for personnel
walking on the cargo platform surface.
[0005] Ball mats are typically in the form of a relatively large
stainless steel ball supported by smaller ball bearings in a
half-round, cup-shaped housing, thereby allowing for
multi-directional conveyance of the ULD. Ball mats have the
advantage of being relatively shallow and do not skew the cargo,
nor require large openings in the conveying surface. However, ball
mats have a small contact point with the underside of the ULD,
creating high level local loads and wear on the bottom of the ULDs.
In addition, ball mats frequently collect dirt and debris in the
cup housing, which can restrict the rotation of the ball bearings
and subsequently prevent the main ball from freely turning.
[0006] In addition, casters and ball mats are susceptible to damage
from heavy and irregular shaped cargo or from equipment such as
forklifts used to position ULDs and other cargo on the surface of
the cargo platform. Moreover, both casters and ball mats contain
multiple moving parts which frequently get contaminated, damaged,
or worn, causing malfunction which impedes the smooth transfer of
ULDs and may also damage the ULDs.
[0007] In a further aspect of aircraft loader systems, it is
necessary to keep loading personnel safe during the cargo loading
and unloading processes. In this regard, aircraft cargo doors exist
both above and below the water line of an aircraft fuselage. The
fuselage does not have a straight or consistent common (straight
and/or flat) surface in which to align the loader system. Further,
the fuselage surface is typically in the form of a compound curve.
As such, the cargo loader does not make uniform contact with the
fuselage. Nonetheless, during the loading and unloading of
aircraft, personnel must enter and exit the aircraft from the cargo
loader. Typically, handrails and other protective devices are used
to protect personnel from falling from the loader. However,
heretofore, due to the varying shapes of aircraft fuselages, often
a gap exists between the handrails and the fuselage, wherein
personnel are not protected from falling off the loader.
[0008] The foregoing drawbacks or limitations of current aircraft
loaders are sought to be addressed by the various aspects of the
present disclosure.
SUMMARY
[0009] This summary is provided to introduce a selection of
concepts in a simplified form that are further described below in
the Detailed Description. This summary is not intended to identify
key features of the claimed subject matter, nor is it intended to
be used as an aid in determining the scope of the claimed subject
matter.
[0010] An aircraft loader for transferring loads into and out of an
aircraft includes a ground-engaging frame and a loading platform
adapted to raise and lower relative to the frame. The loading
platform defines an upper deck having a top surface. In addition, a
plurality of static upwardly concave cargo slider elements are
disposed on the upper deck to project above the top surface of the
upper deck, thereby to support loads carried by the loading
platform and also to facilitate movement of loads about the loading
platform.
[0011] In a further aspect of the present disclosure, the upwardly
convex cargo slider elements comprise an upper surface disposed
substantially parallel to the top surface of the upper deck of the
loading deck, thereby to define a bearing surface for bearing
against loads being transferred.
[0012] In accordance with a further aspect of the present
disclosure, the cargo slider elements are in the shape selected
from the group including a truncated dome, a truncated dome with a
base, a truncated cone, and a truncated cone with a base.
[0013] An aircraft loader for transferring loads into and out of an
aircraft includes ground-engaging frame and a loading platform
adapted to raise and lower relative to the frame. The loading
platform includes side portions and a forward end portion, with the
forward end portion positionable adjacent an aircraft fuselage when
the aircraft loader is in use. A retractable side guardrail is
located along the side portion of the loading platform. The side
guardrail is rotatable between a stowed position and an extended
position, wherein the guardrail extends forwardly relative to the
loading platform. The side guardrail, when in extended position, is
shaped to correspond to the exterior circumferential shape of the
aircraft fuselage below the waterline of the fuselage.
[0014] In the aircraft loader, the guardrail extends downwardly and
forwardly relative to the loading platform to simulate the exterior
circumferential shape of the aircraft fuselage adjacent the side
guardrail.
[0015] An aircraft loader for transferring loads into and out of an
aircraft includes a ground-engaging frame and a loading platform
adapted to raise and lower relative to the frame. An auxiliary lift
system is provided for assisting in the lifting of the loading
platform upwardly relative to the frame. The auxiliary lift system
includes at least one linear actuator acting between the frame and
the lifting platform, and a spring acting between the linear
actuator and either the loading platform or the frame.
[0016] In the aircraft loading platform, the linear actuator for
the auxiliary lift system is mounted on the frame to extend in the
upwardly direction toward the loading platform or is mounted on the
loading platform to extend downwardly toward the frame.
Correspondingly, the spring is mounted on the linear actuator to
act against the loading platform or against the frame.
[0017] An aircraft loader for transferring loads into and out of an
aircraft includes a ground engaging frame and a loading platform
adapted to raise and lower relative to the frame. Wheels are
provided to support the frame. In addition, a suspension system is
interposed between the wheels and the frame. The suspension system
includes a swing arm assembly pivotally connected between the wheel
and the frame. In addition, a shock absorber acts between the swing
arm assembly, with the shock loads imposed on the aircraft loader
during travel of the aircraft loader.
[0018] A snubber is positioned between the shock absorber and the
frame to absorb shock loads transmitted from the wheel to the shock
absorber. The snubber is composed of a compressible elastomeric
material, for example, natural or synthetic rubber.
DESCRIPTION OF THE DRAWINGS
[0019] The foregoing aspects and many of the attendant advantages
of this invention will become more readily appreciated as the same
become better understood by reference to the following detailed
description, when taken in conjunction with the accompanying
drawings, wherein:
[0020] FIG. 1 is an isometric view of an aircraft loader, showing a
loading platform separated from and disposed above an underlying
frame structure, wherein for clarity the lift structure acting
between the frame and loading platform is not illustrated;
[0021] FIG. 2 is a view similar to FIG. 1, but taken from the
opposite end of the illustrated aircraft loader;
[0022] FIG. 3 is a fragmentary view of the underside of the cargo
platform of FIGS. 1 and 2, wherein certain roller assemblies are
disassembled from the platform;
[0023] FIG. 4 is an isometric view of one type of roller
assembly;
[0024] FIG. 5 is an elevational view of FIG. 4;
[0025] FIG. 6 is a cross-sectional view of FIG. 5, taken
substantially along line 6-6 thereof;
[0026] FIG. 7 is an isometric view of another type of roller
assembly;
[0027] FIG. 8 is an elevational view of FIG. 7;
[0028] FIG. 9 is an enlarged, fragmentary view of the cargo
platform of FIG. 1, illustrating the position of cargo slider
elements;
[0029] FIG. 10 is an enlarged isometric view of the cargo slider
element shown in FIG. 9;
[0030] FIG. 11 is a top view of FIG. 10;
[0031] FIG. 12 is a cross-sectional view of FIG. 11, taken along
line 12-12 thereof;
[0032] FIG. 13 is an enlarged isometric view of the walkway
illustrated in FIGS. 1 and 2;
[0033] FIG. 14 is an isometric view of the walkway of FIG. 13 shown
in extended position;
[0034] FIG. 15 is an elevational view of a portion of the cargo
platform illustrating the walkway disposed in extended position
closely adjacent the exterior of an aircraft fuselage at an
elevation below the water line of the aircraft;
[0035] FIG. 16 is a fragmentary view of a portion of the loader
frame of FIG. 1, illustrating the position of a helper lift
assembly;
[0036] FIG. 17 is an exploded view of the helper lift assembly of
FIG. 16;
[0037] FIG. 18 is an isometric view of the helper lift assembly of
FIG. 17, taken from beneath;
[0038] FIG. 19 is a fragmentary view of the loader frame of FIG. 1,
illustrating the location of bogey wheels and associated suspension
mounted to the frame;
[0039] FIG. 20 is an isometric view of the bogey wheel and
suspension of FIG. 19 from another orientation; and
[0040] FIG. 21 is a further view of the bogey wheel and suspension
of FIG. 19 shown from beneath.
DETAILED DESCRIPTION
[0041] The attachments to this application, as well as the detailed
description set forth below in connection with the appended
drawings, where like numerals reference like elements, are intended
as a description of various embodiments of the disclosed subject
matter and are not intended to represent the only embodiments. Each
embodiment described in this disclosure is provided merely as an
example or illustration and should not be construed as preferred or
advantageous over other embodiments. The illustrative examples
provided herein are not intended to be exhaustive or to limit the
disclosure to the precise forms disclosed. Similarly, any steps
described herein may be interchangeable with other steps, or
combinations of steps, in order to achieve the same or
substantially similar result.
[0042] In the following description, numerous specific details are
set forth in order to provide a thorough understanding of exemplary
embodiments of the present disclosure. It will be apparent to one
skilled in the art, however, that many embodiments of the present
disclosure may be practiced without some or all of the specific
details. In some instances, well known process steps have not been
described in detail in order to not unnecessarily obscure various
aspects of the present disclosure. Further, it will be appreciated
that embodiments of the present disclosure may employ any
combination of features described herein.
[0043] The present application may include references to
directions, such as "forward," "rearward," "front," "back,"
"upward," "downward," "vertical," "horizontal," "lateral,"
"transverse," "diagonal," "upright," "right-hand," "left-hand,"
"in," "out," "extended," "advanced," and "retracted." These
references and other similar references in the present application
are only to assist in helping describe and understand the present
disclosure and invention and are not necessarily intended to limit
the present disclosure or invention to these directions.
[0044] In the following description, various embodiments of the
present disclosure are described. In the following description and
in the accompanying drawings, the corresponding systems assemblies,
apparatus and units may be identified by the same part number, but
with an alpha or other suffix. The descriptions of the
parts/components of such systems assemblies, apparatus and units
are the same or similar, and therefore are not repeated so as to
avoid redundancy in the present application.
[0045] FIGS. 1 and 2 illustrate the loading platform 50 and the
underlying frame structure 52 of an aircraft loader 54 used for
transferring loads into and out of an aircraft. A lift system, not
shown, is utilized to raise and lower the platform 50 relative to
the frame 52. Such lift systems may include, for example, a pair of
scissors arms connected between the platform and the frame, with
hydraulic cylinders acting on the scissors to extend and retract
the scissors arms. An example of such a lift system is disclosed in
PCT Publication WO 2011/142835, incorporated by reference herein.
The loader may include a drive motor and drive wheels (not shown)
incorporated into the forward section 56 of the frame 52. A bogey
suspension system 60 supports the rear section 62 of frame 52.
[0046] The loading platform 50 is illustrated as including a rear
section 64 disposed above frame rear section 62 and a platform
forward section 66 disposed above frame forward section 56. A
control platform 68 is mounted to one side of the forward platform
section 66 to support a control console 70 for operating the
aircraft loader. The control platform 68 also serves as a walkway
to enable personnel to move along the side of the aircraft
loader.
[0047] Describing the foregoing aspects of the aircraft loader 54
in greater detail, platform rear section 64 includes a deck main
section 80 and side sections 82 and 84. The main deck section 80
can be composed of several sub-sections, or as a singular unitary
section. Referring initially to FIG. 3, the platform rear section
64 includes an underlying support frame composed of side beam
structures 86 and 88 tied together at their rear ends by a
transverse rear beam structure 90 as well as a front beam
structure, not shown. Also, a central longitudinal beam 89 extends
parallel to the side sections 82 and 84 along the center of the
rear section 64. Such beam structures are securely fixed to the
deck main section 80 and side sections 82 and 84. In addition,
transverse beam structures may extend laterally outwardly from side
beam structures 86 and 88 to provide support for the platform side
sections 82 and 84, for example, transverse beam structures 92 and
94, shown in FIG. 3.
[0048] Powered roller assemblies of various configurations are
mounted beneath the deck main section to project upwardly through
openings formed in the deck, thereby to support and move ULDs about
the deck when loading or unloading aircraft. FIG. 3 illustrates two
basic types of powered roller assemblies, including roller assembly
100, composed of straight standard rollers 102 mounted on a hollow
drive shaft 104 having drive sprockets 106 attached to an end
thereof adjacent beam 88. See also FIGS. 4, 5, and 6. The roller
assembly 100 extends transversely half-way across the deck 80 with
a second roller assembly 110 constructed similarly to roller
assembly 100 positioned on the other side of the deck. Use of two
separate roller assemblies 100 and 110 facilitates assembly of the
roller assemblies. Roller assembly 110 also includes rollers 112, a
hollow drive shaft 114, and drive sprockets (not shown). The end
portions of the hollow drive shafts 104 and 114 are mounted to the
frame side beams 86 and 88 and center beam 89 by bearing assemblies
having housings or flanges attachable to the beam structures. Such
bearing assemblies may take many forms. Nonetheless, by
constructing the roller assemblies 100 and 110 with hollow drive
shafts and in two sections in the manner shown in FIG. 3, such
drive shafts can be conveniently installed or removed from the
loading platform 50. Moreover, the hollow drive shaft reduces the
weight of the roller assemblies of similar roller assemblies
constructed with solid drive shafts, without any significant loss
in structural integrity of the roller assemblies or their drive
shafts while significantly reducing the rotational mass of the
roller assemblies.
[0049] Next, also referring to FIGS. 7 and 8, a second
configuration of roller assembly 120 is illustrated. The roller
assembly 120 includes a plurality of roller subassemblies 122
mounted on a hollow drive shaft 124 in a manner similar to rollers
102 mounted to drive shaft 104. It is noted that subassemblies 122
are shown schematically in FIGS. 1, 2 and 3. Also similarly, a pair
of drive sprockets 126 are mounted to one distal end of the drive
shaft 124. The other end of the drive shaft 124 is positioned
adjacent roller assembly 130 positioned on the other side of center
beam 89 from the location of the roller assembly 120. Roller
assembly 130 is constructed similarly to roller assembly 120,
including having roller subassemblies 132 mounted on a hollow drive
shaft 134, and drive sprockets, not shown. The roller assemblies
120 and 130 are mounted to the underside of deck main section 80 in
a manner similar to that described above with respect to roller
assemblies 100 and 110. As such, the roller assemblies 120 and 130
may be conveniently installed and removed from the deck section
80.
[0050] Referring specifically to FIGS. 7 and 8, roller
subassemblies 122 and 132 are each composed of a plurality of
generally barrel-shaped rollers 148 mounted in canted or helical
fashion so as to impart a rotational force on the underside of the
ULDs, thereby causing the ULDs to rotate relative to the platform
deck 80. Such roller subassemblies 122 and 132 are articles of
commerce, e.g., HELIROLL.RTM. multi-directional rollers
manufactured by Applicant's assignee. The roller assemblies 120 and
130, as in roller assemblies 100 and 110, enable convenient
assembly and disassembly from the loader 54. Moreover, with the
drive shafts 124 and 134 being of hollow construction, the overall
weight of the roller assemblies 120 and 130 is reduced relative to
if the shafts 124 and 134 were of solid construction.
[0051] Referring to FIGS. 1, 2, and 9-12, in addition to utilizing
powered rollers to move ULDs during the loading and unloading
process, the loading platform 50 also includes a plurality of
static cargo slider elements 200, which are shown as mounted along
the length of the side portions 82 and 84 of platform rear section
64 as well as along side portions 202 and 204 of platform forward
section 66. It will be appreciated that the platform forward
section 66 may be constructed similarly to platform rear section
64, including utilizing roller assemblies similar to roller
assemblies 100, 110, 120, and 130. Moreover, the forward platform
section 66 may include an underlying frame structure similar to
that described above with respect to rear platform section 64.
[0052] As shown most clearly in FIGS. 10, 11, and 12, the slider
element 200 is upwardly convex in shape, having a substantially
flat upper circular surface 210 and downwardly extending side
surface 212 that are illustrated as intersecting a vertical base
section 214. Although the side surface 212 is shown in the form of
a truncated dome, the side surface could be of other shapes, such
as with straight sides, in the form of a cone or a truncated cone.
Moreover, the side section 212 can extend all the way down to the
lower surface 216 of the slider element 200 and thus not utilize a
vertical base section such as base section 214 per se.
[0053] The slider element 200 is secured to the platform sections
64, 66, 202, and 204 by a hardware member, for example, in the form
of bolt 217, extending through a washer 218 and then through a
close-fitting through-hole 220 formed in the slider element. A nut
or other type of fastener, not shown, may be used to engage the
bolt 217 from beneath the platform sections 64, 66, 202, and 204. A
counterbore 222 is formed above through-hole 220 to receive the
head of the bolt 217 and position such head below the top surface
210 of the slider element. In installed position, the top surface
210 of the slider element is preferably essentially level with or
slightly below the conveying surface as defined by the various
rollers utilized on the loader.
[0054] The slider element can be composed of numerous types of
materials, including high-density plastic materials that exhibit
low sliding or conveying resistance. One such material is PTFE,
which is a relatively hard material with high wear resistance. This
material is an organic polymer having high molecular mass. The
plastic material utilized to form the slider element 200 may
include a reinforcement or filler material, as well as an exterior
coating. The filler can have lubricating properties.
[0055] It will be appreciated that the angled or sloped side
surface 212 of the slider element will force the edges of a bent or
sagging ULD upward to prevent such edges from getting stuck or
hanging up on the slider element. Moreover, the relatively large
flat top 210 of the slider element 200 provides a relatively large
bearing area to support the ULD without significant risk of damage
or wear on the bottom of the ULD. Further, the relatively
straightforward construction of the slider element 200, not
requiring any moving parts, reduces the susceptibility of the
slider element to damage, wear, or contamination.
[0056] The slider element 200 can be constructed of various sizes.
For example, the slider element may have a base diameter in the
range from about 3 to about 7 inches and the diameter of the top
surface 210 can be from about 11/2 to 31/2 inches. Further, the
radius of curvature of the side section 212, if in the form of a
truncated dome, could be in the range of 1 inch to about 5 inches,
again depending in part on the overall diameter of the slider
element 200.
[0057] Next, referring to FIGS. 1, 2, 13, 14, and 15, the control
platform 68 is illustrated as mounted along the side of the forward
platform section 66. The control platform includes a telescoping
deck portion 300 composed of the rearward stationary section 302
and a forward telescoping section 304. Control console 70 is
mounted on the stationary section 302. The rear, outward side and
forward end of the deck platform is bounded by railing structure
306 that accommodates the extension retraction of telescoping
section 304. The railing structure 306 includes a forward section
308 composed of upright posts 310 extending upwardly from the end
of the deck of telescoping section 304. A transverse intermediate
cross rail 312 interconnects the posts 310 intermediate their
heights, and a top cross rail 314 interconnects the upper ends of
posts 310. A retractable side guardrail 316 is pivotal between a
storage position shown in FIG. 13 to extend generally parallel to
the forward section 308 of the rail structure to swing
approximately 270.degree. to assume the extended position shown in
FIGS. 14 and 15.
[0058] The purpose of the side guardrail 316 is to form a barrier
in the lateral direction of the loader 54 adjacent the fuselage F
of the aircraft. The side guardrail 316 seeks to simulate or
correspond to the exterior circumferential shape and curvature of
the fuselage F along the side portion of the loader 54. In this
regard, see FIG. 15. To this end, side guardrail 316 includes a
railing section 320 that extends downwardly and forwardly relative
to the loading platform 50. Though the railing section 320 is
illustrated as composed of a straight segment, the railing section
could be curved or could be composed of multiple segments. The side
guardrail 316 also includes a shorter upper section 322 projecting
transversely from post 310, and a longer lower section 324
generally parallel to upper section 322 and longer in length so as
to meet the lower end of the downward rail section 320. A lower
vertical rail section 326 is interposed between downward section
320 and lower section 324. However, the lower section 326 can be
incorporated into the downward section 320.
[0059] The side guardrail 316 is connected or coupled to the post
310 in a manner that locks the side guardrail 316 either in
retracted position as shown in FIG. 15 or extended position as
shown in FIGS. 16 and 17. In this regard, a coupler 330 is
interposed between post 310 and side guardrail 316 to enable the
side guardrail to rotate between extended and stowed position but
then be locked in place once the side guardrail is in either
position. To this end, the couple 330 can be designed to enable the
side guardrail 316 to be lifted in the upward direction for
rotation between retracted and extended position and then lowered
relative to the post 310, thereby locking the side guardrail into
position.
[0060] Resilient pads or bumpers 340 are mounted on the
intermediate and top cross rails 312 and 314, as well as on
downward rail section 320, and further on lower rail section 326.
Such pads can be of various constructions, including composed of a
resilient, compressible elastic material, a foamed material, a
flexible resilient sheet material rolled over, etc. Moreover, the
pads 340 can be mounted on the railing structure and side guardrail
316 in any appropriate manner, including through the use of
hardware members.
[0061] As shown in FIGS. 1 and 2, a railing structure 350 can be
located on the opposite side of the loading platform forward
section 66 from the location of the control platform 68. The
railing section 350 may utilize a forward side guardrail 352 that
is constructed similarly to the side guardrail 316 described above.
As such, the description of the side guardrail 352 need not be
repeated.
[0062] Next, referring to FIGS. 1, 2, and 16-18, as noted above,
loading platform 50 is raised and lowered relative to underlying
frame 52 by a lift system. As noted above, typical lift systems are
not able to apply significant upward force when the loading
platform is in fully lowered position or nearly so. As a
consequence, the loader 54 utilizes an auxiliary lift system 400
for assisting in the lifting of the loading platform 50 relative to
frame 52 when the platform is in lowered position. The auxiliary
lift system 400 includes linear actuators 402 positioned in the
rear corners of the frame rear section 62. In this regard, corner
brackets 404 located at the intersection of the frame side rails
406 and frame rear cross rail 408 have an opening 410 formed
therein for receiving the lift system 400 therethrough.
[0063] The linear actuator 402 can be of a multi-stage telescoping
construction, for example, composed of two or three telescoping
sections, such as sections 414 and 416 shown in FIG. 17. A
cylindrical cover 418 is attached to the upper telescoping section
416 to travel upwardly and downwardly with the telescoping section
416. The outer diameter of the cover 418 is sized to closely engage
the inside diameter of a compression spring 420. The cover 418 is
constructed with the lower circular flange 422 that serves as a
seat for the lower end of the spring 420. The spring 420 is sized
to nominally extend above the upper surface of the cover 418. The
upper end of the compression spring 420 bears against the underside
of loading platform 50 when the loading platform is lowered
sufficiently relative to the frame 52.
[0064] In operation, the linear actuator 402 provides a large
lifting force during the initial upward lifting of the loading
platform 50. As the platform 50 is raised by the actuator 402, the
main lift cylinders, discussed above, gain better mechanical
advantage and are able to contribute more to the total lifting
force. Thus, when the linear actuators 402 reach the end of their
stroke, the required helper force is at a sufficiently low level
that the compression springs 420 are able to extend and provide
additional lifting force against the loading platform 50.
[0065] Moreover, when the lifting platform 50 is lowered, the
springs 420 are contacted first by the platform to compress the
springs. This slows the downward travel of the platform and reduces
the impact force against the linear actuators 402.
[0066] Although two linear actuators 402 are illustrated, the
number of linear actuators may be fewer or greater as required.
Moreover, in the auxiliary lift system 400, the linear actuators
402 are illustrated as mounted on the underlying frame 52. However,
the linear actuators may instead be mounted to the underside of the
lift platform 50 with the springs 420 extending downwardly against
the frame 52.
[0067] Further, the linear actuators 402 may be in the form of a
fluid actuator, such as a hydraulic multi-stage cylinder. However,
other types of fluids, including air, may be utilized as the
operating medium for the linear actuator. Alternatively, other
types of linear actuators may be employed, such as electrical or
piezoelectrical actuators.
[0068] Next, referring to FIGS. 1, 2, 19, 20, and 21, a bogey
suspension system 60 is utilized in conjunction with loader 54. A
suspension system is mounted between interior frame side plate 500
and exterior side plate 502 positioned along frame side rails 406.
The suspension system 60 includes a swing arm assembly 504 that
interconnects wheel 506 to the side plates 500 and 502. In this
regard, the swing arm assembly 504 includes an elongated pivot arm
508 that extends from the wheel axle 510 to a cross brace 512 that
extends laterally from the pivot arm 508 to a shorter parallel
pivot arm 514. Stub shafts 516 project outwardly from the pivot
arms 508 and 514 to engage through close-fitting openings 518
formed in the side plates 502 and 504. The swing arm assembly 504
rotates about the openings 518.
[0069] The swing arm assembly 504 also includes a transverse pivot
shaft 530 spanning across between pivot arm 508 and arm 514
parallel to the stub shafts 516. A shock absorber 532 or similarly
operating component transversely extends from the pivot shaft 530
to an end plate 534. The shock absorber 532 includes an outer
cylinder portion 536 and an interior cylinder rod portion 540, the
distal end of which is fixed to pivot shaft 530. The end plate 534
is bolted to frame cross plate 542 by hardware members in the form
of bolts 544 that capture a resilient snubber member 546
therebetween. Compression springs 548 are engaged over bolts 544
and compressed between the heads 550 of the bolts 544 and the
adjacent face of end plate 534. In addition, a formed top shield
552 is held in place by the upper two bolts 544 to protect fluid
fittings 554 disposed on the upper side of the shock absorber
cylinder portion 536.
[0070] The shock absorber 532 can be part of an active suspension
system wherein fluid is introduced into the cylinder portion 536 to
rotate the swing arm 504 thereby to raise the frame 52 relative to
the ground. Alternatively, fluid may be removed from the shock
absorber to lower the frame 52 relative to the ground. Moreover,
the pressure of the fluid within the cylinder 536 may be altered to
vary the ride characteristics of the suspension system.
[0071] In addition, vibration and low-level forces on the wheel 506
may be absorbed by the snubber 546, composed of a resilient
elastomeric material that is capable of absorbing shock loads. Such
material may include natural or synthetic rubber or similar
dampening/resilient materials. One non-limiting example is
75-durometer rubber. The springs 548 control or limit the rebound
of the end plate 534 relative to the snubber 546.
[0072] It should be appreciated that the suspension system 60 may
increase the life of the loader 54 and particularly frame 52 to
reduce the shock loads imposed thereon during travel of the loader
about an airport, especially if travel occurs over rough surfaces
and/or at high speeds. In addition, the comfort and safety of the
loader operator are improved. Further, the suspension system may
enable the loader 54 to travel at higher speeds from place to place
while still reducing shock loads on the loader during travel.
[0073] While illustrative embodiments have been illustrated and
described, it will be appreciated that various changes can be made
therein without departing from the spirit and scope of the
invention. In this regard, rather than utilizing a loading platform
50 composed of a rear section 64 and a separate forward section 66,
the platform could be composed of a single structure or section. In
addition, the static slider elements 200 may be located elsewhere
on the loading platform other than along deck side sections 82, 84,
202, and 204. For example, the static slider elements may be
located in the central or main deck section 80 of the platform rear
section, as well as similarly positioned in the platform forward
section 66.
* * * * *