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Патент USA US3088713

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May 7, 1963
-
F. LARsoN
3,088,699
RETRACTABLE LANDING GEAR
Filed June 1, 1961
3 Sheets-Sheet 1
IN VEN TOR.
„ed/23617607ß
ATTORNEYS
May 7, 1963
’
FQ LARsQN
RETRACTABLE LANDÍNG GEAR
Filed June 1, 196i
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3,088»699
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3 Sheets-Sheet 2.
INVENTOR.
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May 7,1963
F. LARsoN
3,088,699
RETRACTABLE LANDING GEARFiled June l, 1961
3 Sheets-»Sheet 3
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Patented May 7, 1363
2
retractable landing gear which is indicated generally by
the numeral ‘25, and the landing gear 25 is especially suit
3,038,699
RETRACTABLE LANDING GEAR
Fred Larson, 2313 SE. 3rd Ave., Vero Beach, Fla.
Filed June 1, 1961, Ser. No. 114,106
3 Claims. (Cl. 244-102)
able for relatively -small or lightweight aircraft, and as
shown in the `drawings the retractable landing gear 25 in
cludes -a pair of inclined movable struts or arms 27 which
have landing wheels 26 operatively connected to the lower
ends thereof, and Ias shown in FIGURES 7 and 8, the
The present invention relates to 'an airplane, and more
particularly to a retractable landing gear for an airplane
struts 27 are cutaway or recessed as at 28 so as to insure
or aircraft.
that there will be proper clearance as the struts move in
The primary object of the present invention is -to pro 10 land yout of the fuselage 22. The numeral 29` indicates
a brake mechanism which is operatively associated ywith
each of the landing Wheels 26 whereby the mechanism 29
can be used for controlling spinning or rotation of the
wheels 26 in order t-o help prevent excessive wear on the
vide a retractable landing gear for an airplane such as a
relatively small lightweight airplane, `and wherein the
present invention provides a means whereby the front
landing wheels or undercarriage can be retracted after the
airplane takes off so as to help reduce wind resistance o-r 15 rubber tires of the wheels during landing of the aircraft.
drag on the airplane which would occur if the wheels were
The `struts 27 are provided with passageways 30 therein
permitted to remain in extended position «below the fuse
whereby hydraulic fluid, air under pressure yor other actu
lage.
ating substances can be conveyed from a suitable source
of supply and pumped through flexible hoses or conduits
able landing gear of the type stated wherein there is pro 20 31 and through the passageways 30 in order «to provide a
vided a means for causing extension or retraction of the
means for «actuating the mechanisms 29, and as shown in
FIGURE 2 spring members or coil springs 32 are suitably
lairplane landing wheels, and wherein there is also pro
A further object lof the invention is to provide a retract
vided a locking means for safely maintaining the landing
connected »to the flexible hoses 31 so as to take -up slack
in these hoses at the proper time.
wheels locked in extended or retracted position as desired
or required.
Further objects and advantages are to provide improved
elements and arrangements thereof in a device of the ch-ar
25
‘Positioned within the fuselage 22 are horizontally dis
acter described that is economical to produce, durable
posed support members or walls 33 ‘and 34, and the
numeral 35 indicates a reversible electric motor which is
mounted in the lower portion of the fuselage 22, and the
in form, and conducive to the most economical use of ma
motor 35 may be connected to a suitable source of elec
terials and uniformity of members formed therefrom.
30 trical energy, and the motor 35 may have associated there~
Still further objects and advantages will become appar
with an electrical circuit which includes a manually oper
ent in the subsequent description in the specification.
able control switch for controlling actuation or rotation
of the motor 35.
In the drawings:
FIGURE 1 is ya semi-diagrammatic view, with parts
The numeral 36 indicates a locking mechanism for
broken away and in section, looking towards the front end 35 maintaining the landing wheels safely locked in extended
or retracted position, and there is provided one of the
of an airplane and showing the landing wheels extended.
FIGURE 2 is a View generally similar Áto FIGURE 11
locking mechanisms 36 for each wheel and strut, and »as
but showing the landing wheels retracted.
shown in FIGURE 5 each locking mechanism 36 includes
a solenoid 37 which is suitably secured in place on an
FIGURE 3 is a fragmentary cross sectional View, taken
in plan, and with the landing wheels in extended position 40 upper support member 33, and the numerals 3S indicate
as shown in FIGURE 1.
FIGURE 4 is a fragmentary sectional view showing the
motor means and belts and roller drive for actuating the
struts of the landing wheels.
conductors or wires which are adapted to be electrically
`connected to the -solenoid 37, and a hand switch 39 is
electrically connected to the solenoid 37, as vshown in the
drawings. The numeral 40 indicates a movable plunger
FIGURE 5 is la fragmentary sectional view showing 45 which is actuated by the solenoid 37, and a bell crank
details of the locking mechanism for maintaining the
lever 41 is pivotally connected to the plunger 40 as at
landing wheels extended or retracted.
42, and the lever 4i is pivotally connected to a locking
FIGURE 6 is a fragmentary sectional view showing a
pin or dog 44 as at 43. The pins 44 are mounted for
guide wheel and drive roller for a strut.
movement into and out of engagement with openings 4S
FIGURE 7 is a plan view of one of the struts with 50 and 46 in the struts 27, and as sho-wn in FIGURE 5,
a wheel and hose attached thereto.
FIGURE 8 is another view of a stru-t.
FIGURE 9 is an elevational view of a strut :and wheel
taken at right angles to the view shown in FIGURES 7
tapered or beveled shoulders -47 are arranged in the vicin
ity of the openings I45 and 46 in order to provide a guiding
surface for the pins 44. The pins 44 are movably
mounted and depend from casings 49, and coil springs 48
and 8.
55 are positioned in the casings `49 for biasing the pins 44 in
FIGURE l0 is a fragmentary elevational View, with
the proper direction, and the casings 49 are adapted to be
secured to or formed integral with the upper support
ing of a landing wheel to the strut.
members 3-3.
Referring in detail to the drawings, the numeral Z0 indi
There is provided in the lower side portions of the
cates an Iaircraft or airplane which is provided with a 60
fuselage 22, recessed areas or port-ions «50 which are
fuselage 22 'and a wing 21 as well as the usual propeller
adapted to snugly receive «therein the wheels 26 when the
23, FIGURE 3, and the numeral 24 indicates a portion
of the tail struc-ture for the airplane 20.
landing gear is retracted, as for example as shown in
_According to the present invention there is provided a
FIGURE 2. The numeral 51 indicates the usual braces
parts broken away and in section, illustrating the mount
3,088,699.
3
4.
or strutsV `which extend between the fuselagek 22 _and the
struts areY moved, the hand switch 39 Visuadapted to be
The struts 27 are mounted for extended or
manually actuated in order rto energize the solenoid 37
retracted movement through openings or slots 52 in the
so as to move the plunger 40y which in turn pivots the
wall portion 53 of the fuselage 22.
bell crank 41 whereby the pin 44 can be withdrawn from
The numeral 54 indicates a shaft which is driven by
the reversible motor 35, and a pair of pulleys 55 and 56
are mounted on and añìxed to the shaft 54. A pair of
moved by the friction drive rollers 61. The tapered
shoulders or surfaces 47 adjacent the -openings 45 `and 46
endless belts 57 and 58 are trained around the pulleys
provide a >guiding 4surface `for the pins 44 so as to help
wing 21.
an opening 45 or 46 in order to permit the stru-t 27 to be
insure that the locking action takes place smoothly and
traveling in a generally straight direction, as yfor example 10 eñiciently.
54 and 55, and the belt 5S is adapted to have »its runs
The struts 27 are provided with elongated ducts or pas
sageways 30 which are »adapted to be used .for conveying
hydraulic fluid, air under pressure or the like to the mech
anisms or units 29 which are of convention construction,
as thebelt 58 with a portion lthereof in criss-cross rela
tion is such that ‘both struts 27 Will be simultaneouslyv 15 and these units 29 may be used for causing the wheels
as shown in FIGURE 2, while the runs of the belt 57 are
arranged in criss-cross relation with respect to each other,
and this arrangement of having one of the belts such
retracted or extended in the desired manner. In other
words if one of the belts such as the belt 58 did not have
a portion thereof -in criss-cross relation, upon actuating
of the »moto-r 35, one strut 27 `would move in While the
26 to spin just before the »airplane lands in order to help
reduce unnecessary wear on the rubber tires ofthe wheels.
The passageways 30 are adapted to be connected to a suit
ablesource ofsupplyrof hydraulic fluid, air or the like.
20 by means of the hoses or conduits 3‘1, and these 'hoses 31
are of the llexibletype,` andas the ¿struts 27 move in or
The upper portions of the belts 57 and 58are anranged
other would move out.
out, the coil springs32 provide a means for -automatically
in engagement with pulleys 59 that are suitably affixed
takingu-p. slack in, thehoses.
to driven shañts 60 and the shafts 60 may be journaled
The parts canfbe `made of any suitableV material .and
in wall members 62. Drive rollers 61 are suitably aiïixed
to the 4shafts 60, and these drive rollers 61 frictionally 25 in different shapes or sizes.r
Due to the provision of the reversible motor 35, they
engage the struts 27, so as to cause the struts to move
to extended or retracted positions at the proper time.
drive rollers 61 can be driven or rotated in a clockwise
readily fly through the air.
utilized «as the power driving means.
To move the landing gear to extended or retracted posi
tion, it is only necessary to actuate the reversible motor
35, and as the motor 35 is actuated it rotates the shaft
other types of recesses or caviites can be provided for
or counter-clockwise directionin order toefñciently and
As shown in the drawings guide wheels 63-`-are pro
effectively extend or retract the landing gear.
vided on opposite sides of the struts for serving to main
The retractable landingV gear mechanism'` of the present
tain the struts in their proper aligned position as they 30
inventionY is especially suitable for use with airplanes
move in and out of the fuselage.
having high wings. By retracting the landing. gear after
From the foregoing, it is apparent that there has been
the plane takes off, the speeds ofthe lairplane will. be
provided a retractable landing gear for an `airplane `and
substantially increased,- as for example the airplane may
the present invention is especially suitable for use with
smaller types of aircrafts, and in use with the parts ar 35 have its speed Aincreased `from twenty tothiry miles per»
hour with the same horsepower. In addition, theland
ranged as shown in the drawings, it will be seen that when
ing lgear of the present invention is inexpensive to make
the yairplane is land-ing or taking oif, the Wheels 26 of
and ruggedly constructed and is safe .in operation.
the landing gear 25 are in the extended position as for
The springs 32 are adapted to be used «for tak-ing up
example as shown in FIG. 1_. and the locking mechanism
slackon the flexible tubes 31 which are adapted to be>
36 serves to safely maintain the Wheels and landing gear
used for supplying hydraulic ñuid tothe hydraulic brakes
in extended position during this time. When .the air
29. The> rollers 61 can lbe made of rubber, and Ia plate
plane »is ñying through the air, the wheels and landing
may be used» for'holding the wheel struts apart when
gear are retracted or moved to the posit-ion shown in FIG
retracted. Instead of using the belts 57 and 58, a chain
URE 2 so that there will be less «wind resistance and less
drag whereby the aircraft can more conveniently `and 45 drive can be used, land a gear `mechanism can also be
The wheels 26 are
adapted to be retracted into the portions suchA as the re
cessed portions 50 in the side of the airplane, or else
54 so as to cause the belts 57 and 58 to travel, and this 50 receiving the wheels when the wheels are retracted.
traveling motion of the bel-ts 57 and 58 results in rotation
of the drive rollers 61, and since the drive rollers 61 are
arranged in frictional engagement with the pair of struts
27, it will be seen that by causing the drive rollers 61
Limit stop members can be used for preventing the struts
from «being extended too far out of the Ifuselage.
Although the invention herein described is fully cap
able of achieving the objects and providing the advan
to rotate in one direction, the struts 27 can be extended, 55 tages hereinbefore mentioned, it is to be understood that
and by causing the drive rollers 61 to rotate in the op~
posite direction, lthe struts 27 can be retracted. The struts
-it is merely illustrative of the presently preferred embodi
ment of the invention and that it is not to be limi-ted to
the `details of construction herein »described other than
as defined in the appended claims.
cient clearance in order to permit the struts to move in
What is claimed is:
without jamming, and it will be seen that when the parts 60
l. In an airplane, a fuselage having recessed portions
move into the fuselage as shown in FIGURE 2, the struts
in
the -lower side portions thereof, a retractable landing
are arranged in criss-cross relation with respect to each
gear comprising a pair of inclined struts, wheels connected
other, and the wheels 26 are snugly received in the
to the lower ends of said struts, brake mechanisms opera
‘27 are cutaway or recessed `as at 28 so as to provide sulfi
recessed portions ‘50 adjacent the lower outer portions of
the »fuselage in order to present a generally streamlined
etfect for the aircraft.
There is provided the locking ymechanism 36y which
embodies the pin 44 that is adapted to engage an opening
tively associated with said Wheels, said «struts havingpas
sageways «therein for conveying an actuating medium to
said brake mechanisms, hoses operatively connected to
said passageways, spring `members connected to said hoses,
upper ‘and lower horizontally disposed support members
45 or 46 in a strut 27, and for example with the pin 44 70 mounted in said fuselage, locking mechanisms each com«
prising a solenoid mounted on an upper support member,
urged into an opening 45 by means of the string 48, it
will be seen that the strut will be locked outwardly or
in extended position. Similarly with the pin 44 arranged
in engagement with an opening or aperture 46, the strut
will be locked safely in retracted position.
spring pressed plungers connected to said solenoids, a
bell crank lever connected to each plunger, casings de
pending from the upper support members, vertically dis
Before the 75 posed spring pressed -pìns extending downwardly from
3,088,699
5
said casings, there being a parir of spaced apart apertures
yin each `strut for selectively receiving said pins, a reversible
electric motor mounted in the lower portion of said fuse
lage, `a shafft driven by fsa-id motor, pulleys mounted on
said shaft, endless ‘bel-ts trained around said pulleys, drive
6
said lbelts has portions thereof arranged `in criss-cross
relationship.
References Cited in the ñle of this patent
UNITED STATES PATENTS
rollers operatively driven by said lbelts and said drive
rollers f?ctiorrally engaging said struts, and guide Wheels
1,097,816
McCarroll __________ __ May 26, 1914
arranged in `engagement with said struts.
2. Tlhe structure yas defined ‘in claim l wherein said
»struts >are provided Wit-h opposed elongated recessed cut 10
away portions.
1,662,915
1,812,211
1,857,888
2,429,992
Burnelli _____________ __ Mar. 20,
McCrea _____________ __ June 30,
Stout ________________ __ May 10‘,
Crispell ______________ __ Nov. 4,
3. rPhe structure :as defined in claim 1 wherein one of
2,942,809
Roy ________________ __ June 28, 1960
1928
11931
1932
1947
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