вход по аккаунту


Патент USA US3084608

код для вставки
April 9, 1963
Filed March 50, 1960
40 57
Patented Apr. 9, 1963
rear end 9 to the rear end 110 of the base and on which is
Marion M. Coslowsky, 505 E. Mountain View,
Bar-stow, Calif.
Filed Mar. 3-0, 1960, Ser. No. 18,731
9 Claims. (Cl. 89—-1.7)
This invention relates to a missile launcher and more
slidably mounted the missile sled 20.
Base 5 is rotatable
in a horizontal plane in known manner on an unshown
support in order to aim the missile in the desired direction
and guide member 8 is pivotable in a vertical plane to
provide the proper launching inclination for the intended
trajectory for a given missile and a given target.
The means to pivot the guide member 8 comprises a
frame 16 and hydraulically operated pistons 11. The
ing spin to the missile prior to launching.
10 frame ‘16 is pivotally secured at its upper end to the mem
her 8 and at its lower end to support rollers 15 which in
Guided missiles and modern ballistic missiles carry
turn are pivotally connected to pistons 11 slidable within
guidance control and stabilizing equipment which add to
hydraulic ram cylinders 14 from which they receive power
the weight and to the cost and which reduce both the
particularly to a missile launcher which imparts a stabiliz
range and the load that can be carried.
In the prior
to move rollers 15 along base 5.
As the pistons
practice, bullets and projectiles have been caused to spin, 15 move into the cylinders the frame and the forward end
of the catapult are lowered, and as they are moved out
and thus stabilized in ?ight, by the riding in the gun
wardly ‘from the cylinders the frame and the catapult are
barrel and, accordingly, the rotation imparted has been
limited by the length of the gun. In the spin-stabilizing
As shown in FIGURE 2, the spinner or spin-producing
of missiles, special equipment has been provided within
the missile in which a part of the gas developed ‘by the 20 apparatus 4 is mount-ed in a housing 21 carriedv by a base
22 on elongated sled 20. The latter is suitably mounted
combustion of the fuel is used to actuate spinning de
for longitudinal displacement along the track or guide
Here again, weight and cost are added and, in
member 8 by conventional unshown actuating means
addition, the diversion of a part of the fuel energy de
within the catapult body. Spinner 23 comprises an open
creases the missile range.
According to the present invention the missile launcher 25 ended cylinder mounted for rotation on spaced annular
bearings 26 and abutting at its rear end 27 a thrust hear
imparts spin to the missile prior to launching which occurs
ing 28. At its forward end 29, cylinder 23 is provided
when the missile, or the spinning part thereof, has reached
with saw teeth 30 adapted for engagement with comple
the proper speed. The launcher is aimed and directed in
the usual manner.
mentary teeth 31 at the rear end 3 of missile 1, to be
Accordingly, it is a primary object of the present in
vention to provide an improved missile launcher.
described presently. A sprocket 34 integral with spinner
23 encircles its cylindrical ‘body ‘forwardly of housing 21
It is a principal object of the present invention to pro
vide ‘a missile launcher on which the missile is caused to
in position to receive a rotating force. Mounted below
housing 21 is a variable speed motor 35 having a drive
shaft 36 on which is mounted a drive sprocket 37 engag
ing an endless chain 40 which also engages sprocket 34
to rotate spinner 23 when the motor is operating.
spin so that it continues to spin after it is launched for
purposes of stabilization in ?ight.
It is another object of the present invention to provide
a missile launcher which causes the missile to be stabilized
Positioned forwardly of and in general alignment with
in ?ight in the absence of the usual stabilizing equipment
spinner 23 are two or more missile supports comprising
within the missile.
It is a further object of the present invention to pro
vide a missile launcher the action of which permits the
elimination of stabilizing equipment within the missile
with resulting reduction in weight and increase of its range
and the weight of its payload.
It is aJstill further object of the invention to pro-vide 45
a missile launcher which causes the missile to spin to
upright rigid brackets ?xed to sled 20.
The arcuate
upper edges of these brackets have one or more arcuate
rows of spherical sockets rotatably seating precision balls
Only the outer portions of these balls are exposed
beyond the edges of their respective seating sockets and
these engage and support the exterior of cylindrical sur
face of the missile both during the spinning thereof as
well as during its launching. If desired, the opposite
ends of the bearing provided by balls 42 have pivoted
stabilize its ?ight, which aims it in azimuth toward the
thereto as by pins 43 a pair of hell cranks 44 the longer
target, and which sets its launching inclination to provide
upper arms of which are shaped to embrace the upper
the proper trajectory toward the target.
These and other more speci?c objects will ‘appear upon 50 peripheral surface of the missile when in their closed
positions illustrated in FIGURE 4. The upper end of
reading the following speci?cation and claims and upon
each arm is provided with sets of aligned rollers 45 which
considering in connection therewith the attached draw
cooperate with hearing balls 42 in forming guide bearings
ing to which they relate.
for supporting the missile while being spun.
Referring now to the drawing in which a preferred em
The short arms at the lower ends of hell cranks 44
bodiment of the invention is illustrated.
are connected by suitable links 46 with operating mech
FIGURE 1 is a perspective view of a missile launcher
anism suitable for holding the bell cranks in closed
embodying the present invention;
position with rollers 45 bearing against missile 1 before
FIGURE 2 is a side elevational view of the missile
spinning mechanism of the launcher shown in FIGURE 1; 60 launching. A moment before the missile starts to move
axially out of engagement with teeth 36, links 46 are
FIGURE 3 is {an enlarged fragmentary showing illus
operable to open the bell cranks outwardly to avoid
trating the engagement of the rear end of the missile to
any possibility of interferring with the launching opera
the spinning means which provides the rotational force;
The bell cranks normally would remain open until
after the next missile has been lowered into cradles 41
FIGURE 4 is a view looking in the direction of the
65 by a suitable sling or the like. Once the missile is in
arrows upon the line 4-4 of FIGURE 2.
place, bell cranks 44 are closed.
Referring again to the drawing, in FIGURE 1 the mis
As shown in FIGURES 1 and 3, the missile is on the
sile 1 is shown on the launcher 2 in position for ?ring,
launcher with its nose 49 directed toward the target and
the rea-ward end of its cylindrical surface 3 in engagement
has its main cylindrical body portion 51 rotatably sup
with a spinning apparatus 4. The launcher comprises a 70 ported on balls 42 in cradles 41 with the saw teeth 31
base 5 and a catapult 7 including a track or guide mem
at its rear end engaged with the spinner teeth 30‘. EX
ber 8 pivotally mounted in a horizontal plane adjacent its
tending rearwardly and through the open-ended spinner
23 is an exhaust nozzle 50 through which high pressure
said missile to rotate said missile when said spinning
combustion gases are discharged from the missile to
means is rotated.
provide driving thrust.
The extension of nozzle 5t)‘
4. The invention according to claim 3 in which said
through open-ended spinner 23 permits the engagement
means to rotate said missile comprise a motor means
supported on said support means, a drive shaft extend
of the missile and spinner driving teeth.
In operation, it is ?rst necessary to adjust angularly
ing from said motor means and having a sprocket mount
ed thereon, a sprocket mounted externally on said spin
the launcher base 5 so that the missile is aimed'properly
in azimuth. Then the catapult is raised to the proper
angle so that the missile will be launched into the pre
ning means cylinder in alignment with said sprocket
on said drive shaft, and an endless chain engaging said
determined trajectory. The driving motor for the missile 10 sprockets to transmit a driving force to rotate said
spinner 23 is then operated to spin the missile at a
requisite speed for highly stabilized ?ight. After the
5. A missile launcher for use in open air to launch and
missile has been brought to the desired speed, the missile
fuel is ignited and the catapult is actuated to displace
sled 2t} and the missile along the length of the catapult
stabilize a self-propelling ?nless missile for free ?ight
under its own power comprising a catapult, said catapult
being rotatable in azimuth and pivotable in elevation, a
with maximum thrust and acceleration. As the sled ap
proaches the end of its launching travel, it contacts a
trigger or actuator button 52 controlling the opening of
. sled mounted for movement lengthwise of said catapult,
hell cranks 44. By this time the high speed of the sled
taken with the propulsion generated by the rocket motor
within the missile is sufficient to sustain the ?ight of the
missile along its target trajectory. The rapidly spinning
upwardly facing cradle means carried by said sled and
adapted to receive a ?nless missile'with its axis parallel
to said sled, anti-friction bearing means interposed be
tween the missile and said cradle means on which said
missile is rotatable, annular spinning means supported on
said sled having axially facing teeth on the end face there
missile separates automatically ‘and effortlessly from the:
of engageable with the complementall'y-shaped lower ax
still spinning drive cylinder 23 of the missile spinning
ial end of a missile supported for rotation in said cradle
unit 21 owing to the sawtooth shape of the coupling 25 and cooperating to spin said missile about its axis in prep
31 between the rear end of the missile and spinner 23.
aration for launching, said spinning means being in axial
The missile will continue in ?ight directly to its target
alignment with said cradle, and means to pivot said cata
by the propulsion force supplied by its self-contained
pult at its rear end to incline said missile in proper posi
motor and will not depart from the trajectory determined
tion for launching.
by the launching conditions owing to the stabilizing im
6. Missile launcher apparatus for use in open air to
parted to the missile by the high speed spinning of the
launch and stabilize a self-propelling ?nless missile for
missile as an incident to its launching.
free ?ight under its own power, said apparatus having a
It is pointed out and emphasized that the herein de~
ground-supported base and an elongated catapult having
scribed apparatus and method of assuring the stabilized
means con?ned substantially to the underside thereof for
?ight of a missile or the like space vehicle is equally
pivoting the same selectively to any desired missile launch
advantageous with single or multiple stage launched ob—
ing angle with respect to the horizontal, power~propelled
jects. Accordingly, it will be understood that the in
sled means free of connections to the missile movable
vention herein disclosed and claimed is to be deemed as
lengthwise of the upper side of said catapult from a nor
applicable to the launching of various types and sizes
mally retracted position at the lower end of said catapult,
of rocket propelled vehicles.
40 and power driven means on said sled means having teeth
While the particular missile launcher herein shown and
facing and engageable with'similar teeth on the rearward
disclosed in detail is fully capable of attaining the objects
ly facing rim end of a missile for rapidly spinning a self
and providing the advantages hereinbefore stated, it is
propelling ?nless missile thereon while the missile is be
to be understood that it is merely illustrative of the
ing launched from the propelled sled means for free ?ight
presently preferred embodiments of the invention and
under its own power, said sled means including cradle
that no limitations are intended to the details of construc
tion or design herein shown other than as de?ned in the
appended claims.
means along the upper side thereof for receiving and re
leasably embracing a missile cradled therein and accurate
ly. aligned with the trajectory axis while being launched
I claim:
1. A missile launcher comprising a guide member
pivotable in elevation at its rear end, support means
movable lengthwise of said member including cradle
means underlying and adapted to receive a self-propelling
from said apparatus.
ing mounted cylinder having substantially the same diam
ment therefrom during initial phases of missile launching
7. Missile launcher apparatus as de?ned in claim 6
characterized in that said cradle means includes anti
friction bearing means held captive in said cradle means
and in supporting contact with the exterior of the missile
missile with its axis parallel to said member, bearing
to facilitate the spinning of the missile and its movement
surfaces in said cradle means on which said missile
out of said cradle means during launching.
is rotatable, spinning means on said support means ad 55
8. Missile launcher apparatus as de?ned in claim 6
jacent the rear end thereof and in axial alignment with
characterized in that said cradle means includes means
said cradle means, said spinning means including a bear
for positively holding a missile against lateral displace
eter as the adjacent end portion of said missile for
whereby the missile is con?ned for rotational spinning
rotatable engagement therewith, means on said support
about its own axis While spinning of the missile is being
means to rotate said spinning means, and means to pivot
accelerated, and means for automatically retracting said
said member at its said rear end and to incline said
holding means before the missile is launched from said
missile to a desired position for launching.
sled means.
2. The invention according to claim 1 characterized in
9. A missile launcher for use in open air to launch and
that said cradle means includes anti-friction bearing 65 stabilize a self-propelling ?nless missile for free ?ight
means in direct contact with and restricted primarily to
under its own power, said launcher comprising a guide
the underportion of said missile and operable to rotate
member pivotable in elevation from one end thereof, sled
about axes parallel to the missile axis as said missile
means forming a permanent component of said launcher
is spun about its own longitudinal axis and operable to
slidable lengthwise of said member and including cradle
rotate about an axis extending transversely to the missile
means adapted to underlie, receive and support a self—
axis while the missile is being launched from said
3. The invention according to claim 2 in which said
cylinder spinning means has teeth in its forward end
surface complementary to teeth in the rear end portion of 75
propelling ?nless smooth-surface missile free of irregu
larities and projections extending laterally from the body
thereof, antifriction bearing components mounted within
and forming part of said cradle means on which said
missile is rotatable, spinning means on said sled means
Northrop et a1 _________ __ Feb. 14, 1956
adapted to engage the rearwardly axial end portion of
said missile detachably, said spinning means being in ax
ial alignment with said cradle means, and means to pivot
said guide member to incline said missile to a desired 5
Bach et al ____________ __ May 21, 1957
Kindelberger _________ __ May 20, 1958
Brown _______________ __ Sept. 20, 1960
launching angle with respect to the horizontal.
Strickland et a1. _______ __ Jan. 24, 1961
‘Petre _______________ __ Nov. 14, 1961
'France ______________ __ Apr. 29, 1946
References ?ited in the ?le of this patent
Unge ________________ __ Feb. 5, 1895 10
Bourguard ___________ __ Ian. 17, 1956
Seidner ______________ __ Dec. 6, 1960
Без категории
Размер файла
476 Кб
Пожаловаться на содержимое документа