U.S. patent number 3,916,759 [Application Number 04/772,070] was granted by the patent office on 1975-11-04 for rocket launcher.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Robert H. Forster, Bernard M. Jones, Harry C. Loyal, Donald G. Quist, Gaylon L. West.
United States Patent |
3,916,759 |
Jones , et al. |
November 4, 1975 |
Rocket launcher
Abstract
An easily portable rocket launcher is provided with remote
firing capabil, an antidisturbance mechanism, a time delay
mechanism for delayed firing and a second time delay means for
operation of a self-destruction device. The launcher includes one
or more tubes of fiberglass or the like bonded together with epoxy
cement, for example, and supported on three legs. The two forward
legs are adjustable to facilitate aiming of the launcher.
Inventors: |
Jones; Bernard M. (China Lake,
CA), Forster; Robert H. (China Lake, CA), West; Gaylon
L. (China Lake, CA), Quist; Donald G. (China Lake,
CA), Loyal; Harry C. (China Lake, CA) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (Washington,
DC)
|
Family
ID: |
25093812 |
Appl.
No.: |
04/772,070 |
Filed: |
October 29, 1968 |
Current U.S.
Class: |
89/1.814;
89/1.816 |
Current CPC
Class: |
F41F
3/045 (20130101); F41A 19/58 (20130101) |
Current International
Class: |
F41A
19/00 (20060101); F41F 3/00 (20060101); F41A
19/58 (20060101); F41F 3/045 (20060101); F41F
003/04 () |
Field of
Search: |
;89/1.814,1.816,1.815,28,135 ;102/70,84,8,16 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Bentley; Stephen C.
Attorney, Agent or Firm: Sciascia; R. S. Miller; Roy Baker;
Gerald F.
Claims
What is claimed is:
1. A lightweight easily portable rocket launcher comprising:
a lightweight sheet metal housing having two opposing side walls
and a peripheral wall;
at least one launcher tube protruding slightly through one side
wall of said housing and also protruding to a greater degree
through the opposite side wall of said housing;
contact means associated with each said tube for conduction of
electrical energy to a rocket round;
a source of electrical energy;
timer means electrically connected to each said launcher tube and
to said source of electrical energy;
said timer means including a settable clockwork switch and an
electronic delay timer switch connected in series with said source
and said contact means; and
removable means for positively blocking operation of said timer
means.
2. A rocket launcher according to claim 1 including tube angle
indicating means adjustable from 0.degree. to at least 45.degree.
to facilitate aiming of the launcher.
3. A rocket launcher according to claim 1 wherein said clockwork
switch may be set for delay firing from 1/2 hour to 111/2
hours.
4. A launcher according to claim 1 further comprising explosive
means substantially coextensive with said tube for self-destruction
of the launcher after use or upon sufficient angular movement of
the launcher, when armed.
5. A launcher according to claim 4 further comprising means for
remotely firing said launcher and detonating said explosive
means.
6. A launcher according to claim 1 further comprising removable
means for disabling said contact means.
7. A launcher according to claim 1 further comprising:
means in said housing for receiving said clockwork switch and for
receiving said battery; and
means for preventing removal of said clock and said battery from
said receiving means when such is desired.
Description
BACKGROUND OF THE INVENTION
Weapons of the rocket launching type have been heretofore
constructed of heavy metal and, thus, have been difficult to
transport and as a result were quickly compromised when troops
suddenly withdrew from the position leaving the weapons on the
field. These weapons were usually not provided with anticompromise
devices because of the difficulty of destroying a weapon made of
such heavy material and, further, an anticompromise device
sufficient to destroy such a weapon would be a serious burden and
hazard to troops utilizing the weapon.
SUMMARY OF THE INVENTION
By this invention we have provided an extremely lightweight
portable rocket launcher having many features not found on previous
launchers and including a lightweight safe self-destruct type
anticompromise device. The launcher is constructed of lightweight
materials and incorporates timing mechanisms which allow it to be
armed in the field, fired, and/or destroyed automatically after a
predetermined time. The launcher is also provided with remote
firing capability and an antidisturbance device which causes the
launcher to destroy itself if it is disturbed at any time after
arming. However, the launcher system and especially the destruct
devices according to the invention incorporate safety features
which protect the operator from accidental firing before the system
is in readiness.
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING
FIG. 1 is a perspective view of a single tube embodiment of the
invention;
FIG. 2 is a rear plan view of the device of FIG. 1;
FIG. 3 is a block diagram of the system;
FIG. 4 is a perspective view of a three tube embodiment of the
invention; and
FIG. 5 is a rear plan view of the rocket launcher according to FIG.
4.
DETAILED DESCRIPTION OF THE INVENTION
As shown in FIG. 1 the launcher 10 comprises a launcher tube 12
protruding from bulkhead 40 of housing 14 and supported by two
forward legs 15 attached to the tube 12 by adjustable means 22 and
a third leg 21 attached to the housing 14. Legs 15 have cross
pieces 16 near their ground engaging ends to prevent the legs from
entering the ground to an undesirable depth when the ground is
soft. Also protruding from housing 14 is a destruct tube 24 which
may be filled with explosive material to destroy the launcher under
conditions which will be later described. Because of its light
weight it may be found desirable to fasten the launcher to the
ground by ground stakes 19, 23. Ground stake 19, for example, may
be attached to the tube 12 at ring 17 by a cable 18 and also to leg
21 by adjustable cable assembly 20. Ground stake 23 may be bolted
to leg 21 by passing the bolt provided through hole 25.
CONSTRUCTION
The launcher tube 12 and the self-destruct tube are made of
fiberglass or the like. The housing 14 is closed at each end by
bulkheads 40 and 41, respectively, and the skin of the housing is
manufactured of a lightweight material, for example, such as
aluminum. The bulkheads are preferably of Micarta or the like. As
may be seen from FIG. 1 the rocket may be adjusted in elevation by
means of the adjustment 22 holding legs 15 to the tube 12. The legs
15 are preferably of stainless steel rod with flanges 16 of sheet
metal. Aiming of the launcher is aided by two leveling devices one
of which is shown at 44 in FIG. 1. In use, it is contemplated that
the launcher be transported fully loaded but with the clockwork
mechanism and battery removed. Waterproof caps are provided for the
muzzle, breach and clock openings. The battery compartment is also
rendered waterproof when the cover 36 is in place.
A leveling device 44 is provided to facilitate aiming the launcher
and, as shown, comprises a leveling tube 46 pivoted at 45 to a
bracket 47 fastened to bulkhead 40. The tube 46 may be capped by a
simple bubble type leveling device 48 and may be held in place by
raised detents 49, for example, on bracket 47.
The housing 14 is surmounted by a clock housing 26 and, as shown in
FIG. 2, provides space for a battery compartment closed by a cover
38. Opposite battery housing cover 38 is the cover 36 which closes
the destruct tube 24 described above.
Between the two covers is a rocket contact retaining pin 28
identified by an annular tag 29 and to the left of rocket tube 12
is a launcher safety pin 32 identified by a square tag 30.
The cylindrical battery compartment cover 38 is flush with bulkhead
41 when properly emplaced. A pin 34, in cover 38, blocks a trip
device, not shown, to allow removal of cover 38. Pin 34 is provided
with a pull ring 33 and when pin 34 is extracted, cover 38 can not
then be removed.
The rocket tube 12 is schematically depicted in FIG. 3 with a round
13 in place and schematically connected to the battery 60, clock
mechanism 39, tremblor switch 50 and electronic timer means 52. The
system may also include an explosive squib 62 which is preferably
of the time delay type. The terminals 51, 53 are placed outside the
housing 14 near clock case 26 for easy access.
CLOCK MECHANISM
The clock mechanism is a conventional timer switch which may be set
for operation delay from 10 minutes to 111/2 hours. The clock
mechanism is wound with a key which may be removed or simply folded
down when the clock is placed in position on the launcher. When the
clock is wound, a pin is inserted into the face of the clock and
extends into the clock mechanism to block the gearing and prevent
the clock from running down. The clock cannot be set or run with
this pin in place. The clock is preferably provided with a
removable dial indicating the position of the switch operating
mechanism and the time period remaining until the clock switch will
close. The dial may be attached in any well known manner but is
preferably manufactured of a sheet material with a pressure
sensitive adhesive backing. A flat web cord is preferably placed
under a portion of the dial to facilitate removal when desired. In
addition to the other indicia on the clock dial, there may be also
instructions in printed form for operation and installation. When
desired, the clock and clock receptacle can be so constructed that
when the clock is installed it can not be removed.
OPERATION
As noted in FIG. 3 after the pin 31 has been removed from clock 39,
pin 28 has been removed from its position holding open and shorting
contacts 71, 72, and the main rocket launcher safety pin 32 has
been removed to allow the capacitor 61 to be charged, with a
battery inserted and the clock in place. battery current is
available through either the trembler switch 50 or the clock
mechanism delay switch 39 to fire the rocket. The rocket is fired
when current is passed through a circuit in the missile between
rings 54, 56. Remote firing may be accomplished by connecting any
well known remote firing device to the contacts 51, 53, provided on
the housing 14. When it is desired that the rocket launcher be
destroyed after firing, a delay cap 62 is fastened to contacts 51,
53 by means of its lead wires 63 and, as will be obvious from
viewing the circuit of FIG. 3 the delay cap 62 will be actuated at
the same instant that rocket contact rings 54, 56 are energized.
Because of the inherent delay in delay cap 62, the self-destruct
charge will be detonated until after the rocket has cleared the
launcher.
THREE TUBE LAUNCHER
Turning now to FIG. 4 we will describe a similar launcher having a
plurality of launcher tubes. The launcher shown designated as 100
comprises three launcher tubes 111, 112, and 113. The legs 115 are
identical with legs 15 of the single tube launcher and have metal
crosspieces 116 fastened to the ground engaging end. The legs 115
are respectively fastened to the outboard tubes 112, 113 and are
adjustable through adjustment members 122 fastened to the tubes
112, 113. The three tube launcher also has a leveling device 144
similar to the leveling device 44 of the single tube launcher.
FIG. 5 is a view of the breech end of the three tube embodiment of
the rocket launcher wherein there are three rocket contact shorting
pins 129, one for each of the three rocket tubes. However, only one
main launcher safety pull pin 132 is provided. In the three round
launcher there are two destruct tubes one of which is the full
length of the launcher tubes and one which is only so long as the
housing 114. The rear covers 136, 137 of the destruct tubes may be
removed for loading. Between the two lower rocket tubes is the
battery compartment 138 and the clock mechanism 134 is installed in
the receptacle 126 on the right side of the housing 114 as viewed
from the breech end.
This embodiment of the launcher is designed to simultaneously
launch three bazooka type rockets and is adapted to be destroyed in
the same manner as the single tube launcher by fastening a delayed
action blasting cap in the firing circuit. Also, as in the single
tube device, firing may be initiated either by the clockwork
mechanism and antidisturbance trembler switch, or remotely by a
blasting machine or the like. Launcher elevation angle is set by
means of a leveling device 144 which comprises a leveling tube 146
having a bubble type leveling means 148 and tube 146 is pivoted at
145 to a plate 147 attached to housing 114. The leveling tube 146
is held in place between 0.degree. and 45.degree. by means of
detents 149 placed at 5.degree. intervals on plate 147.
The block diagram of the single tube embodiment (FIG. 3) shows
schematically the operation of pin 29 holding the contacts 71, 72
away from the launcher contacts and at the same time serving as a
short between the contacts 71, 72. Also shown is the safety pin 32
which shorts the condenser 61 in the electronic timer 52. With the
shorting pin 29 and the safety pin 32 removed, however, and a
battery 60 is connected to terminals L.sub.1, L.sub.2 of the
battery compartment, either the trembler switch 50 or clock switch
38 may actuate the rocket firing mechanism through contact rings
54, 56 after the condenser 61 has been sufficiently charged. The
electronic timer 52 is a solidstate delay timing circuit which may
be found more fully disclosed in patent application Ser. No.
753,260, filed Aug. 16, 1968. The delay circuitry uses a dual
unijunction relaxation oscillator which triggers a
silicon-controlled switch. After a 2 minute and 45 second delay
time has elapsed the silicon control switch is triggered, which
reduces the current drain on the battery. As the unijunction
oscillator is turned off, a 300 .mu.fd capacitor is charged up.
This part of the circuitry has a 15 second delay time. As soon as
this capacitor is charged, the circuit is energized and may be
fired either by the trembler switch or the clock.
* * * * *