Multi-head military charge

A multi-head military charge for dispersing multiple warheads from a vehicle has a carrier structure for carrying the projectiles. The carrying structure includes an ejectable casing and a central tube which is substantially coaxial with the longitudinal axis of the carrying vehicle. The central tube holds an annular support upon which the projectiles rest. A plurality of resilient securing devices hold the projectiles onto the annular support member. Each securing device has a bolt for clamping the securing device to the associated projectile. Ejector pistons are disposed within the carrier structure to propel each of the projectiles outside of the vehicle. Each ejector piston simultaneously releases the bolt clamping the securing device to the associated projectile and projects the projectile outside of the carrying vehicle.

BACKGROUND OF THE INVENTION 
The present invention relates to the field of bombs, missiles and similar 
charge transporting vehicles, and particularly to a military multi-head 
charge for such vehicles. 
At the present time, the method used for neutralizing the vital 
installations of the enemy, for example runways of aerodromes, consists in 
launching against the target salvos of projectiles or warheads installed 
in clusters on the structure of an aircraft. The main drawback of this 
method of attack resides in the fact that the carrier aircraft must 
necessarily fly over the objective, the approach to which is usually 
particularly well defended. 
To avoid the aircraft having to fly over the objective, the invention 
provides a multi-head military charge whose destructive power is at least 
equal to that of a salvo of projectiles fired by an aircraft, said 
multi-head military charge being mounted in a vehicle carried by an 
aircraft so that this aircraft remains outside the range of the defensive 
weapons of the enemy. 
There then arises the problem of constructing a multi-head military charge 
in which the sub-ammunition, or projectiles, may be dispersed uniformly 
over the sensitive part of the objective so as to obtain maximum 
destructive effects. Since the cost of bombardment missions is high, the 
reliability of the military charge must be high. Moreover, since the 
military charge is a consumable material, the accuracy of dispersion and 
the reliability must not be obtained at the cost of an appreciable 
increase in the production costs of this charge. 
SUMMARY OF THE INVENTION 
The invention provides a multi-head military charge intended to be carried 
by a bomb, a missile or similar charge carrying vehicle. The charge groups 
of the sub-ammunition, such as projectiles or warheads, are arranged in a 
ring for extraction radially over the terminal trajectory of the carrier 
vehicle. This military charge comprises a streamlined carrier structure 
having an external retractable casing and a central tube which comprises 
an annular support for each of the groups of projectiles. This annular 
support comprises, radially disposed opposite the projectiles, actuatable 
gas ejectors and bolt securing means, which bolts retract under the effect 
of the movement of the gas ejectors.

DESCRIPTION OF THE PREFERRED EMBODIMENT 
FIG. 1a shows in simplified form a missile intended to be carried and 
launched by an aircraft which remains outside the defense perimeter of the 
enemy. This missile is equipped with a multi-head military charge. Missile 
1 comprises three main sections: a front section 2 ogival in shape in 
which are grouped the guide means allowing the missile to follow a course 
to the sensitive point of the objective designated; a middle section 3 
formed by the multi-head military charge and a rear finned section 4 which 
possibly contains the propulsion unit for accelerating the missile which 
is fired after launching from the carrier aircraft. 
The military charge 3 comprises essentially a carrier structure, enclosed 
in a casing, in which are disposed means for radially ejecting groups 
G.sub.1 and G.sub.2 of projectiles P arranged in a ring. The carrier 
structure for the military charge comprises a central tube 5 connected to 
two connecting flanges 6 and 7 and to the casing. The connection of the 
flanges for the casing is temporary, and the casing includes fragmentation 
or sliding means for completely uncovering the projectile a short while 
before they are ejected from the military charge. 
Casing 8 is fitted with a rigid beam 9, having rings 9a and 9b for fixing 
to the aircraft, not shown. The central tube 5 of the carrier structure 
has annular supports 10 and 10' to which the projectiles are fixed. In the 
annular support are disposed ejectors whose function is to eject each of 
the projectiles P radially, said projectiles are secured to their supports 
by securing means which are unlockable in synchronism with the movement of 
the ejectors. 
On approaching the appointed objective, missile 1 is released by the 
carrier aircraft then guided towards the sensitive point. In the vicinity 
of this sensitive point casing 8 of the military charge is expelled; then, 
conjointly, the means for securing the projectiles P are unlocked and then 
the ejectors are actuated so as to impart to the projectiles a given 
lateral ejection speed, which conditions the dispersion of the projectiles 
on the ground. 
Depending on the nature of the objective, the type of sub-ammunition used 
and the firing parameters, the ejection speed is between a few meters and 
a few tens of meters per second. It may be noted that it is possible to 
provide different ejection speeds for the different groups of projectiles 
by dimensioning the ejectors. 
FIG. 1b is a cross section taken along line 1b--1b of the military charge. 
The projectiles P resting on the annular support 10 are secured by 
resilient straps 14 having clamping means 15 which are unlocked when the 
projectiles are expelled by the gas ejectors 13. 
FIG. 2 is a partial view in cross section of one construction of a 
multi-head military charge according to the invention, which shows the 
elements associated with the annular support 10. The outer casing 8 is 
equipped with a rigid beam 9 having securing means, such as ring 9a. This 
casing includes pyrotechnical means 11 for causing fragmentation of the 
casing before projectiles P are ejected. The number of fragmentation 
generatrices is not limited to 3, as in the embodiment shown here, but may 
be more. Similar pyrotechnical means (not shown) free the fragments of the 
casing from the flanges of the carrier structure. Since the techniques for 
retracting the streamlining elements of missiles and rockets are widely 
known, they will not be described. The annular support 10 comprises, at 
its periphery, seats 12 on which the bodies of the projectiles rest, 
spaced evenly apart. In the annular support 10 are incorporated gas 
ejectors 13 which are disposed radially and opposite each of the 
projectiles. The projectiles are held rigidly in position on their seats 
by a resilient strap 14 whose ends press against the body of the adjacent 
projectiles Pi and Pi+1. The median part of these holding straps is 
provided with a clamping rod 15 which comprises a conical base 16 which is 
engaged in a housing 17 situated in the annular support 10 and in the 
plane of the pneumatic ejectors 13. The head of the clamping rod 15 is 
provided with a threaded portion which receives a clamping nut 18. The gas 
ejector 13 comprises a stepped bore 19 inside which is placed a piston 20. 
This piston comprises a thrust head 21 which is in abutment against the 
shoulder of the bore; this thrust head provides a means for locking the 
clamping rod 15 of the resilient strap 14. The base of the piston is 
equipped with a sealing means, such as an O seal 22, which opposes the 
passage of the gases released by a capsule of a pyrotechnique substance 
which is fired, preferably electrically. In a variant which will be 
described later on, the base of bores 19 communicates with a gas source 
situated on the axis of the annular support. Base 16 of clamping rod 15 
and the thrust head 20 of the gas ejector communicate with each other 
through a housing, inside which is placed the locking member (a bolt) 24, 
which may freely slide out of the housing 17 for the clamping rod during 
the translational movement of the piston, as soon as the thrust head 21 
leaves the shoulder of the stepped bore 19. It will be noted that a pin 
25, shearable under the effect of the movement of the piston, is disposed 
in the piston head so as to hold this latter against the shoulder of the 
bore. 
After the operation for expelling the military charge from casing 8, which 
operation uncovers the projectiles, ignition of the pyrotechnique capsule 
23 produces a gas flow which pushes the piston 20 of the ejector 
outwardly. The head of piston 21 is progressively freed and frees the 
locking member 24. This locking member, under the effect of the resilient 
constraint of strap 14 transmitted by the clamping rod 15, moves towards 
the body of the piston and completely frees the housing 17 for base 16 of 
the clamping rod. The head of the piston 21 continues its movement and 
comes into contact with the body of the projectile against which it exerts 
a pressure force which ensures ejection of the projectile. By a judicious 
choice of the characteristics of the ejector, the ejection speed of the 
projectile may be controlled. 
FIG. 3 shows in a sectional view a variant of the construction of the gas 
ejectors. The purpose of this constructional variant is to prevent the 
piston head 21 from striking the body of the projectile and it eliminates 
the above described shear pin 25. Inside the piston is provided a bore 26 
which receives a thrust rod 27. The upper end of the thrust rod is held in 
contact with the body by a resilient means 28 disposed between the lower 
end of this thrust rod and the bottom of bore 26. This resilient means 28 
may be formed by a helical spring, a stack of "belleville" washers or any 
other equivalent means. The purpose of spring 28 is also to delay 
application of the thrust force to the projectile as long as the locking 
member 24 of the clamping rod 15 has not been retracted. The lower ends of 
bores 19 of the gas ejectors are in communication with the central cavity 
29 in which is disposed a gas generator which will be described further 
on. 
FIG. 4 is a partial view in longitudinal section of the military charge 
which shows the details of construction of the annular support of a group 
containing an uneven number of projectiles P. The annular support 10 is a 
solid element which fits onto the central tube 5 of the carrier structure. 
On the periphery of the annular support, on each side of the gas ejectors 
13, are situated two series of projections 30 and 31 forming the seats 12 
on which the bodies of the projectiles rest. The two series of projections 
are sufficiently removed from each other to provide a suitable seat for 
the projectiles. Projections 30 and 31 provide preferably pin point 
contacts with the body of the projectiles and these contact points are 
advantageously situated in diametrical planes which contain the elastic 
forces exerted by the above described straps 14. The central part of the 
annular support comprises a detonatable gas generator 29. The gas 
generator comprises a tube 32 in which is placed a pyrotechnique substance 
and an electric fuse 33 having its electric terminals 34. A chamber 35 
situated concentrically with respect to tube 32 of the gas generator, 
comprises orifices 36 for communicating with the gas ejectors. In this 
FIG. 4 there is shown, diametrically to the gas ejector shown, the housing 
17 of one of the clamping rods for the straps holding the projectiles. For 
positioning the projectiles longitudinally, they are provided with a 
longitudinal positioning element such as stud 37. This stud is freely 
engaged in a hollow recess 38 so as not to disturb the ejection of the 
corresponding projectile. Stud 37 situated in the body of the projectiles 
may be a retractable element for neutralizing the arming of the 
projectile. The point of application of the thrust force provided by the 
thrust head 27 of the gas ejectors is situated accurately with respect to 
the center of gravity CG of the projectiles. 
FIG. 5 shows an external view of the annular support 10 for the projectiles 
and it shows the following elements: the two series of projections 30 and 
31 which provide seats for the bodies of the projectiles; the outlet 
orifices of the stepped bore of the gas ejectors and the hollow recess 38 
which receives the longitudinal positioning elements for the projectiles. 
FIG. 6, in a sectional view, shows a constructional variant of the gas 
ejector and of the means for electrically locking the clamping rod of the 
strap for holding the projectiles on the annular support. The gas ejector 
13 is of the telescopic type comprising a hollow external piston 20a 
placed in this stepped bore 19a and an internal piston 27a. The external 
piston 20a comprises at its base a boss 20b the purpose of which is to 
provide a first bearing surface on the wall of the stepped bore 19a; the 
second bearing surface is provided by a ring 20c bearing on a 
complementary shoulder 19b of the stepped bore; this ring 20c being held 
in place by a circlip 19c. The base of the external piston 20a comprises a 
bearing piece 20b for a spring 28a which also bears against the base of 
the internal piston, 27a. The upper part of the external piston comprises 
a piston head 20a which provides locking of part 24a which blocks the base 
16a of the clamping rod 15 of the resilient strap 14. The base 16a of 
clamping rod 15 is cylindrical in shape so as to provide perfect guiding 
thereof in housing 17 and it comprises a countersunk portion 16b in which 
the locking member 24a may be engaged. The form of construction which has 
just been described allows a considerable lateral ejection force to be 
imparted to the projectiles when that proves necessary and, conjointly, it 
ensures improved guiding of the clamping rod of the resilient strap 
holding the projectiles. 
The form of construction of the streamlined carrier structure may be varied 
and, more particularly the means for retracting the casing may be of a 
type with extraction along the longitudinal axis of the missile. 
The advantages provided by the invention can now be seen more clearly: 
spacing between projectiles is reduced to a minimum so as to confer on the 
charge maximum carrying capacity; the means for fixing and ejecting the 
projectiles operate in perfect synchronism and cooperate judiciously so as 
to provide uniform and controlled dispersion of the projectiles, and the 
simplicity of the mechanisms confer a certain reliability on the military 
charge. 
The invention is not limited in its applications to a military charge 
formed of projectiles, but it may be applied to the launching of explosive 
mines, different ammunition etc which must be deposited on the ground.