Note: Descriptions are shown in the official language in which they were submitted.
CA 02437374 2003-08-14
DESCRIPTION
Apparatus for combating targets
The invention relates to an apparatus for combating targets
within an area to be monitored, comprising a ground-
installed aimable launching device, a target acquisition
device connected to the launching device and at least one
missile launchable from the launching device.
It is known, for example, from DE 31 40 728 C2 to carry out
a precise fixing of the location of the target by means of
a combination of passive and active sensors in order to
combat tanks. The passive sensors (e.g. acoustic sensors)
are used for determining the target direction and the
active sensors are used for determining the target
velocity. The trajectory of the target and therefore the
launching time of the missile can be determined from the
change in the target direction and target velocity.
A disadvantage, among others, of these known devices is
that a relatively large amount of time is required for
determining the trajectory of the target and the subsequent
aiming of the launching device of the missile, so that the
reaction time of the apparatus from receiving the acoustic,
target-characteristic signals to launching the missile for
combating very fast-moving targets, such as helicopters, is
too long. Moreover, the use of the active sensors of the
target acquisition device gives rise to the danger that the
enemy can locate and destroy the ground-installed launching
device.
It is the object of the invention to specify an apparatus
of the above-mentioned type which is constructed in a
CA 02437374 2010-05-31
21712-272
2
simple and low-cost manner, has a short reaction time and
the launching and target acquisition devices of which
cannot be located by the use of corresponding sensors.
The invention is based substantially on the idea that the
apparatus includes a target acquisition device which
utilises only passive sensors and which determines only the
target direction but not the trajectory of the target to be
combated before the launching of the associated missile,
and that the missile of the apparatus has a homing head
which, after launching of the missile in the direction of
the target, autonomously seeks and then destroys the target
(e.g. by means of an infrared sensor). A locatable
connection between the missile and the launching device or
the target acquisition device does not exist during the
flight phase of the missile.
The apparatus according to the invention has the advantage
that, being a relatively small, autonomous unit, it can be
installed, e.g. manually, within an area to be monitored,
and monitors the-corresponding spatial area for a
relatively long time. For this purpose the apparatus is
provided with e.g. an acoustic alerting sensor. The target
acquisition device then carries out a continuous frequency
analysis of the acoustic signals received. As soon as the
acoustic frequency spectrum indicates a target to be
combated, the directional sensor is activated and the
bearing angle of the target is determined. The launching
CA 02437374 2010-05-31
21712-272
3
device is aligned in the direction of bearing and the
missile (e.g. a "Stinger" rocket) is launched. The infrared
sensor of the rocket then seeks a heat source (target) in
the area segment determined by the acoustic direction-
finding, and the rocket is guided to the target by means of
a suitable steering device.
In an advantageous embodiment of the invention the acoustic
directional sensor includes at least four microphones
arranged in each case at the corner-points of a
tetrahedron.
The alerting sensor is preferably one of the microphones of
the directional sensor.
CA 02437374 2010-05-31
21712-272
3a
In accordance with this invention there is provided an apparatus for combating
targets within an area to be monitored, comprising a ground-installed aimable
launching device, a target acquisition device connected to the launching
device
and at least one missile launchable from the launching device, with the
features:
a) the missile has a target-seeking homing head; b) the target acquisition
device
includes an electronic evaluation device, a passive, acoustic alerting sensor
connected to the evaluation device and a passive acoustic directional sensor
for
determining the target direction connected to the evaluation device; c) the
individual assemblies of the apparatus are in eff ective connection with one
another such that, after reception of target-characteristic signals by means
of the
alerting sensor, the electronic evaluation device activates the directional
sensor,
determines signal values for aligning the launching device in the target
direction
and activates the corresponding positioning drives of the aiming arrangement
of
the launching device, and that the missile is then launched in the target
direction
and autonomously takes over the target-finding function with its homing head.
CA 02437374 2010-05-31
21712-272
3b
Further details and advantages of the invention will be
apparent from the following embodiments which are
elucidated with reference to Figures, in which:
Fig. 1 is a schematic side few of an apparatus
according to the invention for combating airborne
targets;
Fig. 2 is a plan view of the apparatus illustrated in
Fig. 1, and
Fig. 3 is a block diagram of a target acquisition
device.
In Figs. 1 and 2 an apparatus according to the invention
for combating helicopters 2 within a predefined area to be
monitored is denoted by reference numeral 1. The apparatus
1 consists of a housing 3 in which an energy supply unit
CA 02437374 2003-08-14
4
and an electronic evaluation device 4 of a target
acquisition device 5 are housed (cf. also Fig. 3).
Adjoining the top of the housing 3 is an aiming arrangement
6 by means of which a launching device 7 can be aimed in
azimuth and in elevation.
Arranged at the sides of the housing 3 are three legs 8
supported on the ground 9, to which three microphones 10 of
an acoustic directional sensor 11 are attached. A fourth
microphone 10 of the acoustic directional sensor 11 is
arranged on the aiming arrangement 6, so that the four
microphones 10 of the directional sensor 11 form the
corner-points of a tetrahedron. All the microphones 10 of
the directional sensor 11 are connected to the electronic
evaluation device 4 via electrical lines 12. The evaluation
device 4 contains a microprocessor 13.
At least one missile 14 which is provided with a target-
seeking IR homing head 15 and a steering device (not
illustrated) is arranged in the launching device 7.
The operation of the apparatus according to the invention
is explained in more detail below.
After the apparatus 1 has been installed it is switched on.
The device 1 is then initially in a so-called listening
mode, i.e. only an acoustic alerting circuit connected to
only one of the microphones 10 is activated. The electronic
evaluation device 4 continuously performs a Fast Fourier
Transform (FFT) of the acoustic signal being measured by
the microphone 10. As soon as the frequency spectrum
resembles the acoustic signature of a helicopter the target
CA 02437374 2003-08-14
acquisition device is switched to the so-called direction-
finding mode.
In the direction-finding mode all four microphones 10 are
5 activated and the electronic evaluation device 4 determines
the spatial direction to the target 2. For this purpose the
acoustic signals coming from the target 2 are measured in a
time-offset manner by the microphones 10. The spatial
direction of the target 2 is then determined from this
1-0 phase displacement by means of the microprocessor 13.
As soon as the direction-finding operation is stable and
the frequency spectrum has been identified as the acoustic
signature of a helicopter, the launching device 7 is
aligned in azimuth and in elevation by means of the aiming
arrangement 6 in such a way that the missile 14 is aligned
in the direction of the acoustic direction-finding. At the
same time the IR sensor of the homing head 15 of the
missile 14 is cooled to operating temperature, a friend-foe
identification inquiry is carried out and, in the case of
an enemy, the missile 14 is launched.
The missile 14 is accelerated to supersonic velocity and
the IR homing head 15 seeks a target (heat source) in the
area segment which has been determined by means of the
acoustic direction-finding. After acquiring the target 2
the missile 14 is guided to the target by means of the IR
homing head 15 and the steering device.
Self-evidently, the invention is not restricted to the
above-described embodiment. For example, the homing head of
the missile can also be a radar homing head.
CA 02437374 2003-08-14
Moreover, if a passive IR homing head is used it can be
provided that the missile is launched only if the homing
head has already detected the target in the area segment
defined by the acoustic direction-finding before the
5 launching of the missile.
CA 02437374 2003-08-14
7
List of reference numerals
1 Apparatus
2 Target, helicopter
3 Housing
4 (Electronic) evaluation device
5 Target acquisition device
6 Aiming arrangement
7 Launching device
8 Leg
9 Ground
10 Sensor, microphone, alerting sensor
11 Directional sensor
12 Electrical line
13 Microprocessor
14 Missile
15 Homing head
