U.S. patent application number 16/465387 was filed with the patent office on 2019-11-14 for launching arrangement for a missile for intercepting alien drones.
The applicant listed for this patent is RHEINMETALL AIR DEFENCE AG, SKYSEC GMBH. Invention is credited to Franco METZ, Manuel METZ.
Application Number | 20190346241 16/465387 |
Document ID | / |
Family ID | 60813790 |
Filed Date | 2019-11-14 |
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United States Patent
Application |
20190346241 |
Kind Code |
A1 |
METZ; Manuel ; et
al. |
November 14, 2019 |
LAUNCHING ARRANGEMENT FOR A MISSILE FOR INTERCEPTING ALIEN
DRONES
Abstract
The invention relates to a launching arrangement (29) for a
missile (1) for intercepting alien drones, wherein the launching
arrangement (29) comprises a launch container (30) with an opening
(31), wherein the missile (1) is or can be arranged within the
launch container (30). The launching arrangement (29) and the
associated missile (1) are improved in that the missile (1) has a
propeller drive (6) in a bow area of the missile (1).
Inventors: |
METZ; Manuel; (Ettenhausen,
CH) ; METZ; Franco; (Ettenhausen, CH) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
RHEINMETALL AIR DEFENCE AG
SKYSEC GMBH |
Zurich
Turbenthal |
|
CH
CH |
|
|
Family ID: |
60813790 |
Appl. No.: |
16/465387 |
Filed: |
December 1, 2017 |
PCT Filed: |
December 1, 2017 |
PCT NO: |
PCT/EP2017/001403 |
371 Date: |
May 30, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
62429153 |
Dec 2, 2016 |
|
|
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F41F 3/077 20130101;
B64C 2201/182 20130101; F41F 3/042 20130101; F41H 13/0006 20130101;
B64C 39/024 20130101; F41H 11/02 20130101; F42B 10/62 20130101;
F42B 12/66 20130101 |
International
Class: |
F41H 11/02 20060101
F41H011/02; F41F 3/042 20060101 F41F003/042; F41F 3/077 20060101
F41F003/077; F41H 13/00 20060101 F41H013/00; F42B 10/62 20060101
F42B010/62; F42B 12/66 20060101 F42B012/66 |
Claims
1. Launching arrangement (29) for a missile (1) for intercepting
alien drones, wherein the launching arrangement (29) comprises a
launch container (30) with an opening (31), wherein the missile (1)
is or can be arranged within the launch container (30),
characterised in that the missile (1) comprises a propeller drive
(6) in a bow area of the missile (1).
2. Launching arrangement according to the preceding claim,
characterised in that the launch container (30) is fitted with a
cover (32) closing the opening (31), wherein the launch container
(30) and the cover (32) are connected to one another via an
actuatable closing mechanism (37), wherein when the closing
mechanism (37) is actuated, the closing mechanism (37) releases the
cover (32) and the missile (1) can leave the launch container
(30).
3. Launching arrangement according to any one of the preceding
claims, characterised in that the closing mechanism (37) is coupled
to on-board electronics of the missile (1) via a connecting line
(39), wherein a signal to open the cover (32) can be sent to the
closing mechanism (37) via the on-board electronics of the missile
(1).
4. Launching arrangement according to any one of the preceding
claims, characterised in that the launch container (30) comprises
at least one, in particular a plurality of guide elements (34),
wherein the missile (1) is guided by the guide elements (34).
5. Launching arrangement according to any one of the preceding
claims, characterised in that the launching arrangement (29)
comprises a power supply (40), wherein the power supply (40) feeds
the electrically actuatable closing mechanism (37).
6. Launching arrangement according to any one of the preceding
claims, characterised in that the missile (1) for intercepting
alien drones (21) comprises a net (9) and a parachute (18), wherein
a plurality of weights (15) are connected to the net (9), wherein
the net (9) can be ejected from the missile, wherein the weights
(15) can be ejected from the missile, wherein the net (9) can be
ejected by means of a first means and the weights can be ejected by
means of a second means, wherein the weights (15) and the net can
be ejected from the missile (1) at different points of time.
7. Launching arrangement according to any one of the preceding
claims, characterised in that the time difference between the
ejection of the net (9) and the weights (15) can be selected
depending on the current airspeed of the missile (1).
8. Launching arrangement according to any one of the preceding
claims, characterised in that the net (9) is arranged in a
container (11), wherein the container (11) forms a rear area of the
missile (1), wherein the container with the net (9) can be ejected
by the first means.
9. Launching arrangement according to any one of the preceding
claims, characterised in that the weights (15) are arranged in
ejector receptacles (14), wherein the ejector receptacles (14) are
arranged in the longitudinal direction of the missile (1) seen in
front of the container (11).
10. Launching arrangement according to any one of the preceding
claims, characterised in that the missile (1) comprises a
replaceable unit (12), wherein the replaceable unit (12) comprises
the net (9), the weights (15) and the ejector receptacles (14).
11. Launching arrangement according to any one of the preceding
claims, characterised in that the replaceable unit (12) comprises a
fuselage part (13), wherein the fuselage part (13) comprises a
hollow space (17), wherein a parachute (18) is arranged in the
hollow space (17), wherein the parachute (18) is connected to the
fuselage part (13) and/or the net (9) via a flexible connection
means (19, 20).
12. Launching arrangement according to any one of the preceding
claims, characterised in that the hollow space (13) adjoins the
container (11), wherein the container (11) comprises an opening
(26), wherein the net (9) is connected to the weights (15) and/or a
parachute (18) via a flexible connection means (16, 19) and this
connection means (16, 19) or the net (9) are guided through the
opening (26).
13. Launching arrangement according to any one of the preceding
claims, characterised in that the internal diameter of the
container (11) is larger than the opening (26).
14. Launching arrangement according to any one of the preceding
claims, characterised in that the net (9) in the form of a coiled
rope is arranged in the container (11) and thus forms a winding,
wherein an end of the rope connected to the weights (15) is found
inside the winding and a free coil end is found on the outside of
the winding.
15. Launching arrangement according to any one of the preceding
claims, characterised in that the missile (1) has the form of a
rocket.
16. Launching arrangement according to any one of the preceding
claims, characterised in that the missile (1) comprises a
plurality, in particular more than three circumferentially spaced
wings (2).
17. Launching arrangement according to any one the preceding
claims, characterised in that the propeller drive (6) is arranged
in the flight direction in front of the centre of gravity of the
missile (1).
18. Launching arrangement according to any one the preceding
claims, characterised in that the weights (15) are arranged in the
area of the centre of gravity of the missile (1).
19. Launching arrangement according to any one of the preceding
claims, characterised in that the maximum airspeed of the missile
(1) is over 100 km/h, in particular over 200 km/h.
20. Launching arrangement according to any one of the preceding
claims, characterised in that the first means and/or the second
means are formed by at least one pyrotechnic propellant and/or a
means operating with pressurised air.
21. Launching arrangement according to any one of the preceding
claims, characterised in that a means for ejecting the parachute
from the hollow space (13) is provided.
Description
[0001] The invention relates to a launching arrangement for a
missile for intercepting alien drones with the features of claim 1.
The launching arrangement comprises a launch container with an
opening, wherein the missile is or can be arranged within the
launch container. The missile comprises a net, wherein a plurality
of weights are attached to the net. The net and the weights can be
ejected at a provided point of time in order to capture an alien
drone. The alien drone is thus entangled in the net and can no
longer continue its planned flight path.
[0002] From the generic EP 0 175 914 A1, a missile in the form of a
projectile for counteracting freely moving objects and a launching
arrangement are known. The projectile is moved in the direction of
an object to be counteracted by thrust power. At a certain distance
from the object, a net is ejected from a sleeve body so that the
net is deployed over a large area. The net is thus deployed in the
flight direction seen behind the projectile. The net is stored in a
rear part of the projectile before ejection. For example, the
projectile can be launched from a gun barrel or a cannister or
moved in the direction of the object to be counteracted by means of
thrust power generated by its own suitable means. The projectile
can be directed by a suitable launcher to the object in a guided,
deflected, ballistic or aerodynamic or hydrodynamic manner. The
projectile can be formed as a drone. Before reaching the object to
be counteracted, a ground part of the missile is ejected from a
sleeve body at a predetermined breaking point by igniting an
ignition element and thus by the action of an ignited propellant
charge. The sleeve body is thus separated into two symmetrical
parts with the ground part and with the ignition element. In one
embodiment, the sleeve parts are connected to the net via a spring
means, wherein after blasting, these sleeve parts serve as weights
which span the net.
[0003] From U.S. Pat. No. 6,626,077 B1 a missile for intercepting
other flying objects with a net is known. A plurality of weights
are attached circumferentially to the net. A rocket or a manned or
unmanned flying object can serve as a missile. The missile
comprises a head with a net, wherein the head can be blasted by
means of an explosive charge, wherein housing parts of the head
serve as weights in order to span the net. As the net is arranged
on the head of the missile, there is a risk that the alien missile
will not be captured by spanning the net, but that the missile
itself will be captured by the net due to the strong braking effect
of the net and thus the actual capturing effect against the alien
missile will not occur. A plurality of parachutes should be
attached to the net, which decelerate the captured alien missile
together with the net during the fall to the ground.
[0004] From RU 249 0 584 C1 a missile for intercepting alien drones
is known. The missile is formed as a type of model aircraft with an
aircraft fuselage, wings and a tail unit. The missile comprises a
plurality of nets at the ends of which weights are attached. Four
cartridges with nets are contained in the missile. The weights are
thus arranged inside the cartridges. The cartridges are arranged to
the right and left and above and below the aircraft fuselage.
Furthermore, a parachute is arranged in each of the cartridges. The
missile is controlled from the ground when accessing the drone so
that the alien drone is approached from behind. When the alien
drone is 500 m away from being reached, the alien drone is detected
by means of a video camera, wherein the operator now adapts the
flight speed to the flight speed of the alien drone. If only one of
the sensors on the aircraft fuselage detects the alien drone, the
net and the weights are automatically shot out together. When the
alien drone is captured by the net, pyrotechnic cartridges are
ignited which jettison the housing of the cartridges and release a
parachute.
[0005] It has been found that in practice it is difficult to unfold
the net during flight and to safely capture the foreign drone.
[0006] The launching arrangement described at the outset is not yet
formed in an optimal manner. It has been found to be difficult to
provide a launching arrangement which can be launched from a launch
container and at the same time an alien drone can be securely
intercepted.
[0007] The object of the invention is thus to improve the launching
arrangement and the associated missile.
[0008] This object of the invention is now achieved by means of a
missile with the features of claim 1.
[0009] The missile comprises a propeller drive in a bow area of the
missile. The missile has a propeller drive in the front area of its
fuselage. The drive is arranged in front of the centre of gravity
of the missile. This has the advantage that the weights and the net
can be arranged behind the drive. This simplifies the capture of
the alien drone. It is not necessary for the missile to be shot out
of the launch container. This has the advantage that a net can be
housed in the rear part of the missile and the launch container can
be designed structurally simply and inexpensively at the same time.
In that the drive is arranged in the bow area, the missile can
launch from the launch container on its own power and must not be
launched from the launching arrangement by means of an external
drive. This simplifies the construction of the launching
arrangement.
[0010] The propeller drive preferably comprises an electric motor.
This makes it possible for the drive to be quickly launched in a
simple manner.
[0011] The weights are preferably arranged in the area of the
centre of gravity of the missile. This improves the manoeuvrability
of the missile.
[0012] The launch container is fitted with a cover closing the
opening, wherein the launch container and the cover are connected
to one another via an actuatable closing mechanism, wherein when
the closing mechanism is actuated, the closing mechanism releases
the cover and the missile can leave the launch container. This has
the advantage that the missile is arranged protected in the launch
container before the launch. After activation of the propeller
drive, the missile can push open the cover.
[0013] The closing mechanism is coupled to on-board electronics of
the missile via a connection line, wherein a signal to open the
cover can be sent to the closing mechanism by means of the on-board
electronics of the missile. This has the advantage that the
container and the closing mechanism do not need to be fitted with
any expensive electronics. All sensitive, electronic components are
contained in the missile. This makes it possible to keep the costs
for the launching arrangement low and at the same time produce the
launch container with the closing mechanism to be robust against
influences from the weather, which facilitates a longer lifespan of
the container and the closing mechanism.
[0014] The launch container comprises at least one, in particular a
plurality of guide elements inside it, wherein the missile is
guided by the guide elements. This ensures that the missile can
safely leave the launch container when launching without catching
on the inside wall of the launch container or similar.
[0015] The launching arrangement preferably comprises a power
supply, wherein the power supply feeds the electrically actuatable
closing mechanism. This has the advantage that a power supply of
the missile is not burdened by unlocking the closing mechanism
during launch. The missile can comprise an accumulator or a battery
as a power source.
[0016] In the following, the embodiment and advantages of the
missile to be used will be discussed in more detail.
[0017] The net can be ejected by means of a first means and the
weights can be ejected by means of a second means, wherein the
weights and the net can be ejected from the missile at different
points of time. This ensures the spanning of the net. The net is
initially arranged inside the container of the missile. The
container of the missile is ejected first, for example by means of
pressurised air or at least one pyrotechnic propellant. Only then,
in a second step, are the weights which are connected to the
circumference of the net via flexible connection means or ropes
ejected from the missile. Thus, the net is pulled out of the
container first. This ensures that when ejecting the weights, the
net is not yet unfolded, but has already unrolled. Thus, the risk
of the net becoming entangled before the alien drone is captured.
The container is arranged on a rear area of the missile. In
particular the container forms the end of the fuselage of the
missile. The container is ejected against the flight direction,
i.e. backwards. The net is located in a container which forms the
rear area of the missile. The container can be ejected by the first
means. The weights are connected with flexible connection means
which lead from the weights to the net. These connection means are
led out of the container and outside on the fuselage to the weights
which are inserted there in ejector receptacles provided for that
purpose. The ejector receptacles are distributed so that they face
away from one another. Spanning of the net takes place in two
phases. In the first phase, the container is ejected backwards with
the net. After a certain defined time, after most of the net has
left the container and the fuselage, the weights are ejected out of
the ejector receptacles. This time preferably depends on the
airspeed of the missile. The ejection force is great enough that
the net can be spanned by the weights. The net ejection sequence is
or can be triggered in different ways, for example by means of a
sensor in a seeker with a proximity radar, with a stereo imaging
system or with an ultrasonic sensor, for example, or by means of
pure external triggering via a wireless connection. Furthermore,
distance triggering of the net ejection sequence is
conceivable.
[0018] In particular, the missile comprises a plurality of wings,
Preferably, the missile comprises four wings to be able to
immediately accelerate the missile in all transverse directions.
The guide elements of the launching arrangement preferably guide
the wings of the missile. The guide elements can have U-shaped
slots, wherein before launch the wings engage in these slots. The
open end of the slots points in the direction of the opening of the
launch container.
[0019] The drive of the missile is realised such that additional
electronics are mounted or can be mounted in front of the drive
and/or behind the drive. The missile has the form of a rocket,
whereby a high airspeed can be achieved. The airspeed is preferably
more than 100 km/h, preferably more than 200 km/h.
[0020] A parachute and the net in particular are arranged in the
central and rear area of the missile. These can be ejected via the
on-board electronics or via an external control command. The
on-board electronics can autonomously or manually trigger an
electric signal which can eject the parachute, the weights by means
of the ejector receptacles and the container in any desired time
sequence.
[0021] The on-board electronics of the missile are able to steer or
navigate the missile autonomously or with external control
commands. The control of the missile is carried out via aerodynamic
control surfaces and/or via swivelling the drive.
[0022] The missile finds the object to be flown towards by means of
a seeker. The seeker is preferably arranged in front of the drive.
The seeker can either have a radar or an optical system.
[0023] The missile serves to convey the net located inside the
container to another missile or object. This can take place in the
air or on the ground. The navigation occurs autonomously or by
means of manual control commands. The missile is sent information
about the location or the direction of the object to be flown
towards by means of a wireless data connection.
[0024] The launch of the missile is alternatively carried out from
a ramp or by means of the launching arrangement from the launch
container. The landing of the missile is carried out with a
parachute. The parachute is initially arranged within the missile.
It is conceivable to arrange a plurality of parachutes in the
missile, wherein at least one of the parachutes is connected to the
missile and at least one of the parachutes is connected to the
net.
[0025] Preferably, a plurality of weights, in particular four
weights are connected with the net edge of the net. The flexible
connection can thus be formed by cords, lines, ropes, wires, chains
or similar. The weights are preferably each attached to the net
with a rope. The weights serve to span the net. If all weights are
pulled away from one another, the net will be spanned. The net is
connected to the missile via a further flexible connection such as
a rope or wire, or chain or similar so that when something is
captured with the net, the net and the captured object are
connected to the missile and thus also to the parachute.
[0026] So that the missile and possible captured objects can be
brought to the ground with as little damage as possible, a
parachute is used which is connected to the missile. The parachute
is preferably located in front of the net. The parachute is
connected to the net and in the event of a hit is automatically
triggered by the braking action or the lag of the captured alien
drone in the net. If the target is missed, the parachute is ejected
by the on-board electronics after a defined amount of time. The net
pulls the parachute out of the missile once the object or alien
drone has been captured in the net and this object and this object
develops a lag or a force on a connecting rope. An ejection charge
is preferably arranged in a front area which serves to eject the
parachute in the event of a missed hit. It is conceivable to
arrange a plurality of parachutes in the missile wherein at least
one of the parachutes is connected to the missile and at least one
of the parachutes is connected to the net.
[0027] Preferably, the missile has a replaceable unit, wherein the
replaceable unit comprises the container for the parachute and a
fuselage part with a hollow space for the parachute. This
replaceable unit furthermore preferably comprises the ejector
receptacles for the weights. The replaceable unit can be or is
preferably connected to the front fuselage part via a catch or
bayonet connection. The use of a replaceable unit with the net, the
weights and the parachute as well as the means assigned for
ejecting these has the advantage that after an interception attempt
the missile can quickly be made ready to use again in that a new
replaceable unit is connected to the fuselage part with the drive.
The use of a replaceable unit has the advantage that the parachute
and/or the net do not have to be folded and rolled up again every
time to be able to make the missile ready for use. The fuselage
part of the replaceable unit comprises an open hollow space in the
direction of the container, wherein the parachute is arranged in
the hollow space. The parachute is thus connected on the one hand
to the net via a connection means or a line, a rope or similar and
preferably connected to a base or a side wall of the fuselage on
the other hand so that both the net with the alien drone and the
missile itself can be landed by means of the parachute. The
fuselage part is preferably coupled to the on-board electronics
and/or a power supply via an electronic or optical contact so that
the ejector receptacles and/or the means of ejecting the container
and/or the means of ejecting the parachute can be triggered during
the flight.
[0028] One a target object has been recognised in terms of its
position or direction vector, the missile can be launched. The
missile flies towards the target by means of the on-board
electronics and the position data of the target which is made
available via a data link of the on-board electronics. In addition,
navigation guidance can be supported by a seeker. Before the
missile crosses the target, object or reaches the target object,
the container with the net are ejected and the weights on the edge
of the net are sequentially ejected so that the net unfolds behind
the missile. Once the target object has been captured in the net,
the net with the captured target object pulls the parachute out of
the missile. If no object has been captured with the net, the
parachute is ejected. The missile can be landed at any time after
launch by means of the parachute.
[0029] The missile can be launched in various different ways to be
able to cover as wide a use spectrum as possible. The missile can
be launched independently under its own power vertically or at an
angle of less than 90.degree. to the earth's surface. The missile
can thus launch from a launch container. Thanks to its ability to
launch vertically, the missile can also be easily launched into the
air by hand. Furthermore, the missile can be carried by another
missile and also launched from there. For example, the missile can
be launched from an aircraft. The missile can furthermore be
mounted on a drone or on another flying object and launched from
there.
[0030] There are now a number of possibilities for configuring and
further developing the missile according to the invention in
advantageous different ways. For this purpose, reference can first
be made to the claims subordinate to claim 1. In the following,
preferred embodiments of the invention are described in detail
using the drawing and the associated description. In the
drawing:
[0031] FIG. 1 shows a schematic view of a missile for intercepting
alien drones,
[0032] FIG. 2 shows a schematic side view of the missile of FIG. 1,
wherein here a net and a parachute have already been ejected,
[0033] FIG. 3 shows a schematic sectional view of a part of the
missile of FIGS. 1 and 2, for example a rear fuselage part, which
forms a replaceable unit and comprises the net and the
parachute,
[0034] FIG. 4 shows a schematic representation of a trajectory of
the missile, wherein an alien drone is captured,
[0035] FIG. 5 shows a schematic sectional view of a container with
the missile, wherein the missile can launch independently from the
container,
[0036] FIG. 6 shows a schematic top view of the opened container
with the missile,
[0037] FIG. 7 shows a schematic sectional representation of the
opened container without the missile, and
[0038] FIG. 8 shows a schematic top view of the container without
the missile.
[0039] In FIGS. 1 to 4, a missile 1 can be clearly seen which forms
part of a launching arrangement 29 according to the invention. The
missile 1 has the form of a rocket. The missile 1 comprises a
plurality of wings 2, in particular three or more wings 2, wherein
each wing 2 in particular comprises an aileron 4. In particular,
four wings 2 are arranged evenly spaced circumferentially around a
fuselage 3.
[0040] A drive 5, in particular in the form of a propeller drive 6,
is provided in a front area of the fuselage 3. The drive 5
preferably has an electric motor. The form of the missile 1 is
selected such that the missile 1 can be easily controlled around
all transverse axes by means of the aileron 4. The wings 2 are
wider in the rear area of the missile 1 than in the front area,
i.e. they substantially taper towards the fuselage 3 in the
direction of the drive. Thus, the missile 1 substantially has the
form of a rocket which allows for a high-top speed. The top speed
of the missile 1 is preferably more than 100 km/h, in particular
more than 200 km/h, preferably in the range between 250 km/h and
350 km/h. This ensures that the missile 1 can be used with a high
differential speed to an alien drone 21 which facilitates the
capture of the alien drone 21 with the present missile 1.
[0041] The tip of the fuselage 3 is formed by a seeker 7, wherein
the seeker 7 has at least one, in particular a plurality of
sensors. The seeker 7 is arranged in front of the drive 5. The
sensors can comprise electro-optical sensors or radar sensors. It
is conceivable for the seeker 7 as an optical system to have a
camera, in particular a 4 K camera.
[0042] Behind the drive 5, the fuselage 3 comprises a central
fuselage part 8. Preferably, the on-board electronics and/or a
power supply are arranged inside the central fuselage part 8. To
capture the alien drone 21, the missile 1 now has a net 9 which in
FIG. 3 is arranged packed in a rear fuselage part 10, for example
in particular in a container 11 at the end of the rear fuselage
part 10. The internal diameter of the container 11 is larger than
an opening 26 in the base 30B of the container so that the net 9 is
only gradually pulled out to avoid it becoming entangled. Flexible
connection means 16, 19 are led through the opening 26 which
connect the net 9 to the weights 15 and a parachute 18.
[0043] The net 9 is arranged in the container 11 in the form of a
coiled rope and thus forms a winding. An end of the rope connected
to the weights 15 is located inside the winding and a free end of
the rope is outside of the winding, i.e. on the inside wall of the
container 11. By means of this spiral-formed winding it is ensured
that the net 9 is gradually pulled out when the container 11 is
ejected without it becoming entangled.
[0044] The unfolded state of the net 9 is represented in FIG. 2.
The rear fuselage part 10 is made up of several individual
components, for example a fuselage part 13 and the container 11,
among others. In a preferred embodiment, the rear fuselage part 10
forms a replaceable unit 12. This facilitates the reloading and
repair of the missile 1 after an interception attempt. A plurality
of replaceable units 12 can be provided so that the missile 1 can
be quickly made ready for use.
[0045] This replaceable unit 12 comprises the fuselage part 13,
wherein a plurality of ejector receptacles 14 with corresponding
weights 15 arranged therein are arranged on the fuselage part 13.
The ejector receptacles 14 and the weights 15 are arranged in the
area of the centre of gravity of the missile 1. The ejector
receptacles 14 are thus aligned such that the weights 15 can be
ejected to transverse to the flight direction and also transverse
to the longitudinal direction of the missile 1. It is conceivable
that the ejector receptacles 14 are thus aligned substantially
radially or that the ejector receptacles 14 point obliquely
backwards. The weights 15 serve to span the net 9. Thus, the
weights 15 are connected to the net 9. In particular, a rope, a
belt or another flexible connection means 16 can be used as a
connection. This connection means 16 is connected to a weight 15 on
the one hand and connected to a circumference of a net 9 (not shown
in detail). Preferably, at least three weights 15 and at least
three corresponding ejector receptacles 14 are provided. In the
embodiment shown, four weights 15 and four corresponding ejector
receptacles 14 are used. In the spread-out state, the net 9 can in
particular be four-sided, in particular square. In an alternative
embodiment, it is conceivable to use a three-sided, five-sided,
six-sided or even a round net 9.
[0046] The fuselage part 13 has a hollow space 17, wherein a
parachute is arranged inside the hollow space 17. The hollow space
17 is opened in the direction of the container 11. The parachute 18
is connected to the net 9 via a further flexible connection means
19 and preferably connected to the fuselage part 13 via a further
flexible connection means 20. When the net 9 is ejected together
with the parachute 18 as will now be described in the following
(cf. FIG. 2), the missile 1 and the net 9 are safely brought to the
ground together with the captured alien drone 21 if present.
[0047] The missile 1 now has a first means (not shown here) for
ejecting the container 11. The means can in particular be arranged
on the front side of the fuselage part 13 facing the container 11.
These means can be formed pneumatically or by a pyrotechnic
propellant, for example. The means can be triggered via the
on-board electronics. The ejector receptacles 14 can also be
actuated via the on-board electronics. It is conceivable that the
ejector receptacles 14 can also be confirmed by pneumatic means or
by pyrotechnic propellants.
[0048] Furthermore, means to eject the parachute 18 are provided.
These means assigned to the net 9, the weights 15 and the parachute
18 can be triggered in any desired sequence.
[0049] The process of the method for intercepting the alien drone
21 will now be described in more detail using FIG. 4. First, the
missile 1 is launched from the ground 22. A radar system or another
sensor system, for example, can be arranged on the ground that
detects the appearance of the alien drone 21. This system transmits
the coordinates and/or the direction vector of the alien drone 21
to the missile 1 via a radio connection 23. It is conceivable that
the missile 1 is initially controlled from the ground. At a point
24 along the flight path 25, the seeker 7 now detects the alien
drone 21. Hereafter, the on-board electronics guide the missile 1
in the direction of the alien drone 21 without external influence,
i.e. without the use of the radio connection 23. The speed of the
alien drone 21 is preferably determined by a seeker 7 or by the
sensor on the ground 22. Furthermore, the speed of the missile 1 is
preferably determined. Depending on the distance from the missile 1
and in particular depending on the relative speed between the alien
drone 21 and the missile 1, the container 11 is ejected with the
described means at a certain point 41. This leads to the net 9
being pulled out through the opening 26 (cf. FIG. 3) in the base 27
of the container 11.
[0050] At a later point in time, at a later point 28 of the flight
path, the weights 15 are then ejected out of the ejector
receptacles 14, whereby the net 9 is spanned. This point in time is
selected such that the alien drone 21 can thus be securely
captured. The flight path of the missile 1 is thus adapted to the
flight path of the alien drone 21 such that the alien drone 21 can
also be captured taking into account the braking effect of the net
9 on the missile 1. By capturing the alien drone 21, the parachute
18 is now also pulled out of the hollow space 17 and the missile 1
now floats to the ground together with the net 9 and the captured
alien drone 21.
[0051] It has proven to be particularly advantageous that the
container 11 and the weights 15 are ejected at different points in
time, i.e. first the net 9 and then at a later point in time the
weights 15. Thus, the net 9 is first unrolled and only when the net
9 has substantially left the container 11 is it spanned by the
weights 15. The time difference between these two points in time
depends in particular on the airspeed of the missile 1.
[0052] In the following, a preferred launching arrangement 29 will
now be described. The launching arrangement 29 comprises a launch
container 30, wherein the missile 1 is initially arranged in the
launch container 30. The launch container 30 has an opening 31
which is initially closed by a cover 32. The cover 32 is arranged
on the launch container 30 such that it can be pivoted by a hinge
33. A plurality of guide elements 34 are arranged inside the launch
container 30, wherein the guide elements 34 are designed
substantially U-shaped so that the wings 2 of the missile 1 are
held in a slot 35. The missile 1 is thus arranged in the launch
container 30 such that the tip or the bow of the missile 1 is
arranged with the drive close to the cover 32 and the rear is
arranged substantially between the guide elements 34 close to the
base 30B of the launch container 30. The cover 32 has a damper 36
inside of it. The damper 36 is thus opposite the tip, i.e. the
seeker 7 of the missile 1.
[0053] A closing mechanism 37 is now arranged on the side of the
launch container 30 opposite the hinge 33. A hook 38 of the closing
mechanism 37 is shown here. The closing mechanism 37 is
electrically actuatable, for example by means of a servo, so that
the closing mechanism 37 securely locks the cover 32 in a base
position and after a corresponding activation releases the cover
32. It is conceivable for the cover 32 to be substantially swung
into the opened stated by a spring or similar. Alternatively, it is
conceivable for the cover to be pushed open by the launching of the
missile 1 alone.
[0054] The signal to open the cover 32 is now transmitted from the
on-board electronics of the missile 1 to the closing mechanism 37.
Thus, the missile 1 is coupled to the closing mechanism 37 by means
of a connecting line 39 The missile 1 is again connected to a
ground station via a radio connection 23 so that the ground station
gives the signal to launch the missile 1, the on-board electronics
automatically send a signal to the closing mechanism 37 via the
connecting line 39 that the cover 32 should now be opened or the
hook 38 should now be retracted in order to release the cover 32.
The connecting line 39 is thus plugged into a jack (not shown in
detail) on the missile 1 so that a data connection to the on-board
electronics is established. The power to open or to activate the
closing mechanism 37 is preferably supplied externally via a power
supply 40.
[0055] This launching arrangement 29 has the advantage that the
launching arrangement 29 can protect the missile 1 from external
weather conditions and at the same time does not comprise any
delicate electronics as these are provided by the on-board
electronics of the missile 1. This facilitates inexpensive
production of the launching arrangement 29. Now, when the signal to
launch is given by the ground station, the drive 5 is activated,
i.e. the propeller begins to rotate and the cover 32 is swung to
the side by the resulting thrust, so that the opening 31 of the
launch container 30 is released and the missile 1 passes out of
this opening 31 out into the open.
LIST OF REFERENCE NUMERALS
[0056] 1 Missile [0057] 2 Wing [0058] 3 Fuselage [0059] 4 Aileron
[0060] 5 Drive [0061] 6 Propeller drive [0062] 7 Seeker [0063] 8
Central fuselage part [0064] 9 Net [0065] 10 Rear fuselage part
[0066] 11 Container [0067] 12 Replaceable unit [0068] 13 Fuselage
part [0069] 14 Ejector receptacle [0070] 15 Weights [0071] 16
Flexible connection means [0072] 17 Hollow space [0073] 18
Parachute [0074] 19 Flexible connection means [0075] 20 Flexible
connection means [0076] 21 Alien drone [0077] 22 Ground [0078] 23
Radio connection [0079] 24 Point on flight path [0080] 25 Flight
path [0081] 26 Opening [0082] 27 Base [0083] 28 Point on flight
path [0084] 29 Launching arrangement [0085] 30 Launch container
[0086] 31 Opening [0087] 32 Cover [0088] 33 Hinge [0089] 34 Guide
element [0090] 35 Slot [0091] 36 Damper [0092] 37 Closing mechanism
[0093] 38 Hook [0094] 39 Connecting line [0095] 40 Power supply
[0096] 41 Point on flight path
* * * * *