U.S. patent application number 11/045318 was filed with the patent office on 2006-03-30 for anti-missile protection device for an aircraft.
This patent application is currently assigned to AIRBUS. Invention is credited to Bernard Catteeuw, Olivier Pujol, Serge Roques.
Application Number | 20060065774 11/045318 |
Document ID | / |
Family ID | 36097941 |
Filed Date | 2006-03-30 |
United States Patent
Application |
20060065774 |
Kind Code |
A1 |
Roques; Serge ; et
al. |
March 30, 2006 |
Anti-missile protection device for an aircraft
Abstract
This protection device (4) includes on the one hand a decoy (10)
that permits sending out electromagnetic signals and on the other
hand a device (8) that winds/unwinds a cable (6) at one end of
which the decoy (10) is secured, with this device permitting to
keep the decoy (10) in its wound position on board of the aircraft
(2) and in its unwound position at a distance from the aircraft
(2).
Inventors: |
Roques; Serge;
(Cornebarrieu, FR) ; Catteeuw; Bernard; (Pibrac,
FR) ; Pujol; Olivier; (Beauzelle, FR) |
Correspondence
Address: |
OBLON, SPIVAK, MCCLELLAND, MAIER & NEUSTADT, P.C.
1940 DUKE STREET
ALEXANDRIA
VA
22314
US
|
Assignee: |
AIRBUS
BLAGNAC
FR
|
Family ID: |
36097941 |
Appl. No.: |
11/045318 |
Filed: |
January 31, 2005 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
60600356 |
Aug 11, 2004 |
|
|
|
Current U.S.
Class: |
244/1TD |
Current CPC
Class: |
F41J 9/10 20130101; F42B
12/382 20130101; B64D 39/00 20130101; F41H 11/02 20130101 |
Class at
Publication: |
244/001.0TD |
International
Class: |
B65D 3/00 20060101
B65D003/00 |
Foreign Application Data
Date |
Code |
Application Number |
Feb 13, 2004 |
FR |
0401477 |
Claims
1. Anti-missile protection device (4) for transportation aircraft
(2) comprising a decoy (10) a winding/unwinding device (8) for a
cable (6) at one end to which is secured decoy (10), with this
device permitting to maintain decoy (10) in its wound up position
inside the aircraft (2) and in its unwound position at a distance
from the aircraft (2) and a control device that manages the winding
and unwinding of cable (6) to which decoy (10) is attached
according to the flight stages of the aircraft (2).
2. Device according to claim 1, characterized by the fact that the
control device adapts the unwinding speed of cable (6) on the basis
of at least a parameter selected from all of the flight parameters
comprising altitude and vertical speed of the aircraft (2).
3. Device according to one of claims 1 or 2 characterized by the
fact that the control device adapts the winding speed of cable (6)
according to at least one parameter selected from all flight
parameters comprising altitude and vertical speed of the aircraft
(2).
4. Device according to one of claims 1 to 3, characterized by the
fact that the control device adapts the length of unwound cable (6)
according to the flight parameters of the aircraft (2).
5. Device according to claim 4 characterized by the fact that the
control device adapts the length of unwound cable (6) according at
least to the altitude of the aircraft (2).
6. Device according to one of claims 1 to 5, characterized by the
fact that decoy (10) is a device that transmits multidirectional
infrared radiation.
7. Device according to claim 6, characterized by the fact that the
frequency of the infrared radiation transmittal is set to the
transmittal spectrum of the aircraft (2) with which the device (4)
is associated.
8. Device according to one of claims 1 to 7, characterized by the
fact that in the wound position of the decoy (10) and the
winding/unwinding (8) take place in a compartment located in the
back of the plane (2) and closed by a trap door (16) leading to the
outside of the airplane (2).
9. Device according to one of claims 1 to 8, characterized by the
fact that the decoy (10) has a conical form.
10. Device according to one of claims 1 to 9, characterized by the
fact that it also includes a surveillance device informing the
pilot of the aircraft (2) of the wound or unwound status of the
cable (6).
11. Device according to one of claims 1 to 10, characterized by the
fact that the length of the cable (6) is between 10 and 150 m,
preferably between 20 and 50 m.
12. Device according to one of claims 1 to 11, characterized by the
fact that the decoy (10) secured to an end of cable (6) is
associated with a missile detection system.
13. Device according to claim 12, characterized by the fact that
the decoy (10) includes an infrared one-directional transmission
device.
14. Device according to one of claims 12 or 13 characterized by the
fact that the decoy (10) includes a device permitting the launching
of light flares.
15. Aircraft (2) characterized by the fact that it includes a
protection device according to one of claims 1 to 14.
16. Aircraft (2) according to claim 15, characterized by the fact
that it is aimed at the transportation of passengers.
Description
[0001] This invention involves a protection device against missiles
aimed at a transport airplane.
[0002] In recent years, it has been observed that an increasing
number of ground-air type missile attacks against civil airplanes
are taking place. A short while ago, in Mombasa (Kenya, November
2002) and in Baghdad (Iraq, November 2003), two civil airplanes
were aimed at with such missiles,
[0003] Following such events and other attacks, it has been decided
to study a system that would counter such threat, but adapted to
civil airplanes.
[0004] At this time, there are numerous devices that permit
misleading or decoying ground-air missiles, particularly in the
military field. Indeed, most of the military airplanes of today are
equipped with ground-air missile detection and decoy systems.
[0005] Several means of detecting a ground-air missile are known.
Such a missile can be actively detected by a Doppler effect radar
or passively by an optical infrared or ultraviolet base system.
[0006] Several ways are also known to decoy a missile aimed at an
airplane. For instance, the plane can sent out flares known to the
specialist by this English name. They are pyrotechnic devices aimed
at producing a very intense pinpoint light source. Another known
method to decoy a missile is to transmit continuous and
multidirectional infrared signals or an infrared directive
transmission (using a laser technology that is called DIRCM or
Directional InfraRed Counter Measures).
[0007] However, all these solution have been developed for military
aircraft where constraints are totally different from those of
civil airplanes. As such, the cost and the false alarm rate are
incompatible constraints for civil applications. Moreover, for
civil airplanes, the solution adopted must be usable in regions
with a high population density. For instance, one cannot use flares
above a city as it is done over more or less deserted areas. As
such, most of the solutions evoked above are not directly
applicable to a civil aircraft.
[0008] As such, the purpose of this invention is to provide an
anti-missile protection device that is adapted for use on board a
transport aircraft (for passengers or freight), such as those used
in civil aviation. Preferably, this device must have a low cost
price so that it can be mounted on a large number of aircraft and
not only, for instance, on board those that fly into areas of the
world where there is aimed conflict. Beneficially also, this device
shall be able to be installed in existing aircraft.
[0009] This invention consequently proposes an anti-missile
protection device for transportation aircraft, comprising: [0010] a
decoy [0011] a winding-unwinding device for a cable at the end of
which the decoy is secured, with this device permitting to maintain
the decoy in its wound up position on board of the aircraft and in
an unwound position at a distance of the aircraft and [0012] a
control device that manages the winding and unwinding of the cable
to which the decoy is secured according to the flight stages of the
aircraft.
[0013] The invention proposes as such a decoy that is not
incorporated in the aircraft to which it is associated and by which
it can be pulled. This decoy remains attached by a cable to the
aircraft. As such, the decoy can be fully controlled and can be
used under all conditions, even in highly populated areas. The fact
of pulling the decoy permits having a decoy of a known type that
does not require any special technical development to adapt it to a
civil aircraft. Moreover, an existing airplane can be equipped with
a device according to the invention without requiring a substantial
modification of its systems.
[0014] Thanks to the automatic management of winding and unwinding
of the cable to which the decoy is secured, the pilot of the plane
does not have to control the protection device and is only
responsible for piloting the aircraft.
[0015] The control device can be beneficially adapted to the speed
of winding and/or unwinding the cable on the basis of at least a
parameter selection from the flight parameters comprising altitude
and vertical speed of the aircraft. The parameters selected for
winding can be different from those selected for unwinding. As
such, it is theoretically possible to avoid that the decoy does not
touch the ground during the takeoff and landing stages. It can also
be provided for the same purpose that the control device adapts the
length of the unwound cable on the basis of flight parameters of
the aircraft, for instance, at least on the basis of the aircraft's
altitude.
[0016] The decoy used in this invention is for instance a device
that transmits multidirectional infrared radiation. This solution
appears being the most simple technically speaking and the easiest
to implement. In this form of implementation, the frequency of the
infrared radiation transmissions is preferably set on the
transmission spectrum of the aircraft with which the device is
associated to increase decoy efficiency.
[0017] For instance, such a device is placed in the aircraft in
such a way that in the wound up position the decoy and the
winding-unwinding device take place in a compartment located in the
back of the aircraft and closed by a trap door leading to the
outside of the aircraft. Other positions in the aircraft can be
considered but the position proposed here permits the easiest
adaptation of this device to any type of aircraft.
[0018] To limit the aerodynamic drag induced by the presence of the
decoy, the latter shall preferably have a conical form.
[0019] In a device according to the invention, it is preferable to
provide for a surveillance device that will notify the pilot of the
aircraft of the wound or unwound condition of the cable so as to
provide a warning in the event of failure of the device.
[0020] The length of the cable is for instance between 10 and 150
m, preferably between 20 and 50 m. Lengths are such that a missile
can confuse hot sources of the aircraft with the decoy but are also
rather large so that the explosion of the missile hitting the decoy
does not seriously damage the airplane. This explosion should not
affect safety and handling of the aircraft.
[0021] In a perfected form of implementation, the decoy secured at
an end of the cable can also be associated with a missile detection
system. In this case, the decoy comprises beneficially also a
one-directional infrared transmission device so as to be able to
react if a missile is detected. For the same purpose, the decoy can
also include a device that permits launching flares.
[0022] This invention also involves an aircraft characterized by
the fact that it includes a protection device as described above.
This aircraft is for instance used for the transportation of
passengers.
[0023] Details and advantages of this invention shall be revealed
even better by the description below with reference to the attached
drawing where:
[0024] FIG. 1 shows an aircraft equipped with a device according to
the invention;
[0025] FIG. 2 shows schematically a device according to the
invention;
[0026] FIG. 3 is an enlarged scaled cross-section according to
cross-section line III-III of FIG. 2;
[0027] FIG. 4 shows the back of the plane of FIG. 1 and the device
according to the invention in the external position
[0028] FIG. 5 shows schematically a detail of the aircraft
[0029] FIG. 6 illustrates schematically the transmissions of the
device according to the invention, and
[0030] FIGS. 7 to 12 show the plane of FIG. 1 in various stages of
flight to illustrate the operation of the device according to the
invention.
[0031] FIG. 1 represents schematically a plane 2 used for
transporting passengers or freight. In a classic form, such a plane
includes inside storage rooms or compartments for transporting the
most diverse objects: luggage, containers, etc. This invention
proposes the use of a part of these storage rooms to install an
anti-missile protective device 4 and in particular, the part of
these storage rooms located in the back of the plane. Protective
device 4 represented is as such located in a rear part of these
storage rooms.
[0032] Protective device 4 includes a cable 6 rolled around a
cylindrical base 8. Cable 6 is connected at an end to a power
supply system (not shown) and at its other end to a decoy 10.
Cylindrical base 8 is secured in the rear part of the storage rooms
and can turn around its main axis to control the winding or
unwinding of cable 6. The rotation control of the cylindrical base
8 can be electric or pneumatic for instance. The winding/unwinding
device thus obtained can be compared with a device of this type
used for fire hoses.
[0033] Cable 6 includes (FIG. 3) a central metal core 12 that
provides essentially the mechanical resistance of cable 6 as well
as the peripheral power conductors 14 that assure the link between
the decoy 10 and a control and management device inside the
aircraft as well as the electric power supply of this decoy 10.
[0034] FIGS. 4 and 5 show that the rear part of the storage rooms
includes a trap door 16 leading to the outside of the plane. When
this trap door 16 is open, decoy 10 and cable 16 can extend outside
the plane (FIG. 4). When cable 6 is fully wound on its cylindrical
base 8 and decoy 10 is inside the aircraft 2, trap door 16 can be
closed.
[0035] Decoy 10 is to be dragged by the aircraft at the end of
cable 6 as shown for instance on FIG. 4. When it is outside the
aircraft, decoy 10 issues a multidirectional infrared radiation.
This radiation is used to deceive a possible ground-air missile and
so that the missile detection system "may confuse" its target (hot
source of the engines or APU--Auxiliary Power Unit) with decoy 10.
Decoy 10 can also be called the "Illuminator". The frequency of
these transmissions is adjusted to the transmission spectrum of
plane 2. FIG. 6 illustrates schematically the radiation issued by
decoy 10.
[0036] Such a decoy 10 is known to the specialist in the field. It
is a "classic" decoy 10 that aircraft 2 is dragging. It functions
independently from the aircraft systems of aircraft 2.
[0037] Preferably, decoy 10 will have a conical form such as the
one shown on the drawing. This form is selected for its aerodynamic
properties. The purpose here is to have the weakest aerodynamic
drag possible. Needless to say, other forms inducing preferably
weaker drag can be selected here.
[0038] The length of cable 6 is sufficient so that in case of
explosion of a missile hitting decoy 10, aircraft 2 is not damaged.
On the other hand, cable 6 or more precisely the length of cable 6
unwound, must not be too long so that the missile detection system
may confuse the hot sources of the aircraft with decoy 10.
Moreover, if cable 6 is not too long, it can be extended very early
after takeoff and pulled in very late at the time of landing. The
length of cable 6 extending outside aircraft 2 can as such be
between 20 and 50 m, preferably.
[0039] FIGS. 7 to 12 show a possible operation of the protection
device according to the invention.
[0040] On FIG. 7, aircraft 2 is in the taxi stage or starts to take
off. Its wheels are still on the ground. Protective device 4 is in
the wound up position inside aircraft 2. Cable 6 is wound up on its
cylindrical base 8 and trap door 6 is closed.
[0041] During takeoff (FIG. 8), as soon as the wheels of the plane
do not touch the ground anymore, protective device 4 is activated.
Initially, trap door 16 opens fully to permit the full deployment
of the mechanism. Then, cylindrical base 8 is rotated in such as
way that cable 6 unwinds to release decoy 10 by letting it extend
from the storage room. Decoy 10 then starts to transmit in all
directions, even before cable 6 is fully unwound. The speed of
unwinding cable 6 and as such the extension outside of decoy 10 is
controlled (for instance according to the vertical speed of plane
2) so that decoy 10 never touches the ground which might damage
it.
[0042] During the climbing phase (FIG. 9), cylindrical base 8 turns
until cable 6 is fully unwound. Decoy 10 continues to transmit
radiation up to a given predetermined altitude. Once this altitude
has been reached, the infrared radiation stops and cable 6 winds
until decoy 10 has been fully retracted inside plane 10. Trap door
16 closes again and plane 2 is flying normally.
[0043] Inversely, during a descending phase (FIG. 10), protection
device 4 makes decoy 10 exit as described above in FIGS. 8 and 9
for the takeoff phase. This exit takes place automatically as soon
as a predetermined altitude is reached (which may be different from
the altitude at which decoy 10 moves back into the storage room
during a climbing phase) or when reaching a predetermined distance
separating aircraft 2 from the ground where it has to land.
[0044] During the landing phase (FIG. 11), protective device 4
starts to pull in decoy 10 that continues to transmit, as soon as a
pre-selected altitude radio signal orders it to do so. Cable 6 then
winds around its cylindrical base 8. The rewind speed of decoy 10
or the rewind speed of cable 6 is calculated by the control and
management device on the basis for instance of the vertical speed
so as to avoid any contact of decoy 10 with the ground and so as
not to damage decoy 10 this way. Other flight parameters can be
taken into account to control the retraction/extension of decoy 10
and the unwinding/winding of cable 6. The transmittal of infrared
radiation only stops when trap door 16 is closed again. During
landing, in other words, contact of the wheels with the ground
(FIG. 12), protective device 4 is fully inside the storage room of
aircraft 2.
[0045] In all its stages of flight, a display enables the pilot and
also other members of the cockpit to know whether protective device
4 is in its extended or retracted position. As such, members of the
cockpit are always informed of the position (wound or unwound) of
the protective device. In case of breakdown of the automatic
winding device, a control panel is provided to enable the pilot to
retract (extend) dragged decoy 10. In case of a complete failure, a
control of last resort triggered from the cockpit enables cable 6
to be cut, thus freeing the aircraft from the whole protective
device 4 located outside plane 2, and thus assuring a landing
without a problem.
[0046] The protective device described above offers the
considerable advantage of being able to use a considerable number
of already existing devices in the aeronautical field. First of
all, as already indicated, the decoy used can be a classic decoy.
The originality here consists of dragging it. The system that
permits this dragging can be derived by a system already known and
used for in-flight re-fueling of planes. It is also known on test
aircraft to conduct static pressure measurements using a dragged
device. The protective device thus obtained can this way be of a
relatively cheap cost price.
[0047] Moreover, the device described above is considered as
automatic, to the extent that no action of the pilots is required
to meet its proper operation. The only thing that the pilots have
to do is to check (through light indicators for instance) whether
the device is operating properly.
[0048] The device according to the invention also offers the
advantage of being able to be installed in aircraft already built
because it is independent from aircraft systems and as such does
not require any substantial modification of these systems.
[0049] Variants of the protective device described above can also
be considered. As such, decoy 10 is scheduled to transmit
multidirectional infrared radiation. An extension of operation can
be considered. This decoy 10 can also include a detection system
for instance. The latter includes for instance a Doppler effect
radar or conducts infrared and/or ultraviolet detection. Once such
a detection device is installed, decoy 10 can then be coupled to a
decoy system by pyrotechnical flares or by infrared one-directional
transmission, for instance of the DIRCM type. This extension
permits the triggering of the transmittal (flares or infrared) only
in case of detection of a ground-air missile.
[0050] Numerous variants can be considered in combination with
detection systems and various decoy systems. One can foresee a
detection system with a one-directional radiation system
complementing a multidirectional radiation system or else, one or
the other of such systems. In all cases, the device according to
the invention can be considered as being an independent system. As
such, its operation on all aircraft programs is large
simplified.
[0051] This invention is not limited to the forms of implementation
and their variants described above as non-limiting examples. It
also involves implementation variants within the reach of the
specialist in the field within the framework of the following
claims.
* * * * *