FR2841333A1 - WEAPON ARRANGED ON A FURTHER AIRCRAFT AND PROVIDED WITH A MISSILE, AND AN ARM SYSTEM COMPRISING A FURTHER AIRCRAFT AND A SUCH ARMY - Google Patents

Abstract

The system has first control units for separating the lower longitudinal part (7A) of the low radar signature tube from the top part (7B) which is connected to the external body of the aircraft (A) such that it creates in the tube, by its separation, an opening (8) allowing the complete ejection of the missile, with second control units (9) for controlling the first units, and third control units (10) controllable for movably connecting the missile when it is controlled, and fourth control units (11) for controlling the third control units. The weapon system is carried by a stealth aircraft, and has a low radar signature tube (4) which is radar absorbing, with a missile (M) located inside this tube.

Description

The present invention relates to a weapon mounted on a stealth aircraft and

  provided with at least one missile, as well as a common weapon system

  taking a stealth aircraft with such a weapon.

  Since a weapon system of this type is generally intended to perform a mission in a hostile environment, the success of such a mission often depends in large part on the ability of the weapon system to be able to escape completely or at least as long as possible to any type of detection, and in particular to detection by ra dar. Also, to increase the efficiency of such a weapon system, it is interesting to reduce its radar signature so as to make it more difficult to detect. It is apparent that the radar signature of an aircraft, in particular a combat aircraft, comprising one or more missiles is modified by

  cc (s) last (s), during the carriage of cc (s) missile (s).

  Typically, such a weapon system includes means for external delivery of the missiles to the aircraft. Such external means of transport includes a missile launcher which is fixed under the aircraft and retains the missile (s). Such a means of transport presents a significant disadvantage with regard to furtivity. Indeed, it causes the presence of many strong electromagnetic couplings between the aircraft, the missile launcher and the wings, control surfaces and fuselage of the missile, which makes it very difficult to reduce the radar signature of this assembly forming the said system.

weapon teme.

  To remedy this drawback, document FR-2 796 454 of the Applicant provides a weapon which comprises, in addition to the missile: - a stealthy tube fixed on the external structure of said aircraft and having a shape that minimizes the reflection of electromagnetic waves at least according to predefined priority directions of observation, said missile being entirely housed inside said stealth tube; controllable ejection means making it possible to eject said missile out of said stealth tube; and - controllable triggering means for effecting the triggering of propulsion means for said missile after its ejection to said stealth tube, when the aircraft is at least one second

  pre-determined distance (safety distance) to the ejected missile.

  This weapon makes it possible to reduce the radar signature of the weapon system (form of the weapon and the stealth aircraft). However, it makes it necessary, during firing of the missile, the implementation of a difficult and dangerous operation, namely the injection of the missile out of the stealth tube. In addition, this ejection operation requires particular ejection means, which increases, although moderately, the cost and size of said weapon. The present invention relates to a weapon, reduced cost, provided with at least one missile and intended to be mounted on a stealth aircraft, the said weapon can be mounted on existing aircraft and being such that the weapon system formed by said weapon and the aircraft carrying it, has a reduced radar signature during the mission phase during which Itaeronef stealth carries the weapon, and especially said weapon allowing a

firing sr and missile missile.

  For this purpose, according to the invention, said weapon mounted on a stealth aircraft and comprising: a stealth tube which is connected to the external structure of said aircraft and which has a shape making it possible to minimize the reflection of electromagnetic waves at least following predetermined directions of observation; and at least one missile which is entirely housed inside said furtive tube is remarkable in that it furthermore comprises: first controllable means for separating a longitudinal lower part from said furtive tube from a higher part; which remains connected to said external structure of said aircraft so as to create in said tube, by this separation, an opening allowing complete ejection to said missile; second means for controlling said first means; third controllable means for releasably connecting the said missile to said external structure to said aircraft, said third means releasing said missile when they are ordered; and fourth means for controlling said third means. Thus, thanks to the invention, for firing the missile, it is sufficient: to control said first means so that it creates said opening enabling the passage of the missile; and then to control said third means so that they automatically release said missile so that the latter then falls, thanks to its weight alone, through said opening of the stealth tube or is ejected (from

  usual way) towards ['before through this opening.

  Consequently, thanks to the weapon according to the invention, the missile is released (or launched) in the usual way, which makes it possible to reduce the cost and

The encumbrance of the weapon.

  In addition, since the missile is housed in a tube that exhibits furtive characteristics, specified below, it is possible to reduce the radar signature to said weapon system. In addition, the weapon complies

  The invention can be easily mounted on any type of aircraft.

  In particular, it is not necessary to design a specific aircraft to cover the present invention. In addition, the present invention is applicable to any type of missile (or bomb) fired from aero

  nave, be it an air-to-air, air-sea or air-to-ground missile.

  In a particular embodiment, said first means comprise cutting means, of mechanical and / or pyrotechnic type, for cutting the wall to said stealth tube so as to separate said

  lower part of said upper part.

  Furthermore, advantageously, the weapon according to the invention further comprises a pivotal auxiliary connection system, which is provided between said lower and upper parts of the stealth tube and which allows the complete paration of said lower part, only when, after the control of said first means, this rear has, with respect to the longitudinal axis of said stealth tube, a predetermined angle. Thus, it is possible to adapt the separation angle, in particular, to the conditions of carriage and firing of the missile under the aircraft so as to ensure separation without risk.

  only for the aircraft of said lower part of the stealth tube.

  In addition, to increase the furtivity of said weapon, advantageously, said stealth tube also surrounds said third means.

  which links the missile to the external structure of the aircraft.

  Furthermore, in a first embodiment, said weapon comprises: - fifth controllable means for releasably connecting said upper part of the stealth tube to said external structure to said aircraft, said fifth means releasing said upper part when they are orders; and

  sixth means for controlling said fifth means.

  Furthermore, in a second embodiment, said weapon further comprises: at least one airbag which is arranged in said upper part of the stealth tube and which is intended to close at least in part said opening which is formed in the stealth tube by separating said lower part; seventh controllable means for inflating said cushion; and

  - Eighth means for controlling said seventh means.

  These last two embodiments make it possible to reduce the

  of the aircraft after firing, as well as the radar signature of the weapon system. Preferably, said stealth tube has a cylindrical shape and comprises a nose-shaped cap a ['before, in the direction of flight of the aircraft, which makes it possible to minimize or even cancel the reflections of electromagnetics in the directions of observations generally considered as main or priority, namely those corresponding to

  laying down the front and the lateral parts of the tube.

  In addition, according to the invention, said stealth tube preferably has

  a circular, rhombic or lenticular cross section.

  Moreover, to increase the furtivity of the tube and thus the weapon system formed by the weapon and the aircraft, advantageously, said stealth tube is provided at least on a portion of its outer face with a coating.

  absorb electromagnetic waves.

  In addition, advantageously, said tube is made of composite material of known type, having a high mechanical strength and a reduced mass, such as an epoxy composite material or a

  base of carbon or aramid fibers (of the "Kevlar" type).

  In addition, according to the invention: when the missile is of the type having lateral air entrances, preferably, the stealth tube has a cross section having a direction of greater width, and said missile is housed in said stealth tube so that said lateral air entrances vent arranged in said direction of greater width; and when the missile is of the type comprising a main air inlet (ventral or dorsal), advantageously the stealth tube has a transverse section presenting at least one elongated direction, and said missile is housed in said stealth tube so that said main air inlet (ventral or dorsal) is arranged in said allon gee direction. The present invention also relates to a means of carrying missiles, intended to be mounted on the external structure of an aircraft, no

especially a stealth aircraft.

  According to the invention, said carrying means comprises a stealth tube

  presenting the characteristics mentioned above.

  The present invention further relates to a weapon system which includes a stealth aircraft and a weapon such as that mentioned above, which is

mounted on said stealth aircraft.

  The figures of the annexed drawing will make it clear how the invention can be realized. In these figures, identical references

design similar elements.

  Figures 1 to 3 respectively show three successive phases of the launching of a missile forming part of a weapon system.

according to the invention.

  Figures 4 and 5 schematically illustrate in longitudinal section a weapon according to the invention and mounted on an aircraft, respecti

  in two different situations.

  FIGS. 6 and 7 schematically illustrate an auxiliary linkage system, respectively corresponding to the situations of FIGS. 4 and 5. FIGS. 8 to 10 show, in cross-section, an agency missile in a missile carrying means respectively conforming to FIG.

  different embodiments of the invention.

  The weapon system 1 according to the invention and represented in particular in FIG. 1 comprises a stealth-type aircraft A, for example a stealth fighter plane, and at least one weapon 2 comprising a missile M. FIGS. represent the weapon system 1 in successive phases during a firing of the missile M. Said weapon 2 is of the type comprising, as represented in particular in FIG. 4, in addition to the missile M, a means of 3 comprising a stealth tube 4 specified below, which is an agency under aircraft A and which is connected by an end portion 5 to the structure (fuselage F) to said aircraft A. The missile M, an air missile - air, air-ground or air-sea, or a bomb (guided or not, propelled or not), is completely housed in said tube 4 so as not to be visible from the outside and so not to

  modify the radar signature of the weapon system 1.

  According to the invention, said weapon 2 further comprises: controllable means 6 diagrammatically shown in FIG. 4, for separating a lower longitudinal portion 7A from said stealth tube 4 from an upper remaining portion 7B which remains connected to said structure external F aviation A so as to create in said tube 4, by this separation, an opening 8 (Figure 5) for eject complete said missile M; means 9 (automatic or manual) shown schematically in Figures 4 and 5 for controlling said means 6; controllable means 10 for releasably connecting said set M to said external structure F to said aircraft A, said means 10 releasing said missile M when they are commanded; and - means 11 (automatic or manual) represented schematically

  4 and 5, for controlling said means 10.

  In a preferred embodiment, said means 6 comprise mechanical and / or pyrotechnic cutting means for cutting along a cutting line 12 the wall 4A to said stealth tube 4 in a manner that

  separating said lower portion 7A from said upper portion 7B.

  The weapon 2 further comprises an auxiliary linkage system 13 (FIGS. 4 to 7) which is provided at the rear of the stealth tube 4 between said lower portions 7A and 7B of the stealth tube 4 and which allows the separa o complete tion of said lower part 7A, only when, after the control of said means 6, this rear presents relative to the longitudinal axis said stealth tube 4 a predetermined angle a, as represente

in Figures 5 and 7.

  This auxiliary connection system 13 is a pivot system 14 which comprises, as represented in FIGS. 6 and 7, a ball 15 secured to the upper part 7B of the tube 4. This ball 15 is provided with a cutter 16 and cooperates with with an end 17 in an arc of a circle, which is connected to the lower part 7A of the tube 4 and which surrounds the ball 15. Thanks to the cut-out 16, it is possible to adjust the separation angle a and thus to adapt, in particular, the conditions of carriage and firing of missile M under aircraft A, so as to ensure a safe separation for aircraft A from

  said lower part 7A of the stealth tube 4.

  The means 10 comprise a usual pylon 18 to which the missile M is connected. This pylon 18 comprises means for fixing the missile M and

  2 means for unlocking this attachment.

  In addition, the stealth tube 4 also surrounds said pylon 18 by its end portion, which makes it possible to minimize the reflections of electromagnetic waves.

tromagnetic at this level.

  Thus, as thanks to the invention, the missile M and the wind pylon 18 housed in said tube 4 which has the characteristics of furtivity, specified below, it is possible to reduce the radar signature

weapon system 1.

  In addition, the weapon 2 does not require specific ejection means for ejecting the missile M out of the tube 4, the missile M being released and ejected conventionally (especially by falling with its own weight), which makes it possible to reduce the cost and the bulk of said weapon 2. The missile M can also be ejected by ['before being drawn on rail of

  as usual, the aperture 8 releasing a passage forward for this purpose.

  In addition, thanks to the ejection according to the invention, it is safe to perform a shot on and not dangerous for the aircraft A. Note that, in the context of the present invention, the installation of the tube 4 under aircraft A is identical to that of an additional fuel tank. The mechanical links of the same type and the electrical connections are assured by a small number of con nec tors. The mechanical connections and the electrical connections are carried out by the pylon 18. The interface between the tube 4 and the aircraft A is thus simplified. Wile is moreover, preferably, standardized, especially for

facilitate the manufacture.

  The tubes 4 wind longitudinally fixed to said aircraft A, under the wings B. C and / or the fuselage F of the latter. The number of weapons 2 and 4 tubes is adapted to the dimensions of the aircraft A and mission to achieve. In the embodiment shown in FIG. 1, two fixed wind turrets 4 under the wings B and C of the aircraft A and a third tube 4 is fixed in the center below the fuselage F. However, it will be noted that in the of the present invention, a stealth tube may comprise, in a particular embodiment not

  represents, more than one missile, for example two, trots ... missiles.

  Furthermore, to reduce the dimensions of the tube 4, the missile M comprises bearing surfaces l9 (wings, control surfaces) may take one of two positions: a folded position (Figure 4) and an expanded position. Said bearing surfaces 19 are in the folded position that the missile M is housed in the stealth tube 4 and they have been driven mechanically by means of co-ordinated and non-repetitive means. in the deployed position, for a part of them when the lower part 7A is separated (Figures 2 and 5) and for the rest when the missile

  M is ejected out of said upper portion 7B of the tube 4 (Figure 3).

  All integration and control operations of the weapon are carried out in the factory, using means appropriate to this type of weapon.

  teriel, which increases the reliability and safety of the weapon 2.

  Thus, the tube 4 protects the missile M at least in favor of the aircraft A,

  but usually during all phases of his operational life.

  The various steps according to the invention of firing or launching an M missile with reference to FIG. 3 are now specified. When, from the flight situation of FIG. 1, a firing order of missile M is given: the means 9 (for example a button which is actuated by a pilot of the aircraft A) controlling the means 6 which then triggers the separation of the lower part 7A of the tube 4 from its upper part 7B, As shown in FIG. 2. Thus separated, this lower part 7A drops and stechts from the aircraft A. The missile M remains linked to the aircraft by the means 10 comprising the pylon 18. The bearing surfaces 19 located under the missile M which are liberated by this separation, while they are automatically deployed; the means 11 (for example a button which is actuated by a pilot of the aircraft A) controlling the means 10 which release the missile M, the latter then falls thanks to its weight alone (or is ejected towards ['before) and 1 1 stecarte the aircraft A, as shown in Figure 3. All bearing surfaces 19 then wind deployed; and when the aircraft A is at a safe distance from the missile M, means of propulsion not represented by this latter wind are discharged. The missile M is then routinely guided to carry out its mission, for example the interception of a mobile (airplane or vehicle)

  restricted or maritime) or the destruction of a building.

  In a particular embodiment shown schematically in Figures 4 and 5, the carrying means 3 further comprises: - means 20 controllable to bind, removably, the end portion 5 (upper end of the part upper 7B) of the stealth tube 4 has said external structure F said aircraft A, said means 20 releasing said upper part 7B when they command; and means 21 (automatic or manual) for controlling said

1 means 20.

  Furthermore, in another embodiment shown diagrammatically in FIG. 8, said carrying means 3 further comprises: at least one usual airbag 22 which is arranged in said upper portion 7B of the stealth tube 4 and which is intended to close (after swelling) at least in part said opening 8 which is formed in said stealth tube 4 by the separation of said lower part 7A; conventional means 23 controllable for inflating said cushion 22; and - means 24 (automatic or manual) for controlling said

means 23.

  2 These last two embodiments make it possible to reduce the

  and the radar signature of aircraft A after the firing of missile M. It should be noted that, for weapon 2 according to the invention, the firing conditions and the security measures to be taken into account by the vehicles themselves. than those taken into account when firing a missile, carrying ex

  dull, with a common missile launcher.

  According to the invention, the stealth tube 4 has a shape that makes it possible to minimize or even cancel the reflection of electromagnetic waves at least along predetermined directions of observation. In the preferred embodiment shown in the figures, said stealth tube 4 has a cylindrical shape and comprises a cap 25 in the form of an ogive a '' before, in the direction of flight of the aircraft A, which allows to minimize the reflection in the directions of observation aiming at the

front and side of the tube 4.

  The tube 4 has at the rear a flattened shape which achieves a compromise between the requirements of furtivity and aerodynamics and which is compatible with the constraints of implantation under aircraft A. In addition, according to the invention, said tube 4: - preferably has a circular cross section (FIGS. 1 a), rhombic (FIGS. 8 3 1 O) or lenticular; - is made of a composite material simultaneously having a high mechanical tone and a reduced mass; and is provided at least on a portion of its outer face 26 (particularly on the front and side faces) of a coating not shown and absorbing electromagnetic waves, which allows to reduce further

the radar signature.

  On the other hand, in the case where the missile M has lateral air inlets 27, the tube 4 has a cross section, for example a blood section 2 as shown in FIG. 8 or lenticular, having a direction XX of greater width, and said missile M is housed in said tube 4 so that said air inlets 27 are arranged in said direction XX of greater width, which allows to adapt the dimen

  4 to those of the M missile and thus reduce them to the maximum.

  In the Gas or missile M comports a ventral air inlet 28

  or a dorsal air inlet 29, the provisions of the wind missile represent

  respectively in Figures 9 and 10. The tube 4 presented in this

  a looser section of the diamond than in Figure 8, with a

  L-L recession (orthogonal to the X-X direction) more elongated. The ventral air inlet 28 or dorsal air lentree 29 is arranged in said direction L-L.

Claims (17)

  1. A weapon mounted on a stealth aircraft (A) and comprising: - a stealth tube (4) which is connected to the external structure of said aircraft (A) and which has a shape that minimizes the reflection of electromagnetic waves at least following pre-determined observation directions; and at least one missile (M) which is entirely housed inside said stealth tube (4), characterized in that it further comprises: o first controllable means (6) for separating a lower part longitudinally (7A) to said stealth tube (4) of an upper part (7B) which remains connected to said external structure to said aircraft (A) in order to create in said tube (4), by this separation, an opening (8); ) allowing complete discharge to said missile (M); Second means (9) for controlling said first means (6); third controllable means (10) for linking, in an amiable manner, said missile (M) to said external structure to said aircraft (A), said third means (10) releasing said missile (M) when they are winding o commands ; and - the fourth means (1 1) for controlling said thirds means (10).   2. Weapon according to claim 1, characterized in that said first means (6) comprise cutting means, for cutting the wall (4A) to said stealth tube (4) so as to separate said lower part (7A) from said upper part (7B). 1 5   3. Weapon according to one of claims 1 and 2,   characterized in that it further comprises an auxiliary linkage system (13) with a pivot (14), which is provided between said lower (7A) and upper (7B) parts of the stealth tube (4) and which allows the separation complete of said lower part (7A), only when, after the control of said first means (6), this rear presents, with respect to the axis   longitudinal to said stealth tube (4), an angle (a) predetermined.   4. A weapon according to any one of claims 1 to 3,   characterized in that said stealth tube (4) surrounds said thirds 0 means (10).   Weapon according to one of Claims 1 to 4,   characterized in that it further comprises: - fifth means (20) controllable for removably connecting said upper part (7B) of the stealth tube (4) to said external structure to said aircraft (A), said fifth means (20) releasing said upper portion (7B) when ordered; and sixth means (21) for controlling said fifth means (20).   6. A weapon according to any one of claims 1 to 4,   characterized in that it further comprises: - at least one airbag (22) which is arranged in said upper part (7B) of the stealth tube (4) and which is intended to close at least part of said opening (8) which is formed in said stealth tube (4) by separating said lower portion (7A); seventh means (23) controllable for inflating said cushion (22), and - eighth means (24) for controlling said seventh means (23).   7. A weapon according to any one of the preceding claims,   characterized in that said stealth tube (4) has a cylindrical shape and has an ogive-shaped coffer (25) in front of it, in the sense of flight of the aircraft (A).   8. A weapon according to any one of the preceding claims,   characterized in that said stealth tube (4) is provided with at least a portion of its outer surface (26) with a coating that absorbs electromagnetic waves.   Weapon according to one of Claims 1 to 8,   characterized in that said missile (M) is provided with lateral air inlets (27), in that said stealth tube (4) has a cross section having a direction (XX) of greater width, and that said set (M) is housed in said stealth tube (4) so that said lateral air entrances (27) are arranged in said direction (XX) of greater width.   10. A weapon according to any one of claims 1 to 8,   characterized in that said missile (M) is provided with a main air inlet (28, 29), in that said stealth tube (4) has a trans-versal section having at least one elongate direction (LL), and in that said missile (M) is housed in said stealth tube (4) so that said input   the main air (28, 29) is arranged in the said extended direction (LL).   11. Means for carrying a missile, intended to be mounted on the outer structure of a stealth aircraft (A) and comprising a stealth tube (4) having a shape that minimizes the reflection of electromagnetic waves at least according to predetermined directions of observation, characterized in that it furthermore comprises: first controllable means (6) for separating a longitudinal lower part (7A) from said stealth tube (4) from a higher part (7B) so as to create in said tube (4), by this separation, an opening (8) for the complete discharge of a missile (M) which is housed in said carrier means (3); and second means (9) for controlling said first means (6). 12. Means of carriage according to claim 11, characterized in that said first means (6) comprise cutting means, for cutting the wall (4A) to said stealth tube (4) in a manner 3   separating said lower portion (7A) from said upper portion (7B).   13. Means of carriage according to one of claims 1 1 and 12,   characterized in that it further comprises an auxiliary linkage system (13) having a pivot (14), which is provided between said lower portions (7A) and the perimeter (7B) of the stealth tube (4) and which allows the complete separation of said lower part (7A), when, after the control of said first means (6), the latter has, in relation to the longitudinal axis   stealth tube (4), an angle (a) predetermined.   14. Means of carriage according to any one of claims 1 1   a 13, characterized in that it further comprises: - fifth means (20) controllable to link, as amovi ble, said upper part of the stealth tube (4) to the structure external to said aircraft (A); and sixth means (21) for controlling said fifth means (20).   15. Means of carriage according to any one of claims 11   a 13, characterized in that it further comprises: - at least one airbag (22) which is arranged in said upper part (7B) of the stealth tube (4) and which is intended to close at least part of said opening (8) formed in said stealth tube (4) by separating said lower portion (7A); seventh means (23) for inflating said cushion (22); and - eighth means (24) for controlling said seventh means (23).   16. Means of carriage according to any one of claims 11   a 15, characterized in that said stealth tube (4) has a cylindrical shape and comprises a nose-shaped coffer (25) in front of, in the direction of flight 0 of the aircraft (A).   17. Means of carriage according to any one of claims 11   a 16, characterized in that said stealth tube (4) is provided at least on a portion of its outer face (26) of a coating absorb electromagnetic waves. 1 8. Weapon system, characterized in that it comprises a stealth aircraft (A) and at least one   weapon (2) as specified in any of the claims