EP1093561B1 - Passive fail-safe device for mobile craft such as a helicopter - Google Patents

Description

The present invention relates to a device for passive self-protection for mobile equipment such as a helicopter.

A constant concern in the field of techniques of armament is to best protect the machines such as ships, land vehicles, planes and helicopters against "hostile" such as rockets with terminal correction of trajectory or missiles.

It is well known to use decoy launchers for this purpose to draw cartridges containing, depending on the type of hostile, infrared lures or many electromagnetic lures. Lures drawn deflect the hostile from its target, thus avoiding the partial or total destruction of it.

It is said that the decoy launchers are passive self-protection devices because they do not do not allow to destroy the hostile.

Document DE 28 09 497 discloses a device in accordance with the preamble of claim 1 appended hereto, allowing to draw several lures in directions possibly different to increase the effectiveness of the decoy. We then implement sequences of decoy.

, In the case of mobile gear whose speed is far below that of the hostile, the adequacy from these decoy sequences to different situations possible is of a critical nature.

The present invention aims to provide means to optimize the decoy sequences for such devices, with the aim of improving their protection.

This object of the invention is achieved with a device for passive self-protection for mobile equipment such as a helicopter, including at least one mounted decoy orientable on said machine, slaved to a detector hostile and a central navigation, remarkable in what he understands means to develop a library of dynamic decoy from information provided by said detector and by said central, in order to define decoy sequences in which orientation and chronometry shots said decoy launchers are optimized.

Thanks to these characteristics, we can define optimized decoy sequences according to the nature the hostile and relative movements of the mobile machine and the hostile.

• la figure 1 est une vue de face du châssis d'un lance-leurres du dispositif selon l'invention monté sur un cardan motorisé, ce châssis étant représenté en position « zéro »;
• la figure 2 est une vue partielle de côté de l'ensemble représenté à la figure 1, le châssis du lance-leurres étant représenté dans trois positions: position de roulis minimal (trait mixte), position zéro (trait plein), et position de roulis maximal (trait discontinu);
• la figure 3 est une vue de dessus de l'ensemble représenté aux figures 1 et 2, le châssis du lance-leurres étant représenté dans trois positions: position de lacet minimal (trait mixte), position zéro (trait plein), et position de lacet maximal (trait discontinu);
• - la figure 4 est une vue de côté d'un hélicoptère équipé de deux lance-leurres du dispositif selon l'invention (un seul d'entre eux étant visible sur cette figure);
• la figure 5 est une vue de face de l'hélicoptère de la figure 4;
• la figure 6 est une vue de dessus de l'hélicoptère de la figure 4;
• la figure 7 est un organigramme décrivant le fonctionnement du dispositif selon l'invention;
• la figure 8 illustre une séquence de leurrage.

Other features of the device according to the invention are defined in the appended claims, and will become clear from reading the following description and examining the accompanying drawings given solely by way of example, in which:

• Figure 1 is a front view of the chassis of a decoy launching device according to the invention mounted on a motorized universal joint, this frame being shown in the "zero"position;
• FIG. 2 is a partial side view of the assembly represented in FIG. 1, the frame of the decoy lance being represented in three positions: minimum roll position (mixed line), zero position (solid line), and position of maximum roll (discontinuous line);
• FIG. 3 is a view from above of the assembly represented in FIGS. 1 and 2, the frame of the decoy lance being represented in three positions: minimum yaw position (mixed line), zero position (solid line), and position of maximum yaw (broken line);
• - Figure 4 is a side view of a helicopter equipped with two decoy launchers of the device according to the invention (only one of them being visible in this figure);
• Figure 5 is a front view of the helicopter of Figure 4;
• Figure 6 is a top view of the helicopter of Figure 4;
• Figure 7 is a flowchart describing the operation of the device according to the invention;
• Figure 8 illustrates a decoy sequence.

In these figures, numerical references identical represent organs or sets identical or similar organs.

Note that the following has been chosen from describe the invention when incorporated into a helicopter because it is a fact that she is particularly suitable for this type of mobile machine. it said, this choice is in no way restrictive, and it is necessary keep in mind that the invention could also be advantageously incorporated in other machines such as ships or land vehicles, or even to planes.

In what follows, the terms "high" and "low" are understood in relation to the vertical, represented on where appropriate by an axis ZZ ', Z being situated downwards and Z 'upwards.

Referring now to Figures 1 to 3, where represented the chassis 1 of a lure of the device according to the invention mounted on a motorized cardan.

This chassis has substantially the shape of a box parallelepipedic open on one of its faces. is intended to receive a charger (not shown) including cartridges of electromagnetic decoys or infrared.

In the case of a helicopter, we will use preferably special payload cartridges adapted, which also reduces the efforts of reaction at the moment of firing.

The bottom of the frame 1, opposed to its opening, has electrical components (amplifiers power, etc., not shown) allowing the fire lure cartridges. These electric organs are connected inside the helicopter by connecting members (not shown).

The frame 1 is rotatably mounted about an axis horizontal 3 on a plate 4, itself rotatably mounted around a vertical axis 5 on a support 6. The support 6 is attached to an appropriate part 7 of the helicopter.

A first electric motor 8, of the "couple" type or "step-by-step", fixed on the plate 4, is intended for rotate the frame 1 about its axis 3.

A second electric motor 9, similar to the engine 8, is fixed on the support 6 and is intended to make rotate around the vertical axis 5 the assembly formed by the plate 4, the chassis 1 and the motor 8.

Figure 2 shows three possible positions of frame 1, the plate 4 being in its "zero" position, that is to say at a median position between his two extreme positions.

The position of the chassis 1 which is represented in continuous line is its zero position.

The position of the chassis 1 which is represented in mixed line is an extreme position down, so-called still minimal roll position.

The position of the chassis 1 which is represented in discontinuous line is an extreme position upwards, said still maximum roll position, symmetrical to the minimum roll position relative to the position zero.

Typically, in the case of a helicopter, the minimum and maximum roll positions are inclined each of an angle α of about 60 ° with respect to the zero position.

Figure 3 shows three possible positions of the chassis 1 corresponding to three possible positions of tray 4.

The position of the chassis 1 which is represented in continuous line is its zero position.

The position of the chassis 1 which is represented in mixed line is an extreme position in the sense of clockwise rotation, also called minimum yaw position.

The position of the chassis 1 which is represented in discontinuous feature is an extreme position in the sense of anti-clockwise rotation, also called yaw position maximum, symmetrical of the minimum yaw position relative to the zero position.

Typically, in the case of a helicopter, the minimum and maximum lace positions are inclined an angle β of about 75 ° with respect to the position zero.

Referring now to FIGS. 4 to 6, where represented a helicopter 10 equipped with two decoy launchers LL, LL 'of the device according to the invention.

Each of these two decoy launchers is mounted on a motorized gimbal as the one just described. However, for the sake of simplification, we have represented each lure-gimbal set by a simple rectangle.

Both decoy launchers are preferably placed symmetrically with respect to the line of faith 13 of the helicopter, at a sufficient distance from the entrances air 14 of the apparatus. They can be fixed on any sufficiently rigid part of the apparatus, such as landing gear supports, as this is represent.

Figures 5 and 6 show the deflections decoy launchers in roll and yaw, corresponding respectively in Figures 2 and 3 described above.

The extreme angles of α roll and yaw ß represented are preferably respectively approximately 60 ° and 75 °. In this case, the decoy launchers then have each a maximum travel of about 120 ° in roll and 150 ° in yaw, which allows a priori to draw lures in almost all directions from space.

On the one hand, it should be noted that the maximum deflections of decoy launchers are likely to vary from one helicopter to another, and secondly that for a given helicopter, authorized fire directions may vary according to a number of settings.

For example, when a helicopter is flying in training, firing decoys towards the aircraft neighbors are forbidden.

In another example, the firing of decoys electromagnetic forward of a helicopter that advance are also prohibited, in order to prevent any penetration of metallic flakes in the entrances air.

According to yet another example, the shots in the mobile wing of a helicopter are prohibited when uses infrared decoys.

As can be understood now, the management shots of the lure launchers of the device according to the invention can quickly prove to be very complex, and in any case impossible to optimize manually.

This is why the invention provides also a system to optimize the sequences of decoy.

Referring now to Figure 7, where. we have represented a flowchart describing this system.

The chassis of each decoy launchers are schematized in this figure by elements bearing the references 1 and 1 ', and the two engines of each of the gimbals on which are mounted these frames are schematized by elements bearing the references 8, 9 and 8 ', 9'.

• un détecteur d'hostile D,
• une centrale de navigation CN,
• une bibliothèque de leurrage statique B,
• un poste de commande PC,
• des. codeurs de position C8, C9 et C8', C9' des moteurs 8, 9 et 8', 9',
• les châssis des lance-leurres 1 et 1'.

As can be seen, the optimization system includes a CT shooting calculator interfaced with:

• a hostile detector D,
• an NC navigation center,
• a library of static decoy B,
• a PC control station,
• of. position encoders C8, C9 and C8 ', C9' of the motors 8, 9 and 8 ', 9',
• the chassis of the decoy launchers 1 and 1 '.

The hostile detector D, which can be a radar, identify a hostile through a plurality antennas A1, A2, A3, A4 located on the outskirts of the helicopter.

Ideally, we can choose a detector D of the type Doppler effect, to obtain information on the cinematic of the hostile.

The detector D is also of a type allowing to identify the category of the hostile. Such a detector, available in the previous hierarchy, must at least to differentiate a hostile to guiding electromagnetic hostile to infrared guidance.

Ideally, the detector D can also, allow to identify with more precision. other characteristics of the hostile.

The information sent by the central CN navigation to the CT shot calculator concern basically attitudes (Euler angles) of the helicopter, its speed and the position of its center gravity.

By bringing together the information provided by the hostile detector D from those provided by the central CN navigation system, the CT Shooting Calculator can determine the exact position of the hostile in the reference system of the helicopter, or even in a absolute reference.

Static Decoy Library B Contains different subroutines that can be used by the CT shot calculator to control decoy sequences. This library is static in this meaning that the different subroutines are Predefined.

Information sent by the order item PC to the CT shooting calculator essentially depend on instructions imposed manually by the pilot and concerning shooting conditions: activation / deactivation of the optimization system, firing prohibitions depending on the circumstances (theft in training for example), etc.

The information sent by the coders of position C8, C9 and C8 ', C9' to the shot computer CT him make it possible to know at every moment the orientation chassis 1 and 1 '. These position encoders can be, for example, optical sensors or potentiometric.

When a threat arises, the system optimization of decoy sequences works from the following way.

Once the detector D has identified the category of the hostile, the CT shot calculator questions the library B to find the subroutine suitable for this category and then it calculates in real time the orientation and chronometry of the launcher shots taking into account the information provided by the hostile detector D and by the central CN navigation.

The CT Shooting Calculator thus produces a dynamic decoy library from the Static Library B and information provided by the hostile detector D and by the central navigation CN, to define a decoy sequence the efficiency is optimized according to the nature of the said hostile and relative movements of the helicopter and hostile.

Thanks to the position encoders of the decoy lance motors, the CT shot calculator knows about every moment their orientations. Comparing these with calculated directions to reach, the calculator determines the movement orders to send to the motors decoy launchers.

The CT shot calculator also checks that the direction of fire to be reached is compatible with instructions imposed by the pilot, provided by the post PC control.

If the firing direction to be reached is prohibited by these instructions, we can advantageously consider that the CT shot calculator determines a new firing orientation that approaches the firing direction ideal.

Once the decoy launcher is oriented suitably and that the instant of fire is reached, the CT shooting calculator sends him a firing order.

FIG. 8 shows an example of decoy sequence, in the case of a helicopter in flight stationary and a hostile infrared guidance arriving to starboard of the helicopter.

As can be seen in this figure, the hostile initially follows a trajectory towards the helicopter turbines 10.

The LL decoy launcher located on the starboard side of the aircraft draws three lures L1, L2, L3 directed more and more forward of the helicopter so as to deflect gradually the initial trajectory 20 of the hostile towards avoidance trajectories 21, 22, 23.

By doing so, we gradually separate the signatures infrared lures from that of the helicopter, and prevents the hostile from reaching his target.

To fix ideas, the time interval separating each lure shot in this example can be from the order of half a second.

The deception sequence described above would not be more suitable if the helicopter moved forward, because then the infrared signature of the helicopter could join the infrared signatures of the lures drawn in latest.

In this case, the dynamic library means above would then make it possible to modify the decoy sequence according to the movements of the helicopter so, for example, to deflect the trajectory of the hostile towards the rear of the aircraft.

In another example, if the helicopter was a half-turn on itself, the library means the dynamics described above would make it possible to switch directly from the starboard decoy launchers to the decoy launchers port, or vice versa, so as to ensure continuity of deception vis-à-vis the hostile.

To increase the safety of the device according to the invention, it is also possible to provide a mode of degraded operation when the optimization system described above breaks down or when it is damaged, for example during a fight.

In this degraded mode of operation, both launchers are set to their zero position by electrical or mechanical means (not shown), and firing orders are sent manually by the pilot via the PC control station.

It is now understood that the present invention allows to define decoy sequences in which orientation and chronometry firing decoy launchers are optimized according to the nature of the hostile and relative movements of this hostile and the helicopter.

Of course, the invention is not limited to the mode embodiment described and shown that was not provided as an example. For example, it is could consider placing more than two decoy launchers on the mobile gear.

Claims (8)

1. Passive autoprotection device for mobile craft such as a helicopter (10), comprising at least one decoy launcher (LL, LL') mounted orientably on the said craft, steered by a foe detector (D) and by a navigation unit (CN), characterized in that it comprises means for formulating a dynamic decoying library from the information provided by the said detector and by the said unit, so as to define decoying sequences in which the orientation and the chronometry of the firing of the said decoy launcher are optimized.
2. Passive autoprotection device according to claim 1, characterized in that the said means for formulating a dynamic decoying library comprise a firing computer interfaced with the said foe detector (D), with the said navigation unit (CN) and with a static decoying library comprising predefined subprograms corresponding to the various types of foes.
3. Device according to either of claims 1 and 2, characterized in that the said dynamic decoying library is suitable for controlling decoying sequences allowing progressive separation of the signatures of the decoys from that of the said mobile craft, in such a way as to divert the initial trajectory of the said foe toward avoidance trajectories.
4. Passive autoprotection device according to any one of claims 1 to 3, characterized in that it comprises means for implementing a degraded mode of operation, making it possible to place the said decoy launcher (LL, LL') at its zero position and to send it firing orders when the steering thereof is inoperative.
5. Passive autoprotection device according to any one of the preceding claims, characterized in that it comprises means for interdicting certain directions of fire.
6. Passive autoprotection device according to any one of the preceding claims, characterized in that the said decoy launcher (LL, LL') is linked to the said mobile craft (10) by a motorized cardan joint, allowing yaw and roll orientation of the said decoy launcher.
7. Passive autoprotection device according to claim 6, the said mobile craft (10) being a helicopter, characterized in that it comprises two decoy launchers (LL, LL') disposed symmetrically with respect to the lubber line (13) of the said helicopter.
8. Passive autoprotection device according to claim 7, characterized in that each of the said decoy launchers has a sweep of around 150° in yaw and 120° in roll about its zero position.

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