EP0628780B1 - Aiming system for aircraft - Google Patents

Description

The present invention relates to an aiming system for a aircraft, in particular a rotary wing aircraft, such as a helicopter.

• d'une fonction d'observation et de détection omnidirectionnelle pour la recherche d'objectifs et la conduite de la mission ;
• d'une fonction de tir, d'une part, rapide, dans un large champ de débattement, pour la désignation d'objectif et le tir réflexe des armements d'autoprotection et, d'autre part, précise, dans un champ réduit de quelques dizaines de degrés, centré autour de l'axe longitudinal de l'aéronef, pour la mise en oeuvre des armements à longue portée.

Analyzes of missions and armaments for aircraft, notably for helicopters, have jointly revealed the need:

• an omnidirectional observation and detection function for finding objectives and conducting the mission;
• a firing function, on the one hand, rapid, in a wide range of travel, for the designation of objective and the reflex shooting of the armaments of self-protection and, on the other hand, precise, in a reduced field of a few tens of degrees, centered around the longitudinal axis of the aircraft, for the implementation of long-range armaments.

We know, from patent EP-0 167 432, an airborne system detection, location and tracking of a target, comprising an adjustable optical head placed under a dome with the exterior of the aircraft fuselage. The mounting of means detection and telemetry optics is an assembly of the gimbal type, comprising two perpendicular frames, one at the other.

Furthermore, the optical sighting system for aircraft, described in patent EP-0 127 914, is mounted in a nacelle comprising a first part fixed to the aircraft, a second part which can be oriented relative to said first part around a first axis, and a third part orientable with respect to said second part around a axis orthogonal to the first axis mentioned.

In addition, patent FR-2 570 195 relates to a device for search for targets, comprising a camera mounted on a tilting stabilization platform, on board of an aircraft. In particular, the movement of the platform stabilization can be a triangular movement, sinusoidal, sawtooth, or spiral.

In each of these cases, it appears as well as the system of sight is mounted, externally to the aircraft, on a platform or the like, stabilized, the description and hardware architecture analysis have highlighted integration difficulties, because such equipment electromechanical are heavy, bulky and complex and difficult to adapt to carriers and different armaments.

The object of the present invention is to avoid these drawbacks, and concerns a sighting system easily integrated into its carrier (aircraft) and can be easily adapted to different carriers, missions and armaments.

To this end, the aiming system for an aircraft, in particular a rotary wing aircraft, such as a helicopter, is remarkable, according to the invention, in that it comprises the combination of a first individual observation device, laterally integrated into the aircraft, and a second individual axial firing device, integrated in front of the aircraft, said first and second devices being connected to the on-board computer of the aircraft.

Thus, unlike the combined devices mounted on mobile supports (mast, platform, nacelle) for art previous, the combination of observation devices and separate sight according to the invention constitutes an architecture original due to the specific fixed location of said devices integrated into the aircraft.

The architecture of the sighting system according to the invention, thanks its modular nature, makes it possible to satisfy the whole existing and projected operational needs, while responding to the many constraints of achieving these functions on an aircraft, in particular a wing aircraft rotating, such as a helicopter. The modular nature of this architecture allows, in particular, to quickly configure the carrier aircraft for a specific mission and a armament given, by the installation of detectors and appropriate guidance equipment, and reduce equipment integration and harmonization constraints on the carrier aircraft.

• une composante assurant les fonctions de veille omnidirectionnelle, d'observation et de pointage ("dispositif d'observation") :
  • capable de détecter des cibles aériennes et terrestres de façon automatique ;
  • offrant des capacités d'observation, par télépointage, d'un champ réduit et avec un grossissement déterminé, pour la validation des détections et la reconnaissance des cibles ;
  • permettant la prise en charge, pour la conduite de tir dans l'axe ("dispositif de tir axial"), de cibles éloignées et fortement dépointées, après ralliement de l'axe de l'aéronef ;
• une composante de tir dans l'axe, performante du point de vue de la qualité de la visionique et de la précision de pointage et d'harmonisation des voies optiques des différents capteurs, mais peu complexe du fait de l'absence de besoin d'orientation et de stabilisation de leurs supports (le terme "capteur", tel qu'utilisé ici, s'applique à un dispositif optoélectronique de détection).

Aiming functions are therefore divided into two main components:

• a component ensuring the functions of omnidirectional watch, observation and pointing ("observation device"):
  • able to detect aerial and ground targets automatically;
  • offering observation capabilities, by telepointing, of a reduced field and with a determined magnification, for validation of detections and recognition of targets;
  • allowing the handling, for the firing control in the axis ("axial firing device"), of distant and highly depointed targets, after rallying of the axis of the aircraft;
• an axis shooting component, efficient from the point of view of the quality of vision and pointing accuracy and harmonization of the optical paths of the different sensors, but not very complex due to the lack of need for orientation and stabilization of their supports (the term "sensor", as used here, applies to an optoelectronic detection device).

Advantageously, the first observation device includes two sensors integrated directly on the fuselage of the aircraft on either side of the axis, respectively longitudinal of the latter, and covering, each, approximately 180 ° in deposit and 20 ° to 40 ° on site. This allows to cover a sweep range in 360 ° bearing.

In particular, each sensor, having a plurality of elementary detectors, may include a first optic scanning comprising a scanning prism in bearing, making it possible to obtain a reservoir sweeping layer, and a tilting prism of said sheet making it possible to perform site scanning.

In addition, each sensor can include a second optic, allowing the exploration of part of the total field, which includes a sweeping mirror in bearing, rotating at reduced speed, and a retractable lens.

Furthermore, the second axial firing device can be, either integrated into the nose of the aircraft, or integrated into the aircraft above its cockpit.

Advantageously, the second axial firing device comprises a thermal camera with two simultaneous fields, namely a large field for the acquisition of objectives and a small field for long-range identification and engagement of a specific target.

Preferably, the first observation device and the second axial firing device working in the strip of 8 to 12 micrometers (infrared range).

Furthermore, the first observation device can work further in the 3 to 5 micrometer band, and / or in the band from 0.45 to 0.9 micrometer, as well as being associated with a speed camera.

According to other features of the invention, the system aiming device comprises means for memorizing targets detected by the first observation device and / or alarms associated with the first observation device, active for fire control.

Advantageously, sensors working in the field infrared or visible allow the piloting of the aircraft in fire control mode.

Preferably, different color symbologies are used according to the results of the identification procedure friend / enemy.

Furthermore, the observation device may have a visualization by visual helmet visor, and the device axial fire, head-up display or visualization in average head. Only shooting symbologies are possibly represented on a clear viewfinder at the head high.

The figures in the accompanying drawing will make it clear how the invention can be realized.

Figure 1 is a schematic perspective view of a helicopter, showing the location of the sighting system according to the invention.

Figure 2 shows, in a simplified and schematic way, the optical chain of a sensor of the observation device.

Figure 3 shows the two simultaneous images provided by the two-field thermal camera of the shooting device axial.

Helicopter 1, shown in Figure 1, has essentially, as is usual, a fuselage 2 extending along the longitudinal axis X-X of the helicopter, a post steering 3, a rotary wing 4, and a fin 5 fitted with an anti-torque propeller 6. Furthermore, it has two fins 7 (only one is visible in Figure 1) intended to receive armaments (missiles, rockets), a barrel which can be possibly accommodated in the nose 8 of the device.

The aiming system according to the invention comprises the combination a first individual observation device 9, laterally integrated into the aircraft (in this application example, helicopter 1), and a second individual device axial fire 10, integrated in the front of the aircraft, the first and second devices 9,10 being connected to the computer on board 11 of the aircraft.

More specifically, the observation device 9 comprises two optoelectronic sensors 12a, 12b, directly integrated on the fuselage 2 of the helicopter 1 on both sides, respectively, from the latter's longitudinal axis X-X, that is to say, each on a side 2a, 2b of the helicopter, and covering, each, about 180 ° in bearing and 20 ° to 40 ° on site, as illustrated by the volumes observation 13a, 13b in Figure 1. A cover 360 ° observation angle can thus be obtained. Furthermore, as seen in Figure 1, each sensor 12a, 12b has an optical window with three windows planes 14a, 14b. It should also be noted that the field covered by the axial firing device 10, which can be either integrated in the nose 8 of the helicopter 1, either integrated into the helicopter 1 above cockpit 3 of this last, is designated by the reference numeral 15.

Figure 2 illustrates the optical chain of each of the sensors 12a, 12b. Each of the sensors 12a, 12b comprising a matrix 16 of elementary detectors 17, the conjugate of the array of detectors is moved in object space by a first scanning optic comprising a prism 18 of field sweep, capable of performing an excursion of 180 °, and thus obtain a sweeping sheet 19 in deposit, while a sheet tilting prism 20 allows for site scanning, the assembly performing a superposition of horizontal layers 19, covering 180 ° in deposit and from 20 ° to 40 ° on site.

For a given position of these two prisms 18 and 20 (deposit and site), a second lens allows exploration part of the total field (approximately 1 ° x 1 ° among 180 ° x 40 °). This second optic includes a mirror scanning in deposit 21 which, rotating at reduced speed, in an alternating movement, in a limited part of the total field, receives more photons, which allows get better contrast (better resolution). The fitting a retractable lens (magnifying glass) 22 ensures moreover a better definition of the image. In addition to the field scan in a reduced field, we could also provide for a site scan in this same field, for the same purpose.

• une fonction de veille panoramique automatique,
• une fonction d'observation dans un champ réduit, orientable par pointage télécommandé.

The observation device 9 must perform two main functions:

• an automatic panoramic standby function,
• an observation function in a reduced field, adjustable by remote control pointing.

For the first function, as it is to detect passively from air and ground targets, the band the best suited spectral should be the band from 8 to 12 micrometers (infrared range). Its complement by the band from 3 to 5 micrometers can be considered.

The second function can be performed by a mode of sub-scanning of the total field of the first function, thanks to the second optic 21,22 described above. The gain of range compared to the first function is obtained thanks to increasing the integration time of elementary detectors (up to complete scanning stop) and, possibly, by the interposition of the lens focusing 22 specific to this mode. The value of the field required is of the order of the degree. In this mode of use, the spectral band of 8 to 12 micrometers offers the operator the advantages and disadvantages of thermal imaging. The usefulness of supplementing it with an intensifying image of light in the visible range (0.45 to 0.9 micrometer) can be considered. The interest of the latter is to offer the operator a visible type image and being able to continue to work in conditions of disappearance of thermal contrasts encountered during heavy precipitation and in strong wind, as well as in inversion conditions of temperature. However, it is then necessary to implant a second sensor and a second optical channel, in the absence of transparent materials at 8-12 micrometers and at 0.45-0.9 micrometer.

The first standby function can be supplemented by a active electromagnetic sensor with the advantages suitable for radar detection (range, capacity all time, Doppler effect detection). However, this device active is not effective for target detection land, apart from helicopters, and present the disadvantage of lack of discretion inherent in the principle radar detection.

The third function of this observation device 9 can also be the pointing and the implementation of armaments. It requires angular measurements and distance. The angular measurements are obtained by copying position of scanning optics. Distance measurements are obtained by stadimetry, triangulation or telemetry.

The axial firing device 10 consists of a certain number of elements whose choice depends on the configuration mission and armament of the helicopter. These are mounted directly on the structure of helicopter 1. They are harmonized with each other and with the structure by a integrated system or ground harmonization bench.

• une image de grand champ 23 (typiquement 40° x 30° et grossissement x1) non orientable, dans l'axe de l'hélicoptère, pour l'acquisition des objectifs 24,25 directement ou par désignation du dispositif d'observation 9 [des symbologies différentes (marqueurs) sont utilisées pour les objectifs aériens 24 et terrestres 25] ;
• une image de petit champ à fort grossissement 26 (typiquement 1° et x10) orientable et incrustée à l'intérieur du grand champ, pour l'identification et l'engagement à longue portée d'une cible déterminée 27.

The main sensor of this axial shooting device is a thermal camera 10 with two simultaneous fields, making it possible to obtain, in timeshare and with a single detection module, two images (FIG. 3):

• a wide field image 23 (typically 40 ° x 30 ° and magnification x1) not orientable, in the axis of the helicopter, for the acquisition of the objectives 24,25 directly or by designation of the observation device 9 [des different symbologies (markers) are used for aerial objectives 24 and terrestrial objectives 25];
• an image of a small field at high magnification 26 (typically 1 ° and x10) orientable and inlaid inside the large field, for the identification and long-range engagement of a determined target 27.

An automatic multi-target pursuit operating indifferently on each of the two images is possible and necessary the overall effectiveness of the proposed sighting system.

The axial firing device 10 has all the functions an air-to-air optoelectronic firing line and air-ground.

• directement, ce qui nécessite la présence d'un champ large, de l'ordre de celui du pilotage (typiquement 40° x 30°) et de grossissement x1, pour assurer la continuité avec la vision extérieure directe ;
• à partir d'une désignation d'objectif du dispositif d'observation 9, grâce à une symbologie appropriée apparaissant dans l'axe de l'hélicoptère et préconisant un mode de ralliement de ce dernier.

On the one hand, the acquisition of the objectives in the axis of the helicopter must be able to be carried out:

• directly, which requires the presence of a wide field, of the order of piloting (typically 40 ° x 30 °) and magnification x1, to ensure continuity with direct external vision;
• from an objective designation of the observation device 9, thanks to an appropriate symbology appearing in the axis of the helicopter and recommending a mode of rallying of the latter.

On the other hand, after acquisition, long-term identification distance must be possible without losing the essential of the great field. This operation requires the presence of a reduced field with high magnification (typically 1 °, x10) and orientable in the main field (typically 40 ° x 30 °).

The simultaneous acquisition of these two images can be obtained by known means (as described, for example, in the document "Multiple Function Flir - A Second Generation Pilotage and Targeting System ": Symposium AGARD-CP411, "Advances in Guidance and Control Systems and Technology ", 7-10 October 1986, London), using a single detection module using time-sharing each of two optical channels. At the visualization level, the image magnified in small field could be presented, either in inlay in the large field, at the place of detection, either in "Head Down Display" screen.

This principle allows a certain multi-target capacity, by rapid sequential processing of detected objectives. The essential function of this device being the shooting, the tape 8 to 12 micrometers seems the most appropriate. In the extent that the large field image is compatible with a control function, the use of a 0.45-0.9 sensor micrometer could be considered to complete it.

The implementation of armaments is carried out from the large field image or the small field overlay, after telemetry and hooking up of automatic tracking and thanks to specific armaments guidance equipment.

The grouping of different equipment for the conduct of shooting in the axis, in a "niche" arranged for this purpose in the structure of the helicopter is advantageous. Indeed, their proximity makes it possible to envisage harmonization operations sighting axes, of the same type as those taken currently between the different optical paths of a gyro-stabilized platform.

The location, on the structure, of these different pieces of equipment can be considered at the current locations of gyro-stabilized platforms (nose, roof).

The reductions in mass and size resulting from this new architecture also allow to consider the mounting the sensors in locations favoring reduction of environmental constraints (vibration and mainly aerodynamic), previously impossible for gyro-stabilized platforms.

The first observation device 9 performs part of the functions traditionally assigned to the skipper, in its role of leading the mission and researching targets. It also allows short reflex engagement range of highly devoid targets, for self-protection or opportunity shooting.

• une tâche de veille omnidirectionnelle automatique, air-air et air-sol, permettant un balayage systématique de l'espace pour la détection des cibles ;
• une tâche d'observation dans un champ réduit, orientable par télépointage, similaire à celle généralement effectuée par le chef de bord pour la recherche d'objectifs. Cette dernière permet en outre la validation, à un niveau défini de reconnaissance et d'identification, des détections effectuées automatiquement par la veille omnidirectionnelle.

The observation function actually combines two types of tasks:

• an automatic omnidirectional air-to-air and air-to-ground watch task, allowing systematic scanning of the space for target detection;
• an observation task in a small field, orientable by telepointing, similar to that generally carried out by the skipper for finding objectives. The latter also allows validation, at a defined level of recognition and identification, of the detections carried out automatically by the omnidirectional watch.

Furthermore, the acquisition requires the completion of angular and distance measurements, for the designation of missile seeker objectives and conduct in the axis.

However, the acquisition phase must be able to be concluded, under certain conditions, by firing certain armaments (gun mounted on turret, air-to-air missiles) in engagement with short range, without necessarily using the phase to join the helicopter and take charge of objectives by the conduct of fire in the axis.

This short-range engagement involves the identification of short-range targets, possibly using a magnification or friend / foe identification procedure (IFF). In general, this function will hardly be used insofar as the engagement will be made at distances short enough to allow identification visual. For the cannon fire control, it is by elsewhere necessary to develop the pointing command and control of the turret, while a function Air-to-air missile rigging is also required. The helicopter rallying, possibly by a mode specific autopilot, can also be asked for the implementation, at short range, of armaments axial orientable in site (guns, rocket launchers).

The second axial firing device 10 constitutes a pipe of multi-armament fire, available to the pilot and the skipper, capable of implementing, thanks to his high accuracy and range performance, all helicopter armaments, in their entire area shooting.

Compared to conventional sights, reducing constraints is possible thanks to the limitation to frontal sector of the angular cover. This limitation, largely offset by omni-directional capabilities of the first observation device 9, does not alter overall system efficiency, especially as the most of the engagements requiring the precision of this fire control, will be carried out in the axis or will tolerate the target acquisition time in the axis, after rallying from the helicopter.

As already indicated, this principle makes it possible to mount the different elements of the fire control (infrared detectors, camera, rangefinders, equipment for guiding armaments, among others) directly on the structure of the helicopter and not, for example, on a platform gyro-stabilized. This architecture gives the system a modular character for quick configuration the helicopter for a specific mission and armament given, by installation of detectors and equipment appropriate guidance, and reduce integration constraints and harmonization of equipment on the helicopter.

Direct target acquisition is possible by driving in the axis. It can be done by the pilot, as is the case with the "head-up" viewfinder ("Head Up Display") or clear sight, for self-protection shots at short range with air-to-air missile or cannon. On the other hand, the care and commitment of the targets to long range (air-air and air-ground) are performed, as this is usual, by the skipper (gunner).

The assumption, by the firing line in the axis, of targets detected by the first observation device 9 requires a lens designation function between the observation device 9 and the axial firing device 10, via the on-board computer 11. The acquisition is then done in the same way as for a detection direct, after rallying the helicopter in the direction of the detected target.

At long distance, the performance of the observation device 9 may not always be sufficient for identification. Under these conditions, the rallying of the helicopter and handling by the firing device axial 10 (firing line in the axis) will remove the ambiguity up to the maximum system identification range in his outfit.

In addition, the telemetry function intervenes just before the implementation of the armament. She may be obtained in several ways: stadimetry, triangulation, telemetry.

The fire control function concerns the implementation armaments. It must be compatible with the largest possible number of armaments and offer all possibilities of modes and commands linked to their use (continuation automatic, manual remote control). In particular, he must be possible to integrate specific guidance equipment of these weapons (distance meters, laser illuminator, alignment laser beam generator). The performance required for the implementation of long-range armaments makes it necessary to have a harmonization function.

The choice of visualizations follows naturally from the analysis of the observation device 9 and of the axial firing device 10.

The functions of the observation device make it suitable for helmet visor control and visualization (head-up display), fast and not very demanding in range and pointing accuracy. The treatment of detections in automatic mode could, in this configuration, generate a symbology of the order director type (up / down, right / left, site / deposit) for acquisition manual and observation on such a viewfinder, by rallying from the operator's head or by rallying the helicopter, for taking charge of the fire control in the axis.

The functions of the axial firing device can be entirely produced in the band from 8 to 12 micrometers by a camera with two simultaneous fields. Visualization suitable for this function can be considered head up. In this configuration, the use of a clear viewfinder is not possible in the current state of technology, insofar as the intensity of the infrared image delivered by the monitor may not be sufficient to be superimposed, in good conditions, in all cases of light atmospheres encountered.

• elle contraint l'opérateur à quitter des yeux l'environnement extérieur, ce qui rend délicate la tâche simultanée de pilotage ;
• dans l'état actuel de la technologie, elle nécessite l'utilisation d'un moniteur spécifique ayant une résolution suffisante que n'atteignent pas encore les écrans à multiples fonctions.

In addition, the display of this sensor with the head down faces two drawbacks:

• it forces the operator to take his eyes off the outside environment, which makes the simultaneous piloting task difficult;
• in the current state of technology, it requires the use of a specific monitor with sufficient resolution that multi-function screens do not yet reach.

Consequently, a suitable solution seems to be a sight "average head". This is, by an instructor through a magnifying optics, to present to the pilot and / or to the chief on board, an infrared optoelectronic image of the world outside, in line with the helicopter. This visualization is located in the cockpit in the middle position and, unlike a clear viewfinder, does not allow you to see the direct image of the outside world.

Detection of targets from the observation system or the axial firing device, generate symbologies superimposed on the optoelectronic image of the outside world (markers, identification interrogator results friend / enemy, telemetry) allowing the operator to engage in sequence and in order of priority. For that, he move a cursor on its "medium head" screen, select if necessary, the opening of the magnification window, inside which automatic tracking can be engaged and the shot made, by hooking the seeker air-to-air or air-to-ground missiles, support for guidance by passive distance meters, laser beams directors or illuminators, implementation of firing (cannon or rockets).

A simplified version of the axis firing device can also be considered, which does not present an image optoelectronics in the axis. Only shooting symbologies are then presented on a clear "head-up" viewfinder. In this case the infrared image of the outside world exists but it is not displayed. It is only operated by automatic detection and tracking computers which generate the associated symbologies, directly superimposed on the transmitted image of the outside world. In in particular, the embedded zoom function cannot be carried out. On the other hand, the image with a small orientable field can be presented and operated on a "head down" screen in infrared or visible, depending on the sensors used.

In addition, the targets detected by the first device can be stored for analysis later, for example in the on-board computer 11 of the aircraft. In addition, alarms can be associated with the first observation device, active with a view to fire control, while color symbologies different may be used depending on the results of the friend / foe identification procedure (IFF).

Claims (19)

1. A sighting system for an aircraft, in particular a rotary wing aircraft such as a helicopter,
   characterized in that it comprises in combination observation first individual apparatus (9) integrated in the sides of the aircraft (1) and axial fire second individual apparatus (10) integrated at the front of the aircraft (1), said first and second apparatuses (9, 10) being connected to the onboard computer (11) of the aircraft (1).
2. A sighting system according to claim 1, characterized in that the first observation apparatus (9) comprises two sensors (12a, 12b) integrated directly on the fuselage (2) of the aircraft (1) on respective opposite sides of its longitudinal axis (X-X), each covering about 180° in relative bearing and 20° to 40° in elevation.
3. A sighting system according to claim 2, characterized in that each sensor (12a, 12b) has a plurality of elementary detectors (17), and includes first optical scanning means comprising a bearing scanning prism (18) enabling a bearing scan sheet (19) to be obtained, and a prism (20) for tilting said sheet (19) enabling elevation scanning to be performed.
4. A sighting system according to claim 3, characterized in that each sensor (12a, 12b) includes a second optical system enabling a fraction of the total field to be scanned, which second optical system comprises a bearing scanning mirror (21) rotating at low speed and a retractable lens (22).
5. A sighting system according to any one of claims 1 to 4, characterized in that the axial fire second apparatus (10) is integrated in the nose (8) of the aircraft (1).
6. A sighting system according to any one of claims 1 to 4, characterized in that the axial fire second apparatus (10) is integrated in the aircraft (1) above its cockpit (3).
7. A sighting system according to claim 5 or claim 6, characterized in that the axial fire second apparatus comprises a thermal camera (10) having two simultaneous fields, namely a large field (23) for acquiring targets (24, 25), and a small field (26) for identifying and engaging a determined target (27) at long range.
8. A sighting system according to any one of claims 1 to 7, characterized in that the observation first apparatus (9) and the axial fire second apparatus (10) operate in the 8 micrometer to 12 micrometer band.
9. A sighting system according to claim 8, characterized in that the observation first apparatus (9) also operates in the 3 micrometer to 5 micrometer band.
10. A sighting system according to claim 8 or claim 9, characterized in that the observation first apparatus (9) also operates in the 0.45 micrometers to 0.9 micrometer band.
11. A sighting system according to any one of claims 8 to 10, characterized in that the observation first apparatus (9) is associated with a radar.
12. A sighting system according to any one of claims 1 to 11, characterized in that it includes means for memorizing targets detected by the observation first apparatus (9).
13. A sighting system according to any one of claims 1 to 12, characterized in that it includes alarms associated with the observation first apparatus (9) and active for fire control purposes.
14. A sighting system according to any one of claims 1 to 13, characterized in that sensors operating in the infrared or in the visible spectrum enable the aircraft to be piloted in fire control mode.
15. A sighting system according to any one of claims 1 to 14, characterized in that different color symbology is used as a function of the results of the identification friend or foe procedure.
16. A sighting system according to any one of claims 1 to 15, characterized in that the observation apparatus (9) presents a display by means of a helmet-mounted sight.
17. A sighting system according to any one of claims 1 to 16, characterized in that the axial fire apparatus (10) presents a head-up display.
18. A sighting system according to claim 17, characterized in that the fire symbology is displayed on its own on a head-up brilliant sight.
19. A sighting system according to any one of claims 1 to 16, characterized in that the axial fire apparatus (10) has a "head halfway" display.

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