EP4113052A1 - Seeker device for missile - Google Patents

Abstract

Seeking device (3) for a missile, comprising a module (14) for activating/deactivating the active assembly (6), configured to manage the activation/deactivation of the active assembly (6) during three phases: during a first phase, to deactivate the active set (6); during a second phase, to alternately activate and deactivate the active assembly (6); and during a third phase, called tracking, to activate the active assembly (6), the third phase succeeding the second phase.

Description

The invention relates to missiles equipped with active seekers, that is to say having the ability to transmit and receive a signal. The mission of the seekers can be anti-aircraft or anti-ship, and the present invention requires that the target have an active radar carried.

The purpose of a seeker integrated into a missile is to allow the missile 1 to guide itself on its target 2 in order to be able to intercept it, as illustrated in [ Fig. 1 ].

During a first phase of the mission, called inertial guidance, the missile 1 is based on the information delivered by a fire control radar, placed on the ground or on a nearby aircraft.

Then, during a second phase, called homing, missile 1 uses the information delivered by seeker 3, which is integrated into the front of missile 1, as shown in [ Fig.2 ].

The transition between these two phases takes place when the information delivered by the seeker 3 is sufficiently precise to be used for guidance, called terminal guidance, from a range, called range or homing distance, as illustrated in there [ Fig. 1 ].

During the first phase, the missile 1 relies on the information from the fire control radar (ground radar 4 and/or radar carried 5 on the firing plane of the missile 1). This radar emits a wave and, by receiving the latter's reflection on the target 2, can estimate the information concerning the target 2, i.e. distance, speed and angular direction.

This information will be transmitted to the missile 1, via a data link or at the time of firing, and constitute the target designation, denoted DO. The latter will be delivered with more or less good precision, depending on the quality of the fire control radar (range of uncertainty of the DO). This target designation can be refreshed during the flight. The target designation includes parameters representative of the range of target 2 from missile 1, the relative velocity of target 2 relative to missile 1, and the angular direction of target 2 relative to the direction of travel. of missile 1.

It is possible that the fire control radar is jammed which implies that the missile can be fired without a DO target designation or with a degraded DO target designation, i.e. without information on the distance and/or the speed of the target.

It is also known to have an elaborate DO target designation from passive sensors (electro-optical or electronic warfare GE), which only has information about the angular direction of target 2.

During the second phase, the missile is guided using information from the homing device.

The operation of a seeker device 3 comprises three phases, as follows.

A first so-called standby phase, during which the homing device 3 is deactivated, and therefore does not emit a signal.

A second phase, called search, during which the homing device 3 is activated and scans the area of the target designation (distance/relative speed/angular direction of the target, or the targets, 2 to be detected. At the end of the second phase, it selects target 2 to pursue.

A third phase, called pursuit, during which the missile 1 pursues the target 2 until impact, using the information provided by the activated homing device 3.

Also, missile 1 is fired without distance information from target 2, the seeker is activated as soon as possible and remains so until impact, which leads to a long operating time which may be greater than that for which it is dimensioned, implying a risk of its deactivation when approaching target 2.

Furthermore, this may also have the consequence of increasing the time taken by the seeker 3 to scan the target designation DO, which depends on the magnitude of the uncertainties of the domain of the target designation DO. Also, the duration of this scanning or research phase can potentially be dimensioning.

The consequence is that the seeker 3 must be activated for a long time, which poses problems of energy consumption, the cell or battery of the missile 1 being limited.

This also poses problems of thermal energy management, which is a major issue for seekers 3, because they must emit high-power signals in a restricted volume and without contact with the outside (cooling by conduction) , which imposes a limited operating time for the seekers 3 to avoid overheating or even breakage.

An object of the invention is to overcome the problems cited above, and in particular to make it possible to improve the duration of use of a seeker, by limiting its consumption.

• un ensemble actif comprenant au moins un capteur actif configuré pour émettre et recevoir des signaux pour détecter une cible à radar actif porté dans un domaine de désignation d'objectif correspondant à des intervalles de valeurs de distance de la cible par rapport au dispositif, de vitesse de la cible par rapport au dispositif, et de direction angulaire de la cible par rapport à la direction de déplacement du dispositif ;
• un ensemble passif comprenant au moins un capteur passif configuré pour recevoir des signaux de détection de la cible ;
• un module d'émission/réception de signaux à hautes fréquences ;
• un module de transposition d'un signal haute fréquence en signal basse fréquence ;
• un module de conversion analogique/numérique et de conversion numérique/analogique ; et
• un calculateur comprenant :
• un module de traitement de données associées à l'ensemble actif ;
• un module de traitement de données associées à l'ensemble passif ;
• un module d'activation/désactivation de l'ensemble actif, configuré pour gérer l'activation/désactivation de l'ensemble actif durant trois phases:
• durant une première phase dite de veille, pour désactiver l'ensemble actif, la première phase étant comprise entre le tir du missile et une première distance de la cible valant une distance d'autoguidage du missile augmentée d'une valeur maximale de distance d'incertitude, ou entre le tir du missile et la fin des autotests du dispositif autodirecteur;
• durant une deuxième phase, dite de recherche, pour alternativement activer et désactiver l'ensemble actif, la deuxième phase succédant à la première phase, et se terminant lorsque la puissance du signal reçu par l'ensemble actif lorsqu'il est activé est supérieur à un seuil de puissance détection de la cible ; et
• durant une troisième phase, dite de poursuite, pour activer l'ensemble actif, la troisième phase succédant à la deuxième phase.

le module d'activation/désactivation de l'ensemble actif étant configuré pour, durant la deuxième phase, alternativement activer et désactiver l'ensemble actif, de sorte que la durée d'une activation de l'ensemble actif respecte la relation suivante : $$\mathit{Da}=\frac{\mathit{Dra}\times \mathit{OAIa}}{\mathit{DPAp}}$$

dans laquelle :

• Da représente la durée d'une activation, en s ;
• Dra représente la durée nécessaire pour émettre des signaux par de le dispositif autodirecteur (3), typiquement une salve d'impulsions et recevoir les signaux réfléchis par une cible, en s ;
• OAIa représente l'ouverture angulaire instantanée de l'ensemble actif (6), en sr ; et
• PAp représente le domaine de précision ou d'incertitude angulaire de l'ensemble passif (7), en sr.

It is proposed, according to one aspect of the invention, a homing device for a missile, comprising:

• an active assembly comprising at least one active sensor configured to transmit and receive signals for detecting an active radar target carried in a target designation domain corresponding to intervals of values of distance of the target relative to the device, speed of the target relative to the device, and of angular direction of the target relative to the direction of movement of the device;
• a passive assembly including at least one passive sensor configured to receive target detection signals;
• a module for transmitting/receiving high-frequency signals;
• a module for transposing a high frequency signal into a low frequency signal;
• an analog/digital conversion and digital/analog conversion module; and
• a calculator comprising:
• a module for processing data associated with the active set;
• a module for processing data associated with the passive assembly;
• an active set activation/deactivation module, configured to manage the active set activation/deactivation during three phases:
• during a first so-called standby phase, to deactivate the active assembly, the first phase being between the firing of the missile and a first distance from the target equaling a homing distance of the missile increased by a maximum distance value of uncertainty, or between the firing of the missile and the end of the device self-tests seeker;
• during a second phase, called a search phase, to alternately activate and deactivate the active assembly, the second phase succeeding the first phase, and ending when the power of the signal received by the active assembly when it is activated is greater than a target detection power threshold; and
• during a third phase, called tracking, to activate the active set, the third phase succeeding the second phase.

the module for activating/deactivating the active set being configured to, during the second phase, alternately activate and deactivate the active set, so that the duration of an activation of the active set respects the following relationship: $$\mathit{Da}=\frac{\mathit{Dra}\times \mathit{OAIa}}{\mathit{DPAP}}$$

in which :

• Da represents the duration of an activation, in s;
• Dra represents the time required to emit signals from the homing device (3), typically a burst of pulses, and to receive the signals reflected by a target, in s;
• OAIa represents the instantaneous angular aperture of the active assembly (6), in sr; and
• PAp represents the range of precision or angular uncertainty of the passive assembly (7), in sr.

Such a system makes it possible to improve the duration of use of a seeker, by limiting its consumption, and to guarantee the full performance of the missile, including when the DO is degraded. In addition, even if the DO is nominal, the use of the passive assembly makes it possible to reduce the operating time of the active part, this being likely to reduce the warning to the target defense system (electronic system of the detector type and jammer, defensive manoeuvre, etc. if equipped.

The implementation of such a duration of activation of the active assembly during the second search phase makes it possible to ensure the detection of the target, while limiting the consumption of the seeker device

dans laquelle :

• Ds représente la durée séparant deux activations successives de l'ensemble actif, en s ;
• PDa représente la portée de détection de l'ensemble actif, en m ; et
• VR représente la vitesse relative du missile par rapport à la cible, en m/s.

According to one embodiment, the module for activating/deactivating the active set is configured to, during the second phase, alternately activate and deactivate the active set, so that the time separating two successive activations of the active set respects the following relationship: $$\mathit{ds}=\frac{\mathit{pda}\times \mathit{AD}}{\mathit{VR}}$$

in which :

• Ds represents the duration separating two successive activations of the active set, in s;
• Pda represents the detection range of the active set, in m; and
• VR represents the relative speed of the missile in relation to the target, in m/s.

The implementation of such a period separating two successive activations of the active assembly during the second search phase makes it possible to reduce the electrical energy consumption of the seeker while ensuring that the performance of the seeker is not reduced, in particular by terms of detection range (ensuring the implementation of the active set when detecting the target).

In one embodiment, the computer is configured to, during the third tracking phase, when the power of the signal received by the active assembly is greater than an autoguiding threshold, transmit guidance information to a control unit of the missile, for terminal guidance on target.

Thus, the missile has information on the direction, speed and acceleration of the target which are refreshed at a very high rate (of the order of ten ms).

According to one embodiment, the active assembly comprises at least one transmitter/receiver RF antenna.

Thus, this active RF device will make it possible to estimate the direction, speed and acceleration of the target

In one embodiment, the passive assembly includes at least one receiver RF antenna and/or one electro-optical sensor.

Thus, this passive set will make it possible to estimate the direction of the target.

According to one embodiment, the passive assembly is arranged around the periphery of the seeker device.

Thus, which makes it possible not to impact the performance of the active set, the passive set not being positioned on the same volume as the active device

According to another aspect of the invention, there is also proposed a seeker device according to one of the preceding claims.

• [Fig. 1] illustre schématiquement un mode de réalisation d'un dispositif autodirecteur pour missile, selon l'état de la technique ;
• [Fig.2] illustre schématiquement un mode de réalisation d'un dispositif autodirecteur pour missile, selon l'état de la technique ;
• [Fig.3] illustre schématiquement un mode de réalisation d'un dispositif autodirecteur pour missile, selon l'état de la technique ;
• [Fig.4] illustre schématiquement un mode de réalisation d'un dispositif autodirecteur pour missile, selon un aspect de l'invention ;
• [Fig.5] illustre schématiquement deux dispositions possibles de l'ensemble passif du dispositif autodirecteur ;
• [Fig.6] illustre schématiquement un exemple de trajectoires d'un missile équipé d'un dispositif autodirecteur et de sa cible, selon un aspect de l'invention ;
• [Fig.7] illustre schématiquement le fonctionnement de l'ensemble passif d'un dispositif autodirecteur pour missile, selon un aspect de l'invention ;
• [Fig.8] illustre schématiquement le domaine angulaire de l'ensemble passif d'un dispositif autodirecteur pour missile, selon un aspect de l'invention ;
• [Fig.9] illustre schématiquement le domaine angulaire de l'ensemble actif d'un dispositif autodirecteur pour missile, selon un aspect de l'invention ;
• [Fig.10] illustre schématiquement le fonctionnement de l'ensemble actif d'un dispositif autodirecteur pour missile, selon un aspect de l'invention ;
• [Fig.11] illustre schématiquement le fonctionnement d'un dispositif autodirecteur pour missile durant la transition entre une première phase de veille et une deuxième phase de recherche, selon un aspect de l'invention ; et
• [Fig.12] illustre schématiquement le fonctionnement d'un dispositif autodirecteur pour missile durant la transition entre une deuxième phase de recherche et une troisième phase de poursuite, selon un aspect de l'invention.

The invention will be better understood on studying a few embodiments described by way of non-limiting examples and illustrated by the appended drawing in which:

• [ Fig. 1 ] schematically illustrates an embodiment of a homing device for a missile, according to the state of the art;
• [ Fig.2 ] schematically illustrates an embodiment of a homing device for a missile, according to the state of the art;
• [ Fig.3 ] schematically illustrates an embodiment of a homing device for a missile, according to the state of the art;
• [ Fig.4 ] schematically illustrates an embodiment of a homing device for a missile, according to one aspect of the invention;
• [ Fig.5 ] schematically illustrates two possible arrangements of the passive assembly of the seeker device;
• [ Fig.6 ] schematically illustrates an example of trajectories of a missile equipped with a homing device and its target, according to one aspect of the invention;
• [ Fig.7 ] schematically illustrates the operation of the passive assembly of a homing device for a missile, according to one aspect of the invention;
• [ Fig.8 ] schematically illustrates the angular range of the passive assembly of a homing device for a missile, according to one aspect of the invention;
• [ Fig.9 ] schematically illustrates the angular range of the active assembly of a homing device for a missile, according to one aspect of the invention;
• [ Fig.10 ] schematically illustrates the operation of the active assembly of a homing device for a missile, according to one aspect of the invention;
• [ Fig.11 ] schematically illustrates the operation of a homing device for a missile during the transition between a first standby phase and a second search phase, according to one aspect of the invention; and
• [ Fig.12 ] schematically illustrates the operation of a homing device for a missile during the transition between a second search phase and a third tracking phase, according to one aspect of the invention.

In all of the figures, the elements having identical references are similar.

There [ Fig.4 ] schematically illustrates an embodiment of a seeker device 3 for missile 1, according to one aspect of the invention. The seeker device 3 comprises an active assembly 6 comprising at least one active sensor 6a configured to transmit and receive signals to detect a target 2, with active radar carried, in a target designation domain DO corresponding to intervals of values of distance of target 2 from homing device 3, speed of target 2 from device 3, and angular direction of target 2 from the direction of movement of device 3.

The seeker device 3 also comprises a passive assembly 7 comprising at least one passive sensor 7a configured to receive detection signals from the target 2, and a transmission/reception module 8 of high-frequency signals.

The seeker device 3 is also provided with a module 9 for transposition of a high frequency signal into a low frequency signal, and with a module 10 for analog/digital conversion and digital/analog conversion.

• un module 12 de traitement de données associées à l'ensemble actif 6 ;
• un module 13 de traitement de données associées à l'ensemble passif 7 ;
• un module 14 d'activation/désactivation de l'ensemble actif 6, configuré pour gérer l'activation/désactivation de l'ensemble actif 6 durant trois phases:
• durant une première phase dite de veille, pour désactiver l'ensemble actif 6, la première phase étant comprise entre le tir du missile 1 et une première distance de la cible 2 valant une distance d'autoguidage du missile 1 augmentée d'une valeur maximale de distance d'incertitude, ou entre le tir du missile et la fin des autotests du dispositif autodirecteur 3 ;
• durant une deuxième phase, dite de recherche, pour alternativement activer et désactiver l'ensemble actif 6, la deuxième phase succédant à la première phase, et se terminant lorsque la puissance du signal reçu par l'ensemble actif 6 lorsqu'il est activé est supérieur à un seuil de puissance de détection de la cible 2 ; et
• durant une troisième phase, dite de poursuite, pour activer l'ensemble actif 6, la troisième phase succédant à la deuxième phase.

The seeker device 3 further comprises a computer 11 comprising:

• a module 12 for processing data associated with the active set 6;
• a module 13 for processing data associated with the passive assembly 7;
• a module 14 for activating/deactivating the active set 6, configured to manage the activation/deactivation of the active set 6 during three phases:
• during a first so-called standby phase, to deactivate the active assembly 6, the first phase being between the firing of the missile 1 and a first distance from the target 2 equaling an autoguiding distance of the missile 1 increased by a maximum value of uncertainty distance, or between the firing of the missile and the end of the self-tests of the seeker device 3;
• during a second phase, called research, to alternately activate and deactivate the active set 6, the second phase succeeding the first phase, and ending when the power of the signal received by the active set 6 when it is activated is greater than a target detection power threshold 2; and
• during a third phase, called tracking, to activate the active assembly 6, the third phase succeeding the second phase.

To ensure angular tracking, the homing device 3 measures the elevation and bearing deviations of the target 2, among others, which it delivers to the missile 1. The uncertainty distance associated with these deviation measurements is defined by a standard deviation.

The autoguiding distance (or autoguiding range) corresponds to the distance between the missile 1 and the target 2 from which this standard deviation is less than a threshold. This threshold is defined by the missile manufacturer, to ensure, from this distance, the capacity of the missile 1 to reach the target 2 and which depends on its time constant and on the relative speed of the missile/target.

The missile self-tests correspond to the electronic operations aimed at ensuring that the functions of the missile are operational ("Built In Test" in English).

The homing device 3 comprises conventional elements 15 such as a waveform generation device, power supplies, a pointing management device for the active assembly.

There [ Fig.5 ] represents the passive assembly 7, comprising at least one passive sensor 7a, arranged either in the plane of the active assembly 6, or around the periphery of the envelope of the seeker device 6.

When the passive assembly 7 is arranged on the periphery of the casing of the seeker device 3, it is possible not to impact the operation of the active assembly 6.

However, when they are positioned around the body of the AD, the coverage of the antennas is not optimal in the missile axis.

Thus, depending on the mission (large detection distance, low target SER), it is possible that trajectory formation (a maneuver, for example aimed at pointing the missile axis in another direction) is necessary in order to increase the coverage of the active set 6 in the direction of target 2.

As shown in the [ Fig.6 ], this trajectory formation consists in maintaining the direction of the speed vector of the missile 1 such that the target 2 is in the coverage of the active set 6.

• la manœuvrabilité du missile 1, qui est configuré pour avoir la capacité de modifier sa trajectoire lorsque la cible 2 est détectée ; et
• la couverture de l'ensemble passif.

The angle between the direction of the speed vector of missile 1 and the direction of target 2 depends on:

• the maneuverability of missile 1, which is configured to have the ability to modify its trajectory when target 2 is detected; and
• coverage of the passive set.

There [ Fig.7 ] illustrates the operation of the passive assembly which makes it possible to estimate the angular direction of target 2, from the reception of the wave emitted by the active radar carried by target 2.

When the angular direction of the target designation DO is imprecise, the first phase, standby, can make it possible to refine and reduce the range of uncertainty of this angular direction of the target designation DO, the passive sensors 7a of the passive assembly 7 which can have an angular precision greater than that of the angular direction of the objective designation DO. The passive sensors 7a deliver information on the angular direction of the target 2 associated with an angular precision domain.

As shown in the [ Fig.8 ], the passive set 7 (grey rectangle) will give a domain where the target 2 is located that is more precise than that which was provided by the fire control device (white rectangle). This reduced area can be traveled from faster (or more efficient) way by the antenna of the homing device 3.

As shown in the [ Fig.9 ], depending on the quality of the passive sensors 7a of the passive assembly 7, it is possible that this range of angular precision is less than or equal to the instantaneous angular aperture of the active assembly 6, which avoids sweeping angularly .

In addition, the passive assembly 7 may have processing enabling it to estimate the distance of the target 2 (pseudo-distance) with greater or lesser precision (depending on the quality of the passive sensors 7a). This distance can be estimated when the power level received from target 2 is greater than a defined threshold.

There [ Fig.10 ] illustrates the operation of the active assembly 6 which makes it possible to estimate the distance, the relative speed and the angular direction of the target 2. The active assembly 6 is configured to scan the angular domain and thus cover an area of the space greater than its instantaneous angular aperture which is the aperture it would have in the absence of scanning means.

The emission of signals by the active assembly 6 causes thermal heating of the active assembly 6, and therefore of the seeker device 3, which has no cooling source. The use of the active set 6 is therefore limited.

The use of the three phases as described in the present invention makes it possible to best use the combination of the active assembly 6 and the passive assembly 7.

During the first phase, called standby, the computer 11 deactivates the active assembly 6, the first standby phase being between the firing of the missile 1 and a first distance D from the target equaling an autoguiding distance Dautoguiding of the missile increased of a maximum uncertainty distance value Dmax, or between the firing of missile 1 and the end of the self-tests of seeker device 3.

In the event of possible estimation of the first distance D, the autoguiding device 3 has a domain of uncertainty of the distance from the target 2, in which the real distance from the target 2 is found. research phase, is done when the distance separating the missile 1 from the target 2 becomes less than the first distance D.

There [ Fig.11 ] schematically illustrates the operation of the homing device 3 during the transition between the first standby phase and the second search phase, according to one aspect of the invention.

During the second phase, called the search phase, the computer 11 alternately activates and deactivates the active assembly 6, the second phase succeeding the first phase, and ending when the power of the signal received by the active assembly 6, when it is activated, is greater than a target detection power threshold.

dans laquelle :

• Da représente la durée d'une activation, en s ;
• Dra représente la durée nécessaire pour émettre des signaux par de le dispositif autodirecteur (3) et recevoir les signaux réfléchis par une cible, en s ;
• OAIa représente l'ouverture angulaire instantanée de l'ensemble actif (6), en sr ; et
• DPAp représente le domaine de précision ou d'incertitude angulaire de l'ensemble passif (7), en sr.

The module 14 for activating/deactivating the active set 6 is configured to, during the second search phase, alternately activate and deactivate the active set 6, so that the duration Da of an activation of the active set 6 respects the following relationship: $$\mathit{Da}=\frac{\mathit{Dra}\times \mathit{OAIa}}{\mathit{DPAP}}$$

in which :

• Da represents the duration of an activation, in s;
• Dra represents the time required to emit signals from the homing device (3) and to receive the signals reflected by a target, in s;
• OAIa represents the instantaneous angular aperture of the active assembly (6), in sr; and
• DPAp represents the range of precision or angular uncertainty of the passive assembly (7), in sr.

The duration Da of an activation of the active assembly 6, also called recurrence, is defined as the period during which the seeker 3 emits an impulse and receives the signal coming from the target 2 to analyze it and estimate the characteristics (distance, speed, angular direction).

dans laquelle :

• Ds représente la durée séparant deux activations successives de l'ensemble actif, en s ;
• PDa représente la portée de détection de l'ensemble actif, en m ; et
• VR représente la vitesse relative du missile par rapport à la cible, en m/s.

the active set activation/deactivation module is configured to, during the second phase, alternately activate and deactivate the active set, so that the duration Ds separating two successive activations of the active set respects the following relationship: $$\mathit{ds}=\frac{\mathit{pda}\times \mathit{AD}}{\mathit{VR}}$$

in which :

• Ds represents the duration separating two successive activations of the active set, in s;
• Pda represents the detection range of the active set, in m; and
• VR represents the relative speed of the missile in relation to the target, in m/s.

• la puissance du signal reçu par l'ensemble actif 6 est inférieur au seuil de détection : l'autodirecteur on désactive à nouveau l'ensemble actif 6, et seul l'ensemble passif fournit des informations.
• la puissance du signal reçu par l'ensemble actif 6 est supérieur au seuil de puissance de détection de la cible 2 : l'autodirecteur termine la mission uniquement en activant l'ensemble actif 6 et passe en troisième phase dite de poursuite sur la cible 2 qu'il a détecté.

At the end of the second active set 6 activation search phase, there are two possibilities:

• the power of the signal received by the active assembly 6 is below the detection threshold: the seeker deactivates the active assembly 6 again, and only the passive assembly provides information.
• the power of the signal received by the active assembly 6 is greater than the detection power threshold of the target 2: the seeker ends the mission only by activating the active assembly 6 and passes to the third phase called tracking on the target 2 that he detected.

The computer 11 is configured to, during the third so-called tracking phase, when the power of the signal received by the active assembly 6 is greater than an autoguiding threshold, transmit guidance information to a control unit of the missile 1, for terminal guidance on target 1.

The active assembly 6 comprises at least one transmitter/receiver RF antenna, and/or comprises at least one receiver RF antenna and/or one electro-optical sensor.

During the third and final tracking phase, only the active set 6 is activated. The smooth running of this last phase of the mission requires information on the distance and speed of target 2. When the quality of the information delivered by the seeker 3 is sufficiently precise, it is used by the missile 1 for terminal guidance on the target 2.

In conclusion, this makes it possible to ensure full missile performance (in terms of range in particular) when the DO target designation is degraded and the mission can be long (distance to the large target) by consuming as much energy as when the mission is nominal (DO target designation in known range).

Claims (7)

Seeker device (3) for missile (1), comprising: - an active assembly (6) comprising at least one active sensor (6a) configured to transmit and receive signals for detecting an active radar target (2) carried in a target designation domain corresponding to intervals of distance values of the target (2) relative to the device (3), speed of the target (2) relative to the device (3), and angular direction of the target (2) relative to the direction of movement of the device ( 3); - a passive assembly (7) comprising at least one passive sensor (7a) configured to receive detection signals from the target (2); - a module (8) for transmitting/receiving high-frequency signals; - a module (9) for transposing a high frequency signal into a low frequency signal; - an analog/digital conversion and digital/analog conversion module (10); and - a computer (11) comprising: - a module (12) for processing data associated with the active set; - a module (13) for processing data associated with the passive assembly; - a module (14) for activating/deactivating the active set (6), configured to manage the activation/deactivation of the active set (6) during three phases: - during a first so-called standby phase, to deactivate the active assembly (6), the first phase being between the firing of the missile (1) and a first distance from the target (2) equal to an autoguiding distance of the missile (1) increased by a maximum value of uncertainty distance, or between the firing of the missile (1) and the end of the self-tests of the homing device (3); - during a second phase, called research, to alternately activate and deactivate the active set (6), the second phase succeeding the first phase, and ending when the power of the signal received by the active assembly (6) when it is activated is greater than a detection power threshold of the target (2); and - During a third phase, called continuation, to activate the active assembly (6), the third phase succeeding the second phase. the module (14) for activating/deactivating the active set (6) being configured to, during the second phase, alternately activate and deactivate the active set (6), so that the duration (Da) of a activation of the active set (6) respects the following relationship: $$\mathit{Da}=\frac{\mathit{Dra}\times \mathit{OAIa}}{\mathit{DPAP}}$$

in which : Da represents the duration of an activation, in s; Dra represents the time required to emit signals from the homing device (3) and to receive the signals reflected by a target, in s; GAIa represents the instantaneous angular aperture of the active assembly (6), in sr; and DPap represents the domain of precision or angular uncertainty of the passive assembly (7), in sr. Device according to claim 1, in which the module (14) for activating/deactivating the active set (6) is configured to, during the second phase, alternately activate and deactivate the active set (6), so that the duration (Ds) separating two successive activations of the active set (6) respects the following relationship: $$\mathit{ds}=\frac{\mathit{pda}\times \mathit{AD}}{\mathit{VR}}$$

in which : Ds represents the duration separating two successive activations of the active assembly (6), in s; Pda represents the detection range of the active assembly (6), in m; and VR represents the relative speed of the missile (1) in relation to the target (2), in m/s. Device according to one of the preceding claims, in which the computer (11) is configured so that, during the third tracking phase, when the power of the signal received by the active assembly (6) is greater than an autoguiding threshold , transmitting guidance information to a missile control unit (1), for terminal on-target guidance (2). Device according to one of the preceding claims, in which the active assembly (6) comprises at least one transmitter/receiver RF antenna. Device according to one of the preceding claims, in which the passive assembly (7) comprises at least one receiver RF antenna and/or one electro-optical sensor. Device according to one of the preceding claims, in which the passive assembly (7) is arranged around the periphery of the seeker device. Missile (1) provided with a homing device (3) according to one of the preceding claims.

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