DE3313648A1 - Process for real-time terrain reconnaissance by means of a sensor and device for carrying out the process - Google Patents

Abstract

A process for real-time terrain reconnaissance by means of a sensor (14) and a device for carrying out the process, the sensor (14) being incorporated in a projectile fireable over the reconnaissance terrain and transmitting its sensor reception signals (27) to a ground station (12) by way of a radio-transmission path (20), are to be designed to make it possible, at a low handling outlay, to cover in a controlled manner an extended strip (13) of reconnaissance terrain in the boundary region of the range of modern artillery weapons. For this, the sensor (14) is incorporated in a reconnaissance daughter projectile (15) which is guideable in the final phase of its flight and which is conveyed by means of a carrier missile (17), which is preferably a light artillery rocket, in front of the starting point (z3) of the reconnaissance strip (13) and is ejected there. The carrier missile (17) is braked to a steep fall path, in order, during its service life, to serve behind and above the reconnaissance daughter projectile (15) as a radio-relay station between the latter and the ground station (12). The ejected daughter projectile (15) is controlled into a stable trajectory approximately parallel to the ground (22) of the terrain strip (13) to be reconnoitred and maintained in it for the reconnaissance flight, until it becomes unstable as a result of a loss of speed and crashes. Preferably, a plurality of reconnaissance daughter projectiles (15) are ... simultaneously from a single carrier and relay missile (17) ... Original abstract incomplete. <IMAGE>

Description

Process for real-time terrain reconnaissance using

a sensor and apparatus for practicing the method. The invention relates to a method according to the preamble of claim 1 and a device according to the preamble of claim 10.

Din generic method and a generic device are known from DE-OS 31 14 600. A microwave pulse radar is used as the sensor provided, which is fired by means of a missile, the one of interest Approaching the terrain point in the steep descent. In doing so, the environment of the interested Terrain point is scanned spirally by means of active reflection detection and the Information determined in this way is transmitted by radio to a ground station, wc from it a Doppler information terrain map is developed.

Disadvantages of the previously known, generic method and the corresponding facility is in particular that it is now moving comparatively quickly moving target points in the recorded terrain area or only moving target points image information in the immediate vicinity of the center of the recorded terrain area deliver and therefore no real terrain reconnaissance can be obtained from it; because a Pulse Doppler radar i.a.

System-related does not provide any information about stationary target points and because a sufficiently reliable data evaluation only with high resolution, so only in the case of the radially narrow spiral strips near the center of the recorded Genuine is given. Another disadvantage is that only an extremely short period of time of the falling of the ra] ete as Sensor carrier projectile in their Target point is available as a reconnaissance tent period; and thus only per shot a spatially and temporally limited area is covered in such a way that a tactical Terrain reconnaissance as required for effective use of modern artillery weapons Longitudinal and transverse extension of the reconnaissance area and its distance from the firing position it is desirable that it cannot be taken into account. Finally, it is disadvantageous that according to the previously known measures, the radio transmission time span and thus the actually effective clearing-up time span still thereby considerably additional can be restricted that the missile with the pulse radar reconnaissance sensor in its peak at the steep descent to the target point of the terrain obstacles in the Reconnaissance area, i.e. their target point, dips so that the data radio transmission to the ground station is not guaranteed with the necessary security. In the end even signal processing for image display in the ground station is problematic, because only with considerable additional detection facilities in the available the extremely short period of time for an information correction can be determined, In which current spatial orientation the rocket deviates from the perpendicular to the The target point approaches this, which is recorded in the s-spiral coordinate system So ground point information - denote what momentary, geometrically caused distortion contain as disruptive information.

From DE-AS 25 33 6? 7 it is, similar to the aforementioned prior publication, has already become known to equip a projectile with an image sensor. Whose Image information is transmitted via a wireless signal transmission link, which at the same time is used to remotely control the projectile, transmitted to a ground station, where the The projectile's approach to the target is observed on an image display device and, if necessary can be corrected manually via the control-active connection.

Since here again only the target point directly approached is observed is therefore an actual, larger-area one for the same reasons as discussed above Terrain reconnaissance, as it is needed to derive tactical requirements, not feasible.

The latter also applies to the weapon system known from DE-PS 24 11 790, in the case of the tracking or the image information retransmission of a pilot floor Firing data for combat projectiles to be fired from the same launching system be won.

For data acquisition for terrain reconnaissance in combat areas behind The current front edge of the defense has already been named self-steering Small aircraft deployed after a series of photographs of the flown over Program-controlled return to their starting area, so that the film recordings can be extracted, developed and evaluated. Such so-called drones but are relatively at risk of being shot. And their educational value is limited by that there is no direct local coordinate assignment to the terrain surveys. Above all, however, it is cumbersome that with a limited range and considerable deployment costs in practice, flights of this kind are only started at longer intervals and then the information only after the film material has been developed and through personnel-intensive evaluation and implementation in an information system be fed in 'according to ömnen.

n Recognition of these tjängel or limits of existing means of education the invention is based on the object, the method and the device of the generic type Kind to the point of further training that without great equipment or handling effort extensive information about terrain and in it military objects of interest can be fed directly into a real-time information system can; clearly fixed and moving target objects equally, and classifiable for a target identification> are recorded as well as the recorded Reconnaissance area, even without the possibility of direct inspection, far in front of the radio receiving ground station, at the limit of the combat range of modern artillery weapon systems should be able to.

According to the invention, this object is essentially achieved by that in the method of the generic type in addition the measures according to the characterizing Part of claim 1 are taken, while in a device of the generic type Type this additionally according to the partial features of the characterizing part of the claim 10 is equipped.

So it will be an artillery shell and preferably an artillery missile no longer used directly as a carrier projectile for the sensor, but only as a carrier or means of transport to set down (at least) one daughter lock as the actual sensor missile at the beginning of a reconnaissance strip and thus anywhere within the range of modern artillery. After that serves that carrier missile as "standing" high above the terrain and therefore shadowing between the reconnaissance area and the launch and ground station, Radio relay station for sensor reception signals; that of the ejected reconnaissance daughter floor after controlled descent into a lower, stable and end-phase controlled reconnaissance trajectory, in the case of long-stretched flight, approximately parallel to the ground over a defined strip of terrain, picks up until the relay missile has crashed or the daughter floor due to Speed reduction no longer flies stable and also crashes.

A number of infrared detector elements are preferably used as the sensor, essentially oriented parallel to the direction of flight on the daughter floor, expediently used for mechanized, periodic scanning transversely to the direction of flight. Terrain information is obtained from overlapping image areas. This results in a picture of the terrain primarily as a static representation the target identification criteria according to the contours and / or radiation distributions can be won. At the same time, movement information can be derived from this, by being slightly superimposed on each other (offset in time) and thus essentially overlapping images from the surroundings of the same in each case Terrain point are represented, from which the movement as Ortsverlageruii £ certain pieces of information.

In the interest of a distortion-free recording of the broadest possible reconnaissance strip with optimal utilization of the use of equipment with regard to the launch requirements of (carrier and relay) missiles, it is useful to have several of the same type or with sensors for different information - equipped daughter floors to be housed in a single carrier missile and in front of the one to be overflown To launch reconnaissance strips at the same time. The missile then serves as a radio relay station for all subsidiary floors that are used for control during the descent in the stable, stretched reconnaissance flight phase in a certain geometric Configuration to each other (preferably offset parallel to each other) controlled can be. This results in a broader reconnaissance strip Parallel flight of, for example, three equally equipped daughter floors or a greater variety of information when capturing essentially the same strip of terrain. The dimensions of the after ejection still as a relay station serving Carrier missiles also allow the accommodation of facilities for Data preprocessing in the sense of an assignment with regard to the, for example, three Subsidiary floor sensors with data compression for further transmission via the uni many times greater distance to the ground station.

Additional training as well as other features and advantages of the Invention emerge from the subclaims and from the description below the essential point of view here is the practice of the method according to the invention taking into account an embodiment example shown in a greatly simplified manner for a device according to the invention for carrying out such a method.

It shows: FIG. 1 symbolically simplified and strong in the longitudinal direction compresses a schematic diagram to explain the method and the function of a Device for practicing the method, based on an overview representation; Fig. 2 movement characteristics over time, taking into account the influence of a Pitch or flight angle control on the reconnaissance daughter projectile after it has been ejected from the launch vehicle and relay missile; the corresponding temporal behavior of the aerodynamically decelerated missile after ejection of the reconnaissance daughter projectile; 4 shows the movement of the ejected daughter bullet in comparison to his Missile, represented by route parameters according to FIG. 1; and Fig. 5 with coordinated, parallel reconnaissance flight phase of three subsidiary floors a description of the principle of the transmission paths for signal and control information according to a plan view of the situation in FIG. 1.

To explain the method according to the invention for real-time terrain reconnaissance by means of a sensor built into a floor and the resulting clarification technology s chen possible chains are assumed for the schematic diagram of FIG. 1: z-; en that for example due to terrain obstacles 11 no direct line of sight possibility between an observation ground station 12 and the strip of land of interest 13 is possible. The terrain strip 13 to be recorded by reconnaissance is to be up to the edge of the range of light artillery rockets and, if possible, something else In addition, extend to abrasives quickly, also taking into account immediately advancing formations beyond the remote end of the combat area, static to be able to use them optimally.

A sensor 14 (see FIG. 5) is in a reconnaissance daughter floor 15 installed, the high by means of a launcher 16 and a carrier missile via a point z1 shortly before the beginning z3 of the strip of land to be cleared 13 is promoted. Basically, every artillery shell is a missile carrier 17 suitable. However, the missile 17 is preferably provided as a missile in this case the start-up acceleration in the launching system 16 is relatively small and accordingly lower demands on the mechanical and electromechanical Structures, especially in the reconnaissance subsidiary floor 15, are to be provided must than with a higher starting acceleration. In addition, the launch system 16 in technically safer rooms before the clarifying Terrain strip 13 in or behind the combat zone.

relocated if instead of conventional gun ammunition a medium-range artillery missile is used as a carrier missile 17.

Shortly after exceeding the, with regard to the terrain and distance for the strip of land of interest 13 on the launching system 16 correspondingly predetermined, The apex 19 of the trajectory 18 is - remotely controlled by the launching system 16 off or self-controlled via a built-in, trajectory-dependent program control - An ejection device initiated in the carrier missile 17, the (at least) one carried out reconnaissance daughter floor 15 ejects. By opening the carrier missile 17 or

Simultaneously with this, the flow geometry of the carrier missile becomes 17 changed so that with the ejection time t1 a strong aerodynamic Braking and consequently a steep decrease in speed over time t (Fig. 3), as well as over the flight path z in the direction of the strip of land to be cleared 13 (Fig. 4) a linear decrease in altitude occurs.

These aerodynamically acting braking means are also designed in such a way that that there is a sufficiently stable spatial position of the carrier missile 17 relative to the ground station 12 ur a radio transmission path that can be ensured in a relatively uncomplicated manner 20 sets. This with the launching of the reconnaissance daughter projectiles 15, and the the resulting fluidic change in shape of the missile carrier 17, accompanying Braking and stabilizing measures can be used with (from the technology end-phase steerable Projectiles) known as such measures by means of control or stabilizing fins can be realized, which are extended with the initiation of the ejection device and in the basic representation of the drawing (Fig. 1 and Fig. 5) syrnboliscll simple are indicated as a funnel-shaped front opening 21 in the missile carrier 17. These Measure names are made in such a way that such an aerodynamic Braked rate of descent sets that the falling carrier missile 17 over a period of for example 55 seconds still a height above the Reconnaissance height ah 3/4 of the reconnaissance daughter floor 15 5 of for example 800 meters above ground 22 reserves. As a result, the missile carrier 27 stands as flying relay station for radio information transmission from the ejected Reconnaissance daughter floor 15 to ground station 12 available. Because this relay station stands higher than the reconnaissance sub-level during the reconnaissance period t3 ... t4 15 above the floor 22 and thus represents, even with a topographically blocked line of sight from the ground station 12 to the reconnaissance daughter floor 15, a two-way radio bridge with bundled maximum frequency energy of linear propagation from the reconnaissance subsidiary floor 15 5 to the ground station 12 over the obstacle safely.

As sketched in Fig. 1, and in more detail for a more specific The implementation example shown in FIG. 2 learns this from the missile carrier at time t1 17 ejected reconnaissance daughter projectile 15 a trajectory formation in the manner of the end-phase control known as such for projectiles. It is designed here to to steer as quickly as possible into a reconnaissance trajectory 23, which extends over a longer time span t3 ... t4 and distance z3 ... z4 approximately parallel to the ground 22 extends. Within a first period of time t1 ... t2 ini connection with the ejection point in time t1, each ejected reconnaissance daughter projectile 15 goes through a ballistic Free flight phase of a few seconds, during which rolling movement is slowed down, and the stabilizing wings are folded out in a defined roll position.

After these flight stabilization measures it closes from the point in time t2, ahl a flight phase span t2 ... t3 during further Absixikens from the ejection altitude the trajectory shaping. These consists essentially of how through the qualitative entry of the pitch or flight path angle Wa in FIG. 2 is expressed brought, in a linearly increasing increase in the flight path angle over time t Wa by, for example, program-controlled change of the position of the tail unit wings (not shown in the drawing); until a specified final angle value is reached which initially (until time t3) remains constant.

The point in time t3 of the start of the reconnaissance period is t3 ... t4 essentially determined by the fact that the reconnaissance daughter floor 15 (as a result of that flight angle control during the descent phase t2 ... t3) approximately to the desired one Reconnaissance height swiveled in at 3/4. However, especially in the case of equipment with sensors 14 for visible light or electromagnetic radiation in the infrared spectral range the reconnaissance daughter floor 15 with a cloud detector (not in the drawing shown), which is based on the evaluation of reflected short-wave Infrared radiation determines whether the secondary level is in the descent phase 15 a cloud cover has already been pierced downwards; to only then, so at correspondingly lower height ah 3/4, to switch to the programmed flight path angle Wa and thus to pivot into the reconnaissance trajectory 23.

Then the setting influencing takes place in the reconnaissance daughter floor 15 5, that is, the control of the flight path angle Wa, stores "rograrll: i ert in such a way that a stable reconnaissance trajectory 23 is established at an almost constant altitude, the is given by fluctuation in accordance with a damped sinusoidal oscillation and the The initial height does not exceed 3/4 in the following period.

The end of the reconnaissance trajectory 23, and thus also the reconnaissance period t3. . .t4, is given by the fact that the speed Va of the reconnaissance daughter projectile 15 finally decreases too much, or the required angle of attack on the daughter floor 15 can no longer be adjusted to generate the necessary buoyancy. Then a stable flight attitude can no longer be achieved. Therefore is beyond the point in time t4 the daughter floor 15 can no longer be held via the trajectory angle control, it crashes.

As already mentioned in connection with FIG. 1, and from a comparison the representations of Fig. 3 with Fig. 2 can be seen, the flight behavior of the, Carrier missile serving as a relay station after the daughter projectile ejection 17 in such a way on the flight behavior and the corresponding flight times of its reconnaissance sub-projectiles 15 turned off that the relay station while maintaining the reconnaissance trajectory 23 still has a descent height above this or at least not significantly has sunk below this. This results in Sicnt and radio communication paths S, 24 between the reconnaissance subsidiary projectiles 15 and their relay missile 17, as shown for the central area of the strip of land to be cleared 13 in Fig. 1, and additionally for the starting point z3 and the end point z4 of the reconnaissance trajectory 23 above floor 22 in FIG. 4 are entered. With a realistic mean Descent speed of the carrier missile 17 of less than 50 m / s after ejection the reconnaissance subsidiary floors 15 to.

Time t1 results for the relay missile 17 until it descends at the reconnaissance level ah 3/4 a standing or function time of up to 50 seconds, that of the period t1. . . corresponds to t4, i.e. a clearing-up period of time t3 ... t4 in the order of a few tens of seconds. By influencing the The dynamics of the reconnaissance subsidiary projectile 15 shown in FIG. 2 can be in the trajectory 23 a distance z3 ... z4 in the order of magnitude of a few km is stable overfly. You can thus the launching system 16 (Fig. 1) in a safe "te Relocate positions and even if the reconnaissance area is not directly visible the area of combat operations and the deployment area behind it capture sickle in overflight.

Appropriately, as indicated in syrnbolic form in FIG. 5, in each Reconnaissance daughter floor 15 has a number of detector elements 25 as sensor 14 arranged one behind the other in the direction of flight 26. Their transverse scanning swivel movement determines the width of the strip of terrain 15 covered by a subsidiary floor 15. Tn flight direction 26 offset image information (received signals 27) of the same Auffaßpunkt 28 (Fig. 1) on the floor 22 allow information about a To derive the movement of targets recorded there and their classification.

In particular for target identification with as little effort as possible It is inexpedient for signal processing means to set the desired detection width transversely to the longitudinal extension of the reconnaissance strip of terrain 13 through wide transversal Swing out to paint over. Because the weird constitution is more remote to the side It is well known that objects at a correspondingly flat detection angle lead to distortions and AG shadows that interfere with target identification. This problem does not occur when a carrier missile 17 has multiple reconnaissance daughter projectiles 15 carries over the ejection point z1, which, if possible, at least regionally Detect overlapping, adjacent reconnaissance terrain strips 13. However would be due to uncoordinated movement of the reconnaissance subsidiary floors 15 the output dynamics. usually the terrain strips 13 diverge; with the result that (due to the lack of overlap of the recorded terrain strips 13) at a greater distance target objects captured by their starting points z3 at the respective strip edge jects can no longer be evaluated with regard to movement parameters and in between Wedge-shaped non-recorded land areas remain.

It is therefore more expedient by means of a single carrier missile 17, which later as described as a relay station of a radio bridge to the ground station 12 serves, several Aufki & -rungs subsidiary floors 15 at the same time over the ejection point zl to be transported in accordance with the output-related fishing conditions during their controlled descent phases t2 ... t3 in mutually parallel, and for Strip overlaps defined spaced-apart, reconnaissance trajectories 25 deflected as sketched in FIG. 5. For parallel control, as part of the, Transmitting devices 30, distance measuring devices connected downstream of the sensors 14 (for example, working according to the so-called transponder principle), determine the distance information 31 to the centrally flying daughter floor 15 for keeping the outer reconnaissance trajectories 23 parallel by means of appropriate rudder controls in the outlying subsidiary floors 15.

To several reconnaissance daughter projectiles 15 5 in a carrier missile 17 to accommodate the specified caliber, the equipment required for signal processing between a sensor 14 and its transmitting device 30, and thus the corresponding one Space requirement, kept as tight as possible. Therefore a simultaneous transmission of the Received signals 27 via the transmitting devices 30, to the missile carrier 17 as Radio bridge relay station, preferably in frequency multiplex (i.e. in each other distinguishable frequency bands for assigning information to the individual subsidiary floors 15) provided.

In the larger-volume relay missile 17 there is space for data preprocessing with the aim of compressing the flow of information over the radio transmission path 20 to the ground station 12. D, e information from the individual, against each other parale9-vers The last reconnaissance strip 13, can then use this eg 20 in time division multiplex be transmitted, which means the simultaneous use of the same ground station 12 as well for further relay missiles 17 allows. Frequency division multiplex data transmission only needs to be implemented for the short Furii connection routes 24, for which - as can be seen from FIG. 4 - the antenna characteristics between the Subsidiary projectile 15 and the relay missile 17 in only about a quarter of the room, at most, however, to be laid out in a night room behind the reconnaissance subsidiary floors 15 are.

The data received from the ground station 12 from the individual reconnaissance terrain strips 13 are converted into video signals for image display devices 32, e.g. for real-time display the combat and deployment in the area of the attack, implemented. The image display device needs 32 not to be set up in the radio receiving ground station 12 itself; it can also be a means of representation in a spatially remote location center, in the intelligence information from different areas and from different intelligence agencies merged, according to analysis specifications processed and presented together.

LIST OF REFERENCE SIGNS a Reconnaissance operation r Relay operation h Altitude (above 22) v speed (over 22) t time variable z position variable (in direction 23-26) H Altitude (over 22) V Airspeed W Flight or pitch angle 1 ... 4 flight phases of 15; or coordinates of the beginning of this respective flight phase 1 ballistic Free flight 2 Steering after 23 3 Excursion with 23 4 Fall 5 6 7 8 9 10 11 Direct view of terrain obstacles (between 12/16 and 13) 12 ground station (for 20) 13 reconnaissance patrols (under 23) 14 sensor (in 15 for 29-27) 15 reconnaissance daughter floor (for 23) 15 Launching system (for 17 with 15) 17 carrier and relay missiles 18th Trajectory (from 17 to t1 via z1) 19 vertex (from 13) 20 radio transmission path (from 17 to 12) 21 Front opening (for aerodynamic braking from 17 at t1) 22 Ground (along 13 under 23) 23 Reconnaissance trajectory (z3 ... z4) 24 Radio communication path (from 15/30 to 17) 25 detector elements (at 15 along 26; as 14) 26 flight direction (from 15 along 23/13) 27 received signals (from 25/14, to 30) 28 perception point (at 22 by means of 14) 29 30 transmitting device (for 24) 31 distance information (between 15/30 - 15/30) 32 picture display device (in or behind 12 for 20/27)

Claims (18)

Claims 1. A method for real-time terrain reconnaissance by means of a Sensor that is built into a projectile to be fired over the site and whose sensor reception signals are transmitted from the floor to a ground station via Pui in which signal processing for image displays takes place, characterized in that, that a carrier missile is selected as the projectile, the at least one with the sensor equipped reconnaissance subsidiary floor up to a reconnaissance strip carries where the carrier missile ejects this daughter projectile and at the same time for the steep descent is slowed down, while the reconnaissance daughter floor is program-controlled descends to a reconnaissance height above the ground and into a reconnaissance trajectory, which runs approximately parallel to the ground, is controlled, whereupon the from The sensor of the reconnaissance sub-projectile recorded the reception signals sent to the carrier missile and transmitted by this as a radio relay station to the distant ground station until the carrier missile and / or, due to loss of speed, the Reconnaissance daughter floor crashes. 2. The method according to claim 1, characterized in that the missile as a carrier and as a radio relay station for several reconnaissance subsidiary floors at the same time serves, which after rising to reconnaissance height each have a defined end-phase trajectory control relative to one another, preferably parallel to one another. 3. The method according to claim 1 or 2, characterized in that the Carrier body, through aerodynamic structural changes during or as a result of ejection of reconnaissance daughter bullets, on a steeply sloping ballistic trajectory is controlled, in which it determines the reconnaissance height of the reconnaissance trajectory of the sensor daughter projectiles at least not much before the point in time when the reconnaissance trajectories were reached become unstable as a result of the reduction in speed and the daughter floors are turned off crash these trajectories. 4. The method according to any one of the preceding claims, characterized in, that from the carrier missile ejected reconnaissance daughter projectiles the admission and transmitting ground information reception signals not before reaching a predetermined reconnaissance height above the ground, and not before piercing a after any cloud cover, begin. 5. The method according to any one of the preceding claims, characterized in, that the reconnaissance daughter projectiles during a short ballistic free flight phase after ejection from the carrier missile, in which a deceleration of a rolling motion by extending the stabilizing wings, with a guided descent phase be transferred with pitch angle control in the area of the reconnaissance flight altitude, in which they, also by means of pitch angle control, along an extended reconnaissance trajectory with a slight height fluctuation, e.g. according to the temporal course of a damped Sine function, can be controlled. Method according to one of the preceding: Claims, characterized in that that each sensor provides ground information by means of at least one row of detector elements picks up the one on the reconnaissance daughter floor parallel to its reconnaissance flight direction are arranged. Method according to claim 6, characterized in that alternately Interrogation of staggered partial areas of the arrangement of detector elements in terms of time and locally slightly offset from one another but essentially overlapping one another Reconnaissance information can be obtained from the ground. Method according to one of the preceding claims, characterized in that that, regardless of the movement of the reconnaissance daughter bullet, a periodic one The overflown area is scanned transversely to the direction of flight. Method according to one of the preceding claims, characterized in that that the sensor received signals from reconnaissance daughter projectiles operated in parallel at the same time in frequency nultiplex over the comparatively short radio communication paths to the common relay missile, where a signal preprocessing with data compression for radio transmission along the radio transmission path to the ground station takes place, the information also other relay missiles in the time division multiplex records in front of other reconnaissance patrols. 10. Direction for real-time terrain reconnaissance by means of a lockable Sensor (14), the received signals (27) of which are transmitted without wire to a ground station (12) will be - in particular to :: exercise the procedure according to one of the preceding Claims -, characterized in that a carrier missile (17) for at least an ejectable, flight-phase-steerable reconnaissance sub-projectile (15) is provided, each reconnaissance daughter floor (15) with a sensor (14) and is equipped with a transmission device (30) connected downstream of this, while the carrier missile (17) at the same time as a relay station, with the ejected reconnaissance daughter projectiles (15) assigned receiving device and transmitting device assigned to the ground station (12), is trained. 11. The device according to claim 10, characterized in that the Carrier missile (17) with depending on the output of the reconnaissance daughter projectiles (15) is equipped with effective aerodynamic braking structures. 12. Device according to claim 10 or 11, characterized in that that each reconnaissance sub-level (15) with an altitude-dependent-actuatable Pitch angle control device is equipped. 13. Device according to one of claims 10 to 12, characterized in that that reconnaissance daughter floors (15) with a cooperating with a height measuring device, Cloud detection device are equipped. 14. Device according to one of claims 10 to 13, characterized gekennzeicnret, e that when several of a common carrier and relay missile (17) can be ejected Reconnaissance daughter projectiles (15) these with distance measuring devices and them downstream lateral path control devices are equipped. 15. Device according to one of claims 10 to 14, characterized in that that reconnaissance daughter projectiles (15) are provided with sensors (14) which are shown in a plurality of at least one row parallel to the direction of flight of the daughter floor (26) have on detector elements (25). 16. Device according to one of claims 10 to 15, characterized in that that reconnaissance daughter projectiles (15) are provided with sensors (14) for Recording of image information that is slightly offset in terms of time and location and their transmission via the relay missile (17) to the ground station (12) are set up. 17. Device according to one of claims 10 to 16, characterized in that that reconnaissance daughter floors (15) with sensors (14) for periodic terrain scanning are equipped transversely to the direction of flight (25). 18. Device according to one of claims 10 to 17, characterized in that that the alert tocilter projectiles (15) and their relay missiles (17) with Transmitting devices (30) or. Receiving facilities for simultaneous operation of radio communication paths (24) are equipped in frequency division multiplex, while the relay missile (17) In addition, it has facilities for signal processing and data compression for data retrieval from the ground station (12) via the transmission path (20) in time division multiplex is.