Method for indicating an interceptor missile on a flying object flying on the ground

Abstract

The invention relates to a method for guiding an interceptor missile (50) to an approaching aircraft (30), in which a reconnaissance missile (2) is launched and brought into an IR-transparent atmospheric layer (45), where it tracks the aircraft (30) with an IR sensor (10) and transmits tracking data of the aircraft (30), and the interceptor missile (50) is guided to the aircraft (30) using this tracking data. To enable a rapid and precise guidance of an interceptor missile (50) to an approaching hypersonic aircraft, it is proposed that the reconnaissance missile (2) be rocket-powered and track the aircraft (30) with its launch rocket engine (24) extinguished.

Description

[0001] The invention relates to a method for guiding an interceptor missile towards an approaching flying object, in which a reconnaissance missile is launched and brought into an IR-permeable atmospheric layer suitable for long-range IR reconnaissance, where it tracks the flying object with an IR sensor and transmits tracking data of the flying object, and the interceptor missile is guided towards the flying object using the tracking data.

[0002] Hypersonic missiles pose a challenge for air defenses because they reach their targets very quickly. The reaction time for launching an interceptor missile is therefore short. This is further complicated by the fact that hypersonic missiles can only be engaged from the front, meaning that an interceptor missile must be guided very precisely into the path of the hypersonic missile to successfully defend against air attacks. However, in the short time available, sufficiently accurate data is usually not available to guide the interceptor missile very precisely into the path of the hypersonic missile.

[0003] It is an object of the present invention to provide a method by which an interceptor missile can be quickly and precisely guided towards an approaching hypersonic missile.

[0004] This object is achieved by a method of the type mentioned above, in which, according to the invention, the reconnaissance missile is rocket-motor driven and tracks the flying object.

[0005] The invention is based on the idea that the launch of a hypersonic missile is first detected by a satellite.

[0006] Satellite data can be used to determine the direction of flight of the hypersonic missile and the resulting threat. However, the satellite data is too imprecise to guide an interceptor missile into the hypersonic missile's future or expected trajectory. Ground-based surveillance units can detect the hypersonic missile more accurately, but only when it appears above the horizon. Therefore, their data is too late to guide an interceptor missile. Therefore, an airborne surveillance unit, such as a reconnaissance aircraft or drone, must be launched and placed into the IR-permeable atmospheric layer to accurately determine the hypersonic missile's trajectory and guide an interceptor missile.Precise spatial monitoring of the flying surveillance unit can be achieved with a sensor sensitive in the infrared spectral range, or IR for short. For this purpose, the surveillance unit must be placed in the IR-transparent atmospheric layer to avoid absorption of the hypersonic missile's IR radiation by clouds or high humidity in the atmosphere.

[0007] With an airborne surveillance unit, the approaching aircraft can be tracked with sufficient precision to transmit the acquired data to a central station, which then guides the interceptor missile. However, the surveillance unit cannot usually be launched into the atmosphere quickly enough to track the hypersonic missile before it reaches its target. To solve this problem, a rocket-powered reconnaissance missile can be launched. This missile reaches the IR-permeable atmospheric layer quickly enough and can detect and track the hypersonic missile with an IR sensor early enough to use the acquired tracking data to guide an interceptor missile toward the hypersonic missile.An IR tracking unit, such as an IR seeker on a reconnaissance missile with an IR sensor, detects the IR radiation of the approaching hypersonic missile and tracks this IR signal to determine the hypersonic missile's directional data. Combined with the reconnaissance missile's own flight data, hypersonic missile tracking data can be derived. This data can be used to guide the interceptor missile toward the hypersonic missile. The reconnaissance missile's flight data can include the reconnaissance missile's orientation in space and its position in space. The reconnaissance missile can determine its own flight data, for example, its orientation using inertial navigation and its position using satellite positioning, such as GPS.

[0008] The atmospheric layer is characterized by sufficient IR transparency for long-range IR reconnaissance. Long-range reconnaissance can be reconnaissance beyond a distance of 20 km. The atmospheric layer is expediently located above 10 km above sea level, advantageously between 10 km and 25 km above sea level, and in particular only between 10 km and 20 km above sea level. The atmospheric layer selected for long-range IR reconnaissance can be limited upwards – even if IR transparency is high there – since a view of the flying object from below is useful for IR reconnaissance, as it is then seen against the dark space with little infrared radiation, thus ensuring high IR visibility. The term "atmospheric layer" can therefore be used for the IR-transparent atmospheric layer from which the reconnaissance missile can expediently monitor or track the flying object.

[0009] Guiding the interceptor missile may include transmitting data to it that enables the interceptor missile to intercept the flying object, in particular to fly into the flying object's flight path, whereby a predetermined distance from the flight path that still allows interception can be considered to be included in the flight path. The guidance may come externally as such, e.g. as a specification of target coordinates, or the interceptor missile may guide itself with the data. The guidance may include the target location and, if applicable, a flight path or direction there. The target location may change during the flight, requiring the flight to be adjusted. The tracking data may contain a scanning direction of the interceptor missile in which it sees the flying object. The scanning direction may change over time, so that it may be included in the tracking data as a multiple direction over time.In addition, the location of the reconnaissance missile provides useful tracking data, although this also changes over time and can therefore be multiple locations. A reconnaissance missile preferably contains an IR seeker, a control unit for controlling its flight, e.g., based on the tracking data, a launch rocket engine, particularly one with solid fuel, and guidance vanes or guidance nozzles for controlling its flight. An interceptor missile can contain these same components and additionally an active element for engaging the flying object. The flying object can be a hypersonic missile, such as a hypersonic cruise missile, a hypersonic glide missile, or a ballistic missile.

[0010] Once the reconnaissance missile has reached the atmospheric layer, it can take some time before it can see the flying object and then detect it as such. It is then necessary for it to track the flying object until the interceptor missile has been locked on and, ideally, until the interceptor missile has intercepted the flying object, i.e., engaged it, or until the flying object has been classified as a false object that should not be engaged. It is also useful for tracking to continue even if engagement has failed, so that another interceptor missile can be locked on and, in particular, can be brought in front of the flying object through even more extensive tracking. For this to happen, the reconnaissance missile must remain in the atmospheric layer for one, particularly several minutes, during which time it tracks the flying object, ideally continuously.Tracking may include generating current tracking data.

[0011] To generate as little heat as possible, it is also advantageous for the reconnaissance missile to move slowly through the atmosphere during tracking. It is therefore advisable for the reconnaissance missile to track the flying object with its booster engine off. The booster engine is a rocket engine whose energy brings or has brought the reconnaissance missile into the IR-transparent atmospheric layer. It can be single-stage or multi-stage. When the IR-transparent atmospheric layer is reached, the booster engine may still be burning or already extinguished. The same applies to the position in which the reconnaissance missile can detect the flying object. Here, too, the booster engine may still be burning or already extinguished, although it is more advantageous for actual detection if the booster engine is off and the reconnaissance missile has decelerated to a speed at which its movement through the atmosphere generates little heat.However, it is important that the launch engine is no longer firing during the first or subsequent tracking to ensure reliable tracking. However, tracking does not have to be entirely engine-free if the movement through the atmosphere is slow enough. To achieve a long residence time in the IR-transparent atmospheric layer, an additional engine can be operated during tracking, e.g., to keep the reconnaissance missile in the atmospheric layer. This can be a smaller solid-fuel engine or an air-breathing engine, although its thrust is lower than that of the launch engine.

[0012] In an advantageous embodiment of the invention, a flying surveillance unit tracks the flying object before the reconnaissance missile is launched. The surveillance unit can be a satellite, a surveillance aircraft, a surveillance drone, or another flying object. The surveillance unit is expediently located in or above the IR-transparent atmospheric layer. Depending on the tracking data acquired by the surveillance unit, the reconnaissance missile can be launched and directed toward the flying object based on the tracking data. For example, a launch time for the reconnaissance missile can be determined from the tracking data. One of several reconnaissance missiles can also be selected, for example, based on location data and / or availability data of several reconnaissance missiles.Before, during or after the launch of the reconnaissance missile, it can be guided towards the flying object, whereby the guidance can include a suitable observation position in the atmospheric layer and does not have to be directed towards an encounter with the flying object.

[0013] By tracking the aircraft, the surveillance unit can achieve triple tracking of the aircraft. First, it is tracked by the surveillance unit, then by the reconnaissance unit, and then by the interceptor missile, which can track the aircraft after detection until engagement. This allows for a combination of very fast but inaccurate tracking with a rapidly subsequent and accurate tracking, along with a final tracking until engagement. In addition, the aircraft can be further tracked by a ground-based tracker, for example, once the aircraft rises above the pursuer's horizon.The missile is then tracked first by the surveillance unit—if present, then by the reconnaissance unit, then by the tracker—if present, and finally by the interceptor missile. The order of tracker and interceptor missile can also be reversed, depending on the visibility of the missile by these two units. Tracking data from the ground-based tracker can also be used to track the missile. Tracking can be conducted from one tracker to the next with increasing accuracy. Multiple trackings can overlap, meaning they can take place simultaneously, and the tracking can complement each other. The tracking data from two, three, or four trackers can be combined to create improved tracking data, allowing for more precise guidance or a more accurate approach to the interceptor missile.

[0014] A further embodiment of the invention provides that the reconnaissance missile is launched from a location within the atmosphere depending on the expected visibility of the flying object. Visibility can be determined from tracking data from a monitoring unit. For example, the area from which the flying object is visible is determined as a function of time. From the reconnaissance missile's launch position data, a suitable location or spatial area, combined with a time or period of time, into which the reconnaissance missile is to enter, can be selected. A suitable launch period can be selected based on this. This should also require the reconnaissance missile to reach the location or spatial area within a predetermined period of time before the expected visibility.If the reconnaissance missile arrives too early, it must remain suspended in the atmosphere for a long time to be able to track the flying object, which will be visible much later. The time period should therefore be short, preferably less than 5 minutes, and especially less than 2 minutes.

[0015] The movement of the reconnaissance missile must meet two conflicting requirements. On the one hand, the reconnaissance missile must be able to reach the atmosphere as quickly as possible. It must therefore be able to fly fast. On the other hand, it must be able to remain in the atmosphere for as long as possible in a very thin atmosphere in order to track the flying object for a long time, without requiring or benefiting from a powerful engine. This contradiction can be mitigated if the reconnaissance missile jettisons an engine stage and descends into the atmosphere without an engine stage. This makes the reconnaissance missile significantly lighter after a fast flight, making it easier to slow down.

[0016] After launch, the reconnaissance missile ascends rapidly and ideally reaches the atmosphere while still in the thrust phase, i.e., with the launch engine still pushing. Once in the atmosphere, the engine can be extinguished, with the reconnaissance missile continuing to ascend at high speed in a subsequent ascent phase until it reaches the zenith of its trajectory. The reconnaissance missile then descends again in a descent phase, ideally slowed by a braking unit. The location of the first visibility of the aircraft should be during the thrust phase or the ascent phase, but can also be during the descent phase. If it is in the ascent phase, the reconnaissance missile reaches a location where the aircraft is expected to be visible, ascends further with the engine off, and then detects and tracks the aircraft with the engine off.However, it is also possible that the location of the first visibility of the flying object is only reached during the descent.

[0017] It may happen that a flying object turns out to be harmless during the reconnaissance missile's flight. The reconnaissance missile or another unit, such as a central station, a ground station, or a surveillance unit, can then downgrade the flying object from an intercept target and classify it as a false target. The reconnaissance missile should nevertheless scan the surrounding area for other flying objects and track the object until it visually disappears. This disappearance may be caused by the reconnaissance missile descending into a denser atmosphere. The classification can be based on tracking data determined by the reconnaissance missile.

[0018] To slow the reconnaissance missile's descent within the atmosphere, the use of a descent brake is advantageous. The descent brake can incorporate a parachute to which the reconnaissance missile hangs during descent. Gliding wings, with which the reconnaissance missile glides through the atmosphere, are also possible. More complex but also possible are rotary wings, similar to those of a gyrocopter or autogyro. A propulsion system additional to the takeoff drive is also possible, particularly in combination with gliding wings. A particularly long stay in the atmosphere is possible with a balloon, which is expediently inflated at the zenith of the reconnaissance missile's flight path and exerts an upward force on the reconnaissance missile.

[0019] The tracking data transmitted by the reconnaissance missile is expediently received by a central station, which uses the tracking data, and in particular the tracking data from another surveillance unit, to determine the flight data of the aircraft and guide the interceptor missile toward the aircraft. The central station is, in particular, a ground station and may be a fire control center. The flight data may include data on the location, direction, and speed of the aircraft. After the interceptor missile is launched, it can receive the tracking data directly from the reconnaissance missile and guide itself toward the aircraft, for example, by re-guiding itself.

[0020] If the flying object is tracked from two or more directions simultaneously, both or more tracking data can be combined to produce more accurate tracking data.

[0021] Each tracker sends its tracking data to a central location or directly to the other or several other trackers, where it can be combined to create improved tracking data. In addition to the reconnaissance missile, a surveillance unit can be another tracker. It is also possible for a second rocket-powered reconnaissance missile to be launched separately and placed in the IR-permeable atmospheric layer. It can serve as another tracker and provide tracking data. It is useful for tracking the aircraft in the atmospheric layer with its engine off using an IR sensor. The interceptor missile can be guided to the aircraft using the tracking data from both reconnaissance missiles.

[0022] It is advantageous if both reconnaissance missiles fly in different directions, both below and within the atmosphere, and track the flying object from different directions. The distance between the two reconnaissance missiles is preferably at least 25% of their flight distance from the ground, and in particular at least 40%. When selecting the flight direction for two reconnaissance missiles, and generally for just one reconnaissance missile, a likely landing location can be taken into account, for example, to land the reconnaissance missile in the least populated or unpopulated area possible. The flight direction can be selected depending on the landing location.

[0023] A simple way to provide two trackers is for a reconnaissance missile to deploy at least two reconnaissance units into the atmosphere. The reconnaissance missile therefore has two reconnaissance units, each with an IR sensor for detecting and tracking the flying object, and which can move separately through the atmosphere. At least one of the reconnaissance units can be dropped or ejected, with the remaining reconnaissance missile continuing to fly with the other reconnaissance unit. The two reconnaissance units can move away from each other, both tracking the flying object and sending tracking data about the flying object. This moving away can involve gliding in a different direction than the other reconnaissance unit. It is also possible for at least one of the reconnaissance units to be dropped in the atmosphere and fly in a different direction than the continuing unit, e.g. the remaining reconnaissance missile.A jettisoned engine stage can also contain a spotting unit if the engine stage is equipped with an IR seeker. The engine stage can descend slowly on a parachute. A long tracking phase for both pursuers can be achieved if both spotting units are separated at the zenith of their trajectory and move away from each other during the descent. This can be achieved by gliding in different directions and / or descending at different rates.

[0024] From the tracking data from one or more trackers, such as the reconnaissance missile, a launch time of the interceptor missile is expediently determined, and the interceptor missile is launched at that time. Relatively simple defense of an object can be achieved if the reconnaissance missile and the interceptor missile are launched from the same launch platform. The launch platform can be a multiple launcher with at least one reconnaissance missile and at least one, expediently several, interceptor missiles. The launch platform is advantageously mounted on a vehicle, such as a wheeled vehicle.

[0025] Fast and reliable guidance of the interceptor missile to the flying object is advantageous. Speed ​​can be increased if there is a direct data link between the reconnaissance missile and the flying interceptor missile. Data forwarding or data processing in a central station can be dispensed with, thus accelerating data transmission. In this case, the interceptor missile advantageously guides itself to the flying object using data from the reconnaissance missile itself; it is therefore equipped to carry out its own guidance from the reconnaissance missile's tracking data, even without an intermediate station such as a central station or monitoring unit. The reliability of guidance can be increased if the tracking data is transmitted from both the reconnaissance missile and a central unit to the interceptor missile. The interceptor missile should take any time offset into account when processing the data.If one of the data connections is faulty or briefly interrupted, the data transfer can still be maintained.

[0026] Even with good interceptor missile guidance, engagement of a hypersonic missile can fail. It is therefore advantageous if the failure to engage the aircraft is quickly detected so that another interceptor missile can be launched. This can be achieved if the reconnaissance missile monitors whether the interceptor missile has successfully intercepted the aircraft. Surveillance data obtained from the reconnaissance missile's surveillance can be sent to another unit, such as a central station. If the interception of the aircraft fails, another interceptor missile can be launched using the surveillance data. For this purpose, a launch platform is expediently selected from among several, and the additional interceptor missile is launched from this launch platform. Using tracking data from the reconnaissance missile, the interceptor missile can be guided to the aircraft.

[0027] The invention is also directed to a reconnaissance missile with an IR sensor and a control unit which is designed to control a flight into an atmospheric layer, to track a flying object from there and to send tracking data of the flying object, for example to a central station or to an interceptor missile, for guiding an interceptor missile to the flying object.

[0028] In order to be able to guide an interceptor missile quickly and precisely towards an approaching hypersonic missile, it is proposed that the reconnaissance missile according to the invention contains a rocket motor, wherein the control unit is designed to carry out tracking of the flying object, in particular when the engine is extinguished during a descent phase in the atmospheric layer.

[0029] Furthermore, the invention is directed to a system comprising a reconnaissance missile and an interceptor missile, which is designed to independently guide the system to an approaching flying object based on tracking data of the reconnaissance missile.

[0030] The description of advantageous embodiments of the invention given so far contains numerous features, some of which are summarized in several dependent claims. However, the features can also be expediently considered individually and combined into meaningful further combinations, particularly in the case of claims that refer back to one another, so that an individual feature of a dependent claim can be combined with an individual, several, or all features of another dependent claim. Furthermore, these features can be combined with the method according to the invention as well as with the device according to the invention according to the independent claims. Thus, method features can also be viewed as objectively formulated properties of the corresponding device unit, and functional device features can also be viewed as corresponding method features.

[0031] The above-described properties, features, and advantages of this invention, as well as the manner in which they are achieved, will become clearer and more readily understood in conjunction with the following description of the embodiments, which are explained in more detail in conjunction with the drawings. The embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, including with regard to functional features. Furthermore, suitable features of each embodiment can also be explicitly considered in isolation, removed from one embodiment, incorporated into another embodiment to supplement it, and / or combined with any of the claims.

[0032] They show: FIG 1 a reconnaissance missile with a separate engine stage, FIG 2 a scenario for intercepting a hypersonic cruise missile with a reconnaissance missile in an atmospheric layer, FIG 3 a tracking reconnaissance missile on a parachute and FIG 4 a reconnaissance missile with two separable reconnaissance units.

[0033] FIG 1 shows a reconnaissance missile 2 during a flight and shortly after separation of its engine stage 4 from its main body 6. The reconnaissance missile 2 contains a seeker head 8 with an IR sensor 10, a navigation unit 12, an energy storage unit 14, a control unit 16, a communication unit 18, optionally a descent brake 20, optionally a stage separation 22, a launch rocket engine 24, steering wings 26 and optionally gliding wings 28. The control unit 16 contains image processing for detecting and tracking the flying object and a rudder attitude control for actuating the steering wings 26 and optionally the gliding wings 28.

[0034] The IR sensor 10 is sensitive in the mid- and especially also in the short-wave infrared range and can be pivoted within a field of view that covers at least the front hemisphere, thus allowing it to be directed at a flying object to be monitored. The navigation unit 12 is configured to perform inertial navigation and is equipped with sensors that determine the orientation of the reconnaissance missile 2 in space with high precision. The energy storage unit 14 serves to supply energy to all units in the reconnaissance missile 2 that require electrical energy. The control unit 16 is configured to control the flight and the drives for the guided wings 26 and to generate tracking data from data from the IR sensor 10 and the navigation unit 12. The determination of the position of the reconnaissance missile 2 can also be provided.The communication unit 18 is configured for data exchange with a central station and / or other missiles, for receiving data from a surveillance unit, and for transmitting tracking data to an interceptor missile. The launch rocket engine 24 is configured for flight up to an altitude of at least 20 km, and the guidance vanes 26 serve to guide the reconnaissance missile 2 during flight.

[0035] Depending on the design of the reconnaissance missile 2, it may have one or more of the optional components, such as the descent brake 20, which may be designed as a parachute, balloon, or additional engine, or gliding wings 28, which are designed for gliding at an altitude between 10 km and 20 km above sea level and can be deployed at the beginning of gliding. If a stage separation 22 is present, the engine stage 4 can be jettisoned; otherwise, the launch rocket engine 24 always remains connected to the main body 6 of the reconnaissance missile 2.

[0036] FIG 2 shows a flying object 30 approaching a target 32 ​​on the earth's surface 34. The flying object 30 is a hypersonic cruise missile, which oscillates at many times the speed of sound at an altitude of around 20 km, as in FIG 2 as indicated by its flight path 36. Flying object 30 could just as easily be a hypersonic glide vehicle (HGV) oscillating at altitudes of around 50 km or a ballistic missile flying at altitudes over 100 km. The higher flying object 30 flies, the higher a reconnaissance missile 2 can fly and track flying object 30 against the dark sky.

[0037] The target 32 ​​of the flying object 30 is unknown. A launch of the flying object 30 is detected by a monitoring unit 38 based on the thermal radiation of the flying object 30. The flying object 30 is recognized as a fast flying object 30 and tracked. The monitoring unit 38 can be a satellite, a drone, or another aircraft. The monitoring unit 38 sends the tracking data it generates, i.e., data obtained from tracking the flying object 30, via a data link 40 to a central location. If the flying object 30 is classified as a threat there, a reconnaissance missile 2 is selected, and a launch time for the reconnaissance missile 2 is determined. For example, the data is forwarded to another central location, such as a fire control center, which selects one of several launch platforms 42 with a reconnaissance missile 2. FIG 2 The data link 40 between the monitoring unit 38 and the launch platform 42 is shown in simplified form. This is intended to illustrate that the data comes from the monitoring unit 38 and is used to launch the reconnaissance missile 2, regardless of its path, either directly or indirectly through other stations.

[0038] To determine the launch time, a visibility range is determined from the tracking data, for example, from which - depending on the time - the flying object 30 is visible to the IR sensor 10 of the reconnaissance missile 2 if the latter were located in the visibility range. From the visibility range and the unlaunched position of the reconnaissance missile 2, and in particular additionally its flight data after launch, a position, an altitude, and / or a range can be determined from which the reconnaissance missile 2 can see the flying object 30 at the earliest or at another suitable time. To simplify the terminology, the term "position" generally also includes an altitude and / or a range from which the reconnaissance missile 2 can see the flying object 30 at the earliest or at another suitable time. FIG 2 This position 44 is shown, from which the view from the reconnaissance missile 2 to the flying object 30 extends entirely over a subsphere that extends up to a predetermined altitude, for example, up to 10 km above sea level. The altitude can be fundamentally fixed or variable, for example, depending on atmospheric opacity data of the subsphere, such as clouds and / or humidity. Position 44 lies in the atmospheric layer 45, which, for example, includes the atmospheric layer between 10 km and 20 km and ends at 20 km. At higher altitudes of the flying object than in FIG 2 As shown by way of example, the atmospheric layer 45 can extend further upwards, for example up to 30 km above sea level or include the entire atmosphere above 10 km.

[0039] The launch time of the reconnaissance missile 2 is then set such that it reaches position 44 before the flying object 30 is visible from this position 44. The period of time between reaching position 44 and the flying object 30 becoming visible from this position is predetermined and can generally be predetermined constant or variable depending on the flight data of the flying object 30. The period of time can be selected to be as short as possible, for example between 0.5 minutes and 2 minutes, so that tracking can start quickly and last as long as possible while the reconnaissance missile 2 descends within the atmospheric layer 45. Depending on the distance of the reconnaissance missile 2 from the flying object 30 and / or a reasonable tracking period, the period of time can also be selected to be longer, for example up to 5 minutes. The reconnaissance missile 2 is launched from the launch platform 42, reaches position 44 and shoots beyond it.The launch rocket engine 24 can be extinguished before or after reaching position 44. In any case, after extinguishing, the reconnaissance missile 2 remains in an ascent phase that extends to a zenith 46 of its trajectory 48. The zenith 46 can be in the uppermost third of the atmospheric layer 45 or above the atmospheric layer 45. From all locations along the trajectory 48 above a visibility point, which can be in position 44 or at a different location, since the reality of visibility does not have to match the prediction, the flying object 30 is now visible to the reconnaissance missile 2, and the IR sensor 10 detects the flying object 30, whose expected flight direction is known from the tracking data of the monitoring unit 38. Before the operation of the seeker head 8, a hood can be dropped in front of the seeker head 8, which thermally protects the seeker head 8 and thus increases its sensitivity.Position 44 is communicated to reconnaissance missile 2 as a location or arrival time, so that it knows from where or when it can see the flying object 30. As soon as the flying object 30 is detected by reconnaissance missile 2, the reconnaissance missile 2 tracks the flying object 30 and transmits the resulting tracking data. These are received, for example, by a central location and further processed or forwarded.

[0040] The central station calculates from the tracking data and at least one location of an interceptor missile 50 an optimal engagement or interception time or interception location 52 at which the interceptor missile 50 can reach and intercept the flying object 30. From the interception location 52 and the expected flight data of the flying object 30, a launch time for the interceptor missile 50 is determined, and it is launched at the launch time from a launch platform 42. The launch platform 42 can be the same from which the reconnaissance missile 2 was launched. In the example from FIG 2 it is another. The interceptor missile 50 reaches the interception site 52 and intercepts the flying object 30.

[0041] To guide the interceptor missile 50 to the flying object 30 as precisely as possible, the interceptor missile 50 receives tracking data via a data link 54 directly from the reconnaissance missile 2 and independently determines a guidance to the flying object 30 from this. This guidance is regularly updated until the time of interception based on the tracking data that is regularly or continuously sent from the reconnaissance missile 2 to the interceptor missile 50. To further refine the guidance, the interceptor missile 50 also receives tracking data from the monitoring unit 38 via a data link 56. In this way, the combined tracking data results from two different observation directions of the flying object 30, so that the flight data of the flying object 30, such as its position, flight direction and, if applicable, flight speed, are precisely recorded by the interceptor missile 50, allowing it to precisely guide itself.The data fusion of the two tracking data sets can take place in the interceptor missile 50, so that the flight data, or a portion thereof, is only generated in the interceptor missile 50. Alternatively or additionally, the data fusion can take place in a central location, so that the flight data is determined there and made available to the interceptor missile 50.

[0042] It is possible that the interception of the flying object 30 fails. To be able to detect this quickly, the reconnaissance missile 2 continues to track the flying object 30 even after an expected interception time. The interception is monitored, and the success of the interception is classified. If the interception is classified as a failure, this is transmitted by the reconnaissance missile 2 and received, for example, by a central location, such as a fire control center. Using the current tracking data from the reconnaissance missile 2, another interceptor missile 50 is launched. FIG 2 The first interceptor missile 50 is shown in flight to an interception location 52. A further interceptor missile 50 is also shown, which is still located on the launch platform 42. This can now be launched. Its control, detection, and tracking of the flying object 30 can be carried out in a similar way to that described for the first interceptor missile 50. The second interceptor missile 50 reaches its interception location 55 and either intercepts the flying object 30 or misses it. If the interception fails again, another interceptor missile 50 can be launched. All interceptor missiles 50 are fed with tracking data from the reconnaissance missile 2 and are thus directed to the flying object 30.

[0043] During the tracking of the flying object 30 by the reconnaissance missile 2, it may become apparent that the flying object 30 is not an intercept target that is to be intercepted, but rather a false object that is not to be engaged. Based on tracking data, the reconnaissance missile 2 can classify the flying object 30 as a false object. Alternatively, this can be done by a central location. However, the reconnaissance missile 2 continues to track the flying object 30 even after classification until it visually disappears.

[0044] It also scans the surrounding area for other flying objects in order to track them if they appear and are detected.

[0045] In order to track the flying object 30 for as long as possible, the reconnaissance missile 2 should remain in the atmospheric layer 45 for as long as possible. Since the descent through the atmospheric layer 45 occurs relatively quickly due to the thin atmosphere, one or more descent brakes 20 can slow the descent. Examples of descent brakes 20 are shown in the following FIGS.

[0046] In the FIG 3 In the embodiment shown, the descent brake 20 contains a parachute that brakes the descent. The descent brake 20 is activated at the zenith 46 of the flight path 48; in this case, the parachute is ejected and the reconnaissance missile 2 descends hanging from the parachute. If the engine stage 4 is separated by the stage separation 22, only the main part 6 of the reconnaissance missile 2 hangs from the parachute. The position of the reconnaissance missile 2 lies in the atmospheric layer 45, i.e. usually below the flying object 30, which is being observed against the cold starry sky. It is therefore generally sensible for the reconnaissance missile 2 to hang from the descent brake 20 in such a way that its seeker head 8 can point upwards. For this purpose, the descent brake 20 is positioned and / or configured so that the seeker head 8 can point vertically upwards in order to be able to track an overflying flying object 30.The descent brake 20 can be designed so that a stay of at least 20 minutes, in particular at least 30 minutes, in the atmospheric layer 45 is achieved.

[0047] In the example from FIG 3 the main part 6 hangs diagonally on the parachute with the seeker head 8 pointing diagonally downwards. It is also possible to orient the seeker head 8 diagonally upwards in order to keep the squint angle small. So that the parachute obscures as little of the field of view as possible, it can be spaced at a greater distance than usual from the reconnaissance missile 2 or its main part 6, for example more than 20 m with its nearest parachute edge, in particular more than 50 m. When hanging diagonally, the flying object 30 may fly behind the reconnaissance missile 2, so that it cannot be tracked by the seeker head 8. To avoid this, gliding wings 28 or other guidance units can be provided which rotate the reconnaissance missile 2 in the air, expediently controlled by the control unit 16. For this purpose, the wind present due to the falling speed can be used, which is deflected by the guidance units and converted into a rotational movement of the reconnaissance missile 2 or main part 6.The orientation of the seeker head 8 can be adjusted to follow the movement of the flying object 30 so that it always remains in the field of view of the IR sensor 10 or seeker head 8 and continuous tracking is possible.

[0048] Even in the embodiment shown in FIG 4 an engine stage 4 is separated from the main body 6 of the reconnaissance missile 2, but includes its own seeker head 8, for example at its tip, as in FIG 4 is shown. Engine stage 4 and main part 6 each form a reconnaissance unit, which separately detects and tracks the flying object 30. Both reconnaissance units each have a descent brake 20; engine stage 4, for example, has a parachute, and main part 6, for example, has gliding wings 28, or vice versa. While one reconnaissance unit descends on a parachute, the other glides with gliding wings 28 and thus moves away from the first, increasing their distance, expediently by at least a quarter of the vertical portion of the descent distance of the gliding reconnaissance unit. The flying object 30 is tracked from two directions; tracking data is generated from both directions, which can be converted into more precise tracking data or flight data of the flying object 30 through data fusion.The data fusion can take place in a central unit or, better, in the interceptor missile 50, which is conveniently connected to both reconnaissance units by direct data links 58, as shown in . FIG 4 is shown. The interceptor missile 50 identifies itself using the fused data and intercepts the flying object 30.

[0049] Alternatively or in addition to the two reconnaissance units, two or more reconnaissance missiles 2 can be launched, each having, in particular, two or more reconnaissance units, for example as described above. The reconnaissance missiles 2 fly to different positions 44 in the atmospheric layer 45, from which they can detect the flying object 30. The horizontal distance between the positions 44 is expediently more than one-third of the height of the upper position 44 so that the observation directions are as different as possible. The position 44 of the reconnaissance missile 2 or the positions 44 of two or more reconnaissance missiles 2 can depend on a selected descent range of the respective reconnaissance missile 2 so that a reconnaissance missile 2 or its reconnaissance units land over uninhabited areas as far as possible. List of reference symbols

[0050] 2 Scout missile 4 Engine stage 6 Main body 8 Seeker head 10 IR sensor 12 Navigation unit 14 Energy storage unit 16 Control unit 18 Communication unit 20 Descent brake 22 Stage separation 24 Launch rocket engine 26 Steering vane 28 Gliding vane 30 Flying object 32 Target 34 Earth's surface 36 Flight path 38 Surveillance unit 40 Data link 42 Launch platform 44 Position 45 Atmospheric layer 46 Zenith 48 Flight path 50 Interceptor missile 52 Interception site 54 Data link 55 Interception site 56 Data link 58 Data link

Claims

1. A method for guiding an interceptor missile (50) towards an approaching flying object (30), in which a reconnaissance missile (2) is launched and brought into an IR-permeable atmospheric layer (45) suitable for long-range IR reconnaissance, where it tracks the flying object (30) with an IR sensor (10) and transmits tracking data of the flying object (30), and the interceptor missile (50) is guided towards the flying object (30) using the tracking data, characterized by that the reconnaissance missile (2) is rocket-engine driven and tracks the flying object (30) when the launch rocket engine (24) is extinguished.

2. Method according to claim 1, characterized by that a flying surveillance unit (38) has tracked the flying object (30) and determined tracking data of the flying object (30) and the reconnaissance missile (2) is launched depending on the tracking data and is directed towards the flying object (30) on the basis of the tracking data.

3. Method according to claim 1 or 2, characterized by that the launch of the reconnaissance missile (2) is carried out from a position (44) within the atmospheric layer (45) as a function of an expected visibility of the flying object (30) in such a way that the reconnaissance missile (2) reaches the position (44) within a predetermined period of time before the expected visibility.

4. Method according to one of the preceding claims, characterized by that the reconnaissance missile (2) ejects an engine stage (4) and descends into the atmospheric layer (45) without the engine stage (4).

5. Method according to one of the preceding claims, characterized by that the reconnaissance missile (2) reaches a position (44) of probable visibility of the flying object (30), continues to ascend when the launch rocket engine (24) is extinguished, and detects the flying object (30) with the launch rocket engine (24) extinguished during ascent.

6. Method according to one of the preceding claims, characterized by that the flying object (30) is classified as an intercept target or a false object, the reconnaissance missile (2) searches the surroundings for further flying objects (30) and monitors the flying object (30) until it visually disappears.

7. Method according to one of the preceding claims, characterized by that the reconnaissance missile (2) descends into the atmospheric layer (45) using a descent brake (20), wherein the descent brake (20) contains at least one element from the following group: parachute, gliding wing, rotary wing, second propulsion, balloon.

8. Method according to one of the preceding claims, characterized by that a central station uses the tracking data of the reconnaissance missile (2) and tracking data of another monitoring unit (38) to determine flight data of the flying object (30) and directs the interceptor missile (50) to the flying object (30).

9. Method according to one of the preceding claims, characterized by that a second rocket-engine-driven reconnaissance missile (2) is launched separately and brought into the IR-permeable atmospheric layer (45), where it tracks the flying object (30) with an IR sensor (10) when the launch rocket engine (24) is extinguished, and the interceptor missile (50) is guided to the flying object (30) using the tracking data from both reconnaissance missiles (2).

10. Method according to one of the preceding claims, characterized by that the reconnaissance missile (2) introduces at least two reconnaissance units into the atmospheric layer (45), the two reconnaissance units move away from each other, both track the flying object (30) and transmit tracking data of the flying object (30).

11. Method according to one of the preceding claims, characterized by that the launch of the reconnaissance missile (2) and the interceptor missile (50) takes place from the same launch platform (42).

12. Method according to one of the preceding claims, characterized by that there is a direct data link (54) between the reconnaissance missile (2) and the flying interceptor missile (50) and the interceptor missile (50) uses data from the reconnaissance missile (2) to guide itself to the flying object (30).

13. Method according to one of the preceding claims, characterized by that the reconnaissance missile (2) monitors the success of an interception of the flying object (30) and, in the event of a failed interception, a launch platform (42) is selected from among several using the monitoring data, a further interceptor missile (50) is launched from this launch platform (42) and is guided to the flying object (30) using the tracking data.

14. A reconnaissance missile (2) with an IR sensor (10) and a control unit (16) which is designed to control a flight into an atmospheric layer (45), to track a flying object (30) from there and to send tracking data of the flying object (30) to an interceptor missile (50) for its guidance to the flying object (30), marked through a launch rocket engine (24), wherein the control unit (16) is configured to track the flying object (30) when the launch rocket engine (24) is extinguished in a descent phase in the atmospheric layer (45).

15. System comprising a reconnaissance missile (2) according to claim 14 and an interceptor missile (50) which is designed to independently guide the aircraft to an approaching flying object (30) from tracking data of the reconnaissance missile (2).

Images