Patent Grant
8674276
This invention relates to exo-atmospheric interception of inflatable flying objects.
Ballistic missiles which hit a friendly territory have become a significant threat and accordingly tremendous efforts have been invested to develop interception measures which facilitate interception of the oncoming missile at various flight stages such as Boost phase, Exo-atmospheric phase or Atmospheric stage (when the Ballistic missile threat re-enters the atmosphere). Various approaches have been offered and systems have been developed in order to intercept the Ballistic missiles in space, before they enter the atmosphere. This trend led to the development of counter measures (CM) in order to hinder the intercepting missiles to hit and destroy ballistic missiles in space. Amongst the numerous proposed CMs are decoys integrated with Multiple Reentry Vehicles (MRV) that are accommodated in the attacking ballistic missile, of which a few may be decoys. Thus, in a typical scenario, a ballistic missile may release, at certain stage in space, multiple objects, a few of which may be warheads or others such as decoys. In accordance with advanced counter measure solutions, the released objects are inflatable. This has a few inherent advantages from the standpoint of the ballistic missile. Thus, the main ballistic missile platform may accommodate a plurality of objects in a relatively small volume considering the fact that the inflatable objects are each stored in a wrapped form of a small dimension within the missile. The inflatable objects are inflated to a larger dimension only upon release from the ballistic missile's compartment to space. In addition, inflatable objects are, naturally, of relatively low weight, thereby facilitating accommodation of a plurality of them in the constrained scenario of limited payload that is often posed on a ballistic platform that is launched to space. The net effect is thus that a single ballistic missile can release in space a plurality of flying objects. Considering further that the inflatable objects (some or all of which are decoys) can be a priori designed to have shape and flight dynamics that resemble a true warhead, it readily arises that the interceptor missile which is designated to kill the threat by a direct hit is faced with a significant challenge to discern between the decoys and true warhead threats and focuses on tracking and homing onto the real threats rather than the decoys. It is inherently assumed that even if the interceptor employs multiple kill vehicles (MKV) it does not employ enough vehicles to target each and every inflatable object, whether a decoy or a real threat, and therefore the need to discern between a decoy and a threat is so important.
A system of this kind that releases multiple inflatable objects is, for instance, the known Minitment US system.
In the last few years the Russians have introduced an even more advanced CM system (e.g. the Russian Topol-M system), where a few of the inflatable objects accommodate, each, a longitudinal warhead having smaller dimensions than that of the hosting inflatable object. Thus, even if a vehicle, from among the MKVs of the interceptor, successfully hits an inflatable object of the kind specified and punches it, the longitudinal warhead concealed therein will remain intact and will continue to fly in its designated flight trajectory towards the friendly territory, which is obviously undesired.
The introduction of CM solutions of the kind specified may lead to shifting the efforts of hitting the target missile in space and focus again on the boost and atmospheric stages. Whilst the focus on the specified boost and re-entry stages may achieve the desired results of intercepting a target missile (or its RVs), it is still desired to have an effective intercepting system which will facilitate successful interception in the space of a target ballistic missile that employs a plurality of inflatable objects. As is well known, utilizing an efficient multi-layer solution designed to destroy ballistic missile threats at boost phase or in space or in atmosphere re-entry stage is important in order to reduce the prospect of target leakage to substantially zero, considering the dire consequences that may occur if a target missile, e.g. employing nuclear warhead, hits a friendly territory. Accordingly, there is a need in the art to provide for a Counter-Counter measure (CCM) system which is capable of overcoming CM solutions of the kind specified.
There is still further need in the art to employ a CCM system which facilitates successful kill of attacking missiles which utilize a plurality of inflatable objects that are released in space and in which a few or all of the inflatable objects conceal therein a warhead targeted towards a protected area.
There is still further need in the art to provide for a two phase CCM system which in a first phase will destroy in space the inflatable objects and in a second phase will destroy the flying warheads that were concealed in the inflatable objects.
In accordance with an aspect of the invention there is provided an exo-atmospheric intercepting method for intercepting in space multiple objects, comprising
In accordance with an embodiment of the invention, there is provided a method, wherein the ejection condition includes orientation of the warhead towards the cluster.
In accordance with an embodiment of the invention, there is further provided a method wherein the ejection condition further includes determination of modified flight trajectory of the interceptor towards the cluster.
In accordance with an embodiment of the invention, there is further provided a method wherein the ejection condition further includes evaluation of volume uncertainty.
In accordance with an embodiment of the invention, there is still further provided a method wherein the ejection condition further includes evaluation of time uncertainty.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the interceptor employs an Attitude Control System (ACS) that facilitates rotation of the interceptor, constituting a further parameter of ejection condition.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the ejection condition prescribes the release timing of the punching object from the kill vehicle.
In accordance with an embodiment of the invention, there is still further provided a method, wherein (c) includes utilizing an external station for classifying the multiple objects into at least one cluster and communicating the cluster data to said interceptor missile.
In accordance with an embodiment of the invention, there is still further provided a method, wherein (d) includes utilizing an external station for determining the ejection condition and communicating the ejection condition data to the interceptor missile, for ejecting the kill vehicle responsive to meeting the ejection condition.
In accordance with an embodiment of the invention, there is still further provided a method, wherein (c) is performed in the interceptor missile.
In accordance with an embodiment of the invention, there is still further provided a method, wherein determining the ejection condition is performed in the interceptor missile.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the at least one of inflatable objects accommodates a Reentry Vehicle (RV), such that the flight characteristics of the at least one inflatable object resemble the flight characteristics of another inflatable object that does not accommodate an RV.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the punching object being longitudinal fiber optics having a density larger than the density of the surface of the inflatable object.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the classifying includes, determining at least two objects that are launched from a given platform and classifying them to a cluster of objects.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the determining includes performing backtracking to the at least two objects in order to determine whether they originate from the same missile.
In accordance with an embodiment of the invention, there is still further provided a method, further comprising: detecting and tracking objects that proceed to fly towards protected territory following the punching stage and launching at least one interceptor missile towards at least one of the objects.
In accordance with an embodiment of the invention, there is still further provided a method, wherein (a) includes classifying any tracked suspected inflated object into corresponding inflated object.
In accordance with an embodiment of the invention, there is still further provided a method, wherein the suspected inflated object is classified as an inflated object if it has a flat or substantially flat RCS.
In accordance with an aspect of the invention there is provided a two phase exo-atmospheric intercepting method for intercepting in space multiple objects, comprising:
In accordance with an aspect of the invention there is provided a two phase exo-atmospheric intercepting method for intercepting in space multiple objects, comprising
In accordance with an aspect of the invention there is provided a two phase exo-atmospheric intercepting method for intercepting in space multiple objects, comprising:
In accordance with an aspect of the invention there is provided an exo-atmospheric intercepting system for intercepting in space multiple objects, comprising
In accordance with an embodiment of the invention, there is still further provided a system, the interceptor employing at least one warhead having compartments each accommodating a killing vehicle.
In accordance with an aspect of the invention there is provided a two phase exo-atmospheric intercepting system for intercepting in space multiple objects, comprising
a first phase interception system being configured to:
In accordance with an aspect of the invention there is provided a two phase exo-atmospheric intercepting system for intercepting in space multiple objects, comprising:
In order to understand the invention and to see how it may be carried out in practice, a preferred embodiment will now be described, by way of non-limiting example only, with reference to the accompanying drawings, in which:
Turning now to
Note that the cluster of inflatable objects includes decoys (designated collectively as 9′) and an RV 9″. The inflatable objects 9′ are inflated (e.g. by utilizing a central pneumatic system or a designated reservoir fitted in each of the objects) upon discarding the shroud and the RV 9″ is wrapped with inflatable skin which inflates. The inflated objects, whether a real threat or a decoy, have similar characteristics and have the same RCS (referred to also occasionally also as RF signature) and IR signatures. In accordance with certain embodiments the inflatable objects are balloons.
The initial velocity acquired to each inflatable object will eventually result in that each object flies along a distinct flight trajectory giving rise to a wide spatial spread when the warheads accommodated within inflatable objects eventually hit the protected area 2, thereby hindering a defense system that is designated to intercept them as they re-enter the atmosphere during their final flight stage.
The inflatable objects are either decoys, or they may conceal inside an active RV. For instance, balloons 11 and 12 are decoys whereas balloon 13 conceals an RV 14, obviously having a smaller dimension than the hosting balloon. Note that more than one balloon may accommodate an RV, as the case may be.
In accordance with known multi RV missiles of the kind specified (e.g. the Topol_M system), it is very difficult to discern between a decoy and a real threat (an inflatable object concealing and RV) because the flight characteristics of a decoy and real threat are very similar, namely similar shape, similar Radar Cross Section (RCS) and similar IR signature. Note that an inflatable object that conceals a real threat has the same IR and RF signatures as a dummy inflated object as a result of the special design and material of which the inflatable object is composed. The specified known materials may lock any heat that is dissipated inside the balloon (as a result of the hosted RV) such that the external IR signature is the same as a dummy balloon and likewise the balloon (accommodating an RV) is so designed to have an IR signature that is identical to that of a dummy balloon.
The identical flat RCS of the various objects, whether a decoy or a balloon concealing an RV, is illustrated in
Note, incidentally, that typically the enemy would launch one or more salvos of missiles each including many inflatable objects of which some are decoys and others are RVs. Typically the defense system cannot send a corresponding number of intercepting warheads each designated towards a given inflatable object, and therefore there is a need, notwithstanding the specified limitations, to discern between a real vehicle and threat.
Note that the invention is not bound by targeting a ballistic missile type of the kind described by way of example only with reference to
Turning now to
Thus, after having been released from the ballistic missile and after having been inflated, the inflated objects deviate from the original flight trajectory of the ballistic missile, gaining distance one with respect to the other. The fact that the inflated objects are spaced apart one with respect to the other (as shown in area 31) poses an operational constraint in that they cannot be destroyed by a kill vehicle that will release a salvo of punching objects since the latter cannot embrace the entire area of the inflated objects and accordingly a series of kill vehicles should be ejected each designated towards a cluster of one or more inflated objects that reside in a smaller area, all as will be explained in greater detail below. Before moving on it should be noted that the two phase interception system of the invention focuses on inflatable objects because the latter may conceal real warheads. In the case that the so tracked objects are classified as conventional warheads, the latter are subjected to known per se interception techniques that are designated to acquire track and destroy multiple Reentry Vehicle (RV) threats. In accordance with certain embodiments, the discerning between a real warhead and an inflatable object such as a balloon (whether concealing a warhead or not) is determined by the RCS. Thus, an inflatable object may have a flat or substantially flat RCS, whereas a true warhead has a non-flat RCS. Accordingly, by this embodiment, a suspected inflatable object is classified as an inflatable object or not, according to its RCS.
Bearing this in mind, attention is reverted to
By this particular example each cluster includes a single inflated object, but those versed in the art will appreciate that the invention is not bound by this particular example.
Note that in accordance with certain embodiments, (i) the detection and tracking of the ballistic missile, (ii) the tracking of the clusters of inflated objects released therefrom, (iii) the calculation of the flying trajectory of the intercepting missile 300 (iv) the calculation of the ejection condition of the kill vehicles towards their respective target cluster of inflated objects, are all performed at the ground station using for instance Radar sensors 310. The data that pertains to the flight trajectory of the intercepting missile 300 as well as the timing data and direction of eject of the kill vehicles from the interceptor missiles, are all communicated to the interceptor missile, using known per se communication means.
After having punched the inflatable object, it appears that one of them concealed an RV 311. Note that the RV 311 could not have been revealed when accommodated within an inflated object, since the latter had substantially identical flight characteristics as the other inflated objects, including by way of example, the same shape, IR signature and RCS. The tracking and destruction of the revealed RV is performed by a second phase defense system. Thus the approaching RV 301 is detected and tracked, and responsive thereto, a second interceptor missile 312 is launched into a collision trajectory for eventually hitting the oncoming RV 311 at interception point 314. Note that the operation of the second phase defense system is generally known per se and therefore will not be expounded upon herein.
Turning now to
Note, incidentally, that the set of diverging clusters of inflated objects 401 embraces a considerably larger uncertainty volume of the order of 107 m3, and accordingly the prospects of hitting all the inflated objects by one salvo of punching objects is simply infeasible since a single killing vehicle that is ejected from the intercepting missile cannot accommodate such a large number of punching objects. Consequently, in accordance with certain embodiments, in order to destroy all of the inflatable objects, each cluster of inflatable objects is targeted separately. Thus, a first kill vehicle is ejected at a given location and timing, towards cluster 400. The kill vehicle employs a plurality of punching objects which are designated, as explained in detail above, to kill all or substantially all of the inflatable objects that constitute the specified cluster. Thereafter, another killing vehicle is ejected at a specified timing and location towards a different cluster, say 402 and the punching objects accommodated therein are released towards the inflatable objects of cluster 402 for destroying all or substantially all of them. The procedure is then repeated in respect of all other clusters 403 and 404 each time utilizing a different kill vehicle. The end result would then be that all or substantially all of the inflatable objects that originate from the launched ballistic missile (say 2 of
Turning now to
Those versed in the art will readily appreciate that the numeric examples described with reference to
Bearing this in mind, attention is drawn to
It is recalled that there may be an initial stage of classifying suspected inflatable objects into concealing warheads or not, e.g. according to their RCS. The description with reference to
Reverting now to
Note that in accordance with certain embodiments, the orientation of the warhead, the determination of modified trajectory and the evaluation of volume and time uncertainty, constitute parameters of the ejection condition for determining the timing of ejecting the kill vehicle. Note that the invention is not bound by the specified parameters and other(s) may be added or certain parameter(s) may be modified or ignored. In accordance with certain embodiments, the determination of the ejection condition is performed at an external station (e.g. a ground station), all as will be explained in greater detail below. Note also that although not shown in the Figs, the warhead may employ, e.g. a known per se ACS (Attitude Control System) which facilitates a motion of the kill vehicle relative to the warhead, thereby allowing a further degree of freedom for orienting the kill vehicle towards its target before it is ejected. The ejection direction of the vehicle towards the target (owing to the ACS that allow orientation of the vehicle relative to the warhead) may facilitate a parameter of the ejection condition.
After having targeted the first cluster 601 (resulting in destroying all or substantially all of the inflatable objects), the second cluster 602 is targeted. This may require re calculation of the ejection condition including time and volume uncertainties as well as re modified flight trajectory, e.g. by virtue of the different relative locations between the warhead and the second cluster 602 and possibly also different closing velocity between the warhead and the flying objects of the second cluster.
The re-modified flight trajectory for the intercepting warhead 68, as the ejection timing and the ejection direction of the second kill vehicle 69 are then determined and communicated from the ground station to the intercepting warhead and are implemented thereby for destroying the inflatable objects of the second cluster. This procedure is repeated in respect of the third to fifth cluster each time determining a different flight trajectory (if necessary) and an ejection timing of the corresponding kill vehicle.
Note that whereas in the various embodiments described herein the term ground station is used, this is only one example of an external station. The latter can be by way of non-limiting example, a space station.
Note that whilst in the embodiments discussed above, the parameters that form part of the stipulation of the ejection timing are the volume and time uncertainties, those versed in the art will readily appreciate that the invention is not bound by these parameters and accordingly the specified parameters may be modified and/or others may be added, all as required and appropriate.
Note also that the description with reference to
It is accordingly appreciated that a particular embodiment e.g. where the logic resides in the external (e.g. ground station), or all of the logic (including sensors, e.g. radar sensors) is accommodated partially or wholly in the intercepting missile, is selected depending upon the particular application and possibly operational constraints.
Attention is now drawn to
Note that the invention is not bound by the specific architecture of the kill vehicles within the warhead, as depicted in
Note also that each killing vehicle accommodates a plurality of punching objects that may be placed in neighboring compartments (not shown in
Attention is now drawn to
Attention is now drawn to
Note that the invention is neither bound by the split into the various sequences, nor by the stages of each sequence.
Bearing this in mind, the first interception system acquires the target(s) 901 and classifies them into clusters of inflatable objects 902. The acquisition and classification can be performed before releasing of the inflatable objects from the target missile or afterwards. In a scenario where the classification is performed before release, an exemplary logic may dictate that all of the inflatable objects that will be released from the missile will be classified as a single cluster. As may be recalled, there may be an initial stage of classifying suspected inflatable objects into concealing real warheads or not, e.g. according to their RCS. The description with reference to
Reverting to
Turning now to sequence 91, the launched platform determines the timing of ejection of the kill vehicle towards the first cluster 911 (upon meeting the ejection condition), based on considerations that were described in detail above, and ejects the kill vehicle 912. Appropriate reorientation, trajectory modification and ejection timing are calculated in respect of the next kill vehicle 913 and the latter is ejected towards the target 914. The procedure is then repeated in respect of additional kill vehicle(s) each targeting another cluster of inflatable objects.
Turning now to sequence 92, at a certain timing the kill vehicle that is flying towards a given cluster of inflatable objects releases a salvo of punching objects 921 and in pre-defined timings, additional salvos (922, 923) of punching objects are released all as described in detail with reference to
Having punched the inflatable objects, all those that constitute a decoy will be dispersed in space and pose no threat. The inflatable objects which concealed therein a Reentry Vehicle (RV) will, upon being punched, reveal the RV and the latter will be detected by the second phase interception system 931. The latter operates in a known per se manner for destroying incoming RVs, e.g. plans an interception trajectory and updates and launches the interception missile (932 and 933), Any necessary trajectory updates will be communicated to the launched interception missile 934 followed by known per se homing and end game 935 and 936 stages for destroying the oncoming RV.
Turning now to
Note that the logic described with reference to
Note also that in accordance with certain embodiments, certain portions of the first and second phase systems may be shared, e.g. the acquiring and tracking means.
Note also that in accordance with certain embodiments certain stages that are performed in the external station may, in other embodiments, be performed at the interceptor missile and vice versa.
As used herein, the phrase “for example,” “such as” and variants thereof describing exemplary implementations of the present invention are exemplary in nature and not limiting. Reference in the specification to “one embodiment”, “an embodiment”, “some embodiments”, “another embodiment”, “other embodiments” “certain embodiment(s)” or variations thereof means that a particular feature, structure or characteristic described in connection with the embodiment(s) is included in at least one embodiment of the invention. Thus the appearance of the phrase “one embodiment”, “an embodiment”, “some embodiments”, “another embodiment”, “other embodiments” “certain embodiment(s)” or variations thereof do not necessarily refer to the same embodiment(s). It is appreciated that certain features of the invention, which are, for clarity, described in the context of separate embodiments, may also be provided in combination in a single embodiment. Conversely, various features of the invention, which are, for brevity, described in the context of a single embodiment, may also be provided separately or in any suitable sub-combination. While the invention has been shown and described with respect to particular embodiments, it is not thus limited. Numerous modifications, changes and improvements within the scope of the invention will now occur to the reader. In embodiments of the invention, fewer, more and/or different stages than those shown in
Note that the order of the stages in the following Claims are not necessarily binding, for instance the order to stages (b) and (c) in the following Claim 1 may be switched. The same holds true for orders of operations of elements in following system claim.
The present invention has been described with a certain degree of particularity, but those versed in the art will readily appreciate that various alterations and modifications may be carried out without departing from the scope of the following claims:
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