This invention relates to external stores carried on vehicles, especially air vehicles.
There are a wide variety of aircraft and other vehicles (for example land or sea faring vehicles) for which low observability (LO), particularly in terms of radar signature (typically measured in terms of Radar Cross Section—RCS), is important. Such aircraft or vehicles are sometimes referred to as stealth aircraft or vehicles. For example, U.S. Pat. No. 5,250,950 discloses a vehicle in free space or air, with external surfaces primarily fashioned from planar facets. The planar facets or panels are angularly positioned to reduce scattered energy in the direction of the receiver. In particular, radar signals which strike the vehicle are primarily reflected at an angle away from the search radar or are returned to the receiver with large variations of amplitude over small vehicle attitude changes.
External stores may present an undesirable radar signature for such LO aircraft and other aircraft, and this has been addressed in a number of ways including: storing the stores internally rather than externally; and enclosing the stores in an openable low radar signature tube. For example, U.S. Pat. No. 4,829,878 discloses an apparatus for carrying stores such as missiles and the like in a manner which permits the stores to be selectively deployed from a conformal or semi-conformal carriage position, with respect to a mobile vehicle, such as an aircraft, to a launch position from which the stores may be selectively launched, and including apparatus for selectively jettisoning the stores. In EP 1375345, a system is disclosed having a number of control units, some of which are for separating the lower longitudinal part of the low radar signature tube from the top part which is connected to the external body of the aircraft via a pylon, such that it creates in the tube, by its separation, an opening allowing the complete ejection of the missile. The weapon system is carried by a stealth aircraft, and is said to have a low radar signature tube which is radar absorbing, with a missile located inside this tube.
According to a first aspect of the invention, an external stores system, comprising a cluster or assembly of external stores, is provided that provides low observability (LO), in particular low signature including radar signature (e.g. in terms of RCS) and/or optical signature (avoiding glinting in diffuse directions, for example), and/or is attached to a carrier vehicle such as an aircraft, for example in a conformal manner.
Accordingly, the invention relates to an external store system for a carrier vehicle, comprising:
In one embodiment, each said external store element comprises at least two substantially planar side walls joined to a substantially planar base, and a nose section comprised of a plurality of facets. Each said external store element may also comprise a plurality of deployable fins. Carriage lugs are also provided.
Each said external store element may comprise any one of a bomb, electronic or other pod, fuel tank, and the like.
The present invention also relates to an external store assembly for a carrier vehicle comprising an external store system according to the invention, in particular as set out above, said assembly being formed by a plurality of said elements arranged as pairs of juxtaposed adjacent elements, wherein a side surface of one element is facing a side surface of a juxtaposed adjacent element. In one embodiment, the elements each have a substantially triangular transverse cross section, though in other embodiments, the cross-sections may be of a different shape, for example polygonal, or indeed any other shape that provides a conformal configuration with respect to adjacent like elements. In one particular embodiment, particularly in which the elements comprise a triangular cross-section, the assembly comprises three said elements in side-by-side or juxtaposed relationship, providing a composite semi-hexagon configuration for the cross-section of the assembly. The mounting arrangement may comprise suitable lugs comprised on said side walls. In one particular embodiment, the elements each comprises a ridge transversely opposed to said base, and said mounting arrangement comprises suitable lugs comprised on said ridge.
In particular, the assembly may be configured such that facing side walls of each pair of adjacent said elements are in abutting contact such as to provide electrical continuity between said elements. Further in particular, facing free edges of facing side walls of each pair of adjacent said elements are in abutting contact such as to provide electrical continuity between said elements, which also provides continuity between the aerodynamic surfaces. In other embodiments, the facing side walls of each pair of adjacent said elements comprise a gap therebetween, and the assembly further comprises a suitable filler material or gasket accommodated in said gap, in particular at the facing edges, such as to provide electrical and optionally aerodynamic continuity between said elements.
The assembly may be mounted directly to a surface of said vehicle, particularly in a conformal manner with respect thereto. The assembly may be configured for providing electrical continuity with said vehicle when mounted directly to a surface of said vehicle, and the assembly may comprise a mating surface comprising said side walls of at least two said elements, and wherein said vehicle surface is substantially complementary to said mating surface. The assembly may comprise a mating surface comprising said side walls of at least two said elements, wherein said mating surface forms a gap with a vehicle surface when said assembly is mounted thereto: said assembly further comprises a suitable filler material or gasket accommodated in said gap such as to provide electrical continuity between said assembly and said vehicle surface.
Alternatively, the assembly may be mounted to said vehicle via a pylon arrangement.
In described embodiments, the mounting arrangement is configured for enabling selective and/or sequential deployment of individual said elements from said assembly. For example, the assembly may comprise three said elements in side by side or juxtaposed arrangement comprising a port element, a starboard element and a middle element, and wherein said mounting arrangement is configured for deployment of said middle element first from said assembly. Further, the mounting arrangement may be configured for deployment of at least one of said port element and said starboard element from said assembly after deployment of said middle element.
Optionally, the facets of the elements may comprise RCS reducing properties.
According to a second aspect of the invention, an external stores system, comprising one or more external stores, is provided that provide low observability (LO), in particular low signature including radar signature (e.g. in terms of RCS) and/or optical signature (avoiding glinting in diffuse directions, for example), and/or aerodynamic conformality when attached to a carrier vehicle such as an aircraft, for example, such that there is electrical continuity and/or surface continuity, respectively, between the vehicle and the external store(s).
Accordingly, the invention also relates to an external store system for a carrier vehicle, comprising at least one external store element comprising a plurality of surfaces defining an exterior thereof, said surfaces comprising at least one facet; and
Each store element may be as disclosed above according to the aforementioned first aspect of the invention.
The present invention also relates to a carrier vehicle, comprising at least one external store system according to the first aspect of the invention, attached thereto.
The present invention also relates to a carrier vehicle, comprising at least one external store system or assembly according to the second aspect of the invention, attached thereto.
In either case, the carrier vehicle may comprise, for example, any one of an air vehicle such as an aircraft for example, water-borne craft, hovercraft, land vehicles, space vehicles. In some embodiments, the carrier vehicle is an aircraft, and the external store system or assembly is mounted to an underside or upper side of a wing or of a fuselage thereof, or indeed any other suitable external surface. Optionally, the carrier vehicle may be configured for minimizing RCS therefrom.
The present invention also relates to a method for carrying a plurality of external stores on a vehicle, comprising:
For some types of stores, step (a) may be replaced with the following step:-
The assembly may be mounted to said vehicle in a manner such as to maintain electrical continuity between the assembly and an adjacent external surface of the vehicle and/or aerodynamic conformity. In particular, electrical continuity and surface continuity is maintained between free edges of the assembly and an adjacent external surface of the vehicle.
The present invention also relates to a method for selectively deploying a plurality of external stores from a carrier vehicle, comprising:
selectively deploying a desired said element by disconnecting said desired said element from said assembly and/or said vehicle, while maintaining at least one of electrical continuity and aerodynamic continuity at least between remaining said elements of said assembly.
In particular, electrical continuity and/or aerodynamic conformality is maintained between free edges of the assembly and an adjacent external surface of the vehicle.
The present invention also relates to a method for carrying at least one external store on a vehicle, comprising:
For some types of stores, step (a) may be replaced with the following step:-
A feature of at least some embodiments of the invention, particularly for applications of the invention directed to mounting the assembly onto a surface of the carrier vehicle, where the carrier vehicle is aerodynamic, for example a non-stealth or a stealth aircraft, is that the assembly according to the invention provides aerodynamic advantages, in particular drag reduction, compared with that of the configuration obtained when mounting the elements separately and individually to the aircraft, for example in rows, columns, etc, or as compared with clusters, where such elements are not joined to one another and do not provide electrical continuity or aerodynamic conformality.
Another feature of at least some embodiments of the invention is that the external stores elements of an assembly according to the invention may be designed for minimizing RCS individually, as well as in an assembly, and/or when mounted to the carrier vehicle in conformal manner, without necessitating in many cases any modification of the external contours or aerodynamic shape of the vehicle, and in many cases making use of hard points or mounting points already existing in a fuselage or wing, for example. By way of example, an aircraft comprising pylons for carryings stores may be modified to carry an assembly or single element according to the invention by removing the pylon from the wing, and modifying the pylon attachment points on the wing structure to instead enable the assembly or element to be releasably mounted thereto.
Yet another feature of at least some embodiments is that the external store elements may be designed in a modular and conformal manner such that each element may occupy any position in the assembly according to the invention. On the one hand the elements may be mutually conformal one with another when in adjacent relationship in the assembly, either exclusively by virtue of having substantially complementary geometries in the mutually abutting areas thereof, or by having a suitable gasket material therebetween, in any case providing electrical continuity between the elements in the assembly. In particular, electrical continuity is maintained between free edges of the assembly and an adjacent external surface of the vehicle.
On the other hand the elements may be mutually conformal with respect to the aircraft surface (or any other surface of a carrier vehicle) when the assembly, or indeed parts thereof (for example after deployment of some elements of the assembly) are in adjacent relationship in the assembly, either exclusively by virtue of having substantially complementary geometries in the mutually abutting areas thereof, or by having a suitable gasket material therebetween, in any case providing electrical continuity between the assembly and the surface on which the assembly is mounted.
Electrical continuity herein means that electrical conductance between two adjacent components is provided, either by conforming the abutting components or surfaces with respect to one another to avoid gaps between components, or between surfaces thereof, or between edges thereof, or combinations thereof, or by providing a conductive material to fill the gaps between components or surfaces, wherein the open gaps would otherwise represent surface discontinuities that produce a noticeable radar cross-section. The electrical continuity provided between the surfaces or components significantly reduces the radar cross section with respect to that obtained in a comparable configuration comprising untreated gaps that do not provide such electrical conductance.
Herein, “conformal”, “aerodynamic conformality” and the like, in the context of an external stores element or an assembly thereof, for example, refers to the geometry of the geometric interface between such elements or assembly and the structure to which it is attached follows the contour or profile of that structure. Such an interface is thus appropriately contoured such as to provide aerodynamic continuity: between the separate external store elements within an assembly thereof; between the individual elements that are attached to a surface of a vehicle and the vehicle; between an assembly of said elements that is attached to a vehicle and the vehicle; and so on.
In order to understand the invention and to see how it may be carried out in practice, embodiments will now be described, by way of non-limiting example only, with reference to the accompanying drawings, in which:
a) to 8(c) schematically illustrate a deployment sequence for the embodiment of
a) to 11(c) illustrates in front view a deployment sequence for elements of
An external store system for a carrier vehicle according to an embodiment of the invention is illustrated in
In the embodiment of
Referring to
The stores element 20, in particular the externally facing surfaces 21, may be made from any suitable electrically conducting material, for example aluminium, or suitable composite materials.
Optionally, the externally facing surfaces 21 may be radar-absorbing and/or comprise a radar-absorbing coating. Thus externally facing surfaces 21 may be made from a radar-absorbing material or comprise a radar-absorbing material.
Thus, the element 20 may be considered as comprising a forward or nose section 32 longitudinally serially connected to, or integrally formed with, a center section 34 and an aft section 33, the nose section 32 and optionally also the aft section 33 having the form of a tetrahedron, and the center section having the form of a generally triangular prism.
Depending on the particular use or application of the external store element 20, the nose section 32 may house, for example, a guidance system and/or a radar system and/or a reconnaissance system. The center section 34 and/or the aft section 33 may accommodate, for example, a payload and/or a warhead and/or a reconnaissance system. Optionally, and in other variations of this embodiment, the center section 34 and/or the aft section 33 may comprise a propulsion system, such as for example a rocket motor, ramjet engine, turbojet engine, and so on, together with a suitable fuel system.
Optionally, and in other variations of this embodiment, the element 20 is adapted for carrying fuel or another liquid, and thus comprises an internal volume for accommodating the fuel/liquid, and a suitable outlet for connection to a fuel system, for example, of the vehicle 1. In embodiments where the element 20 is adapted for carrying fuel, the element 20 may comprise suitable vents and a suitable interface for connecting to electrical, fuel and pressurizing lines comprised in the vehicle 1, which is thus also suitably adapted for having such an element 20 attached thereto.
Optionally, and in other variations of this embodiment, the element 20 comprises a weapon such as a bomb or missile, for example, and comprises suitable ordinance, for example explosive material, biological chemical or nuclear payload, fuses etc., as required therefor. Optionally, and in other variations of this embodiment, the element 20 is adapted as a platform for launching ordnance such as for example missiles or other weapons, and comprises suitable bays/launching apparatus therefore within the element, with suitable openings (optionally recloseable), for example longitudinal openings or transverse openings, for enabling deployment of the ordnance.
The aft section 33 optionally further comprises a plurality of stabilizing and/or control fins, including a pair of side fins 35 and an upper fin 36. The fins 35, 36 are deployable from a retracted position, in which the fins 35 are flatly abutting the corresponding side wall 23 and the upper fin 36 is housed in aft facing recesses 38 accommodated in the element 20, to a deployed position (shown in phantom lines in
In any case, each element may comprise an external form that is aerodynamically compatible, and thus which induces the minimum drag possible, given the other constraints on its form, as disclosed herein, for example, while still having a faceted form.
Referring to
The middle element 20B may be attached to the vehicle 1, the lugs 42 being configured for cooperating with support hooks 47, for example, comprised on a carrier vehicle 1. Alternatively or additionally, the middle element 20B is reversibly attached to the adjacent elements 20A, 20C via the lugs 46 on facing pairs of side walls 23. For this purpose, and referring to
Alternatively, the elements 20 may be adjacently reversibly mutually attachable one to another without the need for said mating elements 49. For example, and referring to
According to an aspect of the invention, the assembly 50 is connected directly to a surface of the vehicle, for example an aerodynamic lifting surface, such as for example the underside or upper side of a wing or of a lifting body, or for example other parts of the vehicle such as a fuselage of the vehicle, when the vehicle is an aircraft for example, in a substantially pylonless or non-embedded manner, also referred to herein as a “conformal manner”, such that the assembly essentially “sits” on a mating surface of the vehicle, and moreover a clean aerodynamic profile of the vehicle 1 in the mounting area thereof is restored after deployment of the assembly 50.
This vehicle mating surface may be planar or aerodynamically contoured, for example, and the assembly 50 is connected directly to the vehicle loading points within the wing, fuselage and so on, via the mounting arrangement discussed above, for example.
Electrical continuity may be maintained naturally where the vehicle surface is substantially flat and a facing side wall 23 of the elements 20A, 20C are abutted against the vehicle surface, or where the facing surfaces between the elements 20A, 20C and the vehicle surface are geometrically complementary. Alternatively, a suitable electrically conducting filler material or gasket 64 may be provided between the facing side walls 23 of the elements 20A, 20C and the vehicle surface, so that the assembly 50 indirectly abuts the vehicle surface via the gasket/filler material. According to this aspect of the invention, a single external stores element may also be reversibly attached to an external surface of the vehicle 1, the external stores element comprising a plurality of faceted surfaces for providing low observability. For example, a single or a plurality of mutually unconnected elements 20 may be reversibly mounted to a surface of the vehicle 1 in a manner such as to provide electrical continuity with the vehicle surface, while fully projecting therefrom. Alternatively, other embodiments may be provided for a singly attachable external store element. For example, and referring to
Referring to
Thus, where the carrier vehicle comprises a relatively flat surface, the stores element(s) according to the described embodiments, having substantially flat side walls, may be directly mounted to the carrier vehicle surface in a conformal manner. In other carrier vehicles where no such suitable flat surface is available, an optional adaptor is provided having a vehicle facing surface that is complementarily contoured with respect to the particular surface of the vehicle onto which it is desired to mount the external stores, and a stores facing surface that enables the flat surfaces of the elements to be abutted thereto. Electrical continuity is maintained between the stores elements, adaptor and the vehicle surface as described herein, mutatis mutandis.
Optionally, and as illustrated in
Deployment of each of the elements 20 can be effected in a sequential manner, for example in a similar manner to that as described for the embodiment of
While the external stores assembly 50 has been described above in the context of three external stores elements of generally triangular cross section grouped together in a hemi-hexagon configuration (i.e., having a general transverse cross-section generally shaped as a half-hexagon), the invention is not restricted to such a configuration, and many other configurations are possible. For example, four such elements may be grouped together, each element having the cross-section generally similar to an isosceles triangle, with angle α being about 45° to provide a half-octagon as the composite cross-sectional area.
Alternatively, and as illustrated in
Alternatively, the stores need not comprise a triangular cross-section, and each external stores element may comprise a rectangular cross-section or a hexagonal cross-section, and a plurality of such elements may be grouped together according to the invention as illustrated in
Further optionally, a plurality of clusters of stores and/or single stores according to the invention may be mounted in adjacent, juxtaposed or transversely spaced arrangement, and/or in tandem or longitudinally spaced arrangement, and/or in an array (rectangular or otherwise), on one or several surface of the vehicle 1.
Many other variations of the above embodiments according to the invention are also possible.
In the method claims that follow, alphanumeric characters and Roman numerals used to designate claim steps are provided for convenience only, and do not imply any particular order of performing the steps.
Finally, it should be noted that the word “comprising” as used throughout the appended claims is to be interpreted to mean “including but not limited to”.
While there has been shown and disclosed example embodiments in accordance with the invention, it will be appreciated that many changes may be made therein without departing from the invention.
Number | Date | Country | Kind |
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176597 | Jun 2006 | IL | national |