RADAR AUGMENTOR ASSEMBLY

Abstract: In the gun-launched target projectile is included a radar-augmentor to increase the radar cross-section of the projectile to simulate on radar, an actual airborne thread such as aircraft and missiles. The radar augmentor comprises a base member (l4), a uniform dielectric lens (l6) attached to the base member and a resilient support means between the base member and the lens. The dielectric lens is configured to provide a frontal radar return echo which simulates the actual airborne threat on radar.

Description: This invention relates to radar augmentor assemblies for target projectiles, for use in exercising radar systems and operators as well as to permit defence systems to acquire and lock on to supersonic or high subsonic targets. The radar targets commonly used for such training include aircraft-towed targets and reusable drones. Deployment of such systems is expensive, leading to infrequent use and the training provided is inadequate and not representative of the real battle threat. Moreover, the radar response of such targets alone is generally weak and unacceptable. To obviate this situation towed targets and drones have been provided with radar augmentation devices to increase the radar return or echo signal. Such devices include corner reflectors, Luneberg lenses and dielectric lenses. In US-A3,334,345 radar augmentors of the latter type are described. The dielectric lens described is of a uniform dielectric material, ie. a dielectric material having a uniform dielectric constant throughout. The lens is in the shape of a prolate spheroid, having a frontal ellipsoidal refracting surface, a central cylindrical surface and a spherical rear reflecting surface which carries a reflective coating. US-A-3413636 describes a radar augmentor assembly including a dielectric lens fixed to a radiation transparent shell, with a reflector on a rear portion of the lens, and reflective means fixedly mounted forwardly of the lens. In accordance with the present invention, a radar augmentor assembly comprises a uniform dielectric lens configured to provide a frontal radar return echo, the arrangement being such that the assembly increases in use the radar cross-section of the target projectile to simulate an actual airborne threat on radar, while maintaining aerodynamic flight stability, characterised in that the assembly is adapted for mounting to a gun-launched target projectile; in that the assembly includes a base member attached to the uniform dielectric lens; and in that resilient support means is provided in the form of a continuous film of a suitable resilient thermosetting resin material between the base member and the lens. The invention also provides an expendable missile target which will withstand gun-launching. This invention enables a low cost, expendable missile target to be constructed which appears on radar to be an actual airborne threat. The radar augmentor assembly increases the radar cross-section (RCS) of a target projectile to which it is attached to simulate an actual airborne threat on radar, while maintaining aerodynamic flight stability. The resilient support means between the base member and the lens prevents spalling of the lens due to stresses induced during gun-launching, while the dielectric lens is configured to provide a frontal radar return echo which simulates that of an actual airborne threat on radar. The radar cross-section is represented by the visual display a radar operator observes on a radar screen when tracking a projectile. Different projectiles produce different radar cross-sections or radar return echos. For example, a standard 5 inch (12.5 cm) calibre naval shell produces an RCS echo of .001m² which is too small a RCS to be visible to most radars. A typical sea skimmer anti-ship missile produces an RCS of about 0.25m². A typial fighter aircraft produces an RCSof about 2m². Some examples of gun-launched projectiles including radar augmentor assemblies according to the invention will now be described with reference to the accompanying drawings, in which:- Figure 1 is a side elevation, partly in section, of a 5"/54 calibre radar augmented target projectile (Model No.BA240); Figure 2 is a side elevation in section of the radar augmentor assembly illustrated in figure l; Figure 3 is a radar cross-section (frontal x-band) of the radar-augmented target projectile illustrated in figure l; Figure 4 is a side elevation, partly in section, of another embodiment of a 5"/54 calibre radar-augmented target projectile (Model No. BA360); Figure 5 is a radar cross-section (frontal x-band) of the radar-augmented target projectile illustrated in figure 4; Figure 6 is a side elevation, partly in section, of yet another embodiment of a 5"/54 calibre radar-augmented target projectile (Model No. BA480); Figure 7 is a radar cross-section (frontal x-band) of the radar-augmented target projectile illustrated in figure 6; Figure 8 is a side elevation, partly in section, of a further embodiment of a 5"/54 calibre radar-augmented target projectile (Model No. BA450), including an aerodynamic radome; Figure 9 is a radar cross-section (frontal x-band) of the radar-augmented target projectile illustrated in figure 8; and, Figure l0 is a side elevation of a typical prolate spheroid lens element (Model No. 240). As seen in figure l, the radar-augmented target projectile (BA240S, wherein "S" denotes polystyrene as the uniform dielectric lens material, although other materials such as polytetrafluoroethylene, polystyrene, high density polyethylene and polymethylpentene polymer (TPX®) may also be employed as will be apparent hereinafter and wherein 240 designates a 2.4 inch (6 cm) diameter) comprises a standard 5"/54 calibre Mk 64 hollow cylindrical BL&P projectile body l0, filled with an inert filler material l2 such as kaolin/wax. To accommodate a radar-augmentor, the fuze plug, nose fuze adapter and foam pad are removed from the standard projectile body l0 and replaced by a fuze plug replacement augmentor assembly which includes a base member l4 and a uniform dielectric lens l6. Depending upon the depth of the existing inert filler, a small quantity may have to be cut out to accommodate the base of the augmentor. The augmentor assembly is threaded directly into the nose of the projectile body l0, at 20, and the lens l6 is, in turn, threaded into the base l4, at l8. As best seen in figure 2, the base l4 includes a central longitudinal bore 22 of uniform diameter extending therethrough. The bore 22 is filled with a suitable resilient adhesive 25 which extends through the bore 22, along the concave lens receiving recess 26 of the base l4 and along threads l8, to provide a continuous film of adhesive which assures the absence of voids between the lens l6 and base l4 preventing spalling of the lens due to the tensile stresses induced during gun-launching. Moreover, the continuous film of adhesive provides a resilient support which minimizes the tendency of the lens becoming detached from the base during gun launch, i.e. the flexible lens tends to compress at firing and rebound upon release. This places tremendous stress at the lens/base interface which is provided for by the continuous film of resilient adhesive. Suitable resilient adhesives include thermosetting synthetic resins such as epoxy resins and silicone resins. Epoxy resins of minimum tensile yield strength of about 4000 psi are preferred. The method used to adapt the lens to the base is as follows. Both the lens and the base are thoroughly degreased and with the bore opening at the rear of the base covered with tape, a generous coating of adhesive is applied to the threads and lens recess. The lens is then engaged into the base threads. Once the threads are engaged, the assembly is turned so the lens is pointed down and the tape is removed. Threading together of the parts is completed in this position. Surplus adhesive from the threads and the recess is forced upward into the longitudinal bore and fills the bore. This method ensures that the lens is firmly attached and the seating of the lens to the base is free of voids. This is important from the point of view of structural integrity in such a high acceleration environment as gun launching. The adhesive is then cured in situ. Once the lens and base are assembled it is ready to be attached to the projectile body. In the case of the BA240, the 5"/54 MK64 BL & P projectile is not modified in any way. All that is required is that the training fuze be removed and the lens and base, as a unit, be threaded into the projectile in place of the fuse. This causes the RCS of the projectile to change from .00l m² to .2 m². With specific regard to the BA240 lens itself, it is in the form of a prolate spheroid having a front ellipsoidal refracting surface portion 28 and a rear reflecting surface 30 which is metallized, typically silver-plated. Alternatively, a metal foil such as aluminum may be bonded to the lens. The diameter of the lens is about 2.4 inches (6 cm). The radar cross-section (RCS) of the figure l and 2 embodiment (frontal x-band, frequency 9.37 GHz polarization verticalvertical) is presented in figure 3, in the form of a computer generated plot of a typical calibration run. The radar cross-section echo is seen to be essentially linear over about ±30 degrees from the centre line 0, i.e. from the longitudinal axis of the projectile at an average value of 0.2m², i.e. about 7 dB below the lm² calibration level. By way of further explanation, the accepted industrial standard for displaying RCS is in power versus angle graphs wherein power is exposed in units of decibels (dB) and angle in degrees. The relationship between dB and RCS, measured in meters squared (m²) in our case, is a logarithmic function, i.e. Expressed in another way, for each 3 dB increase or decrease, the RCS in m² is either doubled or reduced by one half. Figure 4 illustrates another embodiment of a radar-augmented target projectile according to the invention (BA360S) which comprises a modified 5"/54 calibre Mk 64 BL&P hollow cylindrical projectile body l0A filled with an inert filler l2A, such as kaolin/wax. In this embodiment, the modification of the standard projectile body involves cutting off a portion of the tapered nose section and removing sufficient inert filler to accommodate the augmentor. As in the figure l embodiment, the augmentor assembly is threaded directly into the nose of the projectile body l0A, at 20A, and the lens l6A is, in turn, threaded into the base l4A, at l8A. The base l4A includes a central longitudinal bore 22A of uniform diameter. In the same manner as described respecting the figure 2 embodiment, the bore 22A is filled with a suitable adhesive which provides a continuous film of adhesive from the threads l8A, along the concave surface 26A and through the bore 22A, to hold the lens l6A in position during the stresses induced during gun-launching. The adhesive is cured in situ. The base l4A also includes a central cut-out 23A of larger diameter than the bore 22A for adjusting the weight of the base and the location of the centre of gravity to match those of the unmodified projectile to ensure aerodynamic flight stability of the modified projectile. Accordingly, the weight and centre of gravity of each component part is considered so that the overall requirement for aerodynamic flight stability of the projectile is met. Referring specifically to the BA360S lens, it also is a prolate spheroid having a front ellipsoidal refracting surface portion 28A and a rear reflecting surface 30A which is typically silver-plated. The 360 designation indicates a lens diameter of about 3.6 inches (9 cm) and "S" indicates polystyrene. The radar cross-section of the figure 4 embodiment (frontal x-band, frequency 9.37 Ghz, polarization vertical-vertical) is illustrated in figure 5 as a computer-generated plot of a calibration run of one of the lenses test fired. The radar cross-sectional echo is seen to be linear over about ±50 degrees, symmetrical about the centre line 0, at an average value of 0.63m², i.e. about 2 dB below the lm² calibration level. Figure 6 illustrates yet another embodiment of the target projectile of the invention (BA480S) which also comprises a modified 5"/54 calibre Mk 64 BL&P hollow cylindrical projectile body l0B, filled with inert filler l2B, such as kaolin/wax. It will be observed that in this modification the entire tapered nose section of the standard projectile has been removed and filler removed to accommodate the larger augmentor. The augmentor assembly is threaded directly into the projectile body l0B, at 20B and the lens l6B is, in turn, threaded into the base l4B, at l8B. As in the figure 6 embodiment, the base l4B includes a central bore 22B. The bore is filled with a suitable adhesive which, as with the previous embodiments, provides a continuous film of adhesive from the threads l8B, along the concave lens receiving surface 26B and through the bore 22B, to hold the lens l6B in position during launch. The adhesive is cured in situ. The base l4B also includes a central cut-out 23B of larger diameter than the bore 22B. With respect to the BA480S lens per se, it too is a prolate spheroid having a front ellipsoidal refracting surface portion 28B and a rear reflecting surface 30B, typically silver-plated. The 480 designation indicates a lens diameter of about 4.8 inches (l2 cm ) and "S" denotes polystyrene. The radar cross-section of the figure 6 embodiment (frontal x-band, frequency 9.37 GHz, polarization vertical-vertical) is illustrated in figure 7. It is observed that the average RCS of about 2m², i.e. about 3 dB above the lm² calibration line is linear over about ±40 degrees from the lens centre line 0, i.e. the longitudinal axis of the projectile. A fourth embodiment of the radar augmented target projectile according to the invention is illustrated in figure 8 (BA450SR), which comprises the same modified projectile body as the BA480S projectile described above. The radar augmentor assembly is threaded into the body l0C at 20C and the lens l6C is threaded into the augmentor base l4C, at l8C. Prior to assembly of lens l6C in base l4C, both the lens and concave lens receiving surface 26C are coated with adhesive. The adhesive is cured in situ after assembly of the augmentor. It is noted that the augmentor assembly occupies most of the hollow body interior, i.e. the inert filler is completely replaced except for air space 2l. An aerodynamic ogive-shaped radome 32 is held in position by a retaining ring or collar 34 whioh is screwed into the base l4C, at 36. The radome is conveniently made of fibre reinforced plastic such as epoxy and Kevlar® and the collar is made of AISI 4l40 steel. A foam liner 33 was added to the finished fibre reinforced plastic (FRP) radome using a foam-in-place two element polyurethane foam. The average density attained was 6 lb/ft³(96.1kg/m³) The foam liner does away with the necessity for reinforcing ribs and aluminum nose cups. In this embodiment, the bore 22C is filled with adhesive and is connected to a lateral passage 38 which permits escape of surplus epoxy when the lens is threaded into the base and ensures a continuous void-free film of adhesive between the lens and base. This also avoids having to drill a long longitudinal bore. With respect to the BA450SR lens its prolate spheroid shape is defined by a front ellipsoidal refracting surface portion 28C and a rear reflecting surface 30C, typically silver-plated. The 450 designation indicates a lens diameter of about 4.5 inches (11.25 cm) "S" denotes polystyrene and "R" that a radome is employed. The radar cross-section of the figure 8 embodiment (frontal x-band, frequency 9.37 GHz) is illustrated in figure 9. The radar cross-section is seen to be essentially linear over about ±45 degrees from the centre line 0, at approximately 0.8m², about l dB below the lm² calibration level. By way of further explanation, the combined radome and foam liner cause approximately 3 dB loss which is a 50% reduction in RCS. Hence the BA480 without a radome would have a 2m² RCS which becomes about lm² with the radome. As indicated above, the different augmentor base configurations are required to match the weight and centre of gravity of the modified projectile with that of the original unmodified projectile to ensure aerodynamic flight stability. Thus, the four embodiments of the projectile according to the invention simulate airborne threats bearing radar cross-sections in the range of 0.lm² to 2m² over about ±45 degrees to the longitudinal axis of the projectile at x-band. The design of the prolate spheroid reflecting lenses (see figure l0) is based upon the following mathematical considerations. Taking the centre of the lens as the origin O, the refracting (front) ellipsoïdal surface of a uniform dielectric lens according to the invention may be defined, in Cartesian co-ordinates x and y, by Similarly, the reflecting (rear) surface may be defined as the locus of the normal to the front surface, at a distance f, the focal length, where Once the material has been chosen for the lens a coupon is removed from each end of the commercially available bar stock and its electro/optical properties determined. The lens is then machined on numerically controlled machines according to the prescribed formula substituting in the values for the index of refraction and the dielectric constant. It is of interest to note that depending on the material these two values can make a significant change to the shape of the exposed portion of the lens extending from the projectile which in turn affects the overall projectile design. This will be evident shortly. Once the lens has been machined, the rear surface of the lens is metallized, e.g. an aluminum foil is bonded to the (rear) surface. This completes the lens. The lens must now be adapted to the projectile. In the case of the BA240 design, which is by far the simplest, the lens is attached mechanically through threads to a base which in turn is threaded into a non-modified 5"/54 MK64 blank loaded and plugged (BL & P) projectile. This is a practice round and the cavity normally used to contain high explosives (HE) is filled with an inert filler material. This material must be of the same density as the HE so that the mass and centre of gravity of the projectile remain the same. The lens and base combination are the same weight as the training fuse in the MK64 BL & P or the same as a real fuse in an HE round. With the mass and centre of gravity of the radar augmented projectile matched to the original projectile, its trajectory will also be matched. Also, by matching the weight the standard propelling charge can be used. This is significant as no special charges have to be inventoried for these rounds and there is no risk of overpressuring the barrel due to heavier than normal projectiles. Lens Materials: Four candidate lens materials of a low loss, low dielectric constant material were considered, specifically, Teflon®, TPX®, polystyrene, and high density polyethylene. Structural test firings were made using each material, and RCS measurement were taken with 3.6 inch (9cm) diameter TPX®, polystyrene and polyethylene lenses. The physical, eletro/optical and environmental properties of the four materials selected are presented in Table l. Teflon® , a trademark for polytetrafluoroethylene, has the lowest dielectric constant and dissipation factor of any material surveyed. In comparison with polystyrene lenses, the Teflon® lenses produced about 2 dB greater radar cross-section for both the 2.4 (6cm) and 4.5 inch (11.25 cm) diameter lenses. Two dB is a factor of approximately l.6. Teflon® is the most dense and most expensive and its specific tensile strength (tensile strength divided by density), at 25,000 inches (625 m). is the lowest of the four choices. It is essentially impervious to all environmental hazards, and widely available. TPX® , a trademark for polymethylpentene polymer, is a relatively new, little known plastic, with electrical properties very similar to those of Teflon®, very low density and good, but not well documented physical properties. The data in the table have been substantiated by tensile tests. Its specific tensile strength, a measure of resistance to acceleration induced stress, is ll5,000 inches (2875 m), almost five times that of Teflon®. Its cost is moderate, about the same as polystyrene. Polystyrene is the traditional material used for microwave dielectric applications. The particular brand used here, Rexolite® l422, meets US Federal Specification L-P-5l6a Type E2 (formerly MIL-P-77C-E2). At l32,000 inches (3300m), its specific tensile strength is the best of the four materials surveyed. Polyethylene is cheap and universally available. Its electrical properties are close to those of polystyrene, and its environmental resistance is good. Its specific tensile strength is about 90,000 inches (2250m). The structural test firings indicated that all four materials would be potentially suitable for the ballistic lens. All survived the gun firings with no apparent distortion, and no structural failures. Firings were made at the reasonably representative normal temperature extremes of +40°C (Series l) and -20°C. The radar cross-section of ballistic lenses made with three of the four materials, TPX®, polystyrene and H.D. polyethylene were found to be quite similar. TPX® provides about l½ dB stronger return than polystyrene, but the angular range is somewhat less at ±48 degrees as compared to ±56 degrees. Polyethylene gives about the same return as TPX® at ±52 degrees angular range. The theoretical return for a 3.6-inch (9cm) diameter lens, using the flat plate formula is 0.53 m², or -2.8 dB relative to the l m² calibration level of 20 dB relative power. All of the lenses tested exceed this value. All lenses passed the initial structural test review, and there appeared to be no essential difference in RCS performance amongst the three favoured candidates. However, Rexolite® l422 polystyrene exhibits the largest structural safety margin. Base Materials The base is conveniently constructed of mild steel to be compatible with AISI l020 and l045. Structural Proofing Trials The various types of radar-augmented target projectiles were successfully test fired using a 5"/54 calibre OTO-MELERA gun mount and tracked for ballistic purposes by radar. Compatability With Existing Weapon System: To establish the ability of the radar-augmented target projectiles to pass through the OTO-MELERA feed system, a preliminiary study indicated the following: a) Type BA240 - This type of round configuration will pass through the OTO-MELERA lower and upper hoist system. b) Type BA450SR (with a Radome) - The radome tested will pass through the hoist system. The fuze setter pawls have been removed to allow successful passage of this type of target. c) Types BA360 and BA480 - The tests indicated that these types of rounds can be hand loaded. While it takes a high degree of physical effort to hand load these rounds, they are included in the trial to obtain M-22 radar performance tracking information (particularly using the 2m² RCS augmentor). No physical damage to the ship's gun or mounting is anticipated as the projectile targets have been successfully test fired using a land-based mount. Series l, as fired, included ten firings, although 2l projectiles were provided. The firings were conducted at essentially horizontal quadrant elevation (QE), with the gun aimed at a butt target some l000 m from the muzzle. Instrumentation included smear and high speed framing cameras, muzzle doppler and chamber pressure. The firings included one each of the Teflon®, TPX®, polyethylene and polystyrene BA24 and BA360 projectiles, and one each polyethylene and polystyrene BA480 projectiles. Photographs obtained for each firing confirmed that all rounds survived with no visible deformation. The mean air temperature during the trials was between 35° C and 40° C. Aerodynamic and RCS Proofing Trials: Series 2 was conducted in three steps, primarily because of weather problems. A total of 20 rounds were fired. Mean air temperature during the trials was between 0° C and -30° C. The first sequence of shots was fired at horizontal QE in order to obtain measurements of the shock wave pattern produced by the three blunt nose augmented projectiles. This sequence of firings also included the first test of a BA450SR projectile, with an .030 inch (0.075cm) thick FRP radome. Smear photographs and the shock (N-wave) observations confirmed that all augmented projectiles, including the BA450SR radome projectile, survived the gun firings with no visible damage. The second set of firings under Series 2 was conducted at various quadrant elevations, such that all projectiles fired would have an approximate range of l2,000 m. This range was selected for safety and best fall of shot observations. The radar was placed approximately one km behind the gun on the gun line so that the trajectory of each round could be observed. Firings included two BL&P warmers, three BA240S, four BA360S, and three BA480S. All firings were observed on radar, and impact was observed within the predicted fall of shot area. Some rounds were recovered with the lenses and projectile bodies in remarkably good condition. Coded stakes were placed in the ground to mark the impact point for future triangulation for fall of shot. Sea Trials (Series 3) : The final set of firings under Series 3 was conducted at the same nominal range as Series 2, but the radar was placed 5 km forward of the impact area, so that the inflight RCS return could be observed, along with trajectory information. Rounds fired included two BL&P warmers and two each BA240S, BA360S, BA480S and BA450SR radome rounds. All projectiles were observed by the radar; the radar cross-section was noted by recording the automatic gain control (AGC) output, and comparing it with a standard l m² spherical calibration target balloon, tethered at a known distance from the radar dish. A summary of additional proof-of-concept trials is as follows. A total of 29 firings were conducted using radar augmented projectiles. A critique of the rounds fired was as follows: 9 of BA240, l0 of BA360, 7 of BA480 and 3 of B450R. The lens material used on the various types was as follows: BA240 - high density polyethylene - polystyrene teflon - teflon - polymethylpentene polymer (TPX); BA360 - high density polyethylene - polystyrene - teflon - TPX; BA480 - high density polyethylene - polystyrene; and BA450R - polystyrene - radome. In all cases the structural integrity of the lens material used was satisfactory. In all cases the RCS of the different lens material under dynamic gun launched conditions were detectable with a tracking radar. When considering the cost for lens material, structural integrity, electro/optical properties and availability, the most preferred materials are polystyrene and high density polyethylene. Polystyrene provides the best all-round characteristics for gun launched radar augmented projectiles with the following exception. It is expensive, relatively hard to obtain in large diameters and is easily marked up during normal handling. On the other hand, high density polyethylene is the cheapest of all materials tested, easiest to obtain and capable of rough handling. However, for a given diameter, polystyrene produces the larger RCS. Where the latter is paramount, polystyrene should be used and when it is cost, polyethylene. Three material combinations for the radome used with the figure 8 embodiment were tested satisfactorily. The best results from the viewpoint of minimizing RCS loss has come from a radome made with three layers of 0.010 inch (0.025cm) thick kevlar and one of 0.005 inch (0.0125 cm) thick fiberglass in the base area, and two layers of 0.0l0 inch (0.025mm thick kevlar and one of 0.005 inch (0.0125cm) thick fibreglass near the apex. This type of construction provides a reasonably constant thickness to radius ratio for optimum strength, yet minimizes the wall thickness near the centre. The peak RCS from this type of construction provided about lm² in the region between ±30 degrees and ±45 degrees from the axis, and between 2 and 3 dB below lm² in the core region, ±30 degrees. The effect of the foam is minimal, causing the 2 dB loss at ±l0 degrees. This type of construction and the use of kevlar, which is clearly more effective than fiberglass from the standpoint of minimizing RCS loss, is preferred. The invention is applicable to any projectile calibre. The maximum radar cross-section achievable in a different calibre will be 2.0 m² times the fourth power of the diameter ratio. In l55mm and l05mm calibres, for example, the maximum RCS at x-band will be approximately 4.5 m² and l m² respectively without ballistic match, and 2.25 m² and 0.5 m² with ballistic match. Principal attention has been given to X-band radar energy, and all designs presented have been evaluated at this frequency. It should be noted, however, that the radar cross section echo of a passive reflector varies inversely with the square of the wavelength of the incident radar beam, thus the RCS of a typical augmentor will increase with increasing radar frequency. The nominal wavelength of an X-band radar beam is .032 m, whereas those of Ku and K-band are taken here as nominally .02 m and .0l4 m respectively. The radar-augmented target projectiles may be loaded automatically, or by hand in either Naval or Army guns. Some automatic loading assistance may be necessary for the rounds where the ogive is different from the standard projectile, and where the automatic loader has a sensor pawl which contacts the projectile near the fuze base.

Claims: A radar augmentor assembly comprising a uniform dielectric lens (16,16A,16B,16C) configured to provide a frontal radar return echo, the arrangement being such that the assembly increases in use the radar cross-section of the target projectile to simulate an actual airborne threat on radar, while maintaining aerodynamic flight stability, characterised in that the assembly is adapted for mounting to a gun-launched target projectile; in that the assembly includes a base member (14,14A,14B,14C) attached to the uniform dielectric lens (16,16A,16B,16C); and in that resilient support means (25) is provided in the form of a continuous film of a suitable resilient thermosetting resin material between the base member (14,14A,14B,14C) and the lens (16,16A,16B,16C). An assembly according to claim 1, wherein the base member (14,14A,14B,14C) includes a central longitudinal bore (22,22A,22B,22C) extending therethrough and wherein the bore is at least partially filled with the thermosetting resin material (25). An assembly according to claim 1 or claim 2, wherein the thermosetting resin material (25) is an epoxy resin. An assembly according to any of claims 1 to 3, wherein the uniform dielectric lens (16,16A,16B,16C) is a prolate spheroid having a front ellipsoidal refracting surface (28,28A,28B,28C) and a rear reflecting surface (30,30A,30B,30C). An assembly according to claim 4, wherein the front refracting surface (28,28A,28B,28C) is defined in Cartesian co-ordinates, x and y, and taking the centre of the lens as the origin, by y = √ (b² - (b/a)² x²), where (x,y) are front surface co-ordinates; a is the semi-major axis of the lens; and b is the semi-minor axis of the lens. An assembly according to claim 4 or claim 5, wherein the rear reflecting surface (30,30A,30B,30C) is defined as the locus of the normal to the front surface, at a distance f, the focal length, where a = nf/(n + 1) b = a √(1 - n⁻²) n = √ D K ,wherein n is the index of refraction; and D K is the dielectric constant. An assembly according to any of the preceding claims, wherein the dielectric lens material is selected from the group consisting of high density polyethylene, polystyrene, polymethylpentene polymer and polytetrafluorethylene. An assembly according to any of the preceding claims, wherein the dielectric lens material is selected from high density polyethylene and polystyrene. An assembly according to any of the preceding claims, wherein the diameter of the lens (16) is substantially 2.5 inches (6.25 cm) and provides a frontal radar cross-section at x-band of substantially 0.2m². An assembly according to any of claims 1 to 8, wherein the diameter of the lens (16A) is substantially 3.6 inches (9 cm) and provides a frontal radar-cross section of substantially 0.63m². An assembly according to any of claims 1 to 8, wherein the diameter of the lens (16B) is substantially 4.8 inches (12 cm) and provides a frontal radar cross-section of substantially 2m². An assembly according to any of claims 1 to 8, wherein the diameter of the lens (16C) is substantially 4.5 inches (11.25 cm), the assembly further comprising an ogive-shaped aerodynamic radome (32) covering the lens (16C) to provide a frontal radar cross-section of substantially 1m². A gun-launched target projectile having a radar augmentator assembly according to any of the preceding claims. A target projectile according to claim 13, wherein the calibre of the projectile is 5 inches (12.5 cm).

Inventors: COFFEY, CLAYTON G., FRIEND, WILLIAM H., JONES, WILLIAM A.
Applicants: CANADA MINISTER DEFENCE, THE MINISTER OF NATIONAL DEFENCE OF HER MAJESTY'S CANADIAN GOVERNMENT
Application year: 1987
Main classification: H01Q15
IPC codes: F42B30, F41H3, F42B12, H01Q15, F41J2