GB2490528A

GB2490528A - A self-propelled flying apparatus adapted to emulate a hostile firing action

Info

Publication number: GB2490528A
Application number: GB1107464.8A
Authority: GB
Inventors: John Chester-Parsons
Original assignee: EW Simulation Technology Ltd
Current assignee: EW Simulation Technology Ltd
Priority date: 2011-05-05
Filing date: 2011-05-05
Publication date: 2012-11-07
Anticipated expiration: 2031-05-05
Also published as: US20140076131A1; GB2490528B; WO2012150442A1; GB201107464D0

Abstract

A self propelled flying vehicle (1) adapted to emulate a hostile firing action comprises an ultraviolet light source (5) in communication with a driving means (7) for driving the ultraviolet light source. The driving means (7) stores information indicative of an ultraviolet profile of a hostile firing action and, in use, communicates the ultraviolet profile to the ultraviolet light source (5).

Description

A Seif-Pro_petled Flying_Apparatus adapted to emulate a Hostile FiringAction

Field of the nvent ion

The invention relates to hostile fire indicators, in particular to hostile fire indicators incorporating an ultraviolet light source, which is illuminated with a defined ultra vo[et profile of a known threatening action.

h the context of the application the term "self-propelled flying apparatus" defines all known self propelled flying objects, such as rockets, drones, fixed wing and rotary wing aircraft which are either manned, remotely controlled or both.

Problem to be solved t is known that there is a problem of realistically testing ultra violet missile warning systems (UVMWS) on a firing range. Current test systems are essentially "static" and have difficulty in replicating the specific signal integrity required for such effects as Hostile Fire ndication (HH) and counter countermeasures or false target repUcation.

Another known solution to this problem is to fire actu& rounds at a flying platform, such as a fixed wing or rotary winged aircraft, which gives rise to the primary difficulty in testing, mainly the health and safety aspects of firing live rounds at an approaching aircraft or vehicle. For this purpose the highest quality and expensive ammunition must be used to derive the ± 2 degree accuracy required for Hostile Fire Rounds, which in turn translates I) into increased tolerance from the datum baseline, which must be allowed for the safe proximity of aircraft that can bring a known representative scenario of how the UVMS sensor may react. Therefore, it is evident that the resources required in hardware and manpower is constrained.

The present invention seeks to provide a remedy/solution for these problems.

Summary of the invention

n a first broad independent aspect the invention provides a self propelled flying vehicle adapted to emulate a hostile firing action comprising an ultraviolet light source in communication with a driving means for driving said ultraviolet tight source, wherein said driving means stores information indicative of an ultraviolet profile of a hostile firing action and, in use, communicates said ultraviolet profile to said ultraviolet light source.

This provides a means of testing an ultraviolet missile warning system on a flying platform or land based system. The Ultraviolet (UV) light source of the vehicle is driven / illuminated in accordance with a known UV profile of a known threat. UVMWS are typically tested by exposing them to static UV sources which are easy to detect in a sterile, non-flying environment. However, it has become apparent that UVMS do not adequately detect and recognise a hostile firing action of a device, physically launched towards the platform incorporating the UVMS. The UV light source illuminated/driven in accordance with the UV profile of a known threat, which in combination of the flight characteristics of a flying vehicle, provide a more realistic test for determining the detectability of a known hostile firing action by the UVMS Preferably, a self-propelled flying vehicle further comprising an interface to a programming device which facilitates the communication of information indicative of an ultraviolet profile of a hostile firing action from said programming device to said information storage so means.

This enables selectable information representing the UV profile of a hostile action to be centrally stored in a central storage means, such as a computer or controller device, which can be selected and programmed into an information storage device within the vehicle.

The UV profile can be overwritten at any time to assume the UV characteristics of another hostile firing action or when the vehicle has completed its flight. Therefore, there is no need to store multiple rockets, wherein each rocket is permanently configured to a known UV profile of a known hostile firing action.

Preferably, a self-propelled flying vehicle further comprises a parachute to facilitate the landing and recovery of said vehicle. This enables the soft landing of the vehicle, so that the vehicle's fuselage /body is not damaged, along with the components housed within the vehicle, and therefore enables the subsequent re-use of the vehicle.

Preferably, said stored information indicative of an ultraviolet profile is erased from said storage device upon activation of said parachute. This provides control of the distribution of the potentially "confidential" UV profile of a known hostile firing and prevents the UV profile from being accidentally or inadvertently distributed and / or disclosed.

Preferably said vehicle is a rocket.

This enables the UV light source to be propelled to the UVMS under any manner which is similar to a missile.

Preferably said ultraviolet tight source is disposed in or on a detachable nose portion of said rocket. This enables the UV light source to clearly emit the UV light in the direction of the UVMS under test, which is clearly detectable by the UVMS under test.

Preferably, said rocket motor further comprises a first stage for providing the initial propulsion for said rocket; and / or a second stage for emitting a smoke trail from said rocket and I or a third stage for expelling said parachute from said rocket. This provides the rocket with means of propelling the rocket to simulate a flight of a missile and provides a visual trace for training operators to visually recognise a hostile firing action, and an so automatic deployment of the parachute after the flight.

Preferably said rocket motor is releasably attached to said rocket and thereby facilitates the replacement of said rocket motor once it has been used with a new rocket motor. This enables the rocket to be ready for re-Launch after it has been recovered from an earlier flight.

In a second broad independent aspect the invention provides a system for adapting a self propelled flying vehicle to emulate a hostile firing action comprising: * A self propelled flying vehicle; * An ultraviolet Light source means; * A driving means for driving said ultraviolet Ught source; and * wherein said driving means stores information indicative of an ultraviolet profile means of a hostile firing action and, in use, communicates said ultraviolet profile to said ultraviolet light source.

Preferably, system for adapting a self propelled flying vehicle to emulate a hostile firing action further comprises a parachute; Preferably, system for adapting a self propelled flying vehicle to emulate a hostile firing action further comprising a means of erasing said stored information indicative of an ultraviolet profile upon activation of said parachute.

ln a third broad independent aspect the invention provides a method of adapting a self propelled flying vehicle to emulate a hostile firing action comprising the steps of: * Storing information indicative of an ultraviolet profile of a hostile firing action; and * Communicating said ultraviolet profile to an ultraviolet light source disposed in or on said self propelled flying vehicle.

A method of adapting a self-propelled flying vehicle to emulate a hostile firing action, further comprising the step of erasing said stored information indicative of an ultraviolet profile of a hostile firing action upon the activation of a parachute from said self propelled flying vehicle.

Preferably, said ultra violet light source is an array of one or more Ultra violet light emitting diodes.

ln a fourth broad independent aspect the invention provides a ultraviolet Ught source device adapted to emulate a hostile firing action comprising a body incorporating an ultraviolet light source means in communication with a driving means for said ultravioLet light source; said driving means incorporates a first connection to facilitate the communication of information indicative of an ultraviolet profile of a hostile action from a remote controller means, wherein said driving means stores information indicative of an ultraviolet profile of a hostile firing action received from said first connection and, in use, communicates said ultraviolet profile to said ultraviolet source means. This configuration io provides the means of incorporating a UV profile of a hostile action which is communicated from a remote controller and the drives/illuminates the UV light source in accordance with stored UV profile which can generate UV light radiation that is capable of stimulating the UVMS within a flying platform or [and-based vehicle in excess of 50 metres from the device.

Preferably, an ultraviolet light source device adapted to emulate a hostile firing action further comprising an attachment means for attaching said device to a cable. This enables the device to be attached to a supporting cable at a random or predetermined position.

Preferably, an ultraviolet light source device adapted to emulate a hostile firing action further comprising a first body portion disposed above said attachment means to said cable and in use disposes said UV Ught source above said cable. This enables the UV Ught source to be positioned above the cable, in a position with an unobstructed field of view, and which can be easily detected from a distance.

Preferably, an ultraviolet light source device adapted to emulate a hostile firing action further comprising a second body portion disposed below said attachment means to said cable and incorporates a weighted element. This enables the device to maintain a position where the first body is maintained in an upper vertical position. This overcomes any so deviations caused by twists in the cable or movement of the device caused by the weather, such as wind.

Preferably, an ultraviolet light source device adapted to emulate a hostile firing action further comprising a second connection to facilitate communication of power from an external power supply. This enables the device to be continually powered which is not dependent upon weather conditions. This also eliminates the requirement of incorporating power supply units with the device itself.

Preferably, an ultraviolet light source device adapted to emulate a hostile firing action further comprising a solar energy collection device in communication with an energy storage device. This enables the device to be powered by solar radiation, which is converted into electrical energy that is subsequently stored within the device, This eliminates the requirement of running a power supply to each unit from an external power io supply.

Preferably, said first connection means to facilitate communication with a controller is a connection to said cable, This enables the device to be connected directly onto the cable, which also carried control lines to the controller. This makes the design of the unit simDier arid light weight because there are no other communication means built into the device.

Preferably, said first connection means to facilitate communication with a controller is a wireless connection to said controller. This enables the device to be connected to the controller, without being dependent upon the cable, which makes the device easier to install onto the cable.

Preferably, an ultraviolet light source adapted to emulate a hostile firing action further comprises a visible light source. This enables the device to visibly flash, which provides the means of visibly representing a tracer for training aircrew to spot a hostile firing action.

h a Fifth broad independent aspect the invention provides a system for adapting a plurality of ultraviolet light source devices to emulate a hostile firing action comprising: * A plurality of ultraviolet light source devices; so * A cable means; * A controller means; * A connection means to facilitate communication from said controller means to each said ultraviolet light source devices; and * Wherein said ultraviolet Light source devices are suspended on said cable and said cable is elevated to locate each said ultraviolet light source device in an elevated position; said controRer means communicates information indicative of an ultra violet profile for a hostile firing action to each said ultraviolet Ught source device via said connection means. This configuration provides a means of driving/illuminating an array of UV light source devices attached to a cable. The controller programmes each UV light source device attached to a cable. The controller programmes each UV tight source device with a UV tight profile of a hostile action. The controller will then sequentially flash' each module along the io cable to give the effect of a moving hostile firing action. The sequential flashing of the UV source devices could emulate tracer$, hostile fire indication, or missiles travelling from subsonic to supersonic speeds. By varying the sequence or profile sensitivity measurements may also be obtained. Also this configuration also provides inherent repeatability or the same sequence could be repeated over and over again.

Preferably, said cable further comprises the means of communicating power from a power supply means to each said ultraviolet light source device and / or communicating information from said controller means to each said ultraviolet light source device. This configuration enables each device to be continuously connected by an external power supply.

Preferably, said connection means from said controller means to each said ultraviolet light source device is a wireless communication means. This configuration enables each device to be connected to controller in a wireless network.

Preferably, said ultraviolet light source devices are substantially arranged in a linear array; whereby each said ultraviolet light source device is spaced from a neighbouring ultraviolet light source device. This configuration enables the devices to be spaced apart from each other to form different tracer configuration. The spacing also determines the speed of movement of the emulated UV and/or visible hostile firing along the cable.

Preferably, one end of said linear array is disposed at an elevated position, which is higher than the position of the opposite end of said linear array. This configuration enables the array of devices to have some height perspective above ground level and therefore provide a more realistic effect and a dynamic input to the UVMWs: therefore trials aircraft could then fly a more realistic approach to the apparatus of the system.

n a sixth broad independent aspect the invention provides a method for adapting a plurality of ultraviolet light source devices to emulate a hostile firing action comprising: * Suspending a plurality of ultraviolet source devices on a cable, whereby said cable is elevated to locate each said ultraviolet light source device in an elevated io position; * Communicating information indicative of an ultraviolet profile for a hostile firing action from a controller means to each said ultraviolet light source device; and * Sequentially activating an ultraviolet light source on each said ultraviolet light source device, whereby said sequential activation of each said ultraviolet light is source device along said cable provides the effect of movement.

Preferably, a method for adapting a plurality of ultraviolet light source devices to emulate a hostile firing action comprising a further step of communication power from a power supply means to each said ultraviolet light source device and / or communicating information from said controller means to each said ultraviolet light source device.

Preferably, a method for adapting a plurality of ultraviolet light source devices to emulate a hostile firing action, comprising a further step of wirelessly communicating information indicative of an ultraviolet profile for a hostile firing action from a controller means to each said ultraviolet light source device.

Preferably, a method for adapting a plurality of ultraviolet light source devices to emulate a hostile firing action, comprising a further step of arranging said ultraviolet light source devices in a linear array; whereby each said ultraviolet light source device is spaced from a neighbouring ultraviolet light source device.

Preferably, a method for adapting a plurality of ultraviolet light source devices to emulate a hostile firing action, comprising a further step of elevating one end of said linear array to higher position than the position of the opposite end of said liner array.

h a seventh broad independent aspect the invention provides a method of communicating a simulated radar signal from a radar signal generator to a radar sensing device comprising the steps of: * Generating a first radio frequency signal indicative of a simulated radar signal; * Communicating said first radio frequency signal from said radar signal simulator to an optical modulator device; * Converting said first radio frequency signal into an optical signal indicative of said simulated radar signal; * Communicating said optical signal from said optical modulator to a radar sensing device; * Converting said optical signal into a second radio frequency signal indicative of said simulated radar signal; and is * Communication said second radio frequency to a radar sensing device.

n an eighth broad independent aspect, the invention provides a system for communicating a simulated radar signal from a radar generator to a radar sensing device comprising: * A radar signal generating means for generating a first radio frequency signal indicative of a simulated radar signal; * A first communication means for communicating said first radio frequency signal from said radar signal generating means to an optical modulator device; * An optical modu'ation means for converting said first radio frequency signal into an optical signal indicative of said simulated radar signal; * A second communication means for communicating said optical signal from said optical modulation means to a radar sensing device; * A conversion means for converting said optical signal into a second radio frequency signal indicative of said simulated radar signal; and * A communication means for communicating said second radio frequency signal to a radar sensing device.

This configuration provides a means of generating and communicating radar signals in the frequency range of 1(X) MHz to.40 CHz. These signals are communicated over of optical fibres iink(s) in excess of 25 metres. These lengths provide the means of communicating the radar signals to and about a large piece of prime equipment, such as a flying platform or a land-based vehicle. ft is not possible to transport generated radar signals within the above frequency band by metallic conductors, i.e. copper, due to their inherent signal attenuation of the higher frequencies over long Lengths.

Preferably, said first communication means is a metallic conducting cable. This provides the connection for communicating the RF signal representing a radar signal over a short distance to an optical modulator device.

Preferably, said optical modulation means is a Mach -Zehnder modulator. This provides improved means for transporting RE signals over fibre-optic link(s). This configuration has a good frequency with a good fLatness of the signaL which is just over 3 dB, over the 2 to 18 GHz frequency range.

This configuration also provides: * insertion Loss The insertion loss is minimised.

* Noise Performance The noise performance of this configuration is a minimum of 3 dB headroom for operation.

* 2nd Harmonic Performance This configuration provides satisfactory performance for input levels of approximateLy -3 dBm.

* 3 Harmonic Performance This configuration gives satisfactory performance for all input levels from 0 dB downwards.

* LLW3 Two Tone Test This configuration provides inter-modulation and harmonic products from harmonic analysis. The highest value is seen at 7 GHz and is approximately -dB below the fundamental frequency. This is regarded as almost an acceptabLe level within the peaks at -55 dB. Also from harmonic analysis for a -S dB input, the harmonics are greatly reduced. Harmonic and inter-modulation levels have fallen significantly from 0 dBm input which cannot be discerned in the output.

* Third Order Product Test 0 dB input signals produce outputs above 60 dB, but at -3 dB and below the output levels are acceptable.

Preferably, said second communication means is an optical fibre. This enables the optical signal which represents the radar signal, to be carried over distances of greater than metres. The opticaL fibre is more resilient to noise and harmonic distortion than metallic conductors. The operating frequency range of the optical fibre is 100 MHz to 40 CHz which is a vast improvement over metallic conductor cables which have significant losses which are greater than 10 dB across the 2 to 18 GHz frequency range over lengths of 20 to 40 metres runs.

Preferably, said conversion means is facilitated by an avalanche diode. This enables the modulated laser light communicated &ong the fibre optic to be converted back to a RF-based signaL Preferably, said radar sensing device is disposed in / on a vehicle. This enab'es the communication of radar generated signals to radar sensing devices located about a land-based vehicle.

Preferably, said vehicle is a flying vehde. This enables the communication of radar generated signals to sensors located about a flying vehicle.

Brief Description of the figures

io Figure 1 -shows a perspective view of a rocket adapted to emulate a hostile firing action.

Figure 2 -shows a cross-sectional view of a rocket adapted to emulate a hostile firing action.

Figure 3 -shows a perspective view of an ultra-violet light source device attached to a cable adapted to emulate a hostile firing action.

Figure 4 -shows a cross-sectional view of an ultra-violet light source device attached to a cable, adapted to emulate a hostile firing action.

Figure 5 -shows a schematic view of a linear ray of ultra-violet light source devices, which is elevated at one end.

Figure 6 -shows a schematic view of an individual ultra-violet light source device connected to a cable.

Figure 7 -shows a schematic view of a radar simulator connected at multiple points to an aircraft platform.

so Detailed description of the figures

Figure 1 -shows a rocket generally indicated by 1, which incorporates an elongated cylindrical body 2. A cylindrical body 2 incorporates a tapered portion 3 at one end of the cylindrical body 2, also known as a nose cone. At the opposite end of the cylindrical body 2 is an array of manoeuvring fins 4, which perpendicular to the cylindrical body. Other forms of aerodynamic manoeuvring fins may also be utilised, such as wings, canards or the like. At the tip of the tapered section 3 is an ultraviolet (UV) light source 5. The UV light source S is enclosed under a transparent domed portion 6, which is typically formed from either a glass or plastics materiaL The rocket I is maintained in a vertical position, whereby the cylindrical body and tapered section extends along axes AA and the weight of the rocket is borne by the manoeuvring fins 4.

Figure 2 shows a cross-sectional view of the rocket 1 shown in Figure 1. The UV light io source array 5 is a typical array of one or more UV Light-Emitting Diodes (LED5) located on a horizontal surface beneath the transparent dome 6. Beneath the UV light source array 5 is an electronic and/or electrical control pack 7, which is housed within a tapered section 3 of the rocket 1. The electronic control pack 7 is a driving means for driving and illuminating the UV light source 5. Beneath the electronic control pack is a parachute pack 8. The parachute pack 8 is located substantially towards the upper end of the cylindrical body 2. Beneath the parachute pack 8 is a horizontal supporting portion 9, which is integral to the cylindrical body 2 and extends across the inner cavity of the cylindrical body 2. Beneath the horizontal supporting portion 9 and extending downwards towards the bottom end of the cylindrical 2 is a multi-stage rocket motor 10. The first stage 13 provides initial boast, second stage 12 provides a smoke trail and the third stage 11 provides the expulsion charge for the parachute 8.

h use, the rocket seeks to stimulate with an ultraviolet missile warning system (UVMWS) located on a platform or vehicle, which is either flying, land-based or both. The rocket may be typically in the form of flying vehicles or objects such as missiles, aircraft, fixed-wing and/or rotary-wing vehicles, remote drones or aircraft, or attached or embedded within a carrying platform or vehicle. The UV LEDs located at the tip region of the nosecone of the rocket are driven by a UV LED driving means, which is typically an electrical/electronic controller means incorporated within the electronic contrd pack housed within the nosecone. The UV driving means incorporates an information storage means, typically in the form of a memory device that stores UV profile for the emulated hostile firing action.

Each profile may be differentiated from each other by the stroboscopic frequencies for turning the UV LEDs on/off and adjusting their brightness levels in accordance to the known UV profile for a known hostile firing action.

The combination of illuminating the UV LEDs in accordance with a known threat, with the motion of the rocket during its flight, provides a very realistic training aid for testing the Ultraviolet Missile-Warning Systems (UVMS) of an airborne platform whilst in flight or in motion. This is particularly important as UVMWS are conventionally tested using static systems, which do not test the detectability of a missile in flight. For security purposes, once a parachute has been activated and/or deployed, the stored UV profile for a known hostile firing action is then erased from the UV LED driving leads.

in The rocket has a re-useable body, which incorporates a parachute recovery system that enables the rocket to be used many times.

The motor within the rocket is a three-stage motor, whereby the first stage provides the initial boast to launch the rocket, the second stage provide a means of generating a smoke trail to emulate the smoke trail of a surface-to-air missile and the third stage provides the expulsion charge required to eject the parachute, which returns the rocket safely to ground. The maximum range of the rocket motor is approximately 1,000 metres, The rocket motor is removable; therefore a new motor and a new ultraviolet profile may be installed into the rocket to make it ready again for firing again. The smoke trail emitted by the rocket provides a very realistic training aid to an operator for visually detecting the hostile firing action, such as a launch of a missile.

h an alternative embodiment of the invention, the nosecones are detachable and interchangeable with each other, whereby a second nosecone fitted with an alternative light source array, such as a combination of UV and physical light sources, UV and infrared light sources or the like. Also the alternative light source array may facilitate alternative lighting configurations about the nose cone of the rocket.

Another alternative embodiment of the invention, the UV light source may be integrally so fitted to the body of carrying platform or vehicle or fitted within an additional case or body, such as a carrying pod, which is fitted the body of a carrying vehicle, thereby utilising the propulsion system of the carrying platform or vehicle to provide the means of propelling the UV light source towards the platform incorporating with the UVMWS under test.

Other benefits of the UV light source incorporated within a rocket are: * allow the trials platform to fly a more accurate baseline; * significantly reduce costs of high quality live fire ammunition; * provide a means for developing tactics and doctrine in a controlled realistic environment; * provide a "squadron training solution" prior to theatre operations deployment; * provide a programmable system to replicate sub and supersonic missiles, hostile fire indicators (HH) and false targets.

Figure 3 shows an ultraviolet light source device generally indicated by 20 which incorporates an upper, vertically mounted, cylindrical body portion 21 that incorporates an array of ultraviolet Light-Emitting Diodes (UV LED5) 23. The ultraviolet light source device 20 also incorporates a lower spherical body portion 24. The upper cylindrical body portion 21 is attached to the lower spherical body portion 24 via a body connecting body portion 25.

The upper cylindrical body portion 21 incorporates a domed upper portion 26 and a tapered lower portion 27 which is integral to the connecting body portion 25. The array of UV LEDs incorporates at least three columns of equafly spaced LEDs, which are spaced about the outer surface of the upper body portion, 21 to provide a 120 degree field of view for the ultraviolet light emitted from the device 20. The upper cylindrical body portion 21 is maintained in a vertical upward position above the cable 28.

The lower spherical body portion 24 houses a weighted component to ensure that the device 20 is suspended from a cable 28 so that the upper portion 21 is maintained in a vertical position. The lower body portion 24 is weighted by the driving means for driving the UV LEDs and/or an energy storage device, such as a battery. The driving means may be incorporated within an electronic and/or electronic control pack. The lower spherical body portion 24 is maintained in vertical downward position below the cable 28.

The UV tight source device is attached to the cable 28, via a clamping means 29. The cable 28 is inserted into the connection portion 25 and is clamped into position via a clamping member 30, which is screwed to the connecting portion 25.

Figure 4 shows a cross-sectional view of the ultraviolet light source device 20 shown in Figure 3. The upper body portion 21 is shown to incorporate a void 31 for accommodating the UV LEDs and associated circuitry. The tower body portion 24 is shown to incorporate a second void 32 for accommodating a weighted component. The weighted component may also be an energy storage device or an electrical/electronic control pack for driving the UV LED5. The connecting body portion 25 connects the upper body portion 21 to the lower body portion 24 and incorporates the clamping means 29, which encloses about the cable 28 via a clamping member 30.

In use, the ultraviolet light source device has a field of view of typically 120 degrees and can, without any optical focussing, generate powers capable of stimulating an aircraft in excess of 50 metres from a single illuminated UV LED.

The upper body portion of the ultraviolet light source device is a miniature and aerodynamic body portion and the second body portion is lower weighted box which typicaRy contains an electronic circuitry, control lines and power if needed. The second body portion may also incorporate additional UV LEDs to provide addition UV illumination at the lower body portion of the device. The device may also incorporate an additional visible LED represents a trace and is be strategically positioned along a length of cable, the positioning of each ultraviolet light source device is then fed back to an external control module.

The ultraviolet device is used in an array of ultraviolet devices attached to a cable. Each device is programmable with an ultraviolet profile of a hostile firing action. Each device is sequentially excited along the cable in sequence. Although the cable is static, the ability to so sequentially "flash' each device along a cable would give the effect of movement. This movement can be controlled to emulate a tracer, hostile fire indication (HF1), and missiles travelUng from subsonic to supersonic speeds. This method of flashing multiple UV devices can provide inherent repeatability as the same sequence could be repeated over and over again. By changing the sequence or profile, sensitivity measurements could also be made to the ultraviolet missile warning system (UVMWS) under test A realistic track and a dynamic input to the missile warning system is provided by elevating one end of the cable at the test site to provide some height above the ground leveL The missile warning system (MWS) under test is typically located on a tria' airborne platform, which could then fly a more realistic approach towards the elevate array of UV devices, otherwise known as a "necklace". This concept is very similar to Christmas lights or the conventional disco necklace.

h an alternative embodiment of the invention the lower spherical body 24 may also incorporate an energy storage device, which is subsequently connected to a solar energy collecting device. The solar energy collecting device may be Located on a surface of the upper portion of the device or on the surface of the lower portion of the device.

h another alternative embodiment of the invention, the LED driving means in each device is wirelessly connected to an external system controlling means, which provides the means of wirelessly programming a UV profile into each ultraviolet tight source device.

n an alternative embodiment of the invention the first and second voids typically house either a wireless transmitter/receiver and/or solar energy collecting device.

Other benefits of one or more UV light source devices arranged in an array along a cable are: * remove the health and safety aspects associated with firing live ammunition at a friend'y platform; * remove some of the ethics constrained associated with prolonged testing; * along the trials platform to fly a more accurate baseline; * significantly reduce costs of high quality live fire ammunition; * repeatable test scenario at virtual zero cost once the system was procured; * provide a means of developing tactics and doctrine in a controlled environment; * provide a "squadron training so'ution" prior to theatre operation deployment; and provide a programmable system to replicate sub and supersonic missiles, hostile fire indications and false targets.

These are solutions which could overcome some of the current constraints of testing.

Figure 5 shows an array of ultraviolet LED devices 40 and visible LED sources 41 strategically positioned along a cable 42. The cable 42 is raised at one end 43 to provide a realistic track and a dynamic input into a missile warning system. The cable 42 is held and supported by an array of supporting poles 45. The top most supporting portion of each io pole 43 supports the cable 42 so that the cable 42 linearly ascends from the lowest end to the raised end 43. The UV devices 40 will be flashed in a sequence according to their UV profiles to emulate a hostile firing action originating from the lowest end 44, up to the raised end 43 towards the intended airborne pLatform 46 with the missile warning system under test. The strategically placed visible LED sources 41 provide a visible trace to emulate a trace from a hostile firing action.

Figure 6 shows a schematic view of an individual ultraviolet light source device generally indicated by 50, attached to a cable 51 incorporating one or more control lines connected to a controlling device, such as a computer. The UV LED 52 and visible light LED 53 are attached to the device 50 so that there emitted light is clearly visible. The LEDs 52 and 53 are connected to an LED driving means 54, which is also attached to the one or more control lines.

Figure 7 shows as apparatus for communicating simulated radar signals to remote sensor points on a piece of prime equipment. The prime equipment is typically a flying platform; however it may also be a land-based vehicle.

The apparatus incorporates a radar simulator device 60, which is connected to an optical modulator 61, via a coaxial lead 66 to facilitate the communication of a Radio Frequency (RF) from the radar simulator device 60 to optical modulator 61. The optical modulator 61 is typically a Mach-Zehnder modulator, which incorporates three optical communication outputs 62 that are connected to remote transducer devices 63. The remote transducer devices are located at sensor points on a flying platform 64. The Mach-Zehnder modulator 61 is connected to the remote sensors via optical fibres 65, which facilitate the communication of the optical signal from the Mach -Zehnder modulator 61 to the remote transducer devices 55.

h use, complex radar signals originating from the radar simulator devices are communicated, or "piped" to various operating areas in the vicinity The major drawback of communicating radar signals along a length of "metallic" conductor cable above 25 metres in length is that the signal attenuation at the high frequency end of the spectrum (is GHz) is so large that the signal integrity will fall below an acceptable leveL Due to noise, flaw and harmonic distortion it is not possible to recover the signal by known simple amplification techniques.

Standard RF coaxial cables for 20 and 40 metre runs provide significant signal loss of greater than 10 dB across the 2-13 GHz band. This loss is exacerbated as the range is extended from 0.5 -40 GHz.

Therefore, the optical fibre connections from the radar simulator to the remote transducers located on the flying platform. The optical fibres provide photonic links, which facilitates in the communication of optical signals lengths in excess of 25 metre.

For standard fibre-optic cable, the transmission loss of 1.55 pm laser carrier, is expected to be in order of 0.1 dB per kilometre and in regards to the superimposed RF, it will be constant across the RF band.

The radar simulator device outputs an RF radar signal, which when transmitted is used to amplitude modulate a laser system, such as a Mach-Zehnder Modulator. The modulated laser light is them communicated down a standard fibre-optic cable before being converted into a RF signaL through the use of an avalanche photodiode within a transducer device. The RF signal is then subsequently communicated to the intended sensor under so test.

As in other systems, the frequency response is a function with characteristics of both the modulator and the photodiode receiver within the transducer. In this case the photodiode is a commercial 50 GHz avalanche photodiode it comes with its own bias circuit.

The Mach-lender modulator is packaged with a RIN laser and modulator bias network.

There is no external adjustment of the Mach-lender modulator in this configuration. The use of propriety bias network simpUfies the operation of the device. The bias point and the operation of the Mach-lender modulator are very dependent upon ambient temperature.

The operating temperature of the Mach-lender modulator is controlled by an inbuilt peltier device, which is powered from an external 12 volt power supply. During operation it was noted that the current drawn was very dependent on the external temperature.

Temperature control is an important feature of the realisation of this unit.

The insertion loss of the apparatus is 24.5 dB at 2 GHz with a Laser bias of 8.17 mA.

For system wherein the insertion loss is a combination of transfer functions, from the laser, there is the optical loss due to joints and phase matching cables to the Mach-Lender modulator (LI), the transfer function of Mach-lender modulator (L2), the optical loss from the Mach-lender modulator to the photodiode (L3) and the transfer function of the diode itself (L4).

The insertion loss is simply the combination of all these losses, L total Li # L2 -i-L3 -L4 and the power out is purely a funcfion of these losses with the laser power, P out = P laser -L totaL The optical losses are typically 0.3 dB per connection and 0.5 per kilometre of optical cable.