GB2491963A - Communicating a simulated radar signal from a radar signal generator to a radar sensing device - Google Patents
Communicating a simulated radar signal from a radar signal generator to a radar sensing device Download PDFInfo
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- GB2491963A GB2491963A GB1210427.9A GB201210427A GB2491963A GB 2491963 A GB2491963 A GB 2491963A GB 201210427 A GB201210427 A GB 201210427A GB 2491963 A GB2491963 A GB 2491963A
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J2/00—Reflecting targets, e.g. radar-reflector targets; Active targets transmitting electromagnetic or acoustic waves
- F41J2/02—Active targets transmitting infrared radiation
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Communicating a simulated radar signal from a radar signal generator to a radar sensing device is accomplished by communicating a first radio frequency (RF) signal from a radar signal simulator to an optical modulator device. The RF signal is then converted to an optical signal. The optical signal is communicated from the optical modulator to a radar sensing device. The optical signal is converted to a second RF signal and communicated to the radar sensing device.
Description
A Self-Propelled Flying Apparatus adapted to emulate a Hostile Firing Action
FieLd of the Invention
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 vioLet profile of a known threatening action.
In 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 It 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 Indication (HFI) and counter countermeasures or faLse target repLication.
Another known soLution to this probLem is to fire actuaL 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 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
In a first 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 * Communication said second radio frequency to a radar sensing device.
In a second 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 modulation 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 100 MHz to 40 GHz. These signaLs are communicated over of opticaL fibres Link(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, it 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 RE 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.
* 3rd Harmonic Performance This configuration gives satisfactory performance for all input levels from 0 dB downwards.
* OdBTwoTone 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 -dB in put1 the harmonics are greatly reduced. Harmonic and inter-modulation levels have fallen significantly from 0 dBm input which cannot be disceined 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 GHz, 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 aLong the fibre optic to be converted back to a RF-based signaL.
PreferabLy, said radar sensing device is disposed in / on a vehicle. This enabLes the communication of radar generated signaLs to radar sensing devices Located about a Land-based vehicLe.
Preferably, said vehicLe is a fLying vehicLe. This enables the communication of radar generated signals to sensors Located about a fLying vehicLe.
Brief Description of the figures
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.
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 5 is encLosed under a transparent domed portion 6, which is typically formed from either a glass or plastics material. The rocket 1 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 source array 5 is a typical array of one or more UV Light-Emitting Diodes (LED5) located on is 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.
In 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 control 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.
The rocket has a re-useable body, which incorporates a parachute recovery system that is 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.
In 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 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 (H El) 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 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 equally 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 Light 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 Lower 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 LEDs. 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 is 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 typicaLLy 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 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 (H Fl), and missiles travelling 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 trial 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.
In 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 is 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.
In 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 light source device.
In 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 friendly 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 soLution" 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 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.
In 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 (18 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 RE coaxiaL cabLes for 20 and 40 metre runs provide significant signaL Loss of is greater than 10 dB across the 2 -18 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.
Eor standard fibre-optic cabLe, the transmission Loss of 1.55 im Laser carrier, is expected to be in order of 0.1 dB per kiLometre and in regards to the superimposed RE, it wiLL be constant across the RE band.
The radar simuLator device outputs an RE 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 RE signaL, through the use of an avaLanche photodiode within a transducer device. The RE signaL is then subsequentLy communicated to the intended sensor under 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 kIN Laser and moduLator bias network.
There is no externaL adjustment of the Mach-Lender moduLator in this configuration. The use of propriety bias network simpLifies 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 ([1), the transfer function of Mach-Lender moduLator ([2), the opticaL Loss from the Mach-Lender moduLator to the photodiode ([3) and the transfer function of the diode itseLf ([4).
The insertion Loss is simpLy the combination of aLL these Losses, [totaL = [1 + [2 + [3 + [4 and the power out is pureLy a function of these Losses with the Laser power, P out = P Laser -[totaL.
The opticaL Losses are typicaLLy 0.3 dB per connection and 0.5 per kiLometre of opticaL cabLe.
Claims (8)
- Claims 1. A method of communicating a simulated radar signal from a radar signal generator to a radar sensing device comprising the steps of: 5. 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 * Communication said second radio frequency to a radar sensing device.
- 2. 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 modulation 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.
- 3. A system according to claim 2, wherein said first communication means is a metallic conducting cable.
- 4. A system according to either of the preceding claims, wherein said optical modulation means is a Mach -Zehnder modulator.
- 5. A system according to any of claims 2 to 4, wherein said second communication means is an optical fibre.
- 6. A system according to any of claims 2 to 5, wherein said conversion means is facilitated by an avalanche diode.
- 7. A system according to any of claims 2 to 6, wherein said radar sensing device is disposed in / on a vehicle.
- 8. A system according to claim 7, wherein said vehicle is a flying vehicle.Claims 1. A method of communicating a simulated radar signal from a radar signal generator to a radar sensing device comprising the steps of: 5. 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 * Communication said second radio frequency to a radar sensing device.2. A system for communicating a simulated radar signal from a radar generator to a radar sensing device comprising: C) C\J * 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 modulation 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.3. A system according to claim 2, wherein said first communication means is a metallic conducting cable.4. A system according to either of the preceding claims, wherein said optical modulation means is a Mach -Zehnder modulator.5. A system according to any of claims 2 to 4, wherein said second communication means is an optical fibre.6. A system according to any of claims 2 to 5, wherein said conversion means is facilitated by an avalanche diode.7. A system according to any of claims 2 to 6, wherein said radar sensing device is disposed in / on a vehicle.8. A system according to claim 7, wherein said vehicle is a flying vehicle. (\Jis r C) c\J
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1210427.9A GB2491963B (en) | 2012-06-13 | 2012-06-13 | A self-propelled flying apparatus adapted to emulate a hostile firing action |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1210427.9A GB2491963B (en) | 2012-06-13 | 2012-06-13 | A self-propelled flying apparatus adapted to emulate a hostile firing action |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB201210427D0 GB201210427D0 (en) | 2012-07-25 |
| GB2491963A true GB2491963A (en) | 2012-12-19 |
| GB2491963B GB2491963B (en) | 2013-06-05 |
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| GB1210427.9A Expired - Fee Related GB2491963B (en) | 2012-06-13 | 2012-06-13 | A self-propelled flying apparatus adapted to emulate a hostile firing action |
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| Country | Link |
|---|---|
| GB (1) | GB2491963B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107065594A (en) * | 2017-01-12 | 2017-08-18 | 上海航天控制技术研究所 | A kind of carrier rocket six degree of freedom distributed semi physical simulation method and system |
| FR3103265A1 (en) * | 2019-11-14 | 2021-05-21 | Etienne Lacroix Tous Artifices S.A. | OFFSET ACTIVE LURE |
| US11215696B2 (en) * | 2016-07-15 | 2022-01-04 | Qinetiq Limited | Controlled radar stimulation |
-
2012
- 2012-06-13 GB GB1210427.9A patent/GB2491963B/en not_active Expired - Fee Related
Non-Patent Citations (1)
| Title |
|---|
| None * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11215696B2 (en) * | 2016-07-15 | 2022-01-04 | Qinetiq Limited | Controlled radar stimulation |
| CN107065594A (en) * | 2017-01-12 | 2017-08-18 | 上海航天控制技术研究所 | A kind of carrier rocket six degree of freedom distributed semi physical simulation method and system |
| FR3103265A1 (en) * | 2019-11-14 | 2021-05-21 | Etienne Lacroix Tous Artifices S.A. | OFFSET ACTIVE LURE |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2491963B (en) | 2013-06-05 |
| GB201210427D0 (en) | 2012-07-25 |
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| PCNP | Patent ceased through non-payment of renewal fee |
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