GB2524669A

GB2524669A - A self-propelled flying device to simulate a hostile firing action

Info

Publication number: GB2524669A
Application number: GB1510336.9A
Authority: GB
Inventors: John Chester-Parsons
Original assignee: EW Simulation Technology Ltd
Current assignee: EW Simulation Technology Ltd
Priority date: 2015-06-12
Filing date: 2015-06-12
Publication date: 2015-09-30
Anticipated expiration: 2035-06-12
Also published as: GB2524669B; GB201510336D0

Abstract

A self-propelled device for testing the defensive countermeasures of an aircraft. comprises a housing and propulsion means within said housing. One or more infra-red (IR) emitters 17 is mounted to the housing. The device also includes one or more infra-red sensors 18. The device also includes a controller governing the emission pattern IR emitters 17 and a power source to provide electric power to the controller and emitters. One or more ultra-violet (UV) emitters 16 may be provided. The propulsion means may be a rocket.

Description

A Self-Propelled Flying Device to Simulate a Hostile Firing Action

Field of the Invention

The present invention relates to a flying apparatus to simulate hostile fire, the invention finding particular use in reLation to hostiLe fire aimed at an aircraft The apparatus additionally enables determination of the effectiveness of the aircraft's defences against such hostile fire.

Background to the Invention

Anti-aircraft missiles are becoming increasingly sophisticated, utilising a number of inflight characteristics of the aircraft to detect and Lock on to said aircraft Once launched, they can carry out these without the requirement for guidance from a remotely located operator. Many such missiles search for localised, relatively high intensity infra-red sources as these are an indication of the location of an aircraft's engines which expel exhaust gasses at high temperature. In order to detect the presence of and also the direction and location of the source, which will almost inevitabLy be moving at a high velocity, the missile incLudes one or more infra-red sensors which provide information to a processor unit on the spectral components of the detected infra-red radiation and the intensity of these components.

In order to counter missiles having these capabilities, a variety of defensive options can be provided to an aircraft One of the most commonly utilised methods is to depLoy fLares which aim to imitate an aircraft's radiation emissions and so cause the missile to deviate away from the aircraft.

An alternative or complimentary countermeasure of a more active nature is to carry out an action which affects the missiLe's sensor systems. For exampLe projectiLes such as bulLets can be fired based on the Location co-ordinates provided by the countermeasure.

ALternativeLy, the missiLe's sensors can be overLoaded through the use of a high energy radiation; or the guidance algorithms of the missile can be confused by the receipt of a specific pattern. In this manner the guidance systems of the missiLes are corrupted Leading to the missile being thrown off course.

Many countermeasure systems rely on the detection of a characteristic radiation pattern from a missiLe. Said pattern is typically in the uLtra-violet (UV) range, but aLso in the opticaL or infra-red (1k) range. In order to determine the efficacy of such active defence systems, tests need to be carried out which replicate missile attack.

In prior patent appLication, GB 1107464.8, the current AppLicants discLosed the use of a missiLe which carried ultraviolet emitting sources which were programmed to emit UV radiation in a patent mimicking that of known missiLes. ALternativeLy, a series of UV emitters suspended from a cabLe was also discLosed, the sequence of emitters being such as to mimic a missiLe's fLightpath. Using these devices, the efficacy of the countermeasures couLd be determined at minimaL risk to human life, even when Live ammunition was empLoyed to deactivate the emitters. However, where the defence system uses non-projectiLe means, the determination of efficacy is more probLematic.

The present invention seeks to extend the type of missiLe defence system which can be tested and determined more accurately whether the defence system is effective, especiaLLy where a non-projectiLe means is utiLised against the missiLe.

Summary of the Invention

According to a first aspect of the invention there is provided a seLf-propeLLed device for testing the defensive countermeasures of an aircraft, the device comprising: a housing and propuLsion means within said housing one or more infra-red (1k) emitters, mounted to the housing one or more infra-red sensors, mounted to the housing a controLLer governing the emission pattern of the or each IR emitters, a power source to provide eLectric power to the controLLer and emitters.

S The device is capabLe of emitting IRradiation to mimic emissions from known threats such as missiles and variants thereof. The ability of the defensive countermeasures to detect and recognise the device can therefore be determined and hence the Likely effectiveness against the missiLes themseLves. In addition the device can sense whether IR countermeasures from an aircraft are being correctly targeted on the device.

PreferabLy the device incLudes one or more UV emitters mounted to the housing to enabLe, for example) the device to mimic a known missiLe or the Like.

Preferably the propuLsion means incLudes a rocket to impart a Large acceLeration and a sufficient veLocity to the device to mimic a missiLe.

The or each UV emitter is optionaLLy an LED emitter to give a high photon fLux when required, but with Low power usage. The emitted radiation can thus be of sufficient intensity to be detected by the defensive countermeasures and to remain at the required intensity over the required period.

The or each IR emitter is specificalLy selected to give a high photon flux in the required IR band) but with Low power usage. The emitter can be seLected from a pyrotechnic device) a chip Laser, a quantum cascade Laser, a hot wire or an LED emitter. The emitted radiation can thus be of sufficient intensity to be detected by the defensive countermeasures and to remain at the required intensity over the required period.

The device preferably incLudes locator means enabLing the three-dimensionaL position of the device to be determined) said Location means further preferabLy comprising one or more accelerometers.

The device optionally incLudes a time-measuring device, or further optionaLLy a clock enabling the output from the time-measuring device or clock and the Location means to be Linked and aLLowing veLocity and acceLeration data to be easiLy derivabLe.

PreferabLy the or each 1k sensor incLudes an opticaL device such as a Lens to enhance the signaL received by the or each 1k sensor. The or each 1k sensor is conveniently coupLed to S an amplifier to increase the signal output from the sensor in response to a signal received.

The device preferably incLudes a data memory to receive and store data from the sensor, Location means and the cLock. Said data memory is further preferabLy removabLe aLLowing the data to be fulLy processed remote from a test site and for a new data memory to be instaLLed into a device. The remote processing aLLeviates many security issues and aLso enabLes data from different tests to be compiLed and for detaiLed assessments to be made of performance characteristics.

OptionalLy, the device includes a parachute) reLeasabLe to minimise the damage to a device on impact with the ground after use and aLso faciLitating retrievaL of the device.

ConvenientLy, the emission of 1k is timed to cease after a pre-set period or when data acquisition has been compLeted in order to conserve power) said cessation aLso triggering reLease of the parachute. Further convenientLy the emission of UV is timed to cease after a pre-set period.

Preferably, the housing is generaLly cyLindrical having at a first end of the housing the propuLsion means and at a second head end) one or more of the emitters and sensors and further preferabLy aLl the emitters and sensors.

OptionalLy, the head end comprises a UV/IR transparent medium, further optionaLly dome-shaped to surround and physicaLLy protect the emitters and sensors and yet aLLow radiation through the transparent medium.

The or each emitter, sensor and the transparent medium are conveniently housed in a sensor module, the sensor module being further conveniently removably connected to the housing.

According to a second aspect of the invention there is provided a method of testing the effectiveness of a missile countermeasure, the method comprising: seLecting a device comprising a housing and propuLsion means within said housing, one or more infra-red (IR) emitters, along with one or more IR sensors mounted to the housing, S the device including a controller governing the emission pattern of the or each IR emitters and a power source to provide electric power to the controller, sensors and emitters, propelling said device towards a missiLe countermeasure and emitting IR signals of a predetermined pattern towards a countermeasure.

Brief Description of the Drawings

The invention is now described with reference to the accompanying drawings which show by way of example one embodiment of a device. In the drawings: Figure 1 is a perspective image of a device; Figure 2 shows the head of the device in more detail; and Figure 3 is a timeline of the functioning of the device in use.

Detailed Description of the Invention

Referring initially to figure 1, this discloses a rocket-propelled missile 10, suitable for use to test the effectiveness of countermeasures to such missiles under combat or near-combat conditions. Such countermeasures as specifically contemplated herein are those utilised on aircraft, usually fixed-wing although the invention herein described is also suitable for testing land or sea-based countermeasures.

The countermeasures are designed firstLy to detect the presence) Location and veLocity of a missfte and second to initiate means of deactivating the incoming missi'e.

The means of detection utilised in the countermeasures being tested by the present invention is via the UV and IR emissions from the missile. Such emissions are either inherent in the missiLe and/or its means of propuLsion, but can aLso arise from specific signak sent out by the missiLe as it seeks to Lock onto the target.

In the previous patent appLication cited above, an aspect of the testing of the countermeasure or defensive aid system (DAS) was disdosed which stimubted the countermeasure to aLert the air crew to the situation. However) more recent countermeasures ako automatically engage the missile with a range of countermeasures.

Some of these are passive, such as fLares, or can be active such as infra-red countermeasures (IRCM) or directed infra-red countermeasures (DIRCM). These countermeasures reLy upon putting sufficient energy onto the missiLe's sensors or a specific jamming code to disrupt the missiLes guidance system.

In generaL terms therefore, the device of the current invention provides a means of propeRing a platform on which IR and UV emitters are Located, which emitters are driven by a pre-programmed controLLer to emit radiation such that the emissions of a missiLe are imitated. In addition, a sensor can also be included to determine radiation directed at the device by a countermeasure and hence whether the countermeasure is LikeLy to be effective.

As such, the missiLe 10 comprises a main housing 11, generaLLy cyLindricaL in shape. It wiLL be appreciated that the shape of the discLosed embodiment is chosen to mimic that of conventional missiles. However, given that the principal emissions to imitate no missiles are from the emitters, then other shapes of housing can be empLoyed.

At a first end of the housing 11, extend fins 12 to stabiLise the missiLe 10 in flight.

Propulsion means (not illustrated) are ako included at the first end, which propukion means are most usuaLly rocket means. The interna' volume of the missiLe 10 will therefore normaLLy incLude a fueL storage moduLe, which can be in soLid or Liquid form.

ALso incLuded within the housing 11 can be a parachute. Once the in-fLight tests have been carried out, or the missiLe has otherwise carried out its tasks, the propuLsion means is deactivated. In order to minimise damage to the device and the data accumuLated therefore) a parachute is deployed. Said deployment can aLso function as a visual signaL of the successfuL targeting of the missile.

At the second end of the housing 11 is Located a head moduLe 13 (shown in more detaiL in figure?) in which UV and IR emitters are Located. The head moduLe 13 incLudes a dome 14, formed of a material such as a pLastics or gLass, which materiaL is transparent to the S radiation wavelengths to be transmitted and/or received. The head moduLe 13 shouLd aLso ideaLLy be impact resistant and/or scratch resistant to minimise refLection or diffraction Losses.

The head moduLe is preferably separable from the housing 11 to enabLe defective or damaged parts to be easiLy repLaced without having to repLace the entire missiLe. The head and the housing can be joined by conventionaL methods known in the art such as screw-head fitment or a push-fit mechanism.

Beneath the dome 14 is a disc or annuLar shaped support 15. The support 15 provides a stabLe base to which the more sensitive eLectronic components can be fixed. SimiLarLy to the invention discLosed in the above-cited appLication, a number of UV emitters 16 in the form of LEDs are incLuded. The UV-LEDs are driven by a controLLer within the housing 11 to emit a spectrum which mimics that of known missiLes both in terms of absoLute intensity and aLso reLative intensity of the waveLength.

AdditionalLy, a number of IR emitters 17 are also Located on the support 15 and enabLe IR radiation to be emitted to provide a signaL which can be Locked onto by, for exampLe the fine track sensor of a DIRCM. Once the DIRCM has Locked onto the signaL, the DIRCM transmits a signal to the determined signaL source, which signaL is either of sufficient energy to overLoad the sensor or comprises a jamming signaL specific to the perceived missiLe to inactivate the missiLe or affect the missiL&s guidance system. The IR emitter can be seLected from a pyrotechnic device, a chip laser, a quantum cascade Laser, a hot wire or an LED emitter.

In order for the effectiveness of the signal from the countermeasure signal to be determined, the missile 10 also includes a sensor 18, also located on the support 15. The sensor 18 primarily senses IRradiation, but the range of wavelengths detected can be chosen to suit the test being undertaken. It will be appreciated an array of one or more sensors 18 can be utilised.

In an alternative embodiment of the invention the support 15 can employ a plurality or an array of sensors 18, whereby the configuration of the sensors improves the sensitivity of the sensors and/or facilities the sensing of very high level energy beams.

The signal received may not, in absolute terms be of high intensity and so an amplifier can be included to increase the output from the sensor 18 or also into the sensor 18. The amplified signaL can be coupLed to an analogue to digital convertor. AdditionalLy, a filter can be across the sensor 18, because the filter will prevent any high level energy beam that is sensed by the sensor 18 from damaging the sensor 18. TypicalLy both the filter and sensor 18 are optical devices.

The sensor 18 is connected to a data storage means and aLso optionaLly a processing means located within the housing 11. The intensity of the signal received and/or other information can therefore be stored for later analysis folLowing retrievaL of the data storage means. Additionally, processing of the received signal by the processing means can be used to enable a decision to be made that the test is complete and to end the missile's flight. The processing means can therefore be linked to the propuLsion to cause the propulsion to cease and also for the parachute to deploy.

It is of importance that the data analysis be able to determine the location and velocity of the missile 10 and also to be able to link this information with sensor data. Within the housing 11 therefore is also housed a three axis accelerometer) along with a timing device or a clock. The location of the missile after a given time can therefore be determined and from this data the velocity and acceleration can be caLculated.

The information derived from these measurements can be used to determine when the countermeasure is at its most and also at its [east effective.

In figures 3, is outlined the time lines of events from (a) the missiLe, (b) the countermeasure, defensive aid system (DAS) and (c) the flight of the missile. Upon Launch of the missile (left-hand pictogram in (c)) there is an initial UV spike emission which shouLd be detected by the MissiLe Approach Warning (MAW). The UV emission is then continued by the UV emitters 16 Located in the missile to stimulate the DAS and also to mimic known missiLe systems. The infra-red emitters 17 are aLso programmed to transmit their controlled emission shortly after missile Launch.

The missile's emissions are picked up by the DAS and if the DAS functions according to S specifications, the system will Lock on to the missile and commence countermeasures. The countermeasures should in their turn be detected by the sensor 18. Once the missile has completed the test flight, the parachute is deployed as shown in the right-hand pictogram of (c). The missile can be picked up by ground-based operators and the data storage device within the missile retrieved for subsequent analysis.

Therefore in use, the missiLe [or any other type of flying device] is flown towards a fLying platform, which comprises a Countermeasure System and/or Defensive Aid System [DAS].

The UV and/or IR emissions from the missile are combined with the flight characteristics of the missile to provide an emulation of an in-flight missile threat. When detected) the Countermeasure System and/or the DAS wiLl track and engage the missile with Infra-Red Countermeasures [IRCM], such as flares, or Directed Infra-Red Countermeasures [DIRCM].

The missiLe comprises a radiation sensor) which can be selected to sense a waveLength range) such as IR. The sensor senses the radiation emitted from the IRCM or DIRCM, while both the missile and the vehicle are in flight.

The sensor provides information indicative of the effectiveness of the radiation emitted from the IRCM and/or DIRCM, combined with the flight characteristics of the vehicle, to the missile sensor.

The information indicative of the effectiveness of the radiation is then communicated to an information storage means) which can then be subsequently retrieved for further use.

Thus the missi'e provides the technicM effect of determining the effectiveness of a radiation emission countermeasure which is in response to a detection of an in-fLight missiLe threat.

Claims

Claims 1. A seft-propeRed device for testing the defensive countermeasures of an aircraft, the device comprising: a housing and propukion means within said housing one or more infra-red (IR) emitters, mounted to the housing one or more infra-red sensors, mounted to the housing a controlLer governing the emission pattern of the or each IR emitters, a power source to provide eLectric power to the controLLer and emitters.
2. A device according to CLaim 1, wherein the device incLudes one or more uLtra-vioLet (UV) emitters, mounted to the housing.
3. A device according to CLaim 1 or CLaim 2, wherein the propuLsion means comprises a rocket to impart a Large acceleration and a sufficient velocity to the device to mimic a missiLe.
4. A device according to CLaim 2 or CLaim 3, wherein the or each UV emitter is an LED emitter.
5. A device according to any preceding cLaim, wherein the or each IR emitter is selected from a pyrotechnic device, a chip laser, a quantum cascade laser, a hot wire or an LED emitter.
6. A device according to any preceding claim, wherein the device includes locator means enabLing the three-dimensionaL position of the device to be determined.
7. A device according to Claim 6, wherein said Location means further comprises one or more acceLerometers.
8. A device according to any preceding cLaim, wherein the device incLudes a time measuring device.
9. A device according to CLaim 8, wherein the time measuring device is a dock.
10. A device according to any preceding cLaim, wherein the or each IR sensor incLudes an opticaL device such as a Lens to enhance the signaL received by the or each IR sensor.
11. A device according to Claim 10, wherein the or each IR sensor is coupLed to an amplifier to increase the signaL output from the sensor in response to a signaL received.
12. A device according to Claims 8-11, wherein the device preferably includes a data memory to receive and store data from the sensor, Location means and the time measuring device.
13. A device according to CLaim 12) wherein said data memory is removabLe.
14. A device according to any preceding cLaim, wherein the device incLudes a parachute, releasabLe to minimise the damage to a device on impact with the ground.
15. A device according to any preceding cLaim, wherein the emission of IR is timed to cease after a pre-set period or when data acquisition has been compLeted.
16. A device according to Claims 2-15, wherein the emission of UV is timed to cease after a pre-set period.
17. A device according to CLaim 15 or CLaim 16, wherein said cessation aLso triggers reLease of the parachute.
18. A device according to any preceding daim, wherein the housing is generalLy cyLindricaL having at a first end of the housing the propuLsion means and at a second head end, one or more of the emitters and sensors.
19. A device according to Claim 18, wherein alL the emitters and sensors are at the second head end.
20. A device according to any preceding daim, wherein the second head end comprises a transparent medium.
21. A device according to Claim 20, wherein the transparent medium is dome-shaped to surround and physically protect the emitters and sensors and yet alLow radiation through the transparent medium.
22. A device according to Claim 20 or CLaim 21, wherein the or each emitter, sensor and the transparent medium are housed in a sensor moduLe.
23. A device according to Claim 22, wherein the sensor moduLe is removably connected to the housing.
24. A device substantialLy as herein described with reference to and as iLLustrated by the accompanying drawings.