GB2400644A - Apparatus for the stimulation of a missile approach warning system - Google Patents
Apparatus for the stimulation of a missile approach warning system Download PDFInfo
- Publication number
- GB2400644A GB2400644A GB0023125A GB0023125A GB2400644A GB 2400644 A GB2400644 A GB 2400644A GB 0023125 A GB0023125 A GB 0023125A GB 0023125 A GB0023125 A GB 0023125A GB 2400644 A GB2400644 A GB 2400644A
- Authority
- GB
- United Kingdom
- Prior art keywords
- optical
- missile
- energy
- warning system
- approach warning
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000013459 approach Methods 0.000 title claims abstract description 29
- 230000000638 stimulation Effects 0.000 title claims abstract description 13
- 230000003287 optical effect Effects 0.000 claims abstract description 26
- 230000005855 radiation Effects 0.000 claims abstract description 17
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 claims abstract description 10
- 230000003595 spectral effect Effects 0.000 claims description 21
- 230000002123 temporal effect Effects 0.000 claims description 9
- 238000001228 spectrum Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000002329 infrared spectrum Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000003542 behavioural effect Effects 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000001010 compromised effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 231100000989 no adverse effect Toxicity 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/001—Devices or systems for testing or checking
- F41G7/002—Devices or systems for testing or checking target simulators
- F41G7/004—Devices or systems for testing or checking target simulators for infrared seekers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/22—Homing guidance systems
- F41G7/224—Deceiving or protecting means
Abstract
Apparatus (2) for the stimulation of a missile approach warning system by electro-optical infrared signal generation, which apparatus (2) comprises optical means (4) , an electro-optical infrared source (6) comprising a plurality of individual sources (8, 10) for providing radiation for passing through or being modified by the optical means (4) in order to produce a beam of energy, and modulator means (12) for controlling the beam of energy, the modulator means (12) being programmable for producing a signal having characteristics typical of the radiation emitted from an approaching rocket-propelled missile, and the apparatus (2) being such that the beam of energy is able to be directed through space towards the missile approach warning system. The apparatus may also comprise a source of ultra violet radiation.
Description
APPARATUS FOR THE STIMULATION OF A MISSILE
APPROACH WARNING SYSTEM BY ELECTRO-OPTICAL
INFRARED SIGNAL GENERATION
This invention relates to apparatus for the stimulation of a missile approach warning system and, more especially, this invention relates to apparatus for the stimulation of a missile approach warning system by electro-optical infrared signal generation. The missile approach warning system may be used for the protection of aircraft against approaching rocket-propelled missiles.
INTRODUCTION AND BACKGROUND
Guided rocket-propelled missiles form a significant and widespread threat to aircraft. The propulsion means of the missiles is a fuel burning rocket and this is distinguishable by the characteristics of the associated flare or plume of hot gases and combustion by-products.
Different types of apparatus have been developed that seek and detect certain characteristic electromagnetic energies emitted by the exhaust of the rocket. These different types of apparatus are known as missile approach warning systems.
Certain electro-optical spectral characteristics are typical of the emissions from the plume of hot gases from the rocket exhaust. Known missile approach warning systems exploit both a general similarity of emitted spectral and temporal characteristics and advantageously specific characteristics of known missiles.
Signal processing algorithms may be employed to analyst the detected signals by comparison with known behavioural characteristics and are thereby able to distinguish between true hostile rocket signatures and artifacts that may be otherwise produced for the purposes of deception.
Electronic warfare techniques include the generation of electro-optical signal generators that are designed to generate false alarms from the missile approach warning systems. The reception and declaration of false alarms is wasteful of any deployed countermeasures and may result in a compromised aircraft mission. In order that false alarms may be recognised as such and rejected by the missile approach warning systems, the detection algorithms employed are of increasing complexity and sophistication.
One characteristic detail of a missile rocket plume is the emission of two particular spectral bands, the so-called red and blue bands within the known infrared spectrum. The presence of these two spectral bands and the temporal rate of change of the relative energy levels of these characteristic bands provides a powerful means of distinguishing true alarms from false alarms.
Furthermore, differential atmospheric attenuation of the characteristic red and blue spectral bands results in received energy levels whose relative magnitudes vary according to the separation of the source from the receiver. A true signature may be confirmed by analysis of the rate of change of the ratio of received energy in these two specific spectral wavebands.
BRIEF DESCRIPTION OF THE INVENTION
It is an aim of the present invention to provide apparatus that will simulate the temporal and spectral emissions of a rocket plume by including control of the blue and red spectral bands.
Accordingly, the present invention provides apparatus for the stimulation of a missile approach warning system by electro-optical infrared signal generation, which apparatus comprises optical means, an electro-optical infrared source comprising a plurality of individual sources for providing radiation for passing through or being modified by the optical means in order to produce a beam of energy, and modulator means for controlling the beam of energy, the modulator means being programmable for producing a signal having characteristics typical of the radiation emitted from an approaching rocket-propelled missile, and the apparatus being such that the beam of energy is able to be directed through space towards the missile approach warning system.
The apparatus of the present invention may advantageously be used for the testing and verification of missile approach warning systems. The apparatus of the present invention may also be used for the remote stimulation of air defence systems for training or deceptive purposes. The apparatus of the present invention may further be used for the protection of aircraft against rocket-propelled missiles. I The apparatus of the present invention may be one in which the emissions of the beam of energy specifically control individual spectral bands.
The apparatus may include modifying means for enabling temporal control of the emitted spectral bands according to stored data to represent temporal characteristics typical of the rate of change of radiation received from the approaching rocket propelled missile.
Advantageously, the apparatus includes an additional source of ultra violet radiation for extending the emitted spectrum in order to replicate the radiative effect of heating of the body of the approaching missile. Thus the source of ultra violet radiation may be used in order that certain missile approach warning systems may detect the ultra violet signature characteristic of a body whose temperature is significantly hotter than ambient atmosphere or
background.
The apparatus of the present invention may include further sources or filters and controls for generating additional spectral characteristics.
The optical means may be refractive optical means, reflective optical means, or mechanical shutter means.
Generally, known missile approach warning system stimulators comprise a source of illumination such for I example as an incandescent lamp or arc with spectral energy in the mid-infrared wavebands typical of those of a rocket plume. The temporal characteristics of the emission may be controlled both through the variation of power supplied to the emitter, or additionally by physical obscuration of the emission by mechanical shutter means, acting like an iris. The mechanical shutter means may advantageously be employed to produce fast rates of change of the electromagnetic emission from the apparatus typical of, for example, rocket ignition or extinction.
The optical means may be optical filter means.
The apparatus may be one in which the modulator means is responsive to motion of an aircraft having the missile approach warning system, whereby control of the beam of energy is influenced by the motion of the aircraft.
The apparatus of the present invention may provide the means to emit and control the so called blue and red spectral bands within the known infrared spectrum. The absence of these particular characteristics may otherwise prevent the declaration of a true alarm by the most modern of missile approach warning systems.
DESCRIPTION OF THE DRAWINGS.
Embodiments of the invention will now be described solely by way of example and with reference to the accompanying drawings in which: Figure 1 is a schematic diagram of first apparatus for the stimulation of a missile approach warning system by electro-optical infrared signal generation; and Figure 2 is a schematic diagram of second apparatus for the stimulation of a missile approaching warning system by electro- optical infrared signal generation.
Referring now to Figure 1, there is shown apparatus 2 for the stimulation of a missile approach warning system by electro- optical infrared signal generation.
The apparatus 2 comprises optical means 4, and an electro-optical infrared source 6. The electro-optical infrared source 6 comprises a plurality of individual sources 8, 10. The electro-optical infrared source 6 is for providing radiation for passing through or being modified by the optical means 4 in order to produce a beam of energy.
The apparatus 2 further comprises modulator means 12 for controlling the beam of energy. The modulator means 12 is programmable for producing a signal having characteristics typical of the radiation emitted from an approaching rocket-propelled missile. The modulator means 12 may be programmed with reference data from reference data means 14.
The apparatus 2 is such that the beam of energy that is produced is able to be directed through space towards the missile approach warning system.
In its broadest aspect, the apparatus 2 comprises a plurality of infrared emitters in the form of the individual sources 8, 10. Each of the individual sources 8, 10 separately illuminates optical means 4 in the form of a separate optical filtering means. The filtering means favourably transmits a characteristic spectral band of energy typical of the red and blue spectral bands within the known infrared spectrum. By independent control of the individual sources 8, 10, the ratio of the energy contained within the red and blue bands may advantageously be varied to replicate the temporal and spectral signature of an approaching rocket-propelled missile.
Although the plurality of individual sources 8, 10 are physically separated, there is no adverse effect at the missile approach warning system since the individual sources are parallel and are thus indistinguishable at a distance from a single distributed source having the combined characteristics of each source.
Referring now to Figure 2, there is shown second apparatus 16 for the stimulation of a missile approach warning system by electro-optical infrared signal generation. The apparatus 16 includes the apparatus 2 shown in Figure 1 and similar parts have been given the same reference numerals for ease of comparison and understanding. Figure 2 additionally includes a source of ultra violet radiation 20. The source of ultra violet radiation 20 may be used for extending the emitted spectrum in order to replicate the radiative effect of heating of the body of the approaching missile.
The apparatus 16 shown in Figure 2 may thus operate such that the apparatus 2 generates a temporally and spectrally controlled emission of infrared light having two specific spectral characteristics within the required waveband. These spectral characteristics are determined by the optical means 4 in the form of appropriate filters. The modulator means 12 acts as electronic control means to provide appropriate power to the plurality of individual infrared sources 8, 10. The electrical power so provided is controlled such as to vary the relative and absolute energies emitted by each individual source 8, 10. The radiated energy profile may advantageously be controlled by means of the reference data means 14 which may be in the form of a micro controller. The micro controller may be such that its data input is derived from "look-up" files in order to produce appropriate missile signatures.
A closed-loop form of operation may be employed in which data is derived from real-time measurements such as the flight profile of an aircraft and any counter measures that may be employed. These data are advantageously employed to modify the emitted characteristics of the apparatus 16. The electro- optical infrared source 6 may typically be an incandescent lamp, an arc lamp, plasma device or any other means for producing energy with the appropriate frequency spectrum.
The source of ultra violet radiation 20 is collocated within the apparatus 16 in order to provide a signature extended into the short ultra violet wave bands characteristic of the radiative emissions of a hot missile body.
Flight-line test equipment such as may be used for pre-flight test and verification of missile approach warning systems at close range may use the apparatus 2, 26 in a dual infrared source implementation.
Alternatively if desired, a long range missile approach warning system stimulator may utilise the apparatus 2, 16 with the plurality of infrared sources in order to obtain sufficient energies within selected wavabands.
It is to be appreciated that the embodiments of the invention described above with reference to the accompanying drawings have been given by way of example only and that modifications may be effected.
Claims (11)
1. Apparatus for the stimulation of a missile approach warning system by electro-optical infrared signal generation, which apparatus comprises optical means, an electro-optical infrared source comprising a plurality of individual sources for providing radiation for passing through or being modified by the optical means in order to produce a beam of energy, and modulator means for controlling the beam of energy, the modulator means being programmable for producing a signal having characteristics typical of the radiation emitted from an approaching rocket-propelled missile, and the apparatus being such that the beam of energy is able to be directed through space towards the missile approach warning system.
2. Apparatus according to claim 1 in which the emissions of the beam of energy specifically control individual spectral bands.
3. Apparatus according to claim 1 or claim 2 and including modifying means for enabling temporal control of the emitted spectral bands according to stored data to represent temporal characteristics typical of the rate of change of radiation received from the approaching rocket- propelled missile.
4. Apparatus according to any one of the preceding claims and including a source of ultra violet radiation for extending the emitted spectrum in order to replicate the radiative effect of heating of the body of the approaching missile.
5. Apparatus according to any one of the preceding claims and including further sources or filters and controls for generating additional spectral characteristics.
6. Apparatus according to any one of the preceding claims in which the optical means is refractive optical means.
7. Apparatus according to any one of claims 1 - 5 in which the optical means is reflective optical means.
8. Apparatus according to any one of claims 1 - 5 in which the optical means is mechanical shutter means.
9. Apparatus according to any one of the preceding claims in which the optical means is optical filter means.
10. Apparatus according to any one of the preceding claims in which the modulator means is responsive to motion of an aircraft having the missile approach warning system, whereby control of the beam of energy is influenced by the motion of the aircraft.
11. Apparatus for the stimulation of a missile approach warning system by electro-optical infrared signal generation, substantially as herein described with reference to the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0023125A GB2400644B (en) | 2000-09-20 | 2000-09-20 | Apparatus for the stimulation of a misile approach warning system by electro-optical infrared signal generation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0023125A GB2400644B (en) | 2000-09-20 | 2000-09-20 | Apparatus for the stimulation of a misile approach warning system by electro-optical infrared signal generation |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB0023125D0 GB0023125D0 (en) | 2004-05-05 |
| GB2400644A true GB2400644A (en) | 2004-10-20 |
| GB2400644B GB2400644B (en) | 2005-02-09 |
Family
ID=32247443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0023125A Expired - Lifetime GB2400644B (en) | 2000-09-20 | 2000-09-20 | Apparatus for the stimulation of a misile approach warning system by electro-optical infrared signal generation |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2400644B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2437395A (en) * | 2006-04-18 | 2007-10-24 | Esl Defence Ltd | Apparatus for testing infrared sensors used for missile detection systems |
| EP2224260A1 (en) * | 2009-02-27 | 2010-09-01 | AAI Corporation | Method and apparatus for target range determination |
| US8082832B1 (en) | 2007-05-14 | 2011-12-27 | Lockheed Martin Corporation | Missile system using two-color missile-signature simulation using mid-infrared test source semiconductor lasers |
| US8185350B2 (en) * | 2006-10-23 | 2012-05-22 | Drs Sustainment Systems, Inc. | Systems and methods for operational verification of a missile approach warning system |
| WO2012150442A1 (en) * | 2011-05-05 | 2012-11-08 | Ew Simulation Technology Limited | A self-propelled flying apparatus adapted to emulate a hostile firing action |
| WO2014027342A1 (en) * | 2012-08-13 | 2014-02-20 | Israel Military Industries Ltd. | Threat simulating system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4173777A (en) * | 1977-06-01 | 1979-11-06 | Cincinnati Electronics Corporation | Jet aircraft and/or missile plume simulator |
| US5324937A (en) * | 1993-01-21 | 1994-06-28 | Hughes Aircraft Company | Target for calibrating and testing infrared devices |
| US5378890A (en) * | 1993-04-23 | 1995-01-03 | Northrop Grumman Corporation | Atmospheric scintillation simulator |
| US5703314A (en) * | 1996-11-20 | 1997-12-30 | The United States Of America As Represented By The Secretary Of The Navy | Infrared projector countermeasure system |
-
2000
- 2000-09-20 GB GB0023125A patent/GB2400644B/en not_active Expired - Lifetime
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4173777A (en) * | 1977-06-01 | 1979-11-06 | Cincinnati Electronics Corporation | Jet aircraft and/or missile plume simulator |
| US5324937A (en) * | 1993-01-21 | 1994-06-28 | Hughes Aircraft Company | Target for calibrating and testing infrared devices |
| US5378890A (en) * | 1993-04-23 | 1995-01-03 | Northrop Grumman Corporation | Atmospheric scintillation simulator |
| US5703314A (en) * | 1996-11-20 | 1997-12-30 | The United States Of America As Represented By The Secretary Of The Navy | Infrared projector countermeasure system |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7999228B2 (en) | 2006-04-18 | 2011-08-16 | Esl Defence Limited | Apparatus for use in operator training with, and the testing and evaluation of, infrared sensors which are for missile detection |
| WO2007119163A2 (en) * | 2006-04-18 | 2007-10-25 | Esl Defence Limited | Apparatus for use in operator training with, and the testing and evaluation of, infrared sensors which are for missile detection |
| WO2007119163A3 (en) * | 2006-04-18 | 2007-12-21 | Michael Justin Staniforth | Apparatus for use in operator training with, and the testing and evaluation of, infrared sensors which are for missile detection |
| GB2437395A (en) * | 2006-04-18 | 2007-10-24 | Esl Defence Ltd | Apparatus for testing infrared sensors used for missile detection systems |
| GB2437395B (en) * | 2006-04-18 | 2011-01-12 | Esl Defence Ltd | Apparatus for use in operator training with, and the testing and evaluation of, infrared sensors which are for missile detection |
| US20120215489A1 (en) * | 2006-10-23 | 2012-08-23 | Drs Sustainment Systems, Inc. | Systems and methods for operational verification of a missile approach warning system |
| US8185350B2 (en) * | 2006-10-23 | 2012-05-22 | Drs Sustainment Systems, Inc. | Systems and methods for operational verification of a missile approach warning system |
| US8612179B2 (en) * | 2006-10-23 | 2013-12-17 | Drs Sustainment Systems, Inc. | Systems and methods for operational verification of a missile approach warning system |
| US8082832B1 (en) | 2007-05-14 | 2011-12-27 | Lockheed Martin Corporation | Missile system using two-color missile-signature simulation using mid-infrared test source semiconductor lasers |
| US9031414B1 (en) * | 2007-05-14 | 2015-05-12 | Lockheed Martin Corporation | Two-color missile-signature simulation using mid-infrared test source semiconductor lasers |
| US9791558B2 (en) | 2007-05-14 | 2017-10-17 | Lockheed Martin Corporation | Two-color signature simulation using mid-infrared test source semiconductor lasers |
| EP2224260A1 (en) * | 2009-02-27 | 2010-09-01 | AAI Corporation | Method and apparatus for target range determination |
| US8675183B1 (en) | 2009-02-27 | 2014-03-18 | Aai Corporation | Method and apparatus for target range determination |
| WO2012150442A1 (en) * | 2011-05-05 | 2012-11-08 | Ew Simulation Technology Limited | A self-propelled flying apparatus adapted to emulate a hostile firing action |
| WO2014027342A1 (en) * | 2012-08-13 | 2014-02-20 | Israel Military Industries Ltd. | Threat simulating system |
| US9212872B2 (en) | 2012-08-13 | 2015-12-15 | Israel Military Industries Ltd. | Threat simulating system |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2400644B (en) | 2005-02-09 |
| GB0023125D0 (en) | 2004-05-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PE20 | Patent expired after termination of 20 years |
Expiry date: 20200919 |