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EP0876579A1 - Aerial target system - Google Patents

Aerial target system

Info

Publication number
EP0876579A1
EP0876579A1 EP97900277A EP97900277A EP0876579A1 EP 0876579 A1 EP0876579 A1 EP 0876579A1 EP 97900277 A EP97900277 A EP 97900277A EP 97900277 A EP97900277 A EP 97900277A EP 0876579 A1 EP0876579 A1 EP 0876579A1
Authority
EP
European Patent Office
Prior art keywords
thermal unit
burner
aerial target
thermal
unit according
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
Application number
EP97900277A
Other languages
German (de)
French (fr)
Other versions
EP0876579B1 (en
Inventor
Philip Newman
Alan Richardson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Qinetiq Target Systems Ltd
Original Assignee
Meggitt Defence Systems Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Meggitt Defence Systems Ltd filed Critical Meggitt Defence Systems Ltd
Publication of EP0876579A1 publication Critical patent/EP0876579A1/en
Application granted granted Critical
Publication of EP0876579B1 publication Critical patent/EP0876579B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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

Definitions

  • the present invention relates to an aerial target system.
  • a typical commercially available aerial target for use with an air defence weapon system comprises an unmanned aeroplane which carries a payload of infra-red flares, smoke tracking flares and chaff dispensers.
  • the aircraft is remotely piloted by an operator to simulate a number of different mission profiles. When lit, the infra-red flares carried by the aircraft provide a thermal signature to enable the aircraft to be acquired by an infra-red seeking weapon.
  • the aerial target may simply be used to test the target acquisition and tracking capabilities of the air defence weapon system, in which case the aerial target is recovered, refuelled and a new payload fitted for the next mission. In a live firing test, the aerial target is destroyed by the air defence system.
  • infra-red flares are easily picked up visually and therefore the aerial target does not accurately simulate a normal target. Also, each infra-red flare has a burn time of only around 45 seconds and therefore a number of flares must be lit consecutively to present a target for any length of time.
  • a typical aerial target can carry a payload of up to 16 infra-red flares giving a relatively short total burn time in comparison to an endurance of around 1 hours for the aerial target itself.
  • infra-red flares are classified as a hazardous material making it difficult and expensive to transport the flares to customers, particularly by air. As the infra-red flares are not re-usable a customer will always require replacement stocks of flares.
  • the documents GB-A-1, 454,893 and GB-A-1, 157, 999 disclose aerial target systems which are provided with an aft-mounted thermal unit which heats a mesh surface to provide a thermal signature.
  • the mesh improves the dissipation of heat so that the target can be detected more readily by a heat seeking missile.
  • such a system is also visible to the naked eye, allowing visual targeting by the operator of a weapons system.
  • a method of providing a thermal signature in an aerial target comprises heating an external continuous thermally conductive surface of the aerial target with a burner.
  • an aerial target system comprises an unmanned aircraft having a thermal unit which includes a burner for heating a continuous thermally conductive surface to provide a thermal signature.
  • a thermal unit for fitting to an aerial target comprises a burner arranged to heat a continuous thermally conductive surface to provide a thermal signature.
  • a surface of the aerial target is heated using a burner to a sufficient temperature to provide a thermal signature for acquisition by an infra ⁇ red seeking air defence weapon system.
  • the burner generates a flame which is directed against a continuous thermally conductive surface which then radiates an infra- red signature.
  • the thermal unit of the present invention heats an external continuous surface using an internally mounted burner, the aerial target cannot be tracked and targeted visually by reference to the infra-red source.
  • the thermal unit forms the aircraft nose-cone. This is particularly advantageous as such a nose cone does not affect the aerodynamic performance of the aircraft.
  • the thermal unit may also be mounted in the aircraft tail, on the wings or carried under the aircraft fuselage.
  • the thermal unit comprises a primary chamber which receives ram air from a number of air intakes.
  • the primary chamber provides a source of pressurised air which is used to supply air for the burner.
  • the primary chamber is also provided with a number of air outlets through which air is permitted to bleed to atmosphere.
  • the thermal unit further comprises a secondary chamber through which the burner extends and which receives air from the primary chamber.
  • the thermal unit further comprises a combustion chamber where a flame from the burner heats a surface of the thermal unit.
  • the combustion chamber includes means to spread the flame over the surface of the chamber.
  • the combustion chamber includes guide means to control the flow of hot gasses over the thermally conductive surface.
  • the combustion chamber includes a number of exhaust outlets located adjacent to and upstream of the air outlets of the primary chamber so that the aircraft fuselage is shielded from the hot exhaust gasses of the combustion chamber by cool air from the primary chamber.
  • the system comprises a source of liquid petroleum gas carried by the aircraft which is operatively connected to the burner.
  • suitable liquid petroleum gas fuels include propane and MAPGAS.
  • Liquid petroleum gas is typically supplied in bottles which are preferably located within the aircraft fuselage.
  • the fuel used for the burner may be the same as that used to power the aircraft.
  • the liquid petroleum gas must be vaporised before it is supplied to the burner and therefore preferably, a path of a fluid line connecting the liquid petroleum gas supply to the burner passes through a heat exchanger. Most conveniently, this is achieved by passing the fluid line through the secondary chamber where the liquid petroleum gas within the fluid line is vaporised by the exchange of heat generated within the combustion chamber. Preferably, the gas subsequently passes through a pressure regulator before being fed to the burner.
  • the burner may be ignited by hand before the aerial target gets airborne.
  • an electrical ignition system may be provided which may be remotely operated.
  • an external surface of an aerial target is heated to provide a thermal signature. Accordingly, infra-red flares are no longer required.
  • a thermal unit including a burner means that the aerial target may be re-used many times over and at a fraction of the cost of operating a conventional infra-red flare system.
  • the thermal signature is not visible to the naked eye so that the aerial target system more accurately simulates a real aircraft.
  • Figure 1 shows a simplified view of a remotely piloted aerial target fitted with a thermal unit in accordance with the present invention
  • Figures 2 to 4 show a thermal unit in the form of a nose-cone;
  • Figure 5 shows a split cross-section of the thermal unit of Figures 2 to 4 taken along the lines A-A and B-B in Figure 3; and,
  • Figure 6 shows a modification to the thermal unit of Figure 5 to include a burner fan.
  • Figure 1 shows a remotely piloted aerial target 1 of the type sold by the applicant under the trade name BTT-3 Banshee which is powered by a rear mounted engine 2.
  • the nose-cone of the aerial target has been replaced with a thermal unit 3 which provides a thermal signature for acquisition by an infra-red seeking weapon.
  • the thermal unit 3 replaces the conventional infra-red flares typically used with such an aerial target system.
  • the thermal unit 3 which forms the nose-cone for the aerial target l is shown in Figures 2 to 5.
  • the thermal unit 3 is constructed from sheets of stainless steel which when heated will radiate thermal energy to provide a thermal signature.
  • the thermal unit 3 comprises two sets of three air intakes 4 which face the intended direction of travel of the aerial target 1 and four outlets 5 each of which combines a cold air outlet 6 and an exhaust outlet 7, as is described in detail below.
  • a heat exchange inlet 8 which receives liquid petroleum gas from a number of pressurized bottles 27 housed within the fuselage of the aerial target.
  • a manual on/off valve 28 and fail-safe electrical solenoid valve 29 are provided to isolate the pressurized bottles 27.
  • the fuel is vaporised by the exchange of heat generated within the thermal unit .
  • the gas then passes through a pressure regulator 9, known as a Bijou regulator, where the gas pressure is reduced to around 2 bar.
  • the gas is then fed along a high pressure fluid line 10, through control and fail-safe electrical solenoid valves 11 and 12, respectively, and then along a further length of high pressure pipe 13 to a gas burner inlet 14.
  • Figure 5 shows the interior of the thermal unit 3.
  • ram air from the cold air intakes 4 is received in a primary chamber 15.
  • the cold air is pressurized due to the ram air effect and the majority of this cold air is bled directly out of the cold air outlets 6.
  • the remainder of the cold air passes through a forward bulkhead 16 into a secondary chamber 17 containing a gas burner 18.
  • the gas burner 18 receives gas from the fuel inlet 14 which is mixed with cold air within an air/fuel mixing chamber 19.
  • the cold air is drawn into the air/fuel mixing chamber 19 by a venturi effect.
  • the gas burner includes a flame tube 20 where combustion of the air/fuel mix takes place.
  • the flame tube 20 extends into a combustion chamber 21 so that when the gas burner 18 is lit, a flame is directed into the combustion chamber 21 and against a surface 22 which forms an external wall of the thermal unit 3.
  • a mesh 23 is provided to spread the heat from the flame and thereby avoid overheating the surface of the wall 22 directly facing the flame.
  • the combustion chamber 21 is provided with a number of guide vanes 24 which control the flow of hot gasses around the surface of the wall 22 so that a substantial portion of the surface area of the bulbous front end of the thermal unit is heated. Hot gases are exhausted at the exhaust port 7 where they meet a flow of cold air from the cold air outlet 6. This prevents the aircraft fuselage downstream of the flow of hot exhaust gasses from suffering heat damage.
  • Liquid petroleum gas passes through the heat exchanger inlet 8 to a heat exchanger 25 comprising a length of high pressure pipe where heat from the combustion chamber 21 radiated by the wall 26 vaporizes the liquid petroleum gas.
  • the gas burner 18 is lit using a naked flame before the aerial target is launched.
  • a supply of two bottles of liquid petroleum gas will provide a continuous thermal signature for at least one hour.
  • the thermal unit 3 is formed from two separable parts.
  • the first part comprises the primary chamber 15 and gas burner fittings.
  • the second part comprises the secondary chamber 17 and combustion chamber 21.
  • the first part is mounted directly to the front end of the aircraft fuselage whilst the second part is secured to the first part once the gas burner has been lit shortly before the aerial target is launched. During storage and transit the thermal unit is left attached to the aircraft.
  • Figure 6 shows a modification in which an electric fan 30 is provided which facilitates ground running of the unit prior to launch. It also assists the regulation of airflow in flight instead of relying solely on ram air.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Toys (AREA)
  • Photometry And Measurement Of Optical Pulse Characteristics (AREA)
  • Gas Burners (AREA)

Abstract

A thermally conductive surface (22) of an aerial target (1) is heated using a liquid petroleum gas burner (18) to a sufficient temperature to provide a thermal signature for acquisition by an infrared seeking air defence weapon system. The liquid petroleum gas burner (18) generates a flame which is directed against the thermally conductive surface (22) which then radiates an infrared signature. In the preferred embodiment, the liquid petroleum gas burner (18) is housed within a thermal unit (3) which forms the nose-cone of the aerial target (1).

Description

AERIAL TARGET SYSTEM Technical Field
The present invention relates to an aerial target system.
Background Art
A typical commercially available aerial target for use with an air defence weapon system, including both gun and missile systems, comprises an unmanned aeroplane which carries a payload of infra-red flares, smoke tracking flares and chaff dispensers. The aircraft is remotely piloted by an operator to simulate a number of different mission profiles. When lit, the infra-red flares carried by the aircraft provide a thermal signature to enable the aircraft to be acquired by an infra-red seeking weapon.
The aerial target may simply be used to test the target acquisition and tracking capabilities of the air defence weapon system, in which case the aerial target is recovered, refuelled and a new payload fitted for the next mission. In a live firing test, the aerial target is destroyed by the air defence system.
One problem with infra-red flares is that they are easily picked up visually and therefore the aerial target does not accurately simulate a normal target. Also, each infra-red flare has a burn time of only around 45 seconds and therefore a number of flares must be lit consecutively to present a target for any length of time. A typical aerial target can carry a payload of up to 16 infra-red flares giving a relatively short total burn time in comparison to an endurance of around 1 hours for the aerial target itself. A further problem is that infra-red flares are classified as a hazardous material making it difficult and expensive to transport the flares to customers, particularly by air. As the infra-red flares are not re-usable a customer will always require replacement stocks of flares. The documents GB-A-1, 454,893 and GB-A-1, 157, 999 disclose aerial target systems which are provided with an aft-mounted thermal unit which heats a mesh surface to provide a thermal signature. The mesh improves the dissipation of heat so that the target can be detected more readily by a heat seeking missile. However, like conventional infra-red flares, such a system is also visible to the naked eye, allowing visual targeting by the operator of a weapons system.
Disclosure of Invention
According to a first aspect of the present invention, a method of providing a thermal signature in an aerial target comprises heating an external continuous thermally conductive surface of the aerial target with a burner.
According to a second aspect of the present invention, an aerial target system comprises an unmanned aircraft having a thermal unit which includes a burner for heating a continuous thermally conductive surface to provide a thermal signature.
According to a third aspect of the present invention, a thermal unit for fitting to an aerial target comprises a burner arranged to heat a continuous thermally conductive surface to provide a thermal signature.
In the present invention, a surface of the aerial target is heated using a burner to a sufficient temperature to provide a thermal signature for acquisition by an infra¬ red seeking air defence weapon system. The burner generates a flame which is directed against a continuous thermally conductive surface which then radiates an infra- red signature. As the thermal unit of the present invention heats an external continuous surface using an internally mounted burner, the aerial target cannot be tracked and targeted visually by reference to the infra-red source.
In a preferred embodiment of the present invention, the thermal unit forms the aircraft nose-cone. This is particularly advantageous as such a nose cone does not affect the aerodynamic performance of the aircraft. The thermal unit may also be mounted in the aircraft tail, on the wings or carried under the aircraft fuselage.
Preferably, the thermal unit comprises a primary chamber which receives ram air from a number of air intakes. The primary chamber provides a source of pressurised air which is used to supply air for the burner. Preferably, the primary chamber is also provided with a number of air outlets through which air is permitted to bleed to atmosphere.
Preferably, the thermal unit further comprises a secondary chamber through which the burner extends and which receives air from the primary chamber.
Preferably, the thermal unit further comprises a combustion chamber where a flame from the burner heats a surface of the thermal unit. Preferably, the combustion chamber includes means to spread the flame over the surface of the chamber. Most preferably, the combustion chamber includes guide means to control the flow of hot gasses over the thermally conductive surface.
Preferably, the combustion chamber includes a number of exhaust outlets located adjacent to and upstream of the air outlets of the primary chamber so that the aircraft fuselage is shielded from the hot exhaust gasses of the combustion chamber by cool air from the primary chamber. This arrangement protects the aircraft fuselage from heat damage. Preferably, the system comprises a source of liquid petroleum gas carried by the aircraft which is operatively connected to the burner. Suitable liquid petroleum gas fuels include propane and MAPGAS. Liquid petroleum gas is typically supplied in bottles which are preferably located within the aircraft fuselage. As an alternative, the fuel used for the burner may be the same as that used to power the aircraft.
The liquid petroleum gas must be vaporised before it is supplied to the burner and therefore preferably, a path of a fluid line connecting the liquid petroleum gas supply to the burner passes through a heat exchanger. Most conveniently, this is achieved by passing the fluid line through the secondary chamber where the liquid petroleum gas within the fluid line is vaporised by the exchange of heat generated within the combustion chamber. Preferably, the gas subsequently passes through a pressure regulator before being fed to the burner.
The burner may be ignited by hand before the aerial target gets airborne. Alternatively, an electrical ignition system may be provided which may be remotely operated.
In the present invention, an external surface of an aerial target is heated to provide a thermal signature. Accordingly, infra-red flares are no longer required. Using a thermal unit including a burner means that the aerial target may be re-used many times over and at a fraction of the cost of operating a conventional infra-red flare system. Furthermore, the thermal signature is not visible to the naked eye so that the aerial target system more accurately simulates a real aircraft. Brief Description of Drawings
An example of the present invention will now be described in detail with reference to the accompanying drawings, in which: Figure 1 shows a simplified view of a remotely piloted aerial target fitted with a thermal unit in accordance with the present invention;
Figures 2 to 4 show a thermal unit in the form of a nose-cone; , Figure 5 shows a split cross-section of the thermal unit of Figures 2 to 4 taken along the lines A-A and B-B in Figure 3; and,
Figure 6 shows a modification to the thermal unit of Figure 5 to include a burner fan.
Detailed Description
Figure 1 shows a remotely piloted aerial target 1 of the type sold by the applicant under the trade name BTT-3 Banshee which is powered by a rear mounted engine 2. The nose-cone of the aerial target has been replaced with a thermal unit 3 which provides a thermal signature for acquisition by an infra-red seeking weapon. The thermal unit 3 replaces the conventional infra-red flares typically used with such an aerial target system.
The thermal unit 3 which forms the nose-cone for the aerial target l is shown in Figures 2 to 5. The thermal unit 3 is constructed from sheets of stainless steel which when heated will radiate thermal energy to provide a thermal signature. The thermal unit 3 comprises two sets of three air intakes 4 which face the intended direction of travel of the aerial target 1 and four outlets 5 each of which combines a cold air outlet 6 and an exhaust outlet 7, as is described in detail below.
As shown in Figures 4 and 5, to the rear of the thermal unit 3 there is provided a heat exchange inlet 8 which receives liquid petroleum gas from a number of pressurized bottles 27 housed within the fuselage of the aerial target. A manual on/off valve 28 and fail-safe electrical solenoid valve 29 are provided to isolate the pressurized bottles 27. As is described below, the fuel is vaporised by the exchange of heat generated within the thermal unit . The gas then passes through a pressure regulator 9, known as a Bijou regulator, where the gas pressure is reduced to around 2 bar. The gas is then fed along a high pressure fluid line 10, through control and fail-safe electrical solenoid valves 11 and 12, respectively, and then along a further length of high pressure pipe 13 to a gas burner inlet 14.
Figure 5 shows the interior of the thermal unit 3. As shown by the arrows, ram air from the cold air intakes 4 is received in a primary chamber 15. The cold air is pressurized due to the ram air effect and the majority of this cold air is bled directly out of the cold air outlets 6. The remainder of the cold air passes through a forward bulkhead 16 into a secondary chamber 17 containing a gas burner 18. The gas burner 18 receives gas from the fuel inlet 14 which is mixed with cold air within an air/fuel mixing chamber 19. The cold air is drawn into the air/fuel mixing chamber 19 by a venturi effect.
The gas burner includes a flame tube 20 where combustion of the air/fuel mix takes place. The flame tube 20 extends into a combustion chamber 21 so that when the gas burner 18 is lit, a flame is directed into the combustion chamber 21 and against a surface 22 which forms an external wall of the thermal unit 3. A mesh 23 is provided to spread the heat from the flame and thereby avoid overheating the surface of the wall 22 directly facing the flame. The combustion chamber 21 is provided with a number of guide vanes 24 which control the flow of hot gasses around the surface of the wall 22 so that a substantial portion of the surface area of the bulbous front end of the thermal unit is heated. Hot gases are exhausted at the exhaust port 7 where they meet a flow of cold air from the cold air outlet 6. This prevents the aircraft fuselage downstream of the flow of hot exhaust gasses from suffering heat damage.
Liquid petroleum gas passes through the heat exchanger inlet 8 to a heat exchanger 25 comprising a length of high pressure pipe where heat from the combustion chamber 21 radiated by the wall 26 vaporizes the liquid petroleum gas.
The gas burner 18 is lit using a naked flame before the aerial target is launched. Typically, a supply of two bottles of liquid petroleum gas will provide a continuous thermal signature for at least one hour.
In this example, the thermal unit 3 is formed from two separable parts. The first part comprises the primary chamber 15 and gas burner fittings. The second part comprises the secondary chamber 17 and combustion chamber 21. The first part is mounted directly to the front end of the aircraft fuselage whilst the second part is secured to the first part once the gas burner has been lit shortly before the aerial target is launched. During storage and transit the thermal unit is left attached to the aircraft.
Figure 6 shows a modification in which an electric fan 30 is provided which facilitates ground running of the unit prior to launch. It also assists the regulation of airflow in flight instead of relying solely on ram air.

Claims

1. A thermal unit (3) for fitting to an aerial target (1) comprising a burner (18) arranged to heat a continuous thermally conductive surface (22) to provide a thermal signature.
2. A thermal unit according to claim 1, formed as an aircraft nose cone.
3. A thermal unit according to claim 1 or 2, in which the thermal unit (3) comprises a primary chamber (15) which receives ram air from a number of air intakes (4) .
4. A thermal unit according to claim 3, in which the primary chamber (15) comprises a number of air outlets (5) through which air is permitted to bleed to atmosphere.
5. A thermal unit according to claim 3 or 4, further comprising a secondary chamber (17) through which the burner (18) extends and which receives air from the primary chamber (15) .
6. A thermal unit according to any preceding claim, further comprising a combustion chamber (21) where a flame from the burner (18) heats a surface (22) of the thermal unit.
7. A thermal unit according to claim 6, in which the combustion chamber (21) includes means (23, 24) to spread the flame over the surface (22) of the combustion chamber (21).
8. A thermal unit according to claims 6 or 7, in which the combustion chamber (21) includes guide means (24) to control the flow of hot gases over the thermally conductive surface (22) .
9. A thermal unit according to any one of claims 6 to 8, when dependent on claim 4, in which the combustion chamber (21) includes a number of exhaust outlets (7) each of which is located adjacent to and upstream of a corresponding one of the air outlets (5) of the primary chamber.
10. A thermal unit according to any preceding claim, in which the burner (18) is a liquid petroleum gas burner.
11. An aerial target system comprising an unmanned aircraft (1) including a thermal unit (3) according to any preceding claim.
12. An aerial target system according to claim 11, further comprising a source of liquid petroleum gas carried by the aircraft which is operatively connected to the burner (18) .
13. An aerial target system according to claim 12, in which a path of a fluid line connecting the source of liquid petroleum gas to the burner (18) passes through a heat exchanger (25) .
14. An aerial target system according to any of claims 11 to 13, in which the aircraft (1) is driven by an aft mounted engine unit (2) independent of the thermal unit
(3).
15. An aerial target system according to claim 14, in which the engine (2) is a propeller engine.
16. A method of providing a thermal signature in an aerial target comprising heating an external continuous thermally conductive surface of the aerial target with a burner.
AMENDED CLAIMS
[received by the International Bureau on 10 Oune 1997 (10.06.97); original claims 1 and 16 amended; remaining claims unchanged (2 pages)]
1. A thermal unit (3) for fitting to an aerial target (1) comprising a burner (18) mounted internally within the thermal unit and arranged to heat a continuous thermally conductive surface (22) to provide a thermal signature for acquisition by an infra-red seeking air defence weapon system, wherein the aerial target cannot be tracked and targeted visually by reference to the thermal signature. 2. A thermal unit according to claim 1, formed as an aircraft nose cone.
3. A thermal unit according to claim 1 or 2, in which the thermal unit (3) comprises a primary chamber (15) which receives ram air from a number of air intakes (4) . 4. A thermal unit according to claim 3, in which the primary chamber (15) comprises a number of air outlets (5) through which air is permitted to bleed to atmosphere.
5. A thermal unit according to claim 3 or 4, further comprising a secondary chamber (17) through which the burner (18) extends and which receives air from the primary chamber (15) .
6. A thermal unit according to any preceding claim, further comprising a combustion chamber (21) where a flame from the burner (18) heats a surface (22) of the thermal unit.
7. A thermal unit according to claim 6, in which the combustion chamber (21) includes means (23, 24) to spread the flame over the surface of the combustion chamber (21) .
8. A thermal unit according to claims 6 or 7, in which the combustion chamber (21) includes guide means (24) to control the flow of hot gases over the thermally conductive surface (22) .
9. A thermal unit according to any one of claims 6 to 8, when dependent on claim 4, in which the combustion chamber (21) includes a number of exhaust outlets (7) each of which is located adjacent to and upstream of a corresponding one of the air outlets (5) of the primary chamber. 10. A thermal unit according to any preceding claim, in which the burner (18) is a liquid petroleum gas burner.
11. An aerial target system comprising an unmanned aircraft (1) including a thermal unit (3) according to any preceding claim.
12. An aerial target system according to claim 11, further comprising a source of liquid petroleum gas carried by the aircraft which is operatively connected to the burner (18) .
13. An aerial target system according to claim 12, in which a path of a fluid line connecting the source of liquid petroleum gas to the burner (18) passes through a heat exchanger (25) .
14. An aerial target system according to any of claims 11 to 13, in which the aircraft (1) is driven by an aft mounted engine unit (2) independent of the thermal unit
(3).
15. An aerial target system according to claim 14, in which the engine (2) is a propeller engine.
16. A method of providing a thermal signature in an aerial target comprising heating an external continuous thermally conductive surface of the aerial target with a burner mounted internally within the thermal unit to provide a thermal signature for acquisition by an infra-red seeking air defence weapon system, wherein the aerial target cannot be tracked and targeted visually by reference to the therma1 signa ure.
EP97900277A 1996-01-22 1997-01-06 Aerial target system Expired - Lifetime EP0876579B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB9601207 1996-01-22
GBGB9601207.5A GB9601207D0 (en) 1996-01-22 1996-01-22 Aerial target system
PCT/GB1997/000024 WO1997027446A1 (en) 1996-01-22 1997-01-06 Aerial target system

Publications (2)

Publication Number Publication Date
EP0876579A1 true EP0876579A1 (en) 1998-11-11
EP0876579B1 EP0876579B1 (en) 2000-11-15

Family

ID=10787344

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97900277A Expired - Lifetime EP0876579B1 (en) 1996-01-22 1997-01-06 Aerial target system

Country Status (6)

Country Link
EP (1) EP0876579B1 (en)
AU (1) AU1386897A (en)
DE (1) DE69703532T2 (en)
FR (1) FR2743876B1 (en)
GB (2) GB9601207D0 (en)
WO (1) WO1997027446A1 (en)

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WO2022260629A3 (en) * 2021-06-07 2023-03-02 Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi A thermal trace enhancer system

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GB9722259D0 (en) 1997-10-22 1997-12-17 Global Target Systems Lltd Aerial target system
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RU2187064C2 (en) * 2000-03-14 2002-08-10 ОАО "Станкомаш" Air target
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RU2196953C2 (en) * 2000-12-18 2003-01-20 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Anti-aircraft target missile
RU2204791C1 (en) * 2001-10-05 2003-05-20 ОАО "ФНПЦ "Станкомаш" Air target
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RU2238510C1 (en) 2003-12-10 2004-10-20 Закрытое акционерное общество "СТИВТ" Method and system of automatic control
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DE69703532T2 (en) 2001-03-15
FR2743876A1 (en) 1997-07-25
WO1997027446A1 (en) 1997-07-31
GB2309290B (en) 1997-12-10
DE69703532D1 (en) 2000-12-21
AU1386897A (en) 1997-08-20
GB2309290A (en) 1997-07-23
GB9601207D0 (en) 1996-03-20
FR2743876B1 (en) 1998-04-10
GB9700145D0 (en) 1997-02-26
EP0876579B1 (en) 2000-11-15

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