EP0876579B1 - In der luft fliegendes ziel - Google Patents

In der luft fliegendes ziel Download PDF

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Publication number
EP0876579B1
EP0876579B1 EP97900277A EP97900277A EP0876579B1 EP 0876579 B1 EP0876579 B1 EP 0876579B1 EP 97900277 A EP97900277 A EP 97900277A EP 97900277 A EP97900277 A EP 97900277A EP 0876579 B1 EP0876579 B1 EP 0876579B1
Authority
EP
European Patent Office
Prior art keywords
thermal unit
aerial target
thermal
burner
air
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.)
Expired - Lifetime
Application number
EP97900277A
Other languages
English (en)
French (fr)
Other versions
EP0876579A1 (de
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/de
Application granted granted Critical
Publication of EP0876579B1 publication Critical patent/EP0876579B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 a thermal unit for an aerial target system, and to a method of providing a thermal signature in an aerial target.
  • 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 11 ⁇ 2 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.
  • 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. This arrangement protects the aircraft fuselage from heat damage.
  • 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 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 1 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)
  • Gas Burners (AREA)
  • Photometry And Measurement Of Optical Pulse Characteristics (AREA)

Claims (16)

  1. Wärmeeinheit (3) zur Anbringung an einem Luftziel (1), die einen Brenner (18) aufweist, der innerhalb der Wärmeeinheit montiert und angeordnet ist, um eine kontinuierlich wärmeleitende Fläche (22) zu erwärmen, damit in dem in das Luftziel eingebauten Zustand eine thermische Signatur zur Erfassung durch ein infrarotsuchendes Luftabwehrwaffensystem geschaffen wird, so daß ein fliegendes Luftziel, wenn es solch eine Wärmeeinheit mit einer kontinuierlich wärmeleitenden Fläche trägt, nicht visuell durch Bezug auf die thermische Signatur verfolgt und anvisiert werden kann.
  2. Wärmeeinheit nach Anspruch 1, dadurch gekennzeichnet, daß sie als eine Flugzeugbugverkleidung ausgebildet ist.
  3. Wärmeeinheit nach Anspruch 1 oder 2, in der die Wärmeeinheit (3) eine Primärkammer (15) aufweist, die Frischluft durch eine Anzahl von Lufteinlässen (4) aufnimmt.
  4. Wärmeeinheit nach Anspruch 3, in der die Primärkammer (15) eine Anzahl von Luftauslässen (5) aufweist, durch die ein Ausstoßen der Luft in die Umgebung möglich ist.
  5. Wärmeeinheit nach Anspruch 3 oder 4, dadurch gekennzeichnet, daß zusätzlich eine Sekundärkammer (17) vorgesehen ist, durch die der Brenner (18) sich erstreckt und die Luft von der Primärkammer (15) Luft aufnimmt.
  6. Wärmeeinheit nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß zusätzlich eine Verbrennungskammer (21) vorgesehen ist, in der eine Flamme von dem Brenner (18) eine Fläche (22) der Wärmeeinheit erwärmt.
  7. Wärmeeinheit nach Anspruch 6, dadurch gekennzeichnet, daß die Verbrennungskammer (21) Mittel (23, 24) einschließt, um die Flamme über die Fläche der Verbrennungskammer (21) zu verteilen.
  8. Wärmeeinheit nach Anspruch 6 oder 7, dadurch gekennzeichnet, daß die Verbrennungskammer (21) Führungsmittel (24) einschließt, um den Luftstrom des heißen Gases über die wärmeleitende Fläche (22) zu leiten.
  9. Wärmeeinheit nach einem der Ansprüche 6 bis 8 rückbezogen auf Anspruch 4, dadurch gekennzeichnet, daß die Verbrennungskammer (21) eine Anzahl von Abgasauslässen (7) aufweist, von denen jeder angrenzend an und stromaufwärts von einem entsprechenden Luftauslaß (5) der Primärkammer liegt.
  10. Wärmeeinheit nach einem der vorangehenden Ansprüche, in der als Brenner (18) ein Brenner für flüssiges Petroleumgas vorgesehen ist.
  11. Luftzielsystem mit einem unbemannten Fahrzeug (1), das eine Wärmeeinheit (3) nach einem der vorangehenden Ansprüche aufweist.
  12. Luftzielsystem nach Anspruch 11, dadurch gekennzeichnet, daß zusätzlich ein Tank für flüssiges Petroleumgas durch das Flugzeug getragen wird, der wirksam mit dem Brenner (18) verbunden ist.
  13. Luftzielsystem nach Anspruch 12, dadurch gekennzeichnet, daß der Weg einer Flüssigkeitsleitung, die den Tank für flüssiges Petroleumgas mit dem Brenner (18) verbindet, durch einen Wärmetauscher (25) läuft.
  14. Luftzielsystem nach einem der Ansprüche 11 bis 13, dadurch gekennzeichnet, daß das Flugzeug (1) durch eine heckseitige Motoreinheit (2) unabhängig von der Wärmeeinheit (3) angetrieben wird.
  15. Luftzielsystem nach Anspruch 14, dadurch gekennzeichnet, daß der Motor ein Propellermotor ist.
  16. Verfahren zur Bereitstellung einer thermischen Signatur in einem Luftziel, das Erhitzen einer externen, kontinuierlich wärmeleitenden Fläche des Luftziels mit einem Brenner, der intern innerhalb der Wärmeeinheit befestigt ist, einschließt, um eine thermische Signatur zur Erfassung durch ein infrarotsuchendes Luftabwehrwaffensystem zu schaffen, wobei das Luftziel nicht visuell durch Bezug auf die thermische Signatur verfolgt und anvisiert werden kann.
EP97900277A 1996-01-22 1997-01-06 In der luft fliegendes ziel Expired - Lifetime EP0876579B1 (de)

Applications Claiming Priority (3)

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

Publications (2)

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

Family

ID=10787344

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97900277A Expired - Lifetime EP0876579B1 (de) 1996-01-22 1997-01-06 In der luft fliegendes ziel

Country Status (6)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10210433C1 (de) * 2002-03-09 2003-08-14 Dornier Gmbh Fluggerät zur IR-Flugzieldarstellung
EP1870663A2 (de) 2006-06-22 2007-12-26 EADS Deutschland GmbH Flugziel
US20240263923A1 (en) * 2021-06-07 2024-08-08 Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi A thermal trace enhancer system

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2123168C1 (ru) * 1997-10-20 1998-12-10 Государственное научно-производственное предприятие "Сплав" Имитатор воздушных целей
GB9722259D0 (en) 1997-10-22 1997-12-17 Global Target Systems Lltd Aerial target system
RU2147722C1 (ru) * 1998-06-15 2000-04-20 Государственное научно-производственное предприятие "Сплав" Универсальный имитатор воздушных целей
RU2141094C1 (ru) * 1998-08-17 1999-11-10 Государственный высокогорный научно-исследовательский испытательный центр авиационной техники и вооружения Способ защиты летательных аппаратов от ракет, оснащенных головками самонаведения
FR2785981B1 (fr) 1998-11-13 2001-02-09 Pascal Doe Cible a rayonnements infrarouges autopropulsee par reaction
RU2187064C2 (ru) * 2000-03-14 2002-08-10 ОАО "Станкомаш" Воздушная мишень
RU2184923C2 (ru) * 2000-09-22 2002-07-10 Общевойсковая Академия Вооруженных Сил Российской Федерации Способ защиты летательных аппаратов и устройство для его реализации
US6521904B2 (en) * 2000-12-15 2003-02-18 Precision Combustion, Inc. IR source, method and apparatus
RU2196953C2 (ru) * 2000-12-18 2003-01-20 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Зенитная ракета-мишень
RU2204791C1 (ru) * 2001-10-05 2003-05-20 ОАО "ФНПЦ "Станкомаш" Воздушная мишень
RU2193747C1 (ru) * 2002-02-20 2002-11-27 ОАО "Ковровский механический завод" Имитатор воздушных целей
RU2249172C1 (ru) * 2003-08-27 2005-03-27 Зелевинский Александр Абрамович Способ защиты объектов от оружия с лазерным полуактивным самонаведением (варианты)
RU2238510C1 (ru) 2003-12-10 2004-10-20 Закрытое акционерное общество "СТИВТ" Способ и система автоматического управления
US7170071B1 (en) 2004-09-29 2007-01-30 Broussard Richard D Infrared emitter
RU2321817C1 (ru) * 2006-06-13 2008-04-10 Российская Федерация,от имени которой выступает государственный заказчик-Федеральное агентство по атомной энергии Система защиты гражданских воздушных судов
RU2357188C2 (ru) * 2007-04-02 2009-05-27 Андрей Юрьевич Себякин Имитатор воздушной цели
RU2378603C1 (ru) * 2008-07-01 2010-01-10 Федеральное государственное учреждение "Федеральный государственный научно-исследовательский испытательный центр радиоэлектронной борьбы и оценки эффективности снижения заметности" Министерства обороны Российской Федерации Устройство индивидуальной защиты летательного аппарата от управляемых ракет с оптическими головками самонаведения
RU2390721C1 (ru) * 2008-11-24 2010-05-27 Государственное образовательное учреждение высшего профессионального образования Академия Федеральной службы охраны Российской Федерации (Академия ФСО России) Способ защиты объекта от управляемых ракет
RU2590419C1 (ru) * 2015-03-31 2016-07-10 Павел Александрович Богородецкий Радиоуправляемая летающая мишень
CN111857177B (zh) * 2020-07-20 2022-11-01 西安科为实业发展有限责任公司 一种远程操控靶标指令生成方法、装置、设备及介质

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2869120A (en) * 1956-09-17 1959-01-13 Del Mar Eng Lab Tow target having combustion signal means
US4044683A (en) * 1959-08-20 1977-08-30 Mcdonnell Douglas Corporation Heat generator
US3410559A (en) * 1966-04-26 1968-11-12 Hayes Internat Corp Airborne target with infrared source
US3735985A (en) * 1970-10-15 1973-05-29 Susquehanna Corp Rocket propelled target
SE417011B (sv) * 1979-03-05 1981-02-16 Saab Scania Ab Malanordning
US4253670A (en) * 1979-08-07 1981-03-03 The United States Of America As Represented By The Secretary Of The Army Simulated thermal target
US4428583B1 (en) * 1982-11-19 1996-03-05 Hayes Int Corp Airborne target for generating an exhaust plume simulating that of a jet powered aircraft
US4607849A (en) * 1985-03-07 1986-08-26 Southwest Aerospace Corporation Jet exhaust simulator
DE3608578A1 (de) * 1986-03-14 1987-09-17 Herbert Boese Vorrichtung zum schutz von schiffen od.dgl. gegen infrarotgesteuerte angriffswaffen
JPH03255899A (ja) * 1990-03-02 1991-11-14 Mitsubishi Electric Corp 飛しよう体用囮方法

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10210433C1 (de) * 2002-03-09 2003-08-14 Dornier Gmbh Fluggerät zur IR-Flugzieldarstellung
EP1342978A2 (de) 2002-03-09 2003-09-10 DORNIER GmbH Fluggerät zur Flugzieldarstellung
EP1870663A2 (de) 2006-06-22 2007-12-26 EADS Deutschland GmbH Flugziel
US20240263923A1 (en) * 2021-06-07 2024-08-08 Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi A thermal trace enhancer system

Also Published As

Publication number Publication date
DE69703532T2 (de) 2001-03-15
GB2309290B (en) 1997-12-10
GB9700145D0 (en) 1997-02-26
DE69703532D1 (de) 2000-12-21
AU1386897A (en) 1997-08-20
FR2743876B1 (fr) 1998-04-10
GB2309290A (en) 1997-07-23
FR2743876A1 (fr) 1997-07-25
WO1997027446A1 (en) 1997-07-31
EP0876579A1 (de) 1998-11-11
GB9601207D0 (en) 1996-03-20

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