+

WO2011007164A2 - Radôme et procédé de refroidissement de composants de radar - Google Patents

Radôme et procédé de refroidissement de composants de radar Download PDF

Info

Publication number
WO2011007164A2
WO2011007164A2 PCT/GB2010/051141 GB2010051141W WO2011007164A2 WO 2011007164 A2 WO2011007164 A2 WO 2011007164A2 GB 2010051141 W GB2010051141 W GB 2010051141W WO 2011007164 A2 WO2011007164 A2 WO 2011007164A2
Authority
WO
WIPO (PCT)
Prior art keywords
housing
radome
ram air
radar
air inlet
Prior art date
Application number
PCT/GB2010/051141
Other languages
English (en)
Other versions
WO2011007164A3 (fr
Inventor
Faris Samarai
Original Assignee
Faris Samarai
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 Faris Samarai filed Critical Faris Samarai
Priority to EP10799491.5A priority Critical patent/EP2387809B1/fr
Publication of WO2011007164A2 publication Critical patent/WO2011007164A2/fr
Publication of WO2011007164A3 publication Critical patent/WO2011007164A3/fr

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/02—Arrangements for de-icing; Arrangements for drying-out ; Arrangements for cooling; Arrangements for preventing corrosion
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons

Definitions

  • the present invention relates to a radome particularly, but not exclusively, a radome for mounting on an aircraft's fuselage in order to protect and cool the aircraft's radar scanner components.
  • a method of cooling radar scanner components in order to maintain the working temperature of the radar scanner components is also provided.
  • Radar systems are used in a number of different scenarios in order to retrieve information such as the range, altitude, direction, speed etc. of moving objects such as aircrafts, ships, land based vehicles etc. or fixed objects such as terrain.
  • Radar systems are typically housed in a radome which is designed to streamline and protect the working components of the radar whilst minimising any interference on the returned signal.
  • ESA Electrode Scanned Array
  • Active Phased Array Active Phased Array
  • One of the important differences between the mode of operation of ESA radar systems and previous systems is that ESA systems use their antenna to carry out transmission / reception of the radar signal rather than a discrete transmitter / receiver. This has some significant advantages over previous systems; however, it does produce the side effect that the antenna heats up more during use than in previous radar systems. If left unchecked, this additional heat factor can contribute to a deterioration in equipment performance and or malfunction.
  • Some form of maintaining the scanner components at working temperature in such systems is therefore required.
  • One way of maintaining the working temperature of the radome is to use coolant based refrigeration techniques or recirculation of pressurised air within the housing in order to maintain an optimum temperature within the radome.
  • such systems require undesirably complex
  • a radome comprising:- a radar component housing;
  • a ram air inlet provided in the radar component housing
  • a ram air outlet provided in the radar component housing such that when the radome is installed on the body of a moving craft, air flow relative to the craft will enter the housing by way of the ram air inlet, circulate within the housing, and exit the housing by way of the ram air outlet in order to cool radar components within the radar component housing.
  • the radome may be adapted to be mounted on an aircraft fuselage.
  • the position of the ram air inlet and ram air outlet may be such that a transmission / reception antenna within the radome housing is cooled by the air circulating within the radome housing.
  • the ram air inlet comprises a hole through a wall of the radome housing and a recessed flap surface in the radome housing.
  • the ram air inlet is provided in a side wall of the radome housing.
  • a removable filter element may also be provided at the ram air inlet.
  • the ram air inlet comprises a NACA duct in a wall of the radome housing.
  • the ram air outlet is provided in a lower wall of the radome housing.
  • the ram air outlet is provided with a socket which allows it to be connected to a suction device.
  • the socket may comprise a bayonet connection. For ground operation, this allows a suction device to induce a flow through the radome to provide the necessary flow of air in the radome.
  • the ram air inlet may be provided aft of the ram air outlet in order to encourage circulation of air within the radome housing.
  • a recirculation fan may also be provided to improve circulation of air within the radome housing.
  • a method of cooling radar components comprising the steps of:- housing radar components in a radar housing;
  • Fig. 1 is a schematic plan view from beneath a radome according to the present invention.
  • Fig. 2 is a schematic side view of the radome of Fig. 1 where the radome is installed on the belly of an aircraft's fuselage.
  • a radome, generally designated 10 has a radar housing 12 which has a streamlined profile in order to reduce drag on the aircraft.
  • the radar housing 12 is attached to the underside of an aircraft's fuselage 14 and protects the radar scanner components 16 therein.
  • the radar scanner components may include e.g. a transmission / reception antenna and a processor which are linked to the aircraft avionics in order to provide an integrated radar system.
  • a NACA duct ram air inlet 18 (best seen in Fig. 1 ) is provided through one side of the radar housing 12.
  • the ram air inlet 18 in the embodiment shown comprises a hole with a recessed flap 18 to receive the oncoming airflow (labelled "IN") such that the air IN enters the radar housing 12.
  • a ram air outlet 20 (best seen in Fig. 2) is provided on the bottom of the radar housing 12.
  • the ram air outlet 20 in the embodiment shown comprises a hole having a scooped flap which is directed away from the oncoming airflow (labelled "OUT") in order to encourage air circulating within the radar housing 12 to exit the radar housing 12.
  • a removable filter element (not shown) may also be provided at the ram air inlet. This is useful, to filter out any unwanted contaminants in the incoming air flow. For example, in low level operations, the surrounding air may have a significant salt content; however, the removable filter is able to filter this out in order to prevent long term damage to the radar scanner
  • the air inlet 18 is provided to the side of the radar scanner components 16 and the outlet 20 is provided forward of the radar scanner components 16. This ensures that the air entering the inlet must circulate within the radar housing 12 before it exits the outlet 20 and prevents the air simply entering the inlet 18 and passing straight through the radar housing 12 and out the outlet 20 without circulating over the radar scanner components 16. This forces circulation of the air within the radome 12 thereby ensuring optimum cooling within the radome 10.
  • a recirculation fan 22 (Fig. 2) is also mounted in the radar housing 12. This may or may not be necessary; however, if provided it may further improve the circulation of air within the radar housing 12.
  • the recirculation fan 22 may be driven in order to optimise recirculation of air in the housing 12.
  • ram air IN is forced into the radar housing 12 through the ram air inlet 18.
  • the dynamic air pressure at the inlet 18 may assist with this.
  • the ram air enters the radar housing 12 it circulates around the inside of the housing 12.
  • the distribution of the circulating air in the radar housing 12 can be improved by the recirculation fan 22, if required. Because ram air is typically relatively cool (particularly when the aircraft is flying in cooler, higher air) the flow of the air over the radar scanner components 16 cools those components. After circulating within the radar housing 12, the air will have been warmed by the radar scanner components 16 (in particular the antenna) and will exit the radome housing 12 by way of the ram air outlet 20.
  • the ram air inlet 18 is positioned aft of the ram air outlet 20 such that the air entering the ram air inlet 18 must pass over the radar scanner components 16 before it can exit the ram air outlet 20.
  • the relative positions of the inlet 18 and outlet 20 can be reversed if desired.
  • the aft facing scoop of the ram air outlet 20 and the motion of the air flowing over the outer surface of the radome 12 results in a vacuum effect being created at the ram air outlet 20 to encourage the warmed air to be expelled from the ram air outlet 20 as the flow of air, labelled OUT in the Figs.
  • the invention therefore provides an improved system of cooling
  • the reduced part count and complexity has a number of further steps
  • the invention is installed on an aircraft, it will be appreciated that it could equally be installed over the radar scanner components of any moving craft which is capable of moving at an air speed which results in a sufficient magnitude of ram air being imparted on the air inlet and air outlet.

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Details Of Aerials (AREA)

Abstract

L'invention porte sur un radôme (10), pour refroidir des composants de radar (16). Le radôme (10) a une enveloppe (12) comportant une entrée d'air statique (18) et une sortie d'air statique (20). Le radôme (10) est monté sur le corps d'un véhicule en mouvement de telle manière que le flux d'air relatif au véhicule entre dans l'enveloppe (12) par une entrée d'air statique (18), qu'il circule dans l'enveloppe (12), et qu'il sort de l'enveloppe (12) par une sortie d'air statique (20), afin de refroidir les composants de radar (16) contenus dans l'enveloppe de composant de radar (12). L'invention porte aussi sur un procédé de refroidissement de composants de radar.
PCT/GB2010/051141 2009-07-14 2010-07-13 Radôme et procédé de refroidissement de composants de radar WO2011007164A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10799491.5A EP2387809B1 (fr) 2009-07-14 2010-07-13 Radôme et procédé pour refroidir des composants de radar

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0912158A GB0912158D0 (en) 2009-07-14 2009-07-14 A radome and method of cooling radar scanner components
GB0912158.3 2009-07-14

Publications (2)

Publication Number Publication Date
WO2011007164A2 true WO2011007164A2 (fr) 2011-01-20
WO2011007164A3 WO2011007164A3 (fr) 2011-05-05

Family

ID=41057880

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2010/051141 WO2011007164A2 (fr) 2009-07-14 2010-07-13 Radôme et procédé de refroidissement de composants de radar

Country Status (3)

Country Link
EP (1) EP2387809B1 (fr)
GB (1) GB0912158D0 (fr)
WO (1) WO2011007164A2 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9300040B2 (en) 2008-07-18 2016-03-29 Phasor Solutions Ltd. Phased array antenna and a method of operating a phased array antenna
US9628125B2 (en) 2012-08-24 2017-04-18 Phasor Solutions Limited Processing a noisy analogue signal
US9917714B2 (en) 2014-02-27 2018-03-13 Phasor Solutions Limited Apparatus comprising an antenna array
CN107942292A (zh) * 2017-10-27 2018-04-20 四川嘉义雷科电子技术有限公司 设置有气体冷却装置的测距设备
CN109417230A (zh) * 2016-07-05 2019-03-01 康普技术有限责任公司 用于微波天线的天线罩、反射器和馈电组件
GB2572476A (en) * 2018-02-07 2019-10-02 Airbus Operations Gmbh Antenna assembly for an aircraft
WO2020157011A1 (fr) * 2019-01-29 2020-08-06 Lufthansa Technik Ag Boîtier rapporté destiné à être fixé sur un aéronef
CN113286490A (zh) * 2021-05-12 2021-08-20 北京无线电测量研究所 一种平流层飞艇雷达的主被动热控系统

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007208468A (ja) * 2006-01-31 2007-08-16 Toshiba Corp レドームおよびこのレドームを備えた空中線システム

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9300040B2 (en) 2008-07-18 2016-03-29 Phasor Solutions Ltd. Phased array antenna and a method of operating a phased array antenna
US10008772B2 (en) 2008-07-18 2018-06-26 Phasor Solutions Limited Phased array antenna and a method of operating a phased array antenna
US9628125B2 (en) 2012-08-24 2017-04-18 Phasor Solutions Limited Processing a noisy analogue signal
US10069526B2 (en) 2012-08-24 2018-09-04 Phasor Solutions Limited Processing a noisy analogue signal
US9917714B2 (en) 2014-02-27 2018-03-13 Phasor Solutions Limited Apparatus comprising an antenna array
US11108149B2 (en) 2016-07-05 2021-08-31 Commscope Technologies Llc Radome, reflector, and feed assemblies for microwave antennas
CN109417230A (zh) * 2016-07-05 2019-03-01 康普技术有限责任公司 用于微波天线的天线罩、反射器和馈电组件
CN107942292A (zh) * 2017-10-27 2018-04-20 四川嘉义雷科电子技术有限公司 设置有气体冷却装置的测距设备
GB2572476A (en) * 2018-02-07 2019-10-02 Airbus Operations Gmbh Antenna assembly for an aircraft
WO2020157011A1 (fr) * 2019-01-29 2020-08-06 Lufthansa Technik Ag Boîtier rapporté destiné à être fixé sur un aéronef
US11377195B2 (en) 2019-01-29 2022-07-05 Lufthansa Technik Ag Attachment housing for fastening to an aircraft
CN113286490A (zh) * 2021-05-12 2021-08-20 北京无线电测量研究所 一种平流层飞艇雷达的主被动热控系统
CN113286490B (zh) * 2021-05-12 2022-08-16 北京无线电测量研究所 一种平流层飞艇雷达的主被动热控系统

Also Published As

Publication number Publication date
EP2387809B1 (fr) 2017-01-04
GB0912158D0 (en) 2009-08-26
WO2011007164A3 (fr) 2011-05-05
EP2387809A2 (fr) 2011-11-23

Similar Documents

Publication Publication Date Title
EP2387809B1 (fr) Radôme et procédé pour refroidir des composants de radar
US7861968B2 (en) Air inlet and method for a highspeed mobile platform
US20130048780A1 (en) Ducted ram air generator assembly
US11820496B2 (en) Heat dissipation structure, heat dissipation method and device, unmanned aerial vehicle, and readable storage medium
EP4058360A2 (fr) Systèmes et procédés pour aéronef
US10059435B2 (en) Low drag skin heat exchanger
US7624944B2 (en) Tandem air inlet apparatus and method for an airborne mobile platform
EP2557039B1 (fr) Refroidisseur d'aéronef supplémentaire de liquide et procédé
US20120237332A1 (en) Fluid-cooling device for a turbine engine propulsive unit
CA2720836A1 (fr) Systeme de degivrage pour un avion
CA2547577A1 (fr) Deflecteur de ventilateur de radiateur avec orifices pour diriger l'ecoulement
JP7050958B2 (ja) アンテナ装置
EP3771644B1 (fr) Système d'échangeur de chaleur de véhicule
US4905937A (en) Pod assembly with integrated radiofrequency emitting and aerial refueling equipment
CN211196649U (zh) 一种航空风冷式电动推进单元
JP2002193193A (ja) 無人ヘリコプターのラジエータ構造
CN113911329A (zh) 飞行体以及动力装置
US11326515B2 (en) Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly
WO2022013322A1 (fr) Radôme satcom monté sur une plate-forme aérobie
US11220329B2 (en) Ducted rotor stators
CN208904220U (zh) 一种机载吊挂式风冷雷达天线罩
US20040144097A1 (en) Apparatus and methods for reducing foreign object debris ingestion into aircraft engines
CN221214636U (zh) 一种无人机机体总成及无人机
CA2602214A1 (fr) Systeme de propulsion et moteur daeronef situes dans la cellule
RU2718694C1 (ru) Малозаметный многофункциональный самолет большой дальности и продолжительности полета

Legal Events

Date Code Title Description
REEP Request for entry into the european phase

Ref document number: 2010799491

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2010799491

Country of ref document: EP

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 10799491

Country of ref document: EP

Kind code of ref document: A2

NENP Non-entry into the national phase

Ref country code: DE

点击 这是indexloc提供的php浏览器服务，不要输入任何密码和下载