Nothing Special   »   [go: up one dir, main page]

EP2387809A2 - A radome and method of cooling radar components - Google Patents

A radome and method of cooling radar components

Info

Publication number
EP2387809A2
EP2387809A2 EP10799491A EP10799491A EP2387809A2 EP 2387809 A2 EP2387809 A2 EP 2387809A2 EP 10799491 A EP10799491 A EP 10799491A EP 10799491 A EP10799491 A EP 10799491A EP 2387809 A2 EP2387809 A2 EP 2387809A2
Authority
EP
European Patent Office
Prior art keywords
housing
radome
ram air
radar
air inlet
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
EP10799491A
Other languages
German (de)
French (fr)
Other versions
EP2387809B1 (en
Inventor
Faris Samarai
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP2387809A2 publication Critical patent/EP2387809A2/en
Application granted granted Critical
Publication of EP2387809B1 publication Critical patent/EP2387809B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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

The invention relates to a radome (10) for cooling radar components (16). The radome (10) has a housing (12) provided with a ram air inlet (18)and a ram air outlet (20). The radome (10) is installed on the body of a moving craft so that air flowrelative to the craft will enter the housing (12) by way of the ram air inlet (18), circulate within the housing (12), and exit the housing (12) by way of the ram airoutlet (20) in order to cool radar components (16) within the radar componenthousing (12). A method of cooling radar components is also described.

Description

A Radome and Method of Cooling Radar Scanner Components
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.
A number of different radar systems are available; however, there has recently been an increasing tendency to use ESA (Electronically Scanned Array; also known as Active Phased Array) based systems due to a number of advantages such systems provide. 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. However, such systems require undesirably complex
compression and routing systems if they are to be installed in an aircraft.
According to the present invention there is provided a radome comprising:- a radar component housing;
a ram air inlet provided in the radar component housing;
and 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.
Optionally, the ram air inlet comprises a hole through a wall of the radome housing and a recessed flap surface in the radome housing. Optionally, 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.
Optionally, the ram air inlet comprises a NACA duct in a wall of the radome housing. Preferably, the ram air outlet is provided in a lower wall of the radome housing. Optionally, 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.
According to the present invention there is also provided a method of cooling radar components, the method comprising the steps of:- housing radar components in a radar housing;
providing a ram air inlet in a wall of the radar housing;
providing a ram air outlet in a wall of the radar housing;
mounting the radar housing to a craft; such that, when the craft moves, ram air flows into the air inlet, circulates around the housing to cool the radar components within the housing, and then exits the radar housing by way of the ram air outlet.
Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which:-
Fig. 1 is a schematic plan view from beneath a radome according to the present invention; and
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
components.
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.
In the embodiment shown, 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.
In use, on an aircraft, as the aircraft moves through the air, 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. As 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. In this regard, it should be noted that 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
components of a radar scanner in order to maintain the working
temperature in the radome without the need for complex control or coolant routing systems.
The reduced part count and complexity has a number of further
advantages such as:-
- The radome design and the lack of moving parts makes
manufacture and maintenance straightforward;
- Reduced likelihood of equipment malfunction due to lack of moving parts, reduced part count and overall improved cooling efficiency;
- Weight reduction since no coolant, compression system or coolant pipes are required. This is particularly beneficial in aerospace applications where even a small reduction in weight can result in large gains in overall aircraft performance;
- No additional holes need to be provided in the fuselage. This is particularly important in pressurised aircraft where every additional hole through the fuselage results in the potential for a
corresponding increase in stress concentration points on the fuselage;
- Existing radomes can be replaced with the new radome according to the invention and hence the invention can be easily retrofitted without modification of the existing radar scanner components; and
- A minimum change in overall radome profile is required, which is important to maintain the aircraft's aerodynamic characteristics as well as the radome "transparency" to radio waves. Modifications and improvements may be made to the foregoing without departing from the scope of the invention, for example:-
Although in the described embodiment , 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.

Claims

Claims.
1. A radome comprising:- a radar component housing;
a ram air inlet provided in the radar component housing;
and 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.
2. A radome according to claim 1 , wherein the radar components comprise radar scanner components.
3. A radome according to either of claims 1 or 2, wherein the radome is mountable on an aircraft fuselage.
4. A radome according to any preceding claim, wherein the ram air inlet and ram air outlet are positioned relative to one another such that a transmission / reception antenna within the radome housing is cooled by the air circulating within the radome housing.
5. A radome according to any preceding claim, wherein the ram air inlet comprises a hole through a wall of the radome housing and a recessed flap surface in the radome housing.
6. A radome according to any preceding claim, wherein the ram air inlet is provided in a side wall of the radome housing.
7. A radome according to any preceding claim, wherein a removable filter element is provided at the ram air inlet.
8. A radome according to any preceding claim, wherein the ram air inlet comprises a NACA duct in a wall of the radome housing.
9. A radome according to any preceding claim, wherein the ram air outlet is provided in a lower wall of the radome housing.
10. A radome according to any preceding claim wherein the ram air outlet is provided with a socket which allows it to be connected to a suction device.
11. A radome according to claim 10, wherein the socket comprises a bayonet connection.
12. A radome according to any preceding claim, wherein the ram air inlet is provided aft of the ram air outlet in order to encourage circulation of air within the radome housing.
13. A radome according to any preceding claims, wherein a recirculation fan is provided to facilitate circulation of air within the radome housing.
14. A method of cooling radar scanner components, the method comprising the steps of:- housing radar components in a radar housing;
providing a ram air inlet in a wall of the radar housing;
providing a ram air outlet in a wall of the radar housing;
mounting the radar housing to a craft; such that, when the craft moves, ram air flows into the air inlet, circulates around the housing to cool the radar components within the housing, and then exits the radar housing by way of the ram air outlet.
15. A method according to claim 14, further comprising the step of providing a socket on the ram air outlet and connecting the socket to a suction device.
16. A method according to either of claims 14 or 15, further comprising the step of encouraging circulation of air within the radome housing by providing the ram air inlet aft of the ram air outlet.
17. A method according to claim 16, further comprising facilitating circulation of air within the radome housing by providing a recirculation fan.
EP10799491.5A 2009-07-14 2010-07-13 A radome and method of cooling radar components Active EP2387809B1 (en)

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
PCT/GB2010/051141 WO2011007164A2 (en) 2009-07-14 2010-07-13 A radome and method of cooling radar components

Publications (2)

Publication Number Publication Date
EP2387809A2 true EP2387809A2 (en) 2011-11-23
EP2387809B1 EP2387809B1 (en) 2017-01-04

Family

ID=41057880

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10799491.5A Active EP2387809B1 (en) 2009-07-14 2010-07-13 A radome and method of cooling radar components

Country Status (3)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3482455A4 (en) * 2016-07-05 2020-01-22 Commscope Technologies LLC Radome, reflector, and feed assemblies for microwave antennas

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2474923B (en) 2008-07-18 2011-11-16 Phasor Solutions Ltd A phased array antenna and a method of operating a phased array antenna
GB201215114D0 (en) 2012-08-24 2012-10-10 Phasor Solutions Ltd Improvements in or relating to the processing of noisy analogue signals
GB201403507D0 (en) 2014-02-27 2014-04-16 Phasor Solutions Ltd Apparatus comprising an antenna array
CN107942292A (en) * 2017-10-27 2018-04-20 四川嘉义雷科电子技术有限公司 It is provided with the distance-measuring equipment of gas cooling device
DE102018102765A1 (en) * 2018-02-07 2019-08-08 Airbus Operations Gmbh Antenna arrangement for an aircraft
DE102019201103A1 (en) 2019-01-29 2020-07-30 Lufthansa Technik Aktiengesellschaft Attachment housing for attachment to an aircraft
CN113286490B (en) * 2021-05-12 2022-08-16 北京无线电测量研究所 Active and passive thermal control system of stratospheric airship radar

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007208468A (en) * 2006-01-31 2007-08-16 Toshiba Corp Radome and antenna system with the radome

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011007164A2 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3482455A4 (en) * 2016-07-05 2020-01-22 Commscope Technologies LLC Radome, reflector, and feed assemblies for microwave antennas
US11108149B2 (en) 2016-07-05 2021-08-31 Commscope Technologies Llc Radome, reflector, and feed assemblies for microwave antennas

Also Published As

Publication number Publication date
GB0912158D0 (en) 2009-08-26
WO2011007164A3 (en) 2011-05-05
WO2011007164A2 (en) 2011-01-20
EP2387809B1 (en) 2017-01-04

Similar Documents

Publication Publication Date Title
EP2387809B1 (en) A radome and method of cooling radar components
US8678310B2 (en) Ducted ram air generator assembly
CN113272678B (en) System for cooling sensor components
CA2595154C (en) Air inlet and method for a highspeed mobile platform
WO2021064376A2 (en) Systems and methods for aircraft
US10059435B2 (en) Low drag skin heat exchanger
WO2020033010A3 (en) Aircraft drag reduction system and internally cooled electric motor system and aircraft using same
US9175695B2 (en) Fluid-cooling device for a turbine engine propulsive unit
US11820496B2 (en) Heat dissipation structure, heat dissipation method and device, unmanned aerial vehicle, and readable storage medium
EP2557039B1 (en) Aircraft supplemental liquid cooler and method
US20080099631A1 (en) Tandem air inlet apparatus and method for an airborne mobile platform
JP7050958B2 (en) Antenna device
CA2720836A1 (en) De-icing system for an airplane
CN101730791A (en) Turbojet engine for aircraft
US11673682B2 (en) Vehicle heat exchanger system including an inflatable member operable to press a cooling tube
US20060272800A1 (en) Radiator fan shroud with flow directing ports
CN215590991U (en) Flying body and power device
EP0362796A2 (en) Pod assembly with integrated radio frequency and aerial refueling equipment
US11326515B2 (en) Arrangements for drawing in air and trapping foreign bodies in an aircraft propulsion assembly
CN208904220U (en) A kind of air-cooled radome of airborne suspension type
US20200247535A1 (en) Ducted rotor stators
US20150099446A1 (en) Chilled air plenum system for aircraft galleys
CN221316702U (en) Unmanned aerial vehicle structure of high-efficient heat dissipation
RU2718694C1 (en) Unobtrusive multifunctional aircraft of long range and flight duration
CA2602214A1 (en) Aircraft propulsion system

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20110720

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160517

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 860070

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602010039383

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Ref country code: NL

Ref legal event code: MP

Effective date: 20170104

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 860070

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170504

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170405

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170404

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170504

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170404

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602010039383

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

26N No opposition filed

Effective date: 20171005

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170731

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170713

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170731

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170713

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170713

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20100713

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170104

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230603

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230710

Year of fee payment: 14

Ref country code: DE

Payment date: 20230710

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20240618

Year of fee payment: 15