EP3377404A1 - Aéronef comprenant un composant d'isolation thermique - Google Patents

Aéronef comprenant un composant d'isolation thermique

Info

Publication number
EP3377404A1
EP3377404A1 EP16797544.0A EP16797544A EP3377404A1 EP 3377404 A1 EP3377404 A1 EP 3377404A1 EP 16797544 A EP16797544 A EP 16797544A EP 3377404 A1 EP3377404 A1 EP 3377404A1
Authority
EP
European Patent Office
Prior art keywords
aircraft
thermal insulation
insulation component
component
pressure
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.)
Withdrawn
Application number
EP16797544.0A
Other languages
German (de)
English (en)
Inventor
Florian Kurfiss
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.)
Airbus Defence and Space GmbH
Original Assignee
Airbus Defence and Space GmbH
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 Airbus Defence and Space GmbH filed Critical Airbus Defence and Space GmbH
Publication of EP3377404A1 publication Critical patent/EP3377404A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/58—Thermal protection, e.g. heat shields
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles

Definitions

  • the present invention relates to an aircraft with a thermal insulation component. Furthermore, the invention relates to a method for operating such an aircraft.
  • temperature-sensitive components such as electronic components, in particular avionics components
  • avionics components at high altitudes Protecting low temperatures of up to -90 ° C.
  • HAPS High Altitude Pseudo Satellites
  • foamed insulation components made of styrofoam or the like, mirror films or with granules, such as. Airgel granules, filled vacuum insulation panels installed.
  • the present invention has for its object to provide an aircraft with a weight and at the same time performance optimized thermal insulation component.
  • the invention is also based on the object of specifying a method for operating such an aircraft.
  • An aircraft comprises at least one thermal insulation component which consists of a nanoporous material whose pore structure is designed to be open-pored such that, during flight operation of the aircraft, a pressure in the pores of the thermal insulation component is established which corresponds to the ambient pressure at the altitude of the aircraft.
  • an increase in the ratio between the mean free path of the gas molecules and the average pore diameter in a nanoporous material results in a reduction in the heat conduction of the gas, since the gas molecules then increasingly collide with the pore walls than with other gas molecules and thus their thermal Energy increasingly transferred to the solid phase of the nanoporous material.
  • Pore diameter can be effected by reducing the pressure of the gas in the pores of the nanoporous material.
  • the thermal insulation component of the aircraft in which for the realization of low thermal conductivities inside the panels contained granules are artificially evacuated and then sealed with corresponding outer shells relative to the ambient atmosphere, in the thermal insulation component of the aircraft, the lying well below the normal atmospheric pressure at sea level ambient pressure in the Flight altitude of the aircraft ge ⁇ uses to reduce the pressure of the gas in the pores of the nanoporous material and thereby the heat conduction of this gas.
  • the thermal insulation component therefore has optimized insulation properties for use under a reduced ambient pressure, without it being necessary to artificially generate a pressure in the insulation component that is lower than the normal atmospheric pressure at sea level and then to seal the insulation component from the ambient atmosphere.
  • the thermal insulation component can therefore be dispensed with an outer shell for sealing the insulation component relative to the ambient atmosphere.
  • the insulation component can therefore be made particularly lightweight.
  • damage caused in conventional vacuum insulation panels by mechanical damage of the outer shell can be avoided.
  • the thermal insulation component is insensitive to pressure fluctuations in the ambient atmosphere, since it is ensured by the structure of the insulating component and in particular its open porosity that always a pressure equalization takes place between the ambient atmosphere and the interior of the insulating component.
  • the thermal insulation component can therefore not only be used at altitudes over 20,000 m, where conventional vacuum insulation panels fail due to the remaining in spite of artificial evacuation and subsequent sealing residual pressure, since the panels due to the pressure difference between the present in their interior residual pressure and the low Bloat pressure of the ambient atmosphere.
  • the thermal insulation component can also be used in aircraft, such as planetary probes, which enter after a long residence time in a vacuum back into the atmosphere of a planet or moon and land there, that should remain in the atmosphere of.
  • the thermal insulation component of the aircraft contains an airgel.
  • Aerogels are characterized by their low weight and their nanoporous structure with open pores, which allows a pressure equalization between the ambient atmosphere and the gas inside the pores of the airgel.
  • the airgel may, for example, contain a solid phase content of not more than 10% by volume.
  • silica aerogels and the solid phase has a comparatively low thermal conductivity.
  • the thermal insulation component contains a polymer airgel.
  • polymer aerogels are prepared by adding a crosslinking agent that covalently bonds with hydroxyl groups to form a silica gel prior to its drying.
  • Polymer aerogels are characterized by excellent mechanical properties and in particular a low brittleness and thus good deformability.
  • Airloy® X130 UL can be used to make the thermal insulation component. The thermal insulation component can then be easily and without damaging the insulating component in the form suitable for its intended use on board the aircraft form and mounted in the aircraft.
  • a solid phase material of the thermal insulation component in the infrared wavelength range is intransparent.
  • the thermal insulation component may for example form a battery insulation of the aircraft.
  • the aircraft equipped with the thermal isolation component may be a HAPS, a weather balloon, a HALE UAV (High Altitude Long
  • Endurance Unmanned Aerial Vehicle a manned aircraft, a stratospheric ⁇ balloon, a planetary probe or the like act. All that is essential is that the aircraft be capable of operating at altitudes where ambient pressure so reduced from normal atmospheric pressure at sea level prevails such that the thermal isolation component has the thermal insulation properties required for the specific application onboard the aircraft.
  • Ambient pressure at the altitude of the aircraft corresponds.
  • the thermal insulation component may contain an airgel, in particular a polymer airgel.
  • a solid phase material of the thermal insulation component is preferably intransparent in the infrared wavelength range.
  • FIG. 1 shows a schematic view of an aircraft equipped with a thermal insulation component.
  • FIG. 1 shows an aircraft 10 in which a thermal insulation component 12 is installed as battery insulation.
  • the aircraft 10 shown in FIG. 1 is a HAPS suitable for operation at an altitude of more than 15,000 m.
  • the aircraft 10 may also be used as a weather balloon, HALE UAV, manned aircraft, stratospheric balloon, planetary probe or the like may be formed.
  • the thermal insulation component 12 consists of a nanoporous material, the pore structure is designed so open-pored that in flight operation of the aviation ⁇ zeugs 10 in the pores of the thermal insulation member 12 sets a pressure corresponding to the ambient pressure at the altitude of the aircraft 10.
  • the thermal insulation member 12 is made of a polymer airgel, such as Airloy® X130 UL
  • the insulation performance of the thermal insulation component 12 exceeds the insulation performance of a conventional vacuum insulation panel already at an altitude of 13,716 m. With increasing altitude, the insulation performance gains even increase compared to the conventional vacuum insulation panel.
  • the thermal insulation component 12 has a weight 41% lower than the conventional vacuum insulation panel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Health & Medical Sciences (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • General Health & Medical Sciences (AREA)
  • Remote Sensing (AREA)
  • Thermal Insulation (AREA)
  • Compositions Of Macromolecular Compounds (AREA)

Abstract

L'invention concerne un aéronef (10) qui comprend au moins un composant d'isolation thermique (12) constitué d'une matière nanoporeuse dont la structure de pores est à pores ouverts de telle sorte que, pendant le vol de l'aéronef (10), une pression s'établisse dans les pores du composant d'isolation thermique (12), cette pression correspondant à la pression ambiante à l'altitude de vol de l'aéronef (10).
EP16797544.0A 2015-11-16 2016-11-16 Aéronef comprenant un composant d'isolation thermique Withdrawn EP3377404A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015222528.3A DE102015222528B3 (de) 2015-11-16 2015-11-16 Luftfahrzeug mit einem thermischen Isolationsbauteil
PCT/EP2016/077829 WO2017085107A1 (fr) 2015-11-16 2016-11-16 Aéronef comprenant un composant d'isolation thermique

Publications (1)

Publication Number Publication Date
EP3377404A1 true EP3377404A1 (fr) 2018-09-26

Family

ID=57282008

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16797544.0A Withdrawn EP3377404A1 (fr) 2015-11-16 2016-11-16 Aéronef comprenant un composant d'isolation thermique

Country Status (6)

Country Link
US (1) US10793249B2 (fr)
EP (1) EP3377404A1 (fr)
CN (1) CN108349583B (fr)
DE (1) DE102015222528B3 (fr)
RU (1) RU2705474C1 (fr)
WO (1) WO2017085107A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109533267B (zh) * 2018-12-25 2022-01-25 哈尔滨工业大学 一种恒升力充气闭孔微结构浮空材料单元
CN113188653B (zh) * 2021-04-25 2022-10-11 机械工业第九设计研究院股份有限公司 一种建筑隔音性能检测评估方法及评估系统
GB2618162A (en) * 2022-04-28 2023-11-01 Desmond Lewis Stephen Thermal protection venting system for aircraft and spaceplanes

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3055831A (en) * 1961-09-25 1962-09-25 Johns Manville Handleable heat insulation shapes
US5154373A (en) 1988-09-26 1992-10-13 Rockwell International Corporation Integral structure and thermal protection system
US6840480B2 (en) * 2001-09-27 2005-01-11 Ernest A. Carroll Miniature, unmanned aircraft with interchangeable data module
US20060248854A1 (en) * 2005-05-05 2006-11-09 Bartley-Cho Jonathan D Thermally insulated structure - tapered joint concept
CN1895885A (zh) * 2005-07-12 2007-01-17 上海暄洋纳米材料有限公司 一种低温绝热复合纳米材料多层绝热体
US7781492B2 (en) * 2006-06-08 2010-08-24 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Foam/aerogel composite materials for thermal and acoustic insulation and cryogen storage
US9365279B2 (en) 2007-02-23 2016-06-14 Airbus Operations Gmbh Fuselage of an aircraft or spacecraft and method of actively insulating such a fuselage
EP2649119B1 (fr) * 2010-12-07 2016-04-06 Basf Se Mousses de résine de mélamine contenant des matières de charge nanoporeuses
DE102012001912A1 (de) * 2011-12-22 2013-06-27 Eads Deutschland Gmbh Selbstreinigende und superhydrophobe Oberflächen auf Basis von TiO2-Nanotubes
DE102012013977A1 (de) * 2012-07-16 2014-01-16 Li-Tec Battery Gmbh Gehäusebaugruppe, Sekundärbatterie mit wenigstens zwei Sekundärzellen und dieser Gehäusebaugruppe, sowie Verfahren zum Herstellen der Gehäusebaugruppe
DE102012214957A1 (de) * 2012-08-23 2014-02-27 Basf Se Wärmemanagement-System zur Reichweitenerhöhung eines Elektrofahrzeugs
CN203666965U (zh) * 2013-09-30 2014-06-25 中国人民解放军国防科学技术大学 一种高超声速飞行器热防护机构
EP3020638B1 (fr) * 2014-11-11 2017-07-19 Airbus Defence and Space GmbH Dispositif et procédé de dégivrage et/ou de prévention contre la formation de glace ainsi que corps profilé et aéronef dotés d'un tel dispositif
DE102015200390A1 (de) * 2015-01-14 2016-07-14 Robert Bosch Gmbh Batterie mit thermischer Isolation

Also Published As

Publication number Publication date
RU2705474C1 (ru) 2019-11-07
CN108349583A (zh) 2018-07-31
WO2017085107A1 (fr) 2017-05-26
US20180257758A1 (en) 2018-09-13
DE102015222528B3 (de) 2016-12-01
US10793249B2 (en) 2020-10-06
CN108349583B (zh) 2021-07-13

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