DE3713875C1 - Air inlet on aircraft - Google Patents
Air inlet on aircraftInfo
- Publication number
- DE3713875C1 DE3713875C1 DE19873713875 DE3713875A DE3713875C1 DE 3713875 C1 DE3713875 C1 DE 3713875C1 DE 19873713875 DE19873713875 DE 19873713875 DE 3713875 A DE3713875 A DE 3713875A DE 3713875 C1 DE3713875 C1 DE 3713875C1
- Authority
- DE
- Germany
- Prior art keywords
- air inlet
- lining
- aircraft
- segments
- radar
- 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
Links
- 238000000926 separation method Methods 0.000 claims description 5
- 239000011358 absorbing material Substances 0.000 claims description 4
- 230000011218 segmentation Effects 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 2
- 239000002250 absorbent Substances 0.000 abstract 1
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 239000012790 adhesive layer Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q17/00—Devices for absorbing waves radiated from an antenna; Combinations of such devices with active antenna elements or systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
Description
Die Erfindung betrifft einen Lufteinlauf an Flugzeugen, der eine Aus kleidung aus radarabsorbierendem Material aufweist.The invention relates to an air inlet on aircraft, which has an off has clothing made of radar absorbing material.
Derartige Materialien werden eingesetzt, um die bekannte Reflexion der Radarstrahlen von den Metallflächen des Innenraumes, d.h. von der Luft umspülten Oberfläche von Lufteinläufen zu verhindern. Es wird damit versucht, eine möglichst vollständige Absorption dieser ansonsten das Flugzeug identifizierenden Radarstrahlen zu erreichen.Such materials are used to the known reflection of the Radar beams from the metal surfaces of the interior, i.e. from the air to prevent washed surface of air inlets. It will tries to absorb as completely as possible this otherwise To reach aircraft identifying radar beams.
Aus der unter dem Aktenzeichen P 36 05 430.5 beim Deutschen Patentamt geführten Anmeldung der Anmelderin, geht beispielsweise eine derartige Einrichtung hervor, bei der seitlich zur Strömungsrichtung hintereinan der angeordnete Radarabsorbierräume im Lufteinlauf vorgesehen sind, die mit radarabsorbierendem Material ausgeschäumt sind. Zusätzlich gelangen zur Verbesserung der elektrischen Leitfähigkeit, metallische Werkstoffe, wie Metallstifte und Drahteinlagen hier zur Anwendung.From the file number P 36 05 430.5 at the German Patent Office registration of the applicant, such as Device emerges in the side of the flow direction behind each other the arranged radar absorption spaces are provided in the air inlet, the are foamed with radar absorbing material. Arrive in addition to improve electrical conductivity, metallic materials, like metal pins and wire inserts here.
Sowohl die bekannten radarabsorbierenden Materialien in Form von einiger Größenordnung als auch die metallischen Gegenstände bedeuten eine große Gefahr, falls sie vom Innenraum des Lufteinlaufs losgelöst werden. Dies trifft insbesondere zu, wenn diese Teile vor den Triebwerkseingang oder in das Triebwerk geraten und dabei dessen Störung bzw. Beschädigung oder nachfolgend sogar den Absturz des Flugzeugs herbeiführen können.Both the well-known radar absorbing materials in the form of some Magnitude as well as the metallic objects mean a big one Danger if they are detached from the interior of the air intake. This especially applies if these parts in front of the engine entrance or get into the engine and thereby its fault or damage or subsequently even cause the plane to crash.
Der Erfindung liegt daher die Aufgabe zugrunde, die Anordnung einer radarabsorbierenden Auskleidung von Lufteinläufen derart zu verbessern, daß die vorgenannten Gefahren für das Triebwerk und somit für das Flugzeug, bei einer Einhaltung eines hohen Reflexionswirkungsgrades, vermieden werden können.The invention is therefore based on the object, the arrangement of a to improve radar-absorbing lining of air inlets in such a way that the aforementioned dangers for the engine and thus for the Aircraft, while maintaining a high reflection efficiency, can be avoided.
Diese Aufgabe wird durch die im kennzeichnenden Teil des Anspruches 1 angegebenen Merkmale gelöst. This object is achieved by the characterizing part of claim 1 specified features solved.
Vorteilhafte Weiterbildungen der Erfindung werden in den Unteransprüchen wiedergegeben.Advantageous developments of the invention are set out in the subclaims reproduced.
Die Vorteile der Erfindung liegen insbesondere darin begründet, daß durch die Teilbarkeit der Auskleidung in kleine bis sehr kleine Segmen te, diese im Falle einer Loslösung von der Innenwand des Lufteinlaufs, keinen Schaden am Triebwerk anrichten können. Beispielsweise ist es aufgrund der kleinen Größe der Segmente nicht möglich, durch Verstopfen der Stirnseite des Triebwerks dieses zu überhitzen oder zu ersticken, da zwischen den kleinen Segmenten stets viele kleine Luftdurchlässe offen bleiben und außerdem diese kleinen Segmente problemlos vom Triebwerk aufnehmbar sind. Aus dem gleichen Grund wird dadurch auch eine Beschädi gung der Kompressorschaufeln vermieden, insbesondere dann, wenn z.B. durch einen in den Lufteinlauf eingedrungenen Fremdkörper ein größeres Teil von der Auskleidung abgelöst wird und dieser in Segmente zerfallen kann. Gleichermaßen wirken die Segmente bei einer Klebeschwachstelle zur Innenwand als Rißstopper in der Klebeschicht, wodurch einer Loslösung einer großen oder größeren Platte im Lufteinlauf nach dem Reißverschluß effekt, entgegen getreten wird.The advantages of the invention are in particular that due to the divisibility of the lining into small to very small segments te, in the event of detachment from the inner wall of the air inlet, cannot do any damage to the engine. For example it is due to the small size of the segments not possible due to clogging the front of the engine to overheat or suffocate it between the small segments there are always many small air outlets open remain and also these small segments from the engine without any problems are recordable. For the same reason, this also causes damage Avoid the compressor blades, especially if e.g. due to a foreign body entering the air inlet, a larger one Part is removed from the lining and this disintegrates into segments can. The segments also act in the case of an adhesive weak point Inner wall as a crack stopper in the adhesive layer, which causes detachment a large or larger plate in the air inlet after the zipper effect, is countered.
Die Erfindung wird nachfolgend anhand eines Ausführungsbeispiels be schrieben und in der Zeichnung dargestellt. Es zeigenThe invention will be based on an embodiment wrote and shown in the drawing. Show it
Fig. 1 eine Seitenansicht eines Flugzeugs mit einem Lufteinlauf, Fig. 1 is a side view of an aircraft with an air inlet,
Fig. 2 einen Schnitt nach der Linie A-A in der Fig. 1, Fig. 2 shows a section along the line AA in Fig. 1,
Fig. 3 eine Ansicht in Pfeilrichtung nach der Fig. 2. Fig. 3 is a view in direction of arrow of FIG. 2.
Aus der Fig. 1 ist ein Flugzeug 14 mit einem Lufteinlauf 1 ersichtlich, der sich am Flugzeug 14 vom bugnahen Bereich bis zum im Heck angeordne ten Triebwerk 13 erstreckt. Die Auskleidung 3 kann über die gleiche oder teilweisen Länge etwa radial um die Längsachse 2 im Lufteinlauf 1 vorgesehen werden. From Fig. 1, an aircraft 14 having an air inlet 1 can be seen which extends from the aircraft 14 bugnahen area to be arrange in the rear of th engine. 13 The lining 3 can be provided over the same or partial length approximately radially about the longitudinal axis 2 in the air inlet 1 .
Die Fig. 2 zeigt einen Schnitt nach der Linie A-A in der Fig. 1, der die Anordnung der Auskleidung 3 an den Lufteinläufen 1 bzw. an deren Innen wänden 5 nochmals veranschaulicht. Fig. 2 shows a section along the line AA in Fig. 1, which illustrates the arrangement of the lining 3 at the air inlets 1 and on the inner walls 5 again.
In der Fig. 3 ist eine Ansicht in Pfeilrichtung nach der Fig. 2 darge stellt. Aus dieser Draufsicht geht der gesamte Aufbau hervor, wobei mit 12 die Wand des rohrförmigen Lufteinlaufs 1 bezeichnet ist, auf oder an deren Innenseite 5 - z.B. mittels einer Klebeschicht 11 - die Ausklei dung 3 befestigt ist.In Fig. 3 is a view in the direction of the arrow of FIG. 2 Darge provides. From this top view, the entire structure emerges, with 12 denoting the wall of the tubular air inlet 1 , on or on the inside 5 of which , for example by means of an adhesive layer 11 , the lining 3 is fastened.
Vor der Befestigung der Auskleidung 3 im Lufteinlauf 1, wird diese, beispielsweise mit Hilfe eines Stanzverfahrens, mit Trennstellen 8 zur Bildung von Segmenten 4 versehen, wobei die Trennstellen 8 jedoch die gesamte Dicke 6 der Auskleidung 3 nicht vollständig durchdringen, sondern in Richtung der strömungsseitigen Oberfläche 7 eine Restdicke 10 belassen. Hierdurch werden die Segmente 4 mit einer größeren Festigkeit zusammengehalten und außerdem, wird damit eine ungestörte und strömungs günstige Oberfläche 7 geschaffen.Before the lining 3 is fastened in the air inlet 1 , it is provided, for example with the aid of a stamping process, with separation points 8 for the formation of segments 4 , the separation points 8, however, not completely penetrating the entire thickness 6 of the lining 3 , but in the direction of the flow side Leave surface 7 a remaining thickness 10 . As a result, the segments 4 are held together with greater strength and, moreover, an undisturbed and aerodynamically favorable surface 7 is thus created.
Für eine zusätzliche Festigkeitserhöhung können die Trennstellen 8 zudem mit einer Klebung versehen werden, die ein bestimmtes Bruchverhalten aufweist.For an additional increase in strength, the separation points 8 can also be provided with an adhesive which has a certain breaking behavior.
Das in der Fig. 3 gestrichelt aufgezeigte Muster 16 der Segmente 4, ist in Form eines länglichen Hexagonals ausgeführt, das mit seiner Längs achse spitz gegen die Strömungsrichtung 15 ausgerichtet ist, um die Schubfestigkeit im Verbund der Segmente 4 zu erhöhen und um die Luftan griffsfläche, bei evtl. Loslösung eines Segmentes, relativ gering zu halten. Es sind jedoch auch andere Formbildungen für die Segmente 4 denkbar.The pattern 16 shown in dashed lines in FIG. 3 of the segments 4 is designed in the form of an elongated hexagon, which is aligned with its longitudinal axis sharply against the direction of flow 15 in order to increase the shear strength in the composite of the segments 4 and to grip the Luftan surface , in the event of a segment becoming detached, to be kept relatively low. However, other shapes for the segments 4 are also conceivable.
Die strömungsseitige Oberfläche 7 der Auskleidung 3 kann zusätzlich mit einer radartransparenten Schicht 9 versehen werden, um eine glatte Oberfläche neben einer erhöhten Festigkeit der Auskleidung 3 zu gewähr leisten.The flow-side surface 7 of the lining 3 can additionally be provided with a radar-transparent layer 9 in order to ensure a smooth surface in addition to increased strength of the lining 3 .
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19873713875 DE3713875C1 (en) | 1987-04-25 | 1987-04-25 | Air inlet on aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19873713875 DE3713875C1 (en) | 1987-04-25 | 1987-04-25 | Air inlet on aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE3713875C1 true DE3713875C1 (en) | 1988-07-07 |
Family
ID=6326286
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DE19873713875 Expired DE3713875C1 (en) | 1987-04-25 | 1987-04-25 | Air inlet on aircraft |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE3713875C1 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0378838A1 (en) * | 1989-01-14 | 1990-07-25 | Deutsche Aerospace AG | Method for the reduction of backscattering electromagnetic radiation at cavity structures open at one side |
| DE4121584A1 (en) * | 1991-06-29 | 1993-01-21 | Messerschmitt Boelkow Blohm | Camouflaging and strong elimination of radar radiation in inlet of drive - includes impinging radar radiation in inlet duct using divergent tube and associated mode converter |
| DE4135783A1 (en) * | 1991-10-30 | 1993-05-06 | Deutsche Aerospace | Supersonic flight body with seeker head - has reduced form resistance due to seeker head window acting as compression surface for air intake |
| DE4216837A1 (en) * | 1992-05-21 | 1993-11-25 | Deutsche Aerospace | Radar camouflage for roll-stabilised slow-flying missile - comprises strips and narrow wedges of absorbent material in conjunction with wire grid covering nose only |
| DE4225436C1 (en) * | 1992-07-31 | 1993-11-25 | Daimler Benz Ag | Catalytic hardening of sand mould elements - with two-stage sepn. and removal of amine(s) and solvents from exhaust air |
| DE19528343A1 (en) * | 1995-08-02 | 1997-02-13 | Markus Muehleisen | Appliance for low reflexion absorption of microwaves - consists of cylindrical shell resonator with supply wave guide or quasi-optical transmission path arranged in specific position relative to optical beams or resonator modes |
| FR2859702A1 (en) * | 1994-07-08 | 2005-03-18 | Aerospatiale | Air supply system for aircraft e.g. missile, has duct sub-divided into two branches at continuously varying sections between rear and front sections, where walls of branches are partly covered internally with magnetic material |
| DE102012023718A1 (en) * | 2012-12-05 | 2014-06-05 | Eads Deutschland Gmbh | Inlet for an engine of an aircraft |
| RU2522661C1 (en) * | 2012-11-23 | 2014-07-20 | Государственный научный центр Российской Федерации-федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" | Air intake power unit device of hypersonic aircraft |
| CN111232227A (en) * | 2020-01-16 | 2020-06-05 | 南京航空航天大学 | Electromagnetic stealthy sleeve structure for inner wall surface of air inlet channel |
| WO2024112291A1 (en) * | 2022-11-23 | 2024-05-30 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An air vehicle |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3605430A1 (en) * | 1986-02-20 | 1987-08-27 | Messerschmitt Boelkow Blohm | Device for reducing radar reflection |
-
1987
- 1987-04-25 DE DE19873713875 patent/DE3713875C1/en not_active Expired
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3605430A1 (en) * | 1986-02-20 | 1987-08-27 | Messerschmitt Boelkow Blohm | Device for reducing radar reflection |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0378838A1 (en) * | 1989-01-14 | 1990-07-25 | Deutsche Aerospace AG | Method for the reduction of backscattering electromagnetic radiation at cavity structures open at one side |
| DE4121584A1 (en) * | 1991-06-29 | 1993-01-21 | Messerschmitt Boelkow Blohm | Camouflaging and strong elimination of radar radiation in inlet of drive - includes impinging radar radiation in inlet duct using divergent tube and associated mode converter |
| DE4135783A1 (en) * | 1991-10-30 | 1993-05-06 | Deutsche Aerospace | Supersonic flight body with seeker head - has reduced form resistance due to seeker head window acting as compression surface for air intake |
| DE4216837A1 (en) * | 1992-05-21 | 1993-11-25 | Deutsche Aerospace | Radar camouflage for roll-stabilised slow-flying missile - comprises strips and narrow wedges of absorbent material in conjunction with wire grid covering nose only |
| DE4225436C1 (en) * | 1992-07-31 | 1993-11-25 | Daimler Benz Ag | Catalytic hardening of sand mould elements - with two-stage sepn. and removal of amine(s) and solvents from exhaust air |
| FR2859702A1 (en) * | 1994-07-08 | 2005-03-18 | Aerospatiale | Air supply system for aircraft e.g. missile, has duct sub-divided into two branches at continuously varying sections between rear and front sections, where walls of branches are partly covered internally with magnetic material |
| DE19528343A1 (en) * | 1995-08-02 | 1997-02-13 | Markus Muehleisen | Appliance for low reflexion absorption of microwaves - consists of cylindrical shell resonator with supply wave guide or quasi-optical transmission path arranged in specific position relative to optical beams or resonator modes |
| RU2522661C1 (en) * | 2012-11-23 | 2014-07-20 | Государственный научный центр Российской Федерации-федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" | Air intake power unit device of hypersonic aircraft |
| DE102012023718A1 (en) * | 2012-12-05 | 2014-06-05 | Eads Deutschland Gmbh | Inlet for an engine of an aircraft |
| US9889945B2 (en) | 2012-12-05 | 2018-02-13 | Airbus Defence and Space GmbH | Intake for an engine of an aircraft |
| CN111232227A (en) * | 2020-01-16 | 2020-06-05 | 南京航空航天大学 | Electromagnetic stealthy sleeve structure for inner wall surface of air inlet channel |
| CN111232227B (en) * | 2020-01-16 | 2021-11-05 | 南京航空航天大学 | Electromagnetic stealthy sleeve structure for inner wall surface of air inlet channel |
| WO2024112291A1 (en) * | 2022-11-23 | 2024-05-30 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | An air vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 8100 | Publication of the examined application without publication of unexamined application | ||
| D1 | Grant (no unexamined application published) patent law 81 | ||
| 8364 | No opposition during term of opposition | ||
| 8320 | Willingness to grant licenses declared (paragraph 23) | ||
| 8327 | Change in the person/name/address of the patent owner |
Owner name: DEUTSCHE AEROSPACE AG, 8000 MUENCHEN, DE |
|
| 8327 | Change in the person/name/address of the patent owner |
Owner name: DAIMLER-BENZ AEROSPACE AKTIENGESELLSCHAFT, 80804 M |
|
| 8327 | Change in the person/name/address of the patent owner |
Owner name: DAIMLERCHRYSLER AEROSPACE AKTIENGESELLSCHAFT, 8099 |
|
| 8339 | Ceased/non-payment of the annual fee |