SE519890C2 - Apparatus for mechanical bonding of a ceramic material and a metal, in particular for forming a guide attack edge - Google Patents
Apparatus for mechanical bonding of a ceramic material and a metal, in particular for forming a guide attack edgeInfo
- Publication number
- SE519890C2 SE519890C2 SE9103658A SE9103658A SE519890C2 SE 519890 C2 SE519890 C2 SE 519890C2 SE 9103658 A SE9103658 A SE 9103658A SE 9103658 A SE9103658 A SE 9103658A SE 519890 C2 SE519890 C2 SE 519890C2
- Authority
- SE
- Sweden
- Prior art keywords
- ceramic material
- elements
- metal
- lug
- groove
- Prior art date
Links
- 239000002184 metal Substances 0.000 title claims abstract description 16
- 229910010293 ceramic material Inorganic materials 0.000 title claims abstract description 11
- 239000000919 ceramic Substances 0.000 claims description 6
- 125000006850 spacer group Chemical group 0.000 claims description 6
- 238000004873 anchoring Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
-
- 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
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- 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
- 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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
Abstract
Description
15 20 25 30 35 40 519 §9o inre av ett spår som sträcker sig tvärs roderytans längdrikt- ning inuti metallstrukturen, varvid spåret är inramat mot sin öppning vänd framåt medelst flänsar avsedda att säkra föran- kringen av ansatserna anordnade på klacken hos det keramiska elementet. 15 20 25 30 35 40 519 §9o interior of a groove extending transversely to the longitudinal direction of the rudder surface inside the metal structure, the groove being framed towards its opening facing forward by means of flanges intended to secure the anchoring of the shoulders arranged on the lug of the ceramic element .
Med fördel skall noteras att en mellanläggsdel är anord- nad åtminstone mellan klacken och flänsarna hos spåret även som vid spårets baksida.It should be noted with advantage that an intermediate part is arranged at least between the lug and the flanges of the groove also as at the back of the groove.
Enligt ett annat särskilt kännemärke hos uppfinningen är mellanläggsdelen anordnad utefter en axel parallell med roder- ytan på ett icke kontinuerligt sätt, i form av kontaktelement åtskilda av "tomrum".According to another particular feature of the invention, the spacer part is arranged along an axis parallel to the rudder surface in a non-continuous manner, in the form of contact elements separated by "voids".
Andra särskilda särdrag och fördelar hos uppfinningen framgår vid läsning av beskrivningen under hänvisning till bifogade ritningar, vilka visar i: Fig. 1 en schematisk planvy av en roderyta; Fig. 2 ett schematiskt snitt längs linjen II-II i fig. 1; Pig. 3 ett snitt enligt fig. 2 visande den mekaniska sammanbindningsanordningen enligt uppfinningen; §ig¿_g ett delsnitt längs linjen II-II i fig. 3; och Fig. 5 en schematisk planvy av en roderyta enligt upp- finningen.Other particular features and advantages of the invention will become apparent upon reading the specification with reference to the accompanying drawings, which show in: Fig. 1 a schematic plan view of a rudder surface; Fig. 2 is a schematic section along the line II-II in Fig. 1; Pig. 3 is a section according to Fig. 2 showing the mechanical connecting device according to the invention; Fig. A partial section along the line II-II in Fig. 3; and Fig. 5 is a schematic plan view of a rudder surface according to the invention.
I fig. 1 och 2 visas schematiskt framkanten 1 till en roderyta för missiler förbunden med metallstrukturen 2 hos roderytan i en sammanbindningszon 3. Insidan 4 och utsidan 5 hos panelerna är utsatta för mekaniska påkänningar materia- liserade av'Pí1afHH Öfmedan de yttre termiska flödena utövas på strukturens helhet (pilar 7).Figures 1 and 2 schematically show the leading edge 1 of a rudder surface for missiles connected to the metal structure 2 of the rudder surface in an interconnection zone 3. The inside 4 and the outside 5 of the panels are subjected to mechanical stresses materialized by PI1afHH while the external thermal flows on the structure as a whole (arrows 7).
Anordningen för mekanisk sammanbindning enligt uppfin- ningen visas i fig. 3, 4 och 5. Det keramiska materialet 1 bildar framkanten underkastad den aerodynamiska uppvärmningen (hastighet V) och är delad i flera partier eller element 10, av vilka vart och ett av partierna sträcker sig bakåt längs X- axeln till en klack 8 som ingriper i det inre av ett spår 9, vilket sträcker sig tvärs roderytans längdriktning i det inre av metallstrukturen 2. Klacken och spåret bildar förbindnings- medel av den speciella formen mellan det keramiska elementet och metallstrukturen. Spårets höjd c sett parallellt med en vertikal Y-axel är inramad mot sin öppning orienterad framåt, varvid flänsar 11 begränsar dess ingång med en liten höjd d. 10 15 20 25 30 35 40 519 890 Klacken 8 är själv profilerad för att bilda ansatserna 12 med höjden a och som tar stöd mot flänsarna 11 när de kopplas för förankring av det keramiska elementet 10 vid metallstrukturen.The mechanical bonding device according to the invention is shown in Figs. 3, 4 and 5. The ceramic material 1 forms the leading edge subjected to the aerodynamic heating (speed V) and is divided into several portions or elements 10, each of which extends backwards along the X-axis to a lug 8 which engages in the interior of a groove 9, which extends across the longitudinal direction of the rudder surface in the interior of the metal structure 2. The lug and the groove form connecting means of the special shape between the ceramic element and the metal structure . The height c of the groove seen in parallel with a vertical Y-axis is framed towards its opening oriented forwards, flanges 11 limiting its entrance by a small height d. with the height a and which takes support against the flanges 11 when they are coupled for anchoring the ceramic element 10 to the metal structure.
En mellanläggsdel 13, exempelvis en elastomer, är anordnad i 3 höjd med de verksamma ytornas angränsande sidor bildande förbindningen keramik-metall, dvs. mot klacken 8 (i höjd med ansatserna 12 och den centrala halsen 14 med tjockleken b) och flänsarna 11. Måttet a och måttet b hos klacken 8 av keramiskt material fyller klart den mekaniska spänningen för framkanten.An insert 13, for example an elastomer, is arranged at a height 3 with the adjacent sides of the active surfaces forming the ceramic-metal connection, i.e. against the lug 8 (at the height of the shoulders 12 and the central neck 14 with the thickness b) and the flanges 11. The dimension a and the dimension b of the lug 8 of ceramic material clearly fill the mechanical stress for the front edge.
Styvheten hos förbindningszonen 3 i planet X Y tvärs strukturen är funktionen av tjockleken Jl hos mellanläggsdelarna 13 mot klacken 8 och flänsarna 11. Å andra sidan är styvheten mot rotation, dvs. omkring en axel parallell med X-axeln, säker- ställd av en uppdelad och ej kontinuerlig fördelning av mellan- läggsdelarna 13 (kontaktelement 13, separerade av mellanrummen 15 bildade av genomborrade kontaktelement ur en mycket elastisk produkt) längs Z-axeln för spåren 9, som klart framgår av fig. 4. Det faktum att framkanten består av flera element 10, vart och ett försett med kontaktelement, och detta i mellanrummet J2, varvid mellanläggsdelarna är åtskilda medelst mellanrum, bidrar till att bära de keramiska elementen under deformation av roderytans metallstruktur.The stiffness of the connecting zone 3 in the plane X Y across the structure is the function of the thickness J1 of the liner parts 13 against the lug 8 and the flanges 11. On the other hand, the stiffness against rotation, i.e. about an axis parallel to the X-axis, ensured by a divided and non-continuous distribution of the intermediate parts 13 (contact elements 13, separated by the gaps 15 formed by pierced contact elements from a very elastic product) along the Z-axis of the grooves 9, as is clear from Fig. 4. The fact that the leading edge consists of several elements 10, each provided with contact elements, and this in the space J2, the spacer parts being separated by spaces, contributes to supporting the ceramic elements during deformation of the metal structure of the rudder surface .
Ett visst spel J3 mellan elementen 10 och snitten 16 anordnade på nämnda elements ändytor, gör dem oberoende av varandra utan kontakt dem emellan.A certain play J3 between the elements 10 and the cuts 16 arranged on said end surfaces of said elements, makes them independent of each other without contact between them.
Om man eftersträvar en framkant utformad att absorbera radarvågor, används element 10 av ett keramiskt material absorberande radarvågorna, och kan man använda en mellanläggs- del av bestämd ledningsförmåga. Placeringen av dessa delar 13 i ett område efter klacken i spåret 9, medför genom sin volym ett bidrag till att uppta elektromagnetism i fogen.If a leading edge designed to absorb radar waves is sought, elements 10 of a ceramic material absorbing the radar waves are used, and a spacer of a certain conductivity can be used. The placement of these parts 13 in an area after the heel in the groove 9, due to its volume, makes a contribution to absorbing electromagnetism in the joint.
Medelst en sådan anordning påverkar de termiska belast- ningarna ej själva fogen. Dessa belastningar överförs genom varje parti, tillåtande att paret keramik - metall betraktas, varje bröstparti satisfierar separat den termiska omgivningen.By means of such a device, the thermal loads do not affect the joint itself. These loads are transmitted through each portion, allowing the ceramic-metal pair to be viewed, each chest portion separately satisfying the thermal environment.
En deformation av metallstrukturen är ej i stånd att belasta de keramiska elementen.A deformation of the metal structure is not able to load the ceramic elements.
För övrigt är ett partis uppdelning i element, ej nöd- vändigt för en fog med ringa längd, dock föreslagen huvud- sakligen för åstadkommandet av en fog med stor längd. 519 890 4 Det underförstås att man kan använda olika keramiska material och dess motsvarande mellanliggande delar för att åstadkomma de olika elementen bildande nämnda framkant.Incidentally, the division of a party into elements is not necessary for a joint of short length, however, it is proposed mainly for the creation of a joint of large length. It is understood that one can use different ceramic materials and their corresponding intermediate parts to provide the various elements forming said leading edge.
Claims (7)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9015816A FR2825760A1 (en) | 1990-12-18 | 1990-12-18 | Connection device for securing ceramic material to front edge of rudder for aircraft, joins sections of ceramic material to the metal rudder structure |
Publications (2)
Publication Number | Publication Date |
---|---|
SE9103658L SE9103658L (en) | 2002-02-13 |
SE519890C2 true SE519890C2 (en) | 2003-04-22 |
Family
ID=9403336
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SE9103658A SE519890C2 (en) | 1990-12-18 | 1991-12-11 | Apparatus for mechanical bonding of a ceramic material and a metal, in particular for forming a guide attack edge |
Country Status (6)
Country | Link |
---|---|
CA (1) | CA2057762A1 (en) |
DE (1) | DE4141166B3 (en) |
FR (1) | FR2825760A1 (en) |
IT (1) | IT1316422B1 (en) |
NL (1) | NL194702C (en) |
SE (1) | SE519890C2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112173068A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Adjustable helicopter side end plate structure |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB914548A (en) * | 1960-03-04 | 1963-01-02 | Daimler Benz Ag | Improvements relating to wheel discs with ceramic blades for axial-flow machines |
US3430898A (en) * | 1967-05-01 | 1969-03-04 | Us Navy | Leading edge for hypersonic vehicle |
DE2108176A1 (en) * | 1971-02-20 | 1972-08-31 | Motoren Turbinen Union | Fastening of ceramic turbine blades |
US4790723A (en) * | 1987-01-12 | 1988-12-13 | Westinghouse Electric Corp. | Process for securing a turbine blade |
US4854765A (en) * | 1987-07-13 | 1989-08-08 | The Boeing Company | Reversible thermal compensation joint |
-
1990
- 1990-12-18 FR FR9015816A patent/FR2825760A1/en active Pending
-
1991
- 1991-11-21 IT IT1991MI003106A patent/IT1316422B1/en active
- 1991-12-11 SE SE9103658A patent/SE519890C2/en not_active IP Right Cessation
- 1991-12-13 DE DE4141166A patent/DE4141166B3/en not_active Expired - Lifetime
- 1991-12-17 CA CA2057762A patent/CA2057762A1/en not_active Expired - Lifetime
- 1991-12-18 NL NL9102111A patent/NL194702C/en not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
FR2825760A1 (en) | 2002-12-13 |
DE4141166B3 (en) | 2006-04-06 |
ITMI913106A1 (en) | 1993-05-21 |
NL194702C (en) | 2002-12-03 |
NL194702B (en) | 2002-08-01 |
NL9102111A (en) | 2002-05-01 |
ITMI913106A0 (en) | 1991-11-20 |
CA2057762A1 (en) | 1992-06-19 |
IT1316422B1 (en) | 2003-04-10 |
SE9103658L (en) | 2002-02-13 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
NUG | Patent has lapsed |