GB2267858A - Thermally insensitive connecting seam - Google Patents
Thermally insensitive connecting seam Download PDFInfo
- Publication number
- GB2267858A GB2267858A GB9309793A GB9309793A GB2267858A GB 2267858 A GB2267858 A GB 2267858A GB 9309793 A GB9309793 A GB 9309793A GB 9309793 A GB9309793 A GB 9309793A GB 2267858 A GB2267858 A GB 2267858A
- Authority
- GB
- United Kingdom
- Prior art keywords
- collar
- intermediate ring
- connecting element
- base body
- connecting seam
- 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
Links
- 229910052751 metal Inorganic materials 0.000 claims abstract description 14
- 239000002184 metal Substances 0.000 claims abstract description 14
- 238000005253 cladding Methods 0.000 claims abstract description 5
- 238000005476 soldering Methods 0.000 claims abstract description 4
- 230000001747 exhibiting effect Effects 0.000 claims abstract description 3
- 150000002739 metals Chemical class 0.000 claims abstract description 3
- 239000010936 titanium Substances 0.000 claims description 8
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 5
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229910001092 metal group alloy Inorganic materials 0.000 claims 1
- 238000003466 welding Methods 0.000 abstract description 8
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 5
- 229910052719 titanium Inorganic materials 0.000 description 5
- 238000010276 construction Methods 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000005693 optoelectronics Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/043—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
- F16B5/08—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of welds or the like
-
- 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
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
- F42B10/42—Streamlined projectiles
- F42B10/46—Streamlined nose cones; Windshields; Radomes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/18—Titanium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
- F16B2200/97—Constructional details of connections not covered for in other groups of this subclass having differing thermal expansion coefficients
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Arc Welding In General (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
- Led Device Packages (AREA)
Abstract
A connecting seam connects a base body (10) and an intermediate ring (14) composed of different metals exhibiting different thermal dilatation coefficients. The connecting seam is provided by an annular connecting element (20) composed of two metal layers (22, 24) interconnected by roll-bonded cladding. The thermal dilatation coefficient and the metallic properties of each of these metal layers (22, 24) is similar to those of a collar (18) on the body (10) and the intermediate ring (14), respectively, adjacent thereto. The collar (18) and the intermediate ring (14) are both connected to the connecting element by welding, soldering or cementing. The intermediate ring (14) carries a dome, (Fig. 1 not shown) such as a seeker dome on the front of a missile airframe. <IMAGE>
Description
226 7858 Sealed and temRerature resistant connecting seam The invention
relates to a connecting seam for connecting a base body provided with a collar and an intermediate ring connected, in turn, to the edge of a dome, the connection being sealed and resistant to temperature variations, base body and intermediate ring being composed of two different metals exhibiting different thermal dilatation coefficients.
In particular, the invention relates to the attaching of a "dome" to the airframe of a missile provided with a seeker. The dome covers the seeker. This seeker is a sensitive optical device having an opto-electronic sensor. The connecting seam has to be sealed and temperature resistant. It is exposed to extreme temperature variations as the outside temperature is very low, the skin of the missile, however, is strongly heated during the flight. 20 Numerous constructions have already been tried for attaching such a dome to the airframe of the missile. Partially, such constructions are very complex. Partially, sealing problems result with very high speeds and extreme environmental conditions. It is the object of the invention to achieve a sealed and temperature resistant attachment of a dome to a base body for these and similar purposes, such that 30 the attachment also resists considerable temperature variations. According to the invention this object is achieved with a connecting seam of the above mentioned type in 35 that (a) an annular connecting element is inserted between the collar of the base body and the intermediate 2 ring along the connecting seam, this. connecting element being connected, on one side, to the collar and, on the other s ide, to the intermediate ring, (b) the connecting element is composed of two metal layers interconnected by roll-bonded cladding, the thermal dilatation coeffecient of each of theses metal layers being similar to the thermal dilatation coefficient of the collar and the intermediate ring, respectively, adjacent thereto, (c) the collar and the intermediate ring are both connected to the connecting element by surface bonding means.
According to the invention, the dome, e.g.. the dome of a missile, is held in an intermedate ring. The intermediate ring is fixed to the base body provided, e.g. on the airframe of a missile. The connection between e.g. the titanium of the intermediate ring and e.g. the aluminum alloy of the base body is established through an annular connecting element. The connecting element is supported by a step at the collar of the base body and retained thereby in its position. it is composed of two metal layers connected to each other through roll-bonded cladding. It has been found that such a construction satisfies the above described requirements of missiles. The metal layers may exhibit identical or similar metallic properties. Hereby, the connecting to the respective adjacent parts, e.g.. by welding, is facilitated.
Thermal tensions are compensated within the connecting element.
Modifications of the invention ar subject matter of the dependent claims.
3 An embodiment of the invention will now be described in greater detail with reference to the accompanying drawings.
Fig. 1 is a schematic perspective sectional illustration of the front end of a missile provided with a dome, the dome being connected by means of a sealed and temperature resistant connecting seam to the airframe of the missile.
Fig. 2 shows, at an enlarged scale, a section of the connecting seam between intermediate ring and base body.
in Fig. 1 a base body is designated by 10. in the present example, the base body 10 is a disc-shaped bottom. A dome 12 transparent to the seeker radiation is attached to the base body 10 through an intermediate ring 14. Thereby, a cavity sealed against the outside space results, a seeker (not shown) of the missile being arranged in this cavity. The dome is sealingly connected to the intermediate ring 14 in a way not illustrated in greater detail.
The base body 10 is made of an aluminum alloy. The intermediate ring 14 is made of a titanium alloy or of titanium. A connecting seam between the base body 10 and the intermediate ring 14 is designated by numeral 16 in rig.1 and is illustrated at an enlarged scale in Fig.2.
The base body 10 has a collar 18. A connecting element generally designated by numeral 20 is provided between the collar 18 and the intermediate ring 14. The connecting element 20 is composed of two metal layers connected to each other by roll-bonded cladding. These 4 metal layers are a layer 22 of titanium or a titanium alloy facing the intermediate ring 14 and a layer 24 of an aluminum alloy facing the collar 18. The layer 22 of the connecting element 22 which layer is made of titanium or a titanium alloy, is connected by welding to the intermediate ring 14 also made of titanium or a titanium alloy. Instead of welding, the connection may also be established by soldering or cementing. The collar 18 of the base body 10 is connected the the connecting element 20 also by welding. Also herein, the connection may be established by soldering or cementing instead of welding.
The connecting element 20 has a profile 26. The profile 26 forms a radial step 28 extending approximately perpendicularly to the peripheral surface of the connecting element 20. An edge of the collar 18 extending perpendicularly to the inner surface of the connecting element, engages the step 28.
The connection between the connecting element 20 and the f lange 18 of the base body 10 may be established by welding or cementing on the circumferential surface. However, it may also be sufficient to establish the connection by a welding seam extending between the step 28 and the radial edge of the collar 18.
The connection of the collar 18 of the base body 10 to the intermediate ring 14 by interposing of the connecting element 20 is durable and safe in spite of the different materials and the differece of the thermal dialtation coefficients of the collar 18 and the intermediate ring 14. The connection also resists the mechanical and thermal stresses occuring during operation. The connection also exhibits the vacuum tightness required in numerous applications.
The following alloys have been used for the individual components in the preferred embodiment:
The intermediate ring 14 and the layer 22 of the connecting element are made of Ti 99. The layer 24 of the connecting element 20 is made Of 'k1CUM92. The collar 28 of the base body is made of G-AI Si 7 Mg 0t3. 10 is 6
Claims (9)
- ClaimsI. connecting seam for connecting a base body Provided with a collar and an intermediate ring connected, in turn, to the edge of a dome, the connection being sealed and resistant to temperature variations, base body and intermediate ring being composed of two different metals exhibiting different thermal dilatation coefficients, characterized in that (a) an annular connecting element is inserted between the collar of the base body and the intermediate ring along the connecting seam, this connecting element being connected, on one side, to the collar and, on the other side, to the intermediate ring, (b) the connecting element is composed of two metal layers interconnected by roll-bonded cladding, the thermal dilatation coeffecient of each of theses metal layers being similar to the thermal dilatation coefficient of the collar and the intermediate ring, respectively, adjacent thereto, (c) the collar and the intermediate ring are both connected to the connecting element by surface bonding means.7
- 2. Connecting seam according to claim it characterized in that a radial step is provided at the inner metal layer of theannular connecting element, the end face of the collar engaging the radial step.
- 3. Connecting seam according to claim it characterized in that the surface bonding means comprise a weld joint.
- 4. Connecting eeam according to claim 1, characterized in that the surface connecting means comp..cise a soldering joint.is
- 5. Connecting seam according to claim it characterized in that the surface connecting means are formed by a cenenting joint.
- 6. Connecting seam according to claim 1, characterized in that the annular connecting element (20) is welded to the collar (18) along the step (28).
- 7. Connecting seam according to claim 19 characterized in that the base body (10) with the collar (18) is made of an aluminum alloy and the intermediate ring is made of a titanium alloy, and the connecting element (20) is composed of layers (22,24) of the same or similar metal alloys.
- 8. Connecting seam according to claim 7, characterized in that the intermediate ring (14) is made of Ti 99 and the base body (10) with the collar (18) is made of G-Al Si Mg 0, 3 and the connecting element (20) is made of Ti 99 and Al Cu Mg2.8
- 9. Connecting seam substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE4216337A DE4216337C2 (en) | 1992-05-16 | 1992-05-16 | Connection arrangement, in particular for the seeker head of a missile, according to the preamble of patent claim 1 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9309793D0 GB9309793D0 (en) | 1993-06-23 |
| GB2267858A true GB2267858A (en) | 1993-12-22 |
| GB2267858B GB2267858B (en) | 1995-11-01 |
Family
ID=6459124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9309793A Expired - Fee Related GB2267858B (en) | 1992-05-16 | 1993-05-12 | Sealed and temparature resistant connecting seam |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE4216337C2 (en) |
| FR (1) | FR2691571B1 (en) |
| GB (1) | GB2267858B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9347752B2 (en) | 2011-05-24 | 2016-05-24 | Mbda France | Connecting element for a body made of composite material of a piercing projectile |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19801014B4 (en) * | 1998-01-14 | 2008-09-18 | Schaeffler Kg | Arrangement for connecting two precision-fitted components |
| DE19833590C1 (en) * | 1998-07-28 | 2000-03-30 | Dietmar Eifler | Process for welding an extended optical component to a metal fastening, its use and the optical assembly |
| DE102005018052B4 (en) * | 2005-04-19 | 2010-09-23 | Aeromaritime Systembau Gmbh | Antenna cap for submarines and method of making an antenna cap for submarines |
| CN109854596B (en) * | 2019-03-08 | 2021-02-09 | 北京航天自动控制研究所 | Aircraft optical hood and cabin positioning and mounting equipment and mounting method |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4011819A (en) * | 1976-03-03 | 1977-03-15 | The United States Of America As Represented By The Secretary Of The Navy | Stress relieved molded cover assembly and method of making the same |
| DE3243823A1 (en) * | 1982-11-26 | 1984-05-30 | Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt | Snap connection between bodies |
| IL76971A (en) * | 1984-11-30 | 1990-01-18 | Sundstrand Data Control | Mounting system for precision transducer |
| DE3634196A1 (en) * | 1986-10-08 | 1988-04-21 | Zeiss Carl Fa | Device for connecting two bodies having different coefficients of thermal expansion |
| FR2608266B1 (en) * | 1986-12-11 | 1989-02-24 | Serat | IMPROVEMENTS TO IMPACT CONTACTORS OR CONTACTOR OGIVES FOR PROJECTILES |
| US4969172A (en) * | 1988-08-15 | 1990-11-06 | Machlett Labs. Inc. | X-ray tube rotor structure |
| JPH038562A (en) * | 1989-05-19 | 1991-01-16 | Matsushita Refrig Co Ltd | Laminating type heat exchanger |
-
1992
- 1992-05-16 DE DE4216337A patent/DE4216337C2/en not_active Expired - Fee Related
-
1993
- 1993-05-12 GB GB9309793A patent/GB2267858B/en not_active Expired - Fee Related
- 1993-05-14 FR FR9306021A patent/FR2691571B1/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9347752B2 (en) | 2011-05-24 | 2016-05-24 | Mbda France | Connecting element for a body made of composite material of a piercing projectile |
Also Published As
| Publication number | Publication date |
|---|---|
| DE4216337A1 (en) | 1993-11-18 |
| DE4216337C2 (en) | 2002-10-31 |
| FR2691571A1 (en) | 1993-11-26 |
| GB9309793D0 (en) | 1993-06-23 |
| FR2691571B1 (en) | 1995-06-16 |
| GB2267858B (en) | 1995-11-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20010512 |