US20020003984A1 - Clamping ring for connecting cylindrical units of missiles - Google Patents
Clamping ring for connecting cylindrical units of missiles Download PDFInfo
- Publication number
- US20020003984A1 US20020003984A1 US09/943,519 US94351901A US2002003984A1 US 20020003984 A1 US20020003984 A1 US 20020003984A1 US 94351901 A US94351901 A US 94351901A US 2002003984 A1 US2002003984 A1 US 2002003984A1
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- United States
- Prior art keywords
- clamping ring
- circumferential
- cheeks
- engagement surfaces
- units
- 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
- 230000007704 transition Effects 0.000 claims abstract description 20
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 4
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 2
- 239000000314 lubricant Substances 0.000 claims description 2
- 239000002184 metal Substances 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 229910052759 nickel Inorganic materials 0.000 claims description 2
- 238000005096 rolling process Methods 0.000 claims description 2
- 238000007493 shaping process Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 4
- 230000002093 peripheral effect Effects 0.000 description 4
- 230000000295 complement effect Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
-
- 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
- F16B2200/50—Flanged connections
- F16B2200/509—Flanged connections clamped
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T403/00—Joints and connections
- Y10T403/76—Joints and connections having a cam, wedge, or tapered portion
Definitions
- This invention relates to a clamping ring for connecting cylindrical units of missiles, which have each a circumferential projection having an outer contour and a flat-conical engagement surface.
- the clamping ring comprises: a circumferential portion bent substantially to a arc of a circle and having an inner and an outer surface, a first and a second front surface, a first and a second end and two rims; clamping means adapted to act on said first and second end of said circumferential portion in order to tighten said ends; a central area having an inner surface and an outer surface; a first and a second cheek extending along said rims and having flat-conical engagement surfaces corresponding to said flat-conical engagement surfaces of said circumferential projections of said cylindrical units to be connected, transitions being defined between said central area and said engagement surfaces of said cheeks; wherein: said clamping ring extends with said cheeks over said circumferential projections of said units; and said engagement surfaces of said clamping ring engage said engagement surfaces of said circumferential projections of
- Target-tracking missiles consist of a plurality of substantially tubular or cylindrical units, for example a seeker head, the electronical unit, the warhead and the driving mechanism. Such units are interconnected by means of clamping rings.
- the clamping rings are elements, which are bent approximately to an arc of a circle.
- the ends of the clamping ring are tightened in circumferential direction by means of a turnbuckle.
- the clamping ring has cheeks along its rims. The cheeks extend inwards and the clamping ring extend with these cheeks over circumferential projections of the units to be interconnected. When the clamping ring is tightened, these circumferential projections are pulled together and attached to each other.
- the two cheeks of the clamping ring have flat-conical engagement surfaces on the inner sides facing each other. These engagement surfaces of the cheeks engage engagement surfaces on the circumferential projections provided at the units. These engagement surfaces of the circumferential projections are flat-conical corresponding to the engagement surfaces of the cheeks.
- the circumferential projections of the units engage each other with their front surfaces.
- the ends of the units can be inserted into each other.
- the circumferential projections on the units to be interconnected can have cylindrical peripheral surfaces having different radii.
- a cylindrical peripheral surface can, for example, be connected to the front surface of the circumferential projection by means of a conical surface.
- the circumferential projections can be provided at sections, which are displaced radially inwards relative to the cylindrical peripheral surface of the unit, such that the clamping ring extending over the projections does not substantially project beyond the peripheral surface of the missile. This is desired for aerodynamical reasons.
- the cheeks of the clamping ring can project differently far inwards relative to the central area of the clamping ring.
- a prior art clamping ring of the type mentioned above is shaped such that, taken all tolerances of the units into consideration, the maximum outer diameter of a circumferential projection of a unit is substantially larger than the corresponding inner diameter of the clamping ring.
- the inner surface of the central area of the clamping ring does not at any place positively engage the outer surface of a circumferential projection formed on the units.
- the object of the present invention is to increase the strength of the clamping ring, taking the available space for the clamping ring into consideration, particularly the radial dimensions of the clamping ring.
- the outer surface of the clamping ring has a substantially cylindrical section in the central area and substantially conical sections in the area of the cheeks, the transition between the cylindrical section and the conical sections being rounded.
- the invention is particularly based on the discovery, that overload of the clamping ring can occur in the edges on the inside between the central area of the clamping ring and the cheeks. There, the radius of curvature is small and, thus, the stresses in the material are high there.
- the inner surface of the central area is, in fact, guided as tightly as possible around the outer contours of the circumferential projections of the units, but the inner surface is smooth and continuous without edges.
- the thickness of the clamping ring is made as large as possible, and, on the other hand, steps and edges are avoided, at which small radii of curvature and high material stresses can occur.
- rounded circumferential recesses are provided between the central area and the cheeks. This leads to removal of material, but the radius of curvature is increased. This reduces the specific material stresses.
- the outer surface of the clamping ring has a substantially cylindrical section in the central area. From this section the outer surface continuous in a rounded manner in a substantially conical section, which extends inwards to the radial front surface of the clamping ring.
- the outer contour of the clamping ring extends outside the outer contour of prior art clamping rings. This results in increase of the strength, without exceeding the allowed radial maximum dimensions of the clamping ring.
- FIG. 1 shows a side view of a launcher and a target-tracking missile, individual units of the missile being interconnected by means of clamping rings;
- FIG. 2 is a perspective illustration of a clamping ring
- FIG. 3 shows a broken longitudinal section of adjacent portions of two units of the missile, the circumferential projections engaging each other and being held together by a clamping ring;
- FIG. 4 shows a cross section of the clamping ring, the cross section of a prior art clamping ring being drawn with brocken lines.
- FIG. 1 there is shown a target-tracking missile 10 consisting of cylindrical or tubular units 12 , 14 , 16 , 18 .
- the units 12 , 14 , 16 , 18 are interconnected by means of clamping rings 20 , 22 and 24 .
- the missile 10 is suspended through hangers 26 , 28 , 30 in a launcher 32 . This is known per se and not described in detail herein.
- FIG. 2 there is shown a perspective illustration of a clamping ring, for example the clamping ring 20 .
- the clamping ring 20 has a circumferential portion 34 of approximately circular arc shape.
- the circumferential portion 34 is divided at a location 36 and forms two ends 38 and 40 .
- the two ends 38 and 40 can be tightened against each other by means of a turnbuckle 42 .
- the clamping ring 20 is clamped around the units 12 and 14 to be interconnected.
- the clamping ring 20 has cheeks 44 and 46 projecting inwards and extending along its two rims.
- the cheeks 44 and 46 extend over circumferential projections, which are provided at the units 12 and 14 to be interconnected. This is illustrated in FIG. 3.
- FIG. 3 there are shown adjacent portions of two units 12 and 14 to be interconnected by a clamping ring 20 .
- the outer contour of the unit 12 has a cylindrical section 48 .
- the diameter of this cylindrical section 48 corresponds to the outer diameter of the missile 10 .
- the outer contour of the unit 12 extends inwards forming a cylindrical section 50 .
- the diameter of this cylindrical section 50 is smaller than the diameter of the cylindrical section 48 .
- From this section 48 of reduced diameter a circumferential projection 52 projects outwards.
- the circumferential projection 52 has a flat-conical engagement surface 54 facing the unit 12 .
- a cylindrical circumferential surface 56 is located adjacent to the engagement surface 54 .
- the cylindrical circumferential surface 56 is connected to a radial front surface 60 of the circumferential projection 52 through a conical connection surface 58 . This front surface 60 is here at the same time the front surface of the tubular unit 12 .
- the outer contour of the unit 14 in FIG. 3 likewise has a cylindrical section 62 .
- the diameter of this cylindrical section 62 corresponds to the outer diameter of the missile 10 .
- the outer contour of the unit 14 likewise extends inwards at the end facing the unit 12 and forms a cylindrical section 64 of reduced diameter. From this cylindrical section 64 a circumferential projection 66 projects outwards.
- the circumferential projection 66 has a flat-conical engagement surface 68 adjacent to the cylindrical section 64 .
- the flat-conical engagement surface 68 is inclined to the other side with respect to the inclination of engagement surface 54 .
- the apex of the cone defining the engagement surface 54 is located to the left of the engagement surface 54 towards the unit 12 .
- FIG. 3 the apex of the cone defining the engagement surface 54 is located to the left of the engagement surface 54 towards the unit 12 .
- the apex of the cone defining the engagement surface 68 is located to the right of the engagement surface 68 towards the unit 14 .
- a cylindrical circumferential surface 70 is located adjacent to the engagement surface 68 .
- the cylindrical circumferential surface 70 extends to a radial front surface 72 of the circumferential projection 66 .
- the diameter of the circumferential surface 70 is smaller than the diameter of the circumferential surface 56 .
- the front surfaces 60 and 72 of the circumferential projections 52 and 66 engage each other.
- the unit 14 extends telescopcally with a projection 74 into a bore 76 of the tubular unit 12 .
- This design of the units results in the formation of a kind of a circumferential groove 78 between the units 12 and 14 , which is limited by the radial annular surfaces 80 and 82 and the cylindrical sections 50 and 64 and into which the circumferential projections 52 and 66 extend.
- the clamping ring 20 is located in this circumferential groove 78 .
- the clamping ring 20 extends with the cheeks 44 and 46 over the circumferential projections 52 and 66 and tightens the two units 12 and 14 together.
- the clamping ring 20 should as far as possible be accommodated in this “circumferential groove” 78 . It should not extend more than a certain extent beyond the cylindrical outer contour of the missile 10 . This limits the radial dimensions of the clamping ring 20 .
- the clamping ring 20 has a central area 84 and cheeks 44 and 46 extending inwards along the rims of the clamping ring 20 .
- the cheek 44 has a flat-conical engagement surface 86 complementary to the engagement surface 54 of the circumferential projection 52 .
- the cheek 46 has a flat-conical engagement surface 88 complementary to the engagement surface 68 of the circumferential projection 66 .
- the inner surface 90 of the central area 84 of the clamping ring 20 is free from edges and guided tightly about the outer contour of the circumferential projections 52 and 66 of the units. At the described outer contour of the circumferential projections 52 and 66 the inner surface 90 has, adjacent to the cheek 44 , a substantially cylindrical section 94 .
- the section 94 extends approximately to the central plane 95 of the clamping ring 20 . Tangentially adacent thereto there is a slightly concave section 96 , which passes into the inner surface of the cheek 46 . In order to achieve larger transition radii, rounded circumferential recesses 98 and 100 , respectively, are provided at the transitions between this inner surface 90 free from edges and the engagement surfaces 86 and 88 of the cheeks 44 and 46 , respectively, of the clamping ring 20 .
- FIG. 4 there are shown the contours of the clamping ring 20 and the contours of a prior art clamping ring drawn with broken lines.
- the inner surface 102 of the prior art clamping ring is continuously cylindrical over the total width of the central area.
- Edges 108 and 110 respectively, having a relatively small radius of curvature are formed between the engagement surfaces 104 and 106 of the cheeks 44 and 46 , respectively, and the continuously cylindrical inner surface 102 .
- the clamping ring 20 is thickened towards the cheek 46 beyond the cylindrical surface 102 . This results in a more continuous transition to the engagement surface 88 , the radius of curvature being additionally increased by the circumferential recess 100 .
- the radius of curvature between the inner surface 90 and the engagement surface 86 is increased in the same way. Due to the thickening of the clamping ring 20 towards the cheek 46 , the space between the clamping ring 20 and the contour of the circumferential projections 52 , 66 is optimally used for reinforcement of the clamping ring 20 , without edges being formed at the inner surface as it is the case in another prior art embodiment of the clamping ring, in which the inner surface is stepped according to the contours of the circumferential projections.
- the clamping ring 20 has a substantially cylindrical section 112 in the central area 84 .
- the diameter of the cylindrical section 112 corresponds to the allowed maximum diameter of the clamping ring 20 .
- the cylindrical section 112 extends almost over the total central area of the clamping ring 20 .
- Adjacent thereto in the area of the cheeks 44 and 46 , the outer surface of the clamping ring 20 has convex transition surfaces 114 and 116 , respectively, which pass tangentially into the cylindrical section 112
- the convex transition surfaces 114 and 116 then pass into approximately conical sections 118 and 120 , respectively.
- the sections 118 and 120 end in radial front surfaces 122 and 124 of the cheeks 44 and 46 , respectively.
- the outer contour of the clamping ring 20 extends beyond the outer contour 126 of the prior art clamping ring.
- the cross-section of this outer contour 126 is continuously convex and approximately shaped as an arc of a circle.
- the clamping ring 20 is additionally reinforced in the area of the critical transition between the central area 84 and the cheeks 44 and 46 , without the allowed maximum diameter of the clamping ring 20 being exceeded.
- the inner diameter of the cylindrical section 94 of the inner surface 90 of the clamping ring 20 is manufactured with such tolerances with respect to the outer diameter of the adjacent circumferential projection 52 , that clamping between the clamping ring 20 and the circumferential projection 52 is only just effected with the smallest outer diameter of the circumferential projection 52 and the largest inner diameter of the inner surface 90 of the clamping ring 20 .
- neither the inner diameter of the clamping ring 20 is substantially smaller than the outer diameter of the section 56 , as it is the case in the above mentioned prior art clamping ring, nor the inner diameter of the clamping ring is substantially larger than the outer diameter of the section 56 of the outer contour as in another prior art embodiment.
- transition radii can be cold-worked by chasing or rolling. This results in intentional stresses in the transition areas between the inner surface 90 and the engagement surfaces 86 and 88 , which counteract the bending stresses when the missile and the clamping ring 20 are loaded.
- the clamping ring can be manufactured as cast part.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Clamps And Clips (AREA)
Abstract
The invention relates to a clamping ring for connecting cylindrical units of a missile, which have each a circumferential projection and a flat-conical engagement surface. The clamping ring comprises a circumferential portion bent to a arc of a circle and having two ends, which can be tightened together by means of a turnbuckle. The clamping ring has cheeks along its rims. The cheeks have flat-conical engagement surfaces corresponding to the flat-conical engagement surfaces of the circumferential projections of the cylindrical units to be connected. The clamping ring extends with the cheeks over the circumferential projections of the units. In order to increase the strength of the clamping ring by suitable shaping within a predetermined space, the inner surface of the clamping ring is free from edges and guided tightly about the outer contours of the circumferential projections. Rounded circumferential recesses are provided at the transitions between this inner surface free from edges and the engagement surfaces of the cheeks in order to achieve large transition radii. The outer surface of the clamping ring has a cylindrical section and substantially conical sections in the area of the cheeks, the transition between the cylindrical section and the conical sections being rounded.
Description
- This invention relates to a clamping ring for connecting cylindrical units of missiles, which have each a circumferential projection having an outer contour and a flat-conical engagement surface. The clamping ring comprises: a circumferential portion bent substantially to a arc of a circle and having an inner and an outer surface, a first and a second front surface, a first and a second end and two rims; clamping means adapted to act on said first and second end of said circumferential portion in order to tighten said ends; a central area having an inner surface and an outer surface; a first and a second cheek extending along said rims and having flat-conical engagement surfaces corresponding to said flat-conical engagement surfaces of said circumferential projections of said cylindrical units to be connected, transitions being defined between said central area and said engagement surfaces of said cheeks; wherein: said clamping ring extends with said cheeks over said circumferential projections of said units; and said engagement surfaces of said clamping ring engage said engagement surfaces of said circumferential projections of said cylindrical units when said clamping ring is tightened.
- Target-tracking missiles consist of a plurality of substantially tubular or cylindrical units, for example a seeker head, the electronical unit, the warhead and the driving mechanism. Such units are interconnected by means of clamping rings. The clamping rings are elements, which are bent approximately to an arc of a circle. The ends of the clamping ring are tightened in circumferential direction by means of a turnbuckle. At its inner side the clamping ring has cheeks along its rims. The cheeks extend inwards and the clamping ring extend with these cheeks over circumferential projections of the units to be interconnected. When the clamping ring is tightened, these circumferential projections are pulled together and attached to each other. For this purpose, the two cheeks of the clamping ring have flat-conical engagement surfaces on the inner sides facing each other. These engagement surfaces of the cheeks engage engagement surfaces on the circumferential projections provided at the units. These engagement surfaces of the circumferential projections are flat-conical corresponding to the engagement surfaces of the cheeks.
- Usually the circumferential projections of the units engage each other with their front surfaces. The ends of the units can be inserted into each other. The circumferential projections on the units to be interconnected can have cylindrical peripheral surfaces having different radii. A cylindrical peripheral surface can, for example, be connected to the front surface of the circumferential projection by means of a conical surface. The circumferential projections can be provided at sections, which are displaced radially inwards relative to the cylindrical peripheral surface of the unit, such that the clamping ring extending over the projections does not substantially project beyond the peripheral surface of the missile. This is desired for aerodynamical reasons. The cheeks of the clamping ring can project differently far inwards relative to the central area of the clamping ring.
- A prior art clamping ring of the type mentioned above is shaped such that, taken all tolerances of the units into consideration, the maximum outer diameter of a circumferential projection of a unit is substantially larger than the corresponding inner diameter of the clamping ring. Thus, when the clamping ring is tightened by means of a turnbuckle, the inner surface of the central area of the clamping ring does not at any place positively engage the outer surface of a circumferential projection formed on the units.
- In practice it has been found, that the prior art clamping rings can break under loads occuring in practice. This can lead to serious consequences. It is not possible just to reinforce the clamping rings because of constuctive requirements, for example the shape of the circumferential projections of the units to be interconnected and the radially allowed maximum dimensions of the clamping rings.
- The object of the present invention is to increase the strength of the clamping ring, taking the available space for the clamping ring into consideration, particularly the radial dimensions of the clamping ring.
- According to the invention this is achieved in that the inner surface of the central area of the clamping ring is free from edges and guided tightly about the outer contours of the circumferential projections of the units, and rounded circumferential recesses are provided at the transitions between the inner surface of the central area and the engagement surfaces of the cheeks of the clamping ring in order to achieve large transition radii.
- Preferably the outer surface of the clamping ring has a substantially cylindrical section in the central area and substantially conical sections in the area of the cheeks, the transition between the cylindrical section and the conical sections being rounded.
- The invention is particularly based on the discovery, that overload of the clamping ring can occur in the edges on the inside between the central area of the clamping ring and the cheeks. There, the radius of curvature is small and, thus, the stresses in the material are high there. According to the present invention the inner surface of the central area is, in fact, guided as tightly as possible around the outer contours of the circumferential projections of the units, but the inner surface is smooth and continuous without edges. Thus, at one hand, the thickness of the clamping ring is made as large as possible, and, on the other hand, steps and edges are avoided, at which small radii of curvature and high material stresses can occur. Furthermore, rounded circumferential recesses are provided between the central area and the cheeks. This leads to removal of material, but the radius of curvature is increased. This reduces the specific material stresses.
- In order to increase the thickness of the clamping ring without exceeding the allowed radial dimensions, in a preferred embodiment of the clamping ring the outer surface of the clamping ring has a substantially cylindrical section in the central area. From this section the outer surface continuous in a rounded manner in a substantially conical section, which extends inwards to the radial front surface of the clamping ring. Thus, the outer contour of the clamping ring extends outside the outer contour of prior art clamping rings. This results in increase of the strength, without exceeding the allowed radial maximum dimensions of the clamping ring.
- It has been shown, that the combination of the features of the invention leads to a considerable increase of the strength of the clamping ring. The dimensions of the clamping ring according to the present invention are such, that this clamping ring can be used instead of prior art clamping rings. Missiles can be retrofitted with the clamping rings according to the present invention without change in their design.
- Further objects and features of the invention will be apparent to a person skilled in the art from the following specification of a preferred embodiment when read in conjunction with the appended claims.
- The invention and its mode of operation will be more clearly understood from the following detailed description when read with the appended drawing in which:
- FIG. 1 shows a side view of a launcher and a target-tracking missile, individual units of the missile being interconnected by means of clamping rings;
- FIG. 2 is a perspective illustration of a clamping ring;
- FIG. 3 shows a broken longitudinal section of adjacent portions of two units of the missile, the circumferential projections engaging each other and being held together by a clamping ring; and
- FIG. 4 shows a cross section of the clamping ring, the cross section of a prior art clamping ring being drawn with brocken lines.
- Referring now to FIG. 1, there is shown a target-
tracking missile 10 consisting of cylindrical ortubular units units clamping rings missile 10 is suspended throughhangers launcher 32. This is known per se and not described in detail herein. - With reference to FIG. 2, there is shown a perspective illustration of a clamping ring, for example the
clamping ring 20. Theclamping ring 20 has acircumferential portion 34 of approximately circular arc shape. Thecircumferential portion 34 is divided at alocation 36 and forms twoends turnbuckle 42. By this theclamping ring 20 is clamped around theunits clamping ring 20 hascheeks cheeks units - With reference to FIG. 3, there are shown adjacent portions of two
units clamping ring 20. The outer contour of theunit 12 has acylindrical section 48. The diameter of thiscylindrical section 48 corresponds to the outer diameter of themissile 10. At the end of theunit 12 facing theadjacent unit 14 the outer contour of theunit 12 extends inwards forming acylindrical section 50. The diameter of thiscylindrical section 50 is smaller than the diameter of thecylindrical section 48. From thissection 48 of reduced diameter acircumferential projection 52 projects outwards. Thecircumferential projection 52 has a flat-conical engagement surface 54 facing theunit 12. A cylindricalcircumferential surface 56 is located adjacent to theengagement surface 54. The cylindricalcircumferential surface 56 is connected to a radialfront surface 60 of thecircumferential projection 52 through aconical connection surface 58. Thisfront surface 60 is here at the same time the front surface of thetubular unit 12. - The outer contour of the
unit 14 in FIG. 3 likewise has acylindrical section 62. The diameter of thiscylindrical section 62 corresponds to the outer diameter of themissile 10. The outer contour of theunit 14 likewise extends inwards at the end facing theunit 12 and forms acylindrical section 64 of reduced diameter. From this cylindrical section 64 acircumferential projection 66 projects outwards. Thecircumferential projection 66 has a flat-conical engagement surface 68 adjacent to thecylindrical section 64. The flat-conical engagement surface 68 is inclined to the other side with respect to the inclination ofengagement surface 54. In FIG. 3 the apex of the cone defining theengagement surface 54 is located to the left of theengagement surface 54 towards theunit 12. In FIG. 3 the apex of the cone defining theengagement surface 68 is located to the right of theengagement surface 68 towards theunit 14. A cylindrical circumferential surface 70 is located adjacent to theengagement surface 68. The cylindrical circumferential surface 70 extends to a radialfront surface 72 of thecircumferential projection 66. The diameter of the circumferential surface 70 is smaller than the diameter of thecircumferential surface 56. The front surfaces 60 and 72 of thecircumferential projections - In the arrangement of FIG. 3 the
unit 14 extends telescopcally with aprojection 74 into abore 76 of thetubular unit 12. - This design of the units results in the formation of a kind of a
circumferential groove 78 between theunits annular surfaces cylindrical sections circumferential projections ring 20 is located in thiscircumferential groove 78. The clampingring 20 extends with thecheeks circumferential projections units ring 20 should as far as possible be accommodated in this “circumferential groove” 78. It should not extend more than a certain extent beyond the cylindrical outer contour of themissile 10. This limits the radial dimensions of the clampingring 20. - As best can be seen in FIG. 4, the clamping
ring 20 has acentral area 84 andcheeks ring 20. Thecheek 44 has a flat-conical engagement surface 86 complementary to theengagement surface 54 of thecircumferential projection 52. Thecheek 46 has a flat-conical engagement surface 88 complementary to theengagement surface 68 of thecircumferential projection 66. Theinner surface 90 of thecentral area 84 of the clampingring 20 is free from edges and guided tightly about the outer contour of thecircumferential projections circumferential projections inner surface 90 has, adjacent to thecheek 44, a substantiallycylindrical section 94. Thesection 94 extends approximately to thecentral plane 95 of the clampingring 20. Tangentially adacent thereto there is a slightlyconcave section 96, which passes into the inner surface of thecheek 46. In order to achieve larger transition radii, roundedcircumferential recesses inner surface 90 free from edges and the engagement surfaces 86 and 88 of thecheeks ring 20. - With reference to FIG. 4, there are shown the contours of the clamping
ring 20 and the contours of a prior art clamping ring drawn with broken lines. Theinner surface 102 of the prior art clamping ring is continuously cylindrical over the total width of the central area.Edges cheeks inner surface 102. Compared hereto, the clampingring 20 is thickened towards thecheek 46 beyond thecylindrical surface 102. This results in a more continuous transition to theengagement surface 88, the radius of curvature being additionally increased by thecircumferential recess 100. The radius of curvature between theinner surface 90 and theengagement surface 86 is increased in the same way. Due to the thickening of the clampingring 20 towards thecheek 46, the space between the clampingring 20 and the contour of thecircumferential projections ring 20, without edges being formed at the inner surface as it is the case in another prior art embodiment of the clamping ring, in which the inner surface is stepped according to the contours of the circumferential projections. - At the outside the clamping
ring 20 has a substantiallycylindrical section 112 in thecentral area 84. The diameter of thecylindrical section 112 corresponds to the allowed maximum diameter of the clampingring 20. Thecylindrical section 112 extends almost over the total central area of the clampingring 20. Adjacent thereto in the area of thecheeks ring 20 has convex transition surfaces 114 and 116, respectively, which pass tangentially into thecylindrical section 112 The convex transition surfaces 114 and 116 then pass into approximatelyconical sections sections cheeks - As can be seen from FIG. 4, the outer contour of the clamping
ring 20 extends beyond theouter contour 126 of the prior art clamping ring. The cross-section of thisouter contour 126 is continuously convex and approximately shaped as an arc of a circle. In this manner, the clampingring 20 is additionally reinforced in the area of the critical transition between thecentral area 84 and thecheeks ring 20 being exceeded. - The inner diameter of the
cylindrical section 94 of theinner surface 90 of the clampingring 20 is manufactured with such tolerances with respect to the outer diameter of the adjacentcircumferential projection 52, that clamping between the clampingring 20 and thecircumferential projection 52 is only just effected with the smallest outer diameter of thecircumferential projection 52 and the largest inner diameter of theinner surface 90 of the clampingring 20. Thus, neither the inner diameter of the clampingring 20 is substantially smaller than the outer diameter of thesection 56, as it is the case in the above mentioned prior art clamping ring, nor the inner diameter of the clamping ring is substantially larger than the outer diameter of thesection 56 of the outer contour as in another prior art embodiment. Thus, at one hand, problems with the fitting and engagement of the clamping ring are avoided and, at the other hand, the available space is optimally used for reinforcement of the clamping ring. - The transition radii can be cold-worked by chasing or rolling. This results in intentional stresses in the transition areas between the
inner surface 90 and the engagement surfaces 86 and 88, which counteract the bending stresses when the missile and the clampingring 20 are loaded. - The clamping ring can be manufactured as cast part.
- Furthermore, it is advantageous to provide the engagement surfaces with a dry-film lubricant. However, also a metal layer, preferably of chrome or nickel, can be provided at the engagement surfaces.
Claims (8)
1. A clamping ring for connecting cylindrical units of a missile, which have each a circumferential projection having an outer contour and a flat-conical engagement surface, said clamping ring comprising:
a circumferential portion bent substantially to a arc of a circle and having an inner and an outer surface, a first and a second front surface, a first and a second end and two rims;
clamping means adapted to act on said first and second end of said circumferential portion in order to tighten said ends;
a central area having an inner surface and an outer surface;
a first and a second cheek extending along said rims and having flat-conical engagement surfaces corresponding to said flat-conical engagement surfaces of said circumferential projections of said cylindrical units to be connected, transitions being defined between said central area and said engagement surfaces of said cheeks;
wherein:
said clamping ring extends with said cheeks over said circumferential projections of said units;
said engagement surfaces of said clamping ring engage said engagement surfaces of said circumferential projections of said cylindrical units when said clamping ring is tightened;
said inner surface of said central area of said clamping ring is free from edges and guided tightly about said outer contours of said circumferential projections of said units; and
rounded circumferential recesses are provided at said transitions between said inner surface of said central area and said engagement surfaces of said cheeks of said clamping ring in order to achieve large transition radii.
2. The clamping ring of claim 1 , wherein said outer surface of said clamping ring has a substantially cylindrical section in said central area and substantially conical sections in the area of said cheeks, the transition between said cylindrical section and said conical sections being rounded.
3. The clamping ring of claim 1 , wherein said inner surface of said central area of said clamping ring, adjacent to said first cheek of said clamping ring, has a substantially cylindrical section in the area of a largest diameter of said adjacent circumferential projection of said unit, and a substantially flat-conical section adjacent to said cylindrical section.
4. The clamping ring of claim 3 , wherein the inner diameter of said cylindrical section of said inner surface is manufactured with such tolerances with respect to the outer diameter of said adjacent circumferential projection, that clamping between said clamping ring and said circumferential projection is only just effected with the smallest outer diameter of said circumferential projection and the largest inner diameter of said central area of said clamping ring.
5. The clamping ring of claim 1 , wherein said transition radii are cold-worked by chasing or rolling.
6. The clamping ring of claim 1 , wherein said clamping ring is manufactured as cast part.
7. The clamping ring of claim 1 , wherein said engagement surfaces of said clamping ring are provided with a dry-film lubricant.
8. The clamping ring of claim 1 , wherein said engagement surfaces of said clamping ring are provided with a metal layer, preferably of chrome or nickel
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/943,519 US6371684B2 (en) | 1997-02-14 | 2001-08-30 | Clamping ring for connecting cylindrical units of missiles |
Applications Claiming Priority (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19705712A DE19705712A1 (en) | 1997-02-14 | 1997-02-14 | Tension ring for connecting cylindrical assemblies of missiles |
DE19705712.8 | 1997-02-14 | ||
DE19705712 | 1997-02-14 | ||
US2124898A | 1998-02-10 | 1998-02-10 | |
US09/769,040 US20010009634A1 (en) | 1997-02-14 | 2001-01-24 | Clamping ring for connecting cylindrical units of missiles |
US09/943,519 US6371684B2 (en) | 1997-02-14 | 2001-08-30 | Clamping ring for connecting cylindrical units of missiles |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/769,040 Continuation US20010009634A1 (en) | 1997-02-14 | 2001-01-24 | Clamping ring for connecting cylindrical units of missiles |
Publications (2)
Publication Number | Publication Date |
---|---|
US20020003984A1 true US20020003984A1 (en) | 2002-01-10 |
US6371684B2 US6371684B2 (en) | 2002-04-16 |
Family
ID=7820275
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/769,040 Abandoned US20010009634A1 (en) | 1997-02-14 | 2001-01-24 | Clamping ring for connecting cylindrical units of missiles |
US09/943,519 Expired - Fee Related US6371684B2 (en) | 1997-02-14 | 2001-08-30 | Clamping ring for connecting cylindrical units of missiles |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/769,040 Abandoned US20010009634A1 (en) | 1997-02-14 | 2001-01-24 | Clamping ring for connecting cylindrical units of missiles |
Country Status (3)
Country | Link |
---|---|
US (2) | US20010009634A1 (en) |
EP (1) | EP0859212B1 (en) |
DE (2) | DE19705712A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150048212A1 (en) * | 2013-08-19 | 2015-02-19 | The Boeing Company | Unsteady aerodynamics mitigation for multi-body aerospace apparatus |
USD977044S1 (en) | 2020-05-11 | 2023-01-31 | Gary Kemp | Inflatable zeotrope ball |
Families Citing this family (12)
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US6498561B2 (en) * | 2001-01-26 | 2002-12-24 | Cornerstone Sensors, Inc. | Thermistor and method of manufacture |
US6672537B1 (en) * | 2002-08-14 | 2004-01-06 | The United States Of America As Represented By The Secretary Of The Navy | One-piece wrap around fin |
WO2005094295A2 (en) | 2004-03-26 | 2005-10-13 | Victaulic Company Of America | Pipe coupling having keys with camming surfaces |
DE102005031832B4 (en) * | 2005-07-06 | 2007-09-06 | Visteon Global Technologies Inc., Van Buren | Clamped shaft-hub connection with real cone |
DE102007014013B4 (en) * | 2007-03-23 | 2008-12-11 | Diehl Bgt Defence Gmbh & Co. Kg | Missiles adapter ring |
US8607705B2 (en) | 2010-12-06 | 2013-12-17 | Systima Technologies Inc. | Low shock rocket body separation |
US20130125373A1 (en) | 2011-11-21 | 2013-05-23 | Philip W. Bancroft | Coupling with projections having angularly oriented surface portions |
SE540399C2 (en) * | 2016-04-20 | 2018-09-11 | Bae Systems Bofors Ab | Support device for divisible parachute grenade |
SE541612C2 (en) * | 2016-09-15 | 2019-11-12 | Bae Systems Bofors Ab | Modifiable divisible projectile and method for modifying a projectile |
US10920811B2 (en) | 2018-02-15 | 2021-02-16 | Raytheon Company | Component assembly for high-precision joining of components |
US11530767B2 (en) * | 2019-07-17 | 2022-12-20 | L3Harris Technologies, Inc. | Tool-less joiner clamp |
US11548171B2 (en) * | 2019-10-30 | 2023-01-10 | Industrial Technology Research Institute | Robot arm, mechanical assembly and assembly method thereof |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2809584A (en) * | 1953-04-01 | 1957-10-15 | Smith Bernard | Connector ring for two stage rockets |
US3215082A (en) * | 1962-09-24 | 1965-11-02 | Aerojet General Co | Rapid release device for connecting rocket stages |
US3193129A (en) * | 1963-01-31 | 1965-07-06 | Berkefeld Filter Ges Und Celle | Multiple section container |
US3286630A (en) | 1965-05-04 | 1966-11-22 | Salmirs Seymour | Spacecraft separation system for spinning vehicles and/or payloads |
GB1249499A (en) | 1969-04-29 | 1971-10-13 | Avica Equip | Improvements in and relating to circular clamps |
US4008937A (en) * | 1974-09-20 | 1977-02-22 | Stanley Aviation Corporation | Coupling assembly |
DE3028609A1 (en) * | 1980-07-28 | 1982-02-25 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | Missile body securing strap - has beaded edges locking into grooved ends of body parts when tensioned by end fittings |
US5018768A (en) | 1990-07-19 | 1991-05-28 | Quikcoup, Incorporated | Pipe coupling hinge |
US5286135A (en) * | 1990-09-28 | 1994-02-15 | Martin Marietta Corporation | Joinder of separable tubular structures utilizing preloaded O-ring |
FR2674892B1 (en) * | 1991-04-02 | 1993-08-06 | Pomagalski Sa | TOOL AND METHOD FOR MOUNTING TWO ELEMENTS OF A PYLON. |
US5188400A (en) * | 1991-09-17 | 1993-02-23 | Stanley Aviation Corporation | Spring loaded coupling with positive spring latch |
US5540465A (en) | 1994-08-01 | 1996-07-30 | Sisk; David E. | Pipe, valve and/or tee coupler |
DE19534437C2 (en) | 1995-09-16 | 2000-09-21 | Daimler Chrysler Ag | Clamp for connecting two tubular line parts |
US5708232A (en) | 1996-10-10 | 1998-01-13 | The United States Of America As Represented By The Secretary Of The Navy | Highly maneuverable underwater vehicle |
-
1997
- 1997-02-14 DE DE19705712A patent/DE19705712A1/en not_active Withdrawn
-
1998
- 1998-01-23 DE DE59804615T patent/DE59804615D1/en not_active Expired - Lifetime
- 1998-01-23 EP EP98101114A patent/EP0859212B1/en not_active Expired - Lifetime
-
2001
- 2001-01-24 US US09/769,040 patent/US20010009634A1/en not_active Abandoned
- 2001-08-30 US US09/943,519 patent/US6371684B2/en not_active Expired - Fee Related
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150048212A1 (en) * | 2013-08-19 | 2015-02-19 | The Boeing Company | Unsteady aerodynamics mitigation for multi-body aerospace apparatus |
USD977044S1 (en) | 2020-05-11 | 2023-01-31 | Gary Kemp | Inflatable zeotrope ball |
Also Published As
Publication number | Publication date |
---|---|
DE19705712A1 (en) | 1998-08-20 |
EP0859212A2 (en) | 1998-08-19 |
EP0859212B1 (en) | 2002-07-03 |
EP0859212A3 (en) | 2000-04-26 |
US6371684B2 (en) | 2002-04-16 |
DE59804615D1 (en) | 2002-08-08 |
US20010009634A1 (en) | 2001-07-26 |
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