US3515006A - Spring pivots - Google Patents

Spring pivots Download PDF

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Publication number
US3515006A
US3515006A US529751A US3515006DA US3515006A US 3515006 A US3515006 A US 3515006A US 529751 A US529751 A US 529751A US 3515006D A US3515006D A US 3515006DA US 3515006 A US3515006 A US 3515006A
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United States
Prior art keywords
portions
spring
members
rotor
slot
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 - Lifetime
Application number
US529751A
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English (en)
Inventor
Ivan Alfred Duck
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SG Brown Ltd
Original Assignee
Brown Ltd S G
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from GB803065A external-priority patent/GB1142846A/en
Priority claimed from GB4716265A external-priority patent/GB1142847A/en
Application filed by Brown Ltd S G filed Critical Brown Ltd S G
Application granted granted Critical
Publication of US3515006A publication Critical patent/US3515006A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
    • G01C19/02—Rotary gyroscopes
    • G01C19/04—Details
    • G01C19/16—Suspensions; Bearings
    • G01C19/22—Suspensions; Bearings torsional
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C11/00—Pivots; Pivotal connections
    • F16C11/04—Pivotal connections
    • F16C11/12—Pivotal connections incorporating flexible connections, e.g. leaf springs
    • 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
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/30—Flywheels
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2370/00—Apparatus relating to physics, e.g. instruments
    • 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
    • Y10T74/00—Machine element or mechanism
    • Y10T74/12—Gyroscopes
    • Y10T74/1293—Flexure hinges for gyros

Definitions

  • each of said pivots comprise a pair of spring strips which cross on the pivot axis and extend across a gap separating the parts.
  • the strips are secured between the parts and overlying clamping elements.
  • the effective dimension of each strip can be accurately determined by removal of material from the elements before insertion of the strips, to align edges of the elements with the sides of the gap.
  • the elements can be angle strips secured to tapered faces of the parts adjacent the gap and divided as part of the edge adjustment step.
  • the gap can be a slot formed in a single piece of metal wherein the slot is extended after securement of the spring strips to divide the piece into the parts.
  • the invention relates to flexural spring pivots for use where great precision is essential, for example, in gyroscopes.
  • the invention also relates to gyro rotor assemblies incorporating the flexural spring pivot-s.
  • a gyroscope rotor should ideally be mounted in such a way that any kind of twisting or translation of its housing or other support has no disturbing effect on the orientation of the rotation axis of the rotor.
  • In practice there are obvious difficulties in supporting a mass and applying a rotational drive to it without such disturbances being applied.
  • an article in Control Engineering, June 1964 by Edwin W. Howe and Paul H.'Savet entitled, The Dynamically Tuned Free Rotor Gyro there is explained the basis of a suspension arrangement for a gyro rotor by which the rotor is theoretically decoupled from its suspension.
  • the arrangement proposed employs a gimbal ring between a shaft to which a rotational drive is applied and an annular mass constituting the gyro rotor.
  • the motor is carried by the housing and any radial unbalances are averaged out each rotation.
  • the inertial effects of the gimbal ring on the rotor act as a dynamic negative spring restraint, tending to cause a conical precession of the spin axis in the same direction as the direction of rotation of the rotor; the magnitude of this dynamic restraint increases with increase of rotor speed.
  • spring suspensions can be made with a positive spring restraint, which would cause a conical precession of the spin axis in the direction opposite to that of the rotor.
  • spring suspensions can be made to cancel one another and the precessional period can be brought theoretically to infinity.
  • pairs of flexural spring pivots have to be secured on orthogonal diameters between the rotor and the gimbal ring and the gimbal ring and the shaft respectively.
  • the machining and assembly of the various parts is required to be very accurate as even an extremely small misalignment between the pairs of pivots would introduce abnormal stresses in the flexural springs, which would confer undesirable nonlinear performance characteristics to the gyro.
  • the invention thus has as a major object the provision of an assembly incorporating an advantageous form of flexural spring pivot arrangement. It is also a major object to provide a convenient method of producing such an assembly. Although particularly applicable to assemblies for use as dynamically tuned free rotor gyros, the invention is not so limited and may be applied in other contexts, for example, to accelerometers.
  • the invention accordingly provides an assembly comprising two portions and flexural spring pivot means extending therebetween, the flexural spring pivot means comprising a plurality of leaf spring members integral with or secured directly to the portions.
  • the invention also provides a gyro rotor assembly comprising an outer portion, surrounding an intermediate portion, an inner portion surrounded by the inter mediate portion, first and second pairs of aligned flexural spring pivot means between the outer and intermediate portions and between the inner and intermediate portions respectively, the axes on which the two pairs of flexural spring pivot means are aligned being perpendicular, and the flexural spring pivot comprising leaf spring members secured directly to the respective portions.
  • the invention also provides a method of producing such assemblies, in which positive location of the portions thereof is assured.
  • the portions may be formed separately and then positioned on a jig or like means, a gap or slot provided between them, the leaf spring members being secured, as by spot Welding, across the slot.
  • the portions may instead be relatively located by forming them from a single piece of material, for example, of beryllium copper. A slot can be made in the piece and the spring pivot means secured across the slot, which is subsequently extended to separate the portions.
  • the outer portion of the gyro rotor assembly is of course employed as the actual rotor, the intermediate portion functioning as a gimbal ring between the rotor and the inner portion by which the assembly is mounted on a driving shaft.
  • FIGS. 1 and 2 are axial and edge views respectively of a disc after the first stage of manufacture of an embodiment of an assembly in accordance with the present invention
  • FIG. 3 is a section on a larger scale on the line IIIIII of FIG. 1;
  • FIGS. 4 and '5 correspond to FIGS. 1 and 3, respectively, but show a second stage of manufacture
  • FIGS. 6 and 7 likewise correspond to FIGS. 1 and 3, a third stage having been performed
  • FIGS. 8 and 9 again correspond to FIGS. 1 and 3, but relate to a fourth stage of manufacture.
  • a single piece of material 10 initially having the form of a flat circular disc is in the process of division into a rotor 12, a gimbal ring 11 and a central mounting piece 16.
  • major portions of inner and outer slots 18 and 20 have been cut through the disc 10, as by engraving.
  • the outer slot 20' has major portions on a circle concentric with the disc 10. These portions are later to be extended by the cutting through of portions 22 which extend at right angles to a diameter of the disc. Portions 28 extending inwardly on this diameter from the uncut portions 22 run into portions parallel to the portions 22,
  • the inner slot 18 also has portions 28 which extend along a diameter at right angles to that previously mentioned and which run into portions extending across this second diameter, the outer two of which, marked 22, are not at this stage cut through.
  • the four portions 28 are equal length and are equally spaced from the disc centre.
  • the major portions of the slot 18 extend parallel to the second diameter, being connected at their ends to the portions transverse to this. Because the two portions 22 have yet to be removed to complete each slot, the disc is still an integral piece.
  • a centre hole 24 for receiving a driving shaft on which the assembly is is to be mounted, and outer holes 26 have also been cut through the disc at this stage. The holes 26 are for the reception of suitable weights.
  • Each of the four portions 28 is to accommodate a pair of strip springs which will constitute the only connections between the rotor 12, the ring 11 and the mounting piece 16.
  • the following description will for convenience refer to only one portion 28 but it will be understood that all four portions are treated similarly, each stage of the operation being preferably preformed on all the portions before the next is begun.
  • the second stage comprises the securement of clamping members 42, 44 to the tapered faces 30, 32, 34 and 36.
  • Each of the clamping members 42, 44 is a length of right-angled metal strip, suitably of stainless steel.
  • the clamping member 42 is secured by spot welding at 46 to the upper face at the outer end, radially of the disc 10, and to the upper face 32 at the inner end by spot welding at 48.
  • the clamping member 44 is spot welded to the lower face 36 at the radially inner end to the lower face 34 at the outer end.
  • the clamping members can be fixed in any suitable Way which leaves at least half of the length of the clamping member unsecured to the tapered faces.
  • the next stage, shown in FIGS. 6 and 7 comprises separation of the two flanges of each of the clamping members 42, 44 by removal, as by engraving, of the centre part of the member forming the right angle bend.
  • the member 42 is thus divided into clamping strips 50 and 52 secured on the faces 30 and 32, respectively, and divides the member 44 into strips 54 and 56 on the faces 34 and 36, respectively.
  • the removal of material is carried outwards from the angle of the members until the newly formed edges of the separated clamping strips are flush with the parallel opposed wall portions 38, of the slot portion 28, as shown in FIG. 7.
  • the spacing of these edges determines the efi ective width of the spring strips, which is crucial to the performance of the assembly. It is the major advantage of the method of the invention that it allows the location of these edges to be determined by removal of portions of fixed clamping members, instead of -by the positioning of a finished member; the former step can be performed with much greater accuracy.
  • Spring 58 is slid between the strip 50 and the face 30, at their radially inner ends, and across the slot portion 28 to enter between the face 34 and the clamping strip 54.
  • the spring 60 is slid between the face 32 and the strip 52, across the slot portion 28 to between the face 36 and the strip 56 at the radially outer ends.
  • the springs are then secured, conveniently again by spot welds, the spring 60 being welded at 62 and the 4 spring 58 being welded at 64; welds are also made at the other side of the disc 10 to hold the springs 58 and 60', respectively, between the strip 54 and the face 34 and be tween the strip 56 on the face 36.
  • the ends of the strip springs 58, 60 are then trimmed off, as by grinding.
  • portions 22 are cut to complete the slots 18 and 20, leaving the rotor 12, the gimbal ring 11 and the mounting portion 16 connected only by the four sets of spring strips 58 and 60.
  • Each clamping strip could of course be a separate member originally, instead of being cut from one flange of an angled strip, before its precisely located edge is formed.
  • the method of the invention can be modified by completing the slots 18 and 20' before the welding operations. The portions are then relatively positioned as shown in the figures by any suitable supporting arrangement, conveniently one employing pins for reception in the holes 24 and 26. It will be appreciated that the advantageous location of the edges determining the effective width of the leaf spring strips by removal of fixed material will still be obtained.
  • each spring leaf should be large but choice is limited by the desirability of a compact arrangement and the need, in the embodiment described, to arrange two springs on each half of a diameter between the two portions they connect. Consequently, a choice is made of a convenient ratio of thickness to length which affords a ratio of flexural stiffness to load carrying capacity which is as low as possible.
  • the gyro rotor assembles can incorporate spring suspension systems which have elastic symmetry, that is, which are isoelastic, or, alternatively, which are nonisoelastic by a selected amount. This condition can be achieved in the embodiment described by altering slightly the angle between the leaves of the spring pairs from the perpendicular arrangement shown.
  • a method of assembling a pair of metal members and at least one metal strip in precisely determined relative positions for the strip to function as a flexural spring pivot between the members comprising the steps of securing to each of the members a metal clamping element with a portion of the element overlying a surface portlon of the member to which the strip is to be secured; removing material from at least one of said clamping elements to determine precisely the position of the adjacent edges thereof; placing the strip between said surface portions of the members and said portions of the clamping elements; and securing together said clamping elements, said metal strip and said members.
  • a method as claimed in claim 1 additionally comprising the steps of providing surface portions of the members by symmetrically tapering the edges, and welding the metal strip and a second metal strip to the tapered edges in cross formation to function as a crossed flexural spring pivot between the members.
  • a method as claimed in claim 2 additionally comprising the steps of welding a pair of angled elements to the surface portions of the members to constitute the clamping elements, and removing material from the angled elements to divide each into the two clamping elements.
  • metal members are initialy integral and additionally comprising the steps of assembling the metal strip across a slot and thereafter extending the slot to separate the members.
  • a method as claimed in claim 2 additionally com prising the steps of securing two further strips to the members in a like manner to function as a second crossed flexural spring pivot means betwen the members and aligning the axes on which the strips of the two spring pivot means are crossed.
  • a gyro rotor assembly comprising a rotor member, a gimbal member; and a mounting member, the rotor member surrounding the gimbal and mounting members; a first pair of aligned flexural spring pivot means connecting the rotor member and the gimbal member; a second pair of aligned flexural spring pivot means connecting the gimbal member and the mounting member, the axes on which the two pairs of flexural spring pivot means are aligned being perpendicular, and each flexural spring pivot means of at least one pair thereof including a pair of spring strips having the edges thereof engaging the connected members; and clamping elements overlying said edges and having portions extending beyond the spring strips, said clamping elements being secured directly to the associated members over such portions, said clamping elements, edges and members being welded together.
  • a method of making a gyro rotor assembly which includes an outer member; a gimbal member; a mounting member; the outer member surrounding the gimbal and mounting members; a first pair of aligned flexural spring pivot means connecting the outer and gimbal members; and a second pair of aligned flexural spring pivot means connecting the gimbal and mounting members respectively, the axes on which the pairs of flexural spring pivot means are aligned being perpendicular, the method comprising the steps of forming slots in a single piece of material at positions relatively spaced to correspond to the desired relative spacing of the flexural spring pivot means; forming each flexural spring pivot means by making a symmetrical taper on both sides of the slot; welding clamping elements to selected tapered faces that each of said clamping elements has a portion overlying its associated tapered face; removing material from the clamping elements to align the edges thereof with the associated edges of the tapered faces; sandwiching a first spring strip between an overlying clamping element and

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • General Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Springs (AREA)
  • Transmission And Conversion Of Sensor Element Output (AREA)
  • Vehicle Body Suspensions (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
US529751A 1965-02-24 1966-02-24 Spring pivots Expired - Lifetime US3515006A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB803065A GB1142846A (en) 1965-02-24 1965-02-24 Improvements in or relating to gyroscope rotors
GB4716265A GB1142847A (en) 1965-11-06 1965-11-06 Improvements in or relating to assembly methods for spring pivots

Publications (1)

Publication Number Publication Date
US3515006A true US3515006A (en) 1970-06-02

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US529751A Expired - Lifetime US3515006A (en) 1965-02-24 1966-02-24 Spring pivots
US758242A Expired - Lifetime US3543301A (en) 1965-02-24 1968-09-09 Spring pivots

Family Applications After (1)

Application Number Title Priority Date Filing Date
US758242A Expired - Lifetime US3543301A (en) 1965-02-24 1968-09-09 Spring pivots

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US (2) US3515006A (enrdf_load_stackoverflow)
CH (1) CH483620A (enrdf_load_stackoverflow)
DE (3) DE1500652A1 (enrdf_load_stackoverflow)
NO (1) NO120906B (enrdf_load_stackoverflow)
SE (1) SE337937B (enrdf_load_stackoverflow)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3678764A (en) * 1967-11-20 1972-07-25 Litton Systems Inc Gyroscope having vibrating gimbals
US3702568A (en) * 1970-07-10 1972-11-14 Edwin W Howe Gyroscopes and suspensions therefor
US4002078A (en) * 1974-02-14 1977-01-11 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Dynamically tuned gyroscopes
US4269072A (en) * 1979-02-14 1981-05-26 Sperry Corporation Flexure assembly for a dynamically tuned gyroscope
US4499778A (en) * 1981-02-03 1985-02-19 Northrop Corporation Flexure mount assembly for a dynamically tuned gyroscope and method of manufacturing same
US4694703A (en) * 1984-06-28 1987-09-22 Lear Siegler, Inc. Circumferentially oriented flexure suspension

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3678765A (en) * 1969-12-15 1972-07-25 Ambac Ind Magnetically-tuned resonant gyroscope
US3754475A (en) * 1972-01-10 1973-08-28 Us Navy Controllable precession gyroscope
US3832906A (en) * 1973-07-30 1974-09-03 Teledyne Ind Gimbal structure for dynamically tuned free rotor gyro
US4100813A (en) * 1976-05-13 1978-07-18 The Singer Company Flexure suspension assembly
US4286370A (en) * 1977-08-05 1981-09-01 Incosym, Inc. Universal joint flexure hinge suspension system, and method for manufacturing this system
GB2063471B (en) * 1979-11-16 1984-02-29 Smiths Industries Ltd Gyroscopes
US4528864A (en) * 1980-05-19 1985-07-16 Incosym, Inc. Universal joint flexure hinge suspension system and method for manufacturing this system
DE3328379A1 (de) * 1983-08-05 1985-02-21 Incosym, Inc., Westlake Village, Calif. Traegheitsinstrument mit becherfoermiger traegheitsmasse
ATE55632T1 (de) * 1987-01-20 1990-09-15 Litef Gmbh Biegefedergelenk und verfahren zu seiner herstellung.
FR2682728B1 (fr) * 1991-10-21 1996-02-09 Sfim Articulation a la cardan plane, procede de realisation, gyroscope et support orientable comportant une telle articulation.
JPH08167348A (ja) * 1994-12-14 1996-06-25 Matsushita Electric Ind Co Ltd 回転操作型電子部品
FR2752023B1 (fr) * 1996-08-02 1998-10-30 Sfim Ind Procede pour la realisation et le montage d'une articulation a la cardan plane
JP4113573B2 (ja) * 1998-05-19 2008-07-09 ジンテーズ ゲゼルシャフト ミト ベシュレンクテル ハフツング ジョイント結合が埋め込まれた骨接合術のインプラント

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2581965A (en) * 1950-09-30 1952-01-08 Honeywell Regulator Co Rate gyroscope
US2797580A (en) * 1955-07-18 1957-07-02 Bosch Arma Corp Gyroscope suspension
US3081552A (en) * 1960-04-20 1963-03-19 Rank Precision Ind Ltd Suspension devices
US3211011A (en) * 1961-08-07 1965-10-12 Gen Precision Inc Inertial compensation mechanism for flexure spring suspended gyro
US3264880A (en) * 1961-12-28 1966-08-09 Gen Precision Inc Gyros with compensated flexure pivots

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3301073A (en) * 1963-06-28 1967-01-31 Bosch Arma Corp Gyroscope apparatus
US3315533A (en) * 1963-12-27 1967-04-25 Gen Precision Inc Quadrature torque compensation for flexure spring suspended gyro

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2581965A (en) * 1950-09-30 1952-01-08 Honeywell Regulator Co Rate gyroscope
US2797580A (en) * 1955-07-18 1957-07-02 Bosch Arma Corp Gyroscope suspension
US3081552A (en) * 1960-04-20 1963-03-19 Rank Precision Ind Ltd Suspension devices
US3211011A (en) * 1961-08-07 1965-10-12 Gen Precision Inc Inertial compensation mechanism for flexure spring suspended gyro
US3264880A (en) * 1961-12-28 1966-08-09 Gen Precision Inc Gyros with compensated flexure pivots

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3678764A (en) * 1967-11-20 1972-07-25 Litton Systems Inc Gyroscope having vibrating gimbals
US3702568A (en) * 1970-07-10 1972-11-14 Edwin W Howe Gyroscopes and suspensions therefor
US4002078A (en) * 1974-02-14 1977-01-11 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Dynamically tuned gyroscopes
US4269072A (en) * 1979-02-14 1981-05-26 Sperry Corporation Flexure assembly for a dynamically tuned gyroscope
US4499778A (en) * 1981-02-03 1985-02-19 Northrop Corporation Flexure mount assembly for a dynamically tuned gyroscope and method of manufacturing same
US4694703A (en) * 1984-06-28 1987-09-22 Lear Siegler, Inc. Circumferentially oriented flexure suspension

Also Published As

Publication number Publication date
CH483620A (de) 1969-12-31
DE1673894A1 (de) 1971-10-21
US3543301A (en) 1970-11-24
DE1673893A1 (de) 1971-07-08
NO120906B (enrdf_load_stackoverflow) 1970-12-21
DE1500652A1 (de) 1969-09-25
SE337937B (enrdf_load_stackoverflow) 1971-08-23

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