USH1384H - Continuous bearing - Google Patents

Continuous bearing Download PDF

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Publication number
USH1384H
USH1384H US06/903,628 US90362886A USH1384H US H1384 H USH1384 H US H1384H US 90362886 A US90362886 A US 90362886A US H1384 H USH1384 H US H1384H
Authority
US
United States
Prior art keywords
ball
ball race
race
balls
bail
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.)
Abandoned
Application number
US06/903,628
Inventor
Steven A. Sievert
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.)
US Department of Navy
Original Assignee
US Department of Navy
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
Application filed by US Department of Navy filed Critical US Department of Navy
Priority to US06/903,628 priority Critical patent/USH1384H/en
Assigned to UNITED STATES OF AMERICA, AS REPRESENTED BY THE SECRETARY OF NAVY, THE reassignment UNITED STATES OF AMERICA, AS REPRESENTED BY THE SECRETARY OF NAVY, THE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: SIEVERT, STEVEN A.
Application granted granted Critical
Publication of USH1384H publication Critical patent/USH1384H/en
Abandoned legal-status Critical Current

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    • 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
    • F16C29/00—Bearings for parts moving only linearly
    • F16C29/04—Ball or roller bearings
    • F16C29/06—Ball or roller bearings in which the rolling bodies circulate partly without carrying load
    • F16C29/0614—Ball or roller bearings in which the rolling bodies circulate partly without carrying load with a shoe type bearing body, e.g. a body facing one side of the guide rail or track only
    • F16C29/0621—Ball or roller bearings in which the rolling bodies circulate partly without carrying load with a shoe type bearing body, e.g. a body facing one side of the guide rail or track only for supporting load in essentially two directions, e.g. by multiple points of contact or two rows of rolling elements
    • F16C29/0623—Ball or roller bearings in which the rolling bodies circulate partly without carrying load with a shoe type bearing body, e.g. a body facing one side of the guide rail or track only for supporting load in essentially two directions, e.g. by multiple points of contact or two rows of rolling elements with balls
    • 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
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/50—Other types of ball or roller bearings
    • F16C19/502—Other types of ball or roller bearings with rolling elements in rows not forming a full circle
    • 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
    • F16C29/00—Bearings for parts moving only linearly
    • F16C29/04—Ball or roller bearings
    • F16C29/06—Ball or roller bearings in which the rolling bodies circulate partly without carrying load
    • F16C29/0633—Ball or roller bearings in which the rolling bodies circulate partly without carrying load with a bearing body defining a U-shaped carriage, i.e. surrounding a guide rail or track on three sides
    • F16C29/0669—Ball or roller bearings in which the rolling bodies circulate partly without carrying load with a bearing body defining a U-shaped carriage, i.e. surrounding a guide rail or track on three sides whereby the main body of the U-shaped carriage is an assembly of at least three major parts, e.g. an assembly of a top plate with two separate legs attached thereto in the form of bearing shoes
    • F16C29/0671—Ball or roller bearings in which the rolling bodies circulate partly without carrying load with a bearing body defining a U-shaped carriage, i.e. surrounding a guide rail or track on three sides whereby the main body of the U-shaped carriage is an assembly of at least three major parts, e.g. an assembly of a top plate with two separate legs attached thereto in the form of bearing shoes with balls

Definitions

  • the invention pertains generally to the field of missiles. In greater particularity of invention pertains to missile guidance and tracking sensor systems. In still greater particularity, the invention pertains to the sensor platforms for the above systems. In yet greater particularity, the invention pertains to gimbal sensor platforms. By way of further characterization, the invention relates to the bail bearings of gimbal supported sensors of missile sensor platforms.
  • a purpose of a missile sensor platform is to allow the missile sensor to have limited independent movement within the confines of the missile body. This independent movement allows the sensor to focus upon a target and relay information to the missile guidance system as to the relative position of the target with respect to the missile.
  • By mounting the sensor within orthogonally arranged inner and outer bails isolation of the sensor from the relative movement of the missile can be obtained.
  • the achievement of accurate sensor information using this method is highly dependent upon the precise alignment and movement of the bails relative to their missile base. Complicating this goal are the severe vibrations and loadings the sensor system must endure not only while under operation, but also while being ferried by its delivering platform. Further, weight and size limitations demand proper respect.
  • the present invention provides a continuous-recirculating ball bearing device to support an outer bail of a gimbal supported sensor of a missile sensor platform.
  • the bearing device is fixed to the base of the sensor platforms so that balls may emerge from the device and thereby make contact with a race on the outside edge of the outer bail. Configuration and placement of the device allows the balls to circulate in a wide loop, the axis of which is parallel to the axis of outer bail rotation. The balls travel freely in a ball return section that makes up most of the loop.
  • This section can be fabricated of, for example, soft, easily machinable, lubricant impregnated material because insignificant forces are exerted upon it by the circulating bearings.
  • a race insert section serves to complete the loop. The insert section opposes the bail race for only a small fraction or segment of the race. The insert, therefor described as being segmentally opposite the bail race, has a shallow region that allows balls to emerge from the loop and engage the bail race in load-bearing fashion. A transition plate encloses the balls in the loop except where the shallow region of the insert section ushers the balls into engagement with the bail race.
  • transition plate and insert section shallow region allows a relatively large bearing loop of axis parallel to the outer bail's axis of rotation, to be fitted within the often tight dimensions of a missile sensor section.
  • smoothness of operation can be achieved.
  • use of a multitude of balls inserted into races allows large torque and vibrational loadings to be held in check and closeness of tolerances to be maintained.
  • the primary object of this invention is to provide a bearing suitable for gimbal applications.
  • Another object of the invention is to provide a bail bearing for a gimbal supported missile sensor that can withstand high loads and intense vibrations while at the same time maintain both smooth and precise operation.
  • FIG. 1 is a perspective view of the gimbal sensor platform embodying the present invention.
  • FIG. 2 is a cross-sectional view taken along lines II--II of FIG. 1 illustrating the bearing interfaces.
  • FIG. 3 is a perspective view of the ball loop with the transition plate removed.
  • FIG. 4 is an assembly perspective view of the continuous bearing.
  • a missile platform 10 is comprised of a base 12 that serves as a mount for the inner and outer bails of the platform. Secured to base 12 by a continuous bearing assembly 14 to be described, is the outer bail 16. Pivotally attached to outer bail 16, is the inner bail 18, that cradles the sensor 20.
  • first arcuate ball race 26 has secured to bail 16 by glueing or any other suitable attachment means.
  • second ball race 30 has a shallow region 32.
  • a first plurality of balls 28 are received in load-bearing engagement between first ball race 26 and shallow region 32 of second ball race 30.
  • a ball return 34 is combined with second ball race 30 so as to form a closed ball loop to be described in greater detail below. Ball return 34 is filled with a second plurality of balls 36.
  • first balls 28 with second balls 36 form a continuous chain of balls within the loop.
  • a transition plate 38 covers the loop and retains second balls 36 within ball return 34; however, a slot 40 as best seen in FIG. 4, is provided in the plate to allow first balls 28 to emerge from second ball race 30 and engage first ball race 26. Under operating conditions, the chain of balls comprising first balls 28 and second balls 36 circulate around the loop.
  • Ball return 34 may be fabricated of any suitable material. In practice a lubricant impregnated material such as Micarta was used, however, a variety of metals and plastics can do.
  • FIG. 3 there is illustrated a perspective view of the ball loop with transition plate removed.
  • the ball loop can be seen to be comprised of second ball race 30 and ball return 34. Second balls 36 are completely received within ball return 34. Shallow region 32 of second ball race 30 ushers first balls 28 to emerged from the loop and engage outer bail 16 as illustrated in FIG. 2.
  • Second ball race 30 is secured to ball return 34 by glueing or any other suitable attachment means.
  • Transition plate 38 having slot 40 is secured to both second ball race 30 and ball return 34 by any suitable means such as threaded machine screws 42.
  • the ball loop is next loaded with first balls 28 and second balls 36, FIG. 3.
  • Second ball race 30 and bail 16 are aligned.
  • Bearing assembly 14 is secured to base 12 by suitable attachment means such as the pins 22 and the cap screws 24.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Rolling Contact Bearings (AREA)

Abstract

A outer bail gimbal bearing having a closed loop filled with circulating ls is disclosed. The balls circulate about an axis parallel to the bail's axis of rotation. A shallow region within the loop allows the balls to emerge from the loop and engage a race made in the outer edge of the outer bail.

Description

BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention pertains generally to the field of missiles. In greater particularity of invention pertains to missile guidance and tracking sensor systems. In still greater particularity, the invention pertains to the sensor platforms for the above systems. In yet greater particularity, the invention pertains to gimbal sensor platforms. By way of further characterization, the invention relates to the bail bearings of gimbal supported sensors of missile sensor platforms.
2. Description of the Prior Art
A purpose of a missile sensor platform is to allow the missile sensor to have limited independent movement within the confines of the missile body. This independent movement allows the sensor to focus upon a target and relay information to the missile guidance system as to the relative position of the target with respect to the missile. By mounting the sensor within orthogonally arranged inner and outer bails, isolation of the sensor from the relative movement of the missile can be obtained. The achievement of accurate sensor information using this method is highly dependent upon the precise alignment and movement of the bails relative to their missile base. Complicating this goal are the severe vibrations and loadings the sensor system must endure not only while under operation, but also while being ferried by its delivering platform. Further, weight and size limitations demand proper respect.
Numerous designs for maintaining precision bail alignment and movement have been developed. They have all, however, enjoyed only a limited success. Current methods of aligning the outer bail involve the use of bearing races made a part of the outer edges of the bail itself. A common scheme is to allow the outer bail to ride upon rollers. The rollers mate with a soft metal bearing race cut into the bail's edges. Because of weight and dimensional constraints, a few rollers of relatively large size are utilized. The effect of this design is a concentration of vibrational and other loadings over a small segment of the bail. Another tried method has been to cut a recirculating bearing path into the platform base, thereby allowing circulating ball bearings to contact hardened steel bearing races inserted into the outer edge of the bail. A current example of this design has balls circulating about an axis perpendicular to the outer bails's axis of rotation. Dimensional limitations require the balls to negotiate tight corners, the result of which lessens the smoothness of the bail movement.
SUMMARY OF THE INVENTION
The present invention provides a continuous-recirculating ball bearing device to support an outer bail of a gimbal supported sensor of a missile sensor platform. Though the device is used in opposing pairs, only a single device will be hereafter discussed and the reader may assume that what applies to one device applies equally to the other. The bearing device is fixed to the base of the sensor platforms so that balls may emerge from the device and thereby make contact with a race on the outside edge of the outer bail. Configuration and placement of the device allows the balls to circulate in a wide loop, the axis of which is parallel to the axis of outer bail rotation. The balls travel freely in a ball return section that makes up most of the loop. This section can be fabricated of, for example, soft, easily machinable, lubricant impregnated material because insignificant forces are exerted upon it by the circulating bearings. A race insert section serves to complete the loop. The insert section opposes the bail race for only a small fraction or segment of the race. The insert, therefor described as being segmentally opposite the bail race, has a shallow region that allows balls to emerge from the loop and engage the bail race in load-bearing fashion. A transition plate encloses the balls in the loop except where the shallow region of the insert section ushers the balls into engagement with the bail race. The combination of transition plate and insert section shallow region allows a relatively large bearing loop of axis parallel to the outer bail's axis of rotation, to be fitted within the often tight dimensions of a missile sensor section. By utilizing a large loop, smoothness of operation can be achieved. Furthermore, the use of a multitude of balls inserted into races allows large torque and vibrational loadings to be held in check and closeness of tolerances to be maintained.
OBJECTS OF THE INVENTION
The primary object of this invention is to provide a bearing suitable for gimbal applications.
Another object of the invention is to provide a bail bearing for a gimbal supported missile sensor that can withstand high loads and intense vibrations while at the same time maintain both smooth and precise operation.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a perspective view of the gimbal sensor platform embodying the present invention.
FIG. 2 is a cross-sectional view taken along lines II--II of FIG. 1 illustrating the bearing interfaces.
FIG. 3 is a perspective view of the ball loop with the transition plate removed.
FIG. 4 is an assembly perspective view of the continuous bearing.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to FIG. 1, a perspective view of a representative missile sensor platform with a gimbal supported sensor is useful in discussing the specific construction of the inventive arrangement. As shown, a missile platform 10 is comprised of a base 12 that serves as a mount for the inner and outer bails of the platform. Secured to base 12 by a continuous bearing assembly 14 to be described, is the outer bail 16. Pivotally attached to outer bail 16, is the inner bail 18, that cradles the sensor 20.
Referring to FIG. 2, there is illustrated in cross-section the bearing interfaces between the outer bail 16 and base 12. It is seen that outer bail 16 has secured to it a first arcuate ball race 26. First ball race 26 may be secured to bail 16 by glueing or any other suitable attachment means. Opposite first ball race 26 is a second arcuate ball race 30 of bearing assembly 14. Second ball race 30 has a shallow region 32. A first plurality of balls 28 are received in load-bearing engagement between first ball race 26 and shallow region 32 of second ball race 30. A ball return 34 is combined with second ball race 30 so as to form a closed ball loop to be described in greater detail below. Ball return 34 is filled with a second plurality of balls 36. The combination of first balls 28 with second balls 36 form a continuous chain of balls within the loop. A transition plate 38 covers the loop and retains second balls 36 within ball return 34; however, a slot 40 as best seen in FIG. 4, is provided in the plate to allow first balls 28 to emerge from second ball race 30 and engage first ball race 26. Under operating conditions, the chain of balls comprising first balls 28 and second balls 36 circulate around the loop.
Ball return 34 may be fabricated of any suitable material. In practice a lubricant impregnated material such as Micarta was used, however, a variety of metals and plastics can do.
Referring to FIG. 3, there is illustrated a perspective view of the ball loop with transition plate removed. The ball loop can be seen to be comprised of second ball race 30 and ball return 34. Second balls 36 are completely received within ball return 34. Shallow region 32 of second ball race 30 ushers first balls 28 to emerged from the loop and engage outer bail 16 as illustrated in FIG. 2.
Referring to FIG. 4, an assembly perspective view of the continuous bearing device is presented. Second ball race 30 is secured to ball return 34 by glueing or any other suitable attachment means. Transition plate 38 having slot 40 is secured to both second ball race 30 and ball return 34 by any suitable means such as threaded machine screws 42. The ball loop is next loaded with first balls 28 and second balls 36, FIG. 3. Second ball race 30 and bail 16 are aligned. Bearing assembly 14 is secured to base 12 by suitable attachment means such as the pins 22 and the cap screws 24.
It is thus seen that a continuous bearing for a gimbal supported sensor of a missile sensor platform has been disclosed in which balls circulate about an axis parallel to the outer bail's axis of rotation. Precision movement is maintained by this arrangement. Precision tolerances are maintained by allowing outer bail 16 to ride on balls mated between race 26 of bail 16 and shallow region 32 of assembly 14's race 30.
Obviously, many modifications and variations of this invention are possible, and it is therefor understood that within the scope of the inventive concept disclosed, the invention may be practiced otherwise than as specifically described.

Claims (4)

What is claimed is:
1. A recirculating bearing apparatus comprising:
a first arcuate ball race;
a second arcuate ball race segmentally opposite of said first ball race, of the same radius as, and rotatably concentric to, said first ball race, having a shallow region located between the ends of said second ball race;
a first plurality of balls disposed in load-bearing engagement between said first ball race and said shallow region of said second ball race;
a second plurality of balls;
a ball return connected to said second ball race such that said ball return and said second ball race meet to define a closed loop, so that said first and second pluralities of balls are received within said closed loop so as to circulate around said closed loop;
a transition plate enclosing said ball return and said second ball race, said transition plate having a slot over said shallow region of said second ball race so that said first plurality of balls protrude through said transition plate slot and thereby engage engage said first ball race.
2. A recirculating bearing apparatus according to claim 1 wherein said ball return is made of lubricant impregnated material.
3. A recirculating bearing apparatus for supporting a bail of a gimbal sensor platform comprising:
a first arcuate ball race adapted to be connected with said bail of said gimbal platform;
a second arcuate ball race segmentally opposite of said first ball race, of the same radius as, and rotatably concentric to, said first ball race, having a shallow region located between the ends of said second ball race;
a first plurality of balls disposed in load-bearing engagement between said first ball race and said shallow region of said second ball race;
a second plurality of balls;
a ball return connected to said second ball race such that said ball return and said second ball race meet to define a closed loop, so that said first and second pluralities of balls are received within said closed loop so as to circulate around said closed loop; a transition plate enclosing said ball return and said second ball race, said transition plate having a slot over said shallow region of said second ball race so that said first plurality of balls protrude through said transition plate slot and thereby engage said first ball race;
means for securing said second ball race, ball return and transition plate together;
means for mounting said second ball race, ball return and transition plate on said platform in an operative position relative to said first ball race.
4. A recirculating bearing apparatus according to claim 3 wherein said ball return is made of lubricant impregnated material.
US06/903,628 1986-08-28 1986-08-28 Continuous bearing Abandoned USH1384H (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US06/903,628 USH1384H (en) 1986-08-28 1986-08-28 Continuous bearing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/903,628 USH1384H (en) 1986-08-28 1986-08-28 Continuous bearing

Publications (1)

Publication Number Publication Date
USH1384H true USH1384H (en) 1994-12-06

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US06/903,628 Abandoned USH1384H (en) 1986-08-28 1986-08-28 Continuous bearing

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060081081A1 (en) * 2004-10-19 2006-04-20 Francois Delaney Load displacement apparatus
US20100089701A1 (en) * 2004-10-19 2010-04-15 Delaney Francois Load displacement apparatus

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3477297A (en) * 1966-10-06 1969-11-11 Ambac Ind Caging apparatus and sensor stabilization system employing same
US3527435A (en) * 1969-03-17 1970-09-08 Us Navy Antenna supporting and positioning device
US4152942A (en) * 1976-06-11 1979-05-08 Ferranti Limited Inertial platforms
US4195862A (en) * 1978-05-01 1980-04-01 Shim-A-Line, Inc. Camber adjusting shim arrangement
US4212098A (en) * 1977-12-05 1980-07-15 Eltra Corporation Method and apparatus for aligning a bearing
US4324378A (en) * 1980-03-03 1982-04-13 The United States Of America As Represented By The Secretary Of The Navy High-torque/acceleration stabilized sensor platform
US4444442A (en) * 1980-01-14 1984-04-24 K. K. Tokyo Keiki Bearing apparatus
US4452654A (en) * 1982-05-28 1984-06-05 General Dynamics, Pomona Division Method of assembling a gyroscope gimbal fixture

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3477297A (en) * 1966-10-06 1969-11-11 Ambac Ind Caging apparatus and sensor stabilization system employing same
US3527435A (en) * 1969-03-17 1970-09-08 Us Navy Antenna supporting and positioning device
US4152942A (en) * 1976-06-11 1979-05-08 Ferranti Limited Inertial platforms
US4212098A (en) * 1977-12-05 1980-07-15 Eltra Corporation Method and apparatus for aligning a bearing
US4195862A (en) * 1978-05-01 1980-04-01 Shim-A-Line, Inc. Camber adjusting shim arrangement
US4444442A (en) * 1980-01-14 1984-04-24 K. K. Tokyo Keiki Bearing apparatus
US4324378A (en) * 1980-03-03 1982-04-13 The United States Of America As Represented By The Secretary Of The Navy High-torque/acceleration stabilized sensor platform
US4452654A (en) * 1982-05-28 1984-06-05 General Dynamics, Pomona Division Method of assembling a gyroscope gimbal fixture

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060081081A1 (en) * 2004-10-19 2006-04-20 Francois Delaney Load displacement apparatus
US20100089701A1 (en) * 2004-10-19 2010-04-15 Delaney Francois Load displacement apparatus
US8402850B2 (en) 2004-10-19 2013-03-26 Delaney Technologies Inc. Load displacement apparatus

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