US3142184A

US3142184A - Gyroscope

Info

Publication number: US3142184A
Application number: US156839A
Authority: US
Inventors: George F East; Jr Paul R Studer; John H Wais
Original assignee: Clary Corp
Current assignee: Clary Corp
Priority date: 1961-12-04
Filing date: 1961-12-04
Publication date: 1964-07-28
Anticipated expiration: 1981-07-28

Description

July 1954 a. F. EAST EI'AL GYROSCOPB 2 Shoots-Shut 1 Filed Dec. 4, 1961 0 U h N W W G. F. EAST EI'AL 3,142,184

GYROSCOPE 2 Sheets-Sheet 2 July 28, 1964 Filed Dec. 4, 1961 u m e 4 Wm M mnwu/w 5 w E g M; 2 0 muw n I amw. F W/ United States Patent George F. East, Whittier, Paul R. Strider, Jiu, Vista, and

.lohn H. Wais, San Marino, Calif., assignors to Clary Corporation, San Gabriel, Calif., a corporation of (Jalifornia Filed Dec. 4, 1961, Ser. No. 156,839 7 Claims. ((31. 74-512) This invention relates to gyroscopes and has particular reference to gyroscopes operable by gas generating propellants.

Gyroscopes of the above type are useful, for example, in controlling expendable missiles and the like and comprise a turbine-type rotor which is carried by a suitable gimbal means, the latter being normally locked in caged condition. Prior to or during firing of the missile, t .e rotor is brought up to speed by igniting the propellant to generate operating gases. After the motor has been brought up to its maximum operating speed, the gimbal means is uncaged, leaving the gyro in operating condition.

The principal object of the present invention is to provide a relatively small, compact and simple gyroscope operable by a gas generating propellant.

Another object is to provide a self-contained gyroscope of the above type which is economical to manufacture.

Another object is to provide a highly efficient gyroscope of the above type.

The manner in which the above and other objects of the invention are accomplished will be readily understood on reference to the following specification when read in conjunction with the accompanying drawings, wherein:

FIG. 1 is a longitudinal sectional view through a gyro scope embodying a preferred form of the present invention.

FIG. 2 is a sectional view through the rotor and gimbal means and is taken along the line 22 of FIG. 1.

FIG. 3 is a sectional view taken substantially along the line 33 of FIG. 1.

FIG. 4 is a fragmentary view similar to FIG. 1 but illustrating the caging device in uncaged condition.

FIG. 5 is a side View of part of the movable gimbal.

FIG. 6 is a plan view of a part of the stationary gimbal.

Referring to the drawings, the gyroscope comprises a cylindrical case 11 preferably of aluminum or other nonmagnetic material, to the right-hand end of which is secured on end cap 12. A removable cover 13 is threadably attached to the opposite end of the case. The cover has a central hub 14 and forms an annular propellant chamber or compartment 15 to receive an annular gas generating propellant 16. The chamber is closed by a removable bulkhead or wall 17, the latter being threadably attached to the hub and hermetically sealed around its periphery by an O-ring 18 of rubber or the like fitted within a circumferentially extending groove formed in the bulkhead and engaging the inner surface of the cover.

The remainder of the interior of the case 11 forms a rotor compartment 19 in which a hollow rotor, generally indicated at 20, is provided. The latter is formed of a rim 21 of relatively heavy metal, such as brass, and 1 a hub 22 of relatively light metal, such as aluminum,

' which is suitably secured to the rim. A pair of diametrihead 17 and communicating the interior of the propellant chamber with the rotor compartment. As seen particularly in FIG. 3, the jets are spaced around the bulkhead 17 and are directed at an angle to the turbine head 24 to cause the streams of propellant gases transmitted thereby to impinge on the pockets 25 and thus effect rotation of the rotor.

The rotor is rotatably mounted on a shaft 27 by ball bearings 28 and 29. The bearings are retained on the shaft by a pair of nuts 30 and 31, which are threaded in tandem on one end of the shaft and are formed to jointly comprise a labyrinth seal surrounding the bearing 23 which effectively prevents any products of combustion, such as ashes and other solids, carried by the propelling gases from entering the bearings.

The shaft 27 forms part of a gimbal means generally indicated at 123 and located within the hollow rotor. For this purpose, the shaft is formed at its right-hand end into a bifurcated yoke constituting a first gimbal and comprising two spaced arms 32 and 33 which are pivotally supported by coaxially extending

shaft sections

34 and 35 of a center block 36 through ball bearings 3'7. The center block, constituting a second girnbal, is, in turn, pivotally supported by coaxial shaft sections 38 and 40 pivotally mounted by ball bearings 41 mounted in spaced arms 42 and 43 forming the yoked end of a pedestal 44, the latter being attached by screws, i.e., 45, to the end cap 12. The axes of the shaft sections 34 and 38 are mutually perpendicular to each other and to the axis of rotation of the rotor to permit universal positioning of the case relative to the rotor.

It will be noted that the rotor 2th is balanced about the intersection of the axes of shaft sections 34 and 38 and to effect minor adjustment of such balance, a counterweight in the form of an annular ring 46 is adjustably threaded on the interior of the rim.

The caging mechanism comprises a piston 47 which is slideable in a cylinder 48 formed in the hub 14 of the case cover 13. An annular bushing Stl is threadably mounted in the cover to guide the outer end of the piston and to limit outward movement thereof. The piston carries a caging pin 51 which extends through an opening in the hub 14. The pin has a conical end 49 which is adapted to cage the gyroscope by engaging an axial opening 52 formed in the shaft 27, as shown in FIG. 1.

For the purpose of maintaining the gyroscope in caged condition, a locking plunger 53 is slideably mounted in a guide hole extending radially in the piston and communicating with the atmosphere through a vent 54. The plunger is provided with a latching shoulder 55 which, when the piston is moved to its caging position shown in FIG. 1 against the action of a compression spring 56, may be moved into latching engagement with a shoulder on the bushing 50.

It will be noted that the propellant ring 16 is formed into a combustible solid material and is suitably held out of contact with the walls of the propellant compartment by spacers 57, thereby permitting ignition of all surfaces thereof so as to facilitate rapid generation of propellant gases which are directed in the form of streams onto the turbine head of the rotor by the jets 26. An electrically operable firing cap 58 is attached to the propellant ring 16 and is controlled by wires 60 from a suitable source outside the case. In lieu of the propellant ring 16, the propellant may be formed of a plurality of separate pieces in which the surfaces thereof are preferably out of contact with each other and with the walls of the propellant compartment.

The case 11 is provided with exhaust slots 61 extending through the wall thereof to permit venting of spent propellant gases after they impinge on the turbine head. Prior to ignition of the propellant, such openings are '3 $.5 sealed by frangible covers 62 of aluminum foil or the like.

Upon ignition of the propellant ring, the propellant gases generated thereby cause rotation of the rotor and are also transmitted through an opening 63 in the hub 14 to the cylinder 48. As the pressure of such gas builds up, the piston is forced slightly to the right to center the shaft 27 and thereby hold the gyroscope in proper caged condition. At the same time, the gases force the latching plunger 53 radially inwardly of the piston 47 to remove the latching shoulder 55 from engagement with the bushing 50. Concurrently, the buildup of pressure within the rotor compartment causes rupturing of the covers 62 to permit venting of the spent gases.

After the rotor has been brought up to optimum speed and the propellant ring has burnt out, the pressure of the exhaust gases lowers to a point where the spring 56 becomes eifective to force the pin 51 and piston 47 to the left into their positions shown in FIG. 4, thereby uncaging the gyroscope.

Means are provided for indicating the attitude of the case relative to the axis of the rotor during operation of the gyroscope. For this purpose, two potentiometer pickoff devices, generally indicated at 65 and 66, are mounted on the gimbal means to indicate the relative position of the case about two axes of movement.

The pickotf device 65, which is representative of both pickoff devices, comprises a plate 166 of insulating material which is attached to the shaft section 35 of tthe center block 36. Such plate carries a flexible wiping brush 67 which is in wiping engagement with an electrically resistive layer on a second plate 68 of insulating material which is suitably attached to the yoke arm 33 of the rotor support shaft 27. The similar brush 69 of the second pickoff device is carried by the shaft section 38 of the center block and is in wiping engagement with a resistive layer on a plate 72 carried by the arm 42 of the pedestal 44. Flexible wires connected to the brushes and conductive layers of the pickotf devices are passedthrough longitudinally extending passages, i.e., 70, in the center block and a similar passage 71 in the pedestal 44 to appropriate indicating and/or control devices not shown.

Although the invention has been described in detail and certain specific terms and languages have been used, it is to be understood that the present disclosure is illustrative rather than restrictive and that changes and modifications may be made without departing from the spirit or scope of the invention as set forth in the claims appended hereto.

Having thus described the invention, what is desired to be secured by United States Letters Patent is:

1. A gyroscope device comprising a case having a rotor compartment, a rotor in said compartment, means in said rotor compartment supporting said rotor for spinning about a spin axis and for movement about mutually perpendicular axes, means in said case forming a cylinder, said case having a propellant chamber surrounding said cylinder and a wall intermediate said compartment and said chamber; a plurality of jets spaced around said spin axis and communicating said propellant chamber with said rotor compartment, said jets being adapted to direct streams of fluid propellant against said rotor whereby to spin said rotor, a locking device for locking said supporting means against movement about and said mutually perpendicular axes while permitting said rotor to spin, said locking device comprising a piston in said cylinder; a latch device normally latching said piston in position maintaining said locking device in locking condition, and means communicating said propellant chamber with said piston and said latch device, said latch device being operable by propellant pressure to release said piston, said piston being operable by propellant pressure to maintain said locking device in locking condition, and said propellant pressure being ineffective after a predetermined reduction thereof to maintain said locking device in locking condition.

2. A gyroscope device comprising a case having a rotor compartment, a rotor in said compartment, means in said rotor compartment supporting said rotor for spinning about a spin axis and for movement about mutually perpendicular axes, said case having a second compartment, a locking device in said second compartment, said case having an annular propellant chamber surrounding said second compartment and a wall intermediate said rotor compartment and said propellant chamber; a plurality of jets spaced around said spin axis and communicating said propellant chamber with said rotor compartment, said jets being adapted to direct streams of fluid propellant against said rotor whereby to spin said rotor, and means communicating said propellant chamber with said second compartment, said locking device being responsive to a predetermined propellant pressure for locking said supporting means against movement about said mutually perpendicular axes while permitting said rotor to spin, and said locking device being responsive to reduction in propellant pressure below a predetermined amount for re leasing said supporting means for movement about said mutually perpendicular axes.

3. A gyroscope device according to claim 1 comprising a ring of ignitible gas generating propellant in said propellant chamber, and means for igniting said propellant.

4. A gyroscope device comprising a case having a rotor compartment, a hollow rotor in said compartment, a support member supporting said rotor for spinning about a spin axis, gimbal means extending within said rotor and supporting said support member for movement about mutually perpendicular axes, means in said case forming a cylinder, said case having an annular propellant chamber surrounding said cylinder and a wall intermediate said chamber and said compartment, a plurality of jets spaced around said spin axis and communicating said propellant chamber with said rotor compartment and adapted to direct fluid propellant against said rotor whereby to rotate said rotor, a locking device comprising a piston in said cylinder adapted to lock said supporting member in caged condition; spring means for moving said piston to unlock said supporting member from caged condition, and means communicating said propellant chamber with said cylinder, said piston being responsive to propellant pressure to lock said supporting member in caged condition.

5. A gyroscope device comprising a case having a rotor compartment adjacent one end, a hollow rotor in said compartment, a support member supporting said rotor for spinning about a spin axis, gimbal means extending into said rotor and supporting said support member for movement about mutually perpendicular axes, means in said case adjacent the opposite end thereof forming a cylinder whose axis is coincident with the intersection of said mutually perpendicular axes, said case having an annular propellant chamber adjacent said opposite end and surrounding said cylinder, a wall intermediate said compartment and said chamber, a plurality of jets in said wall, said jets being spaced around said axis of said cylinder and communicating said propellant chamber with said rotor compartment and adapted to direct fluid propellant against said rotor whereby to rotate said rotor, a locking device comprising a piston in said cylinder; spring means for moving said piston to unlock said support member from caged condition, and means communicating said propellant chamber with the interior of said cylinder, said piston being responsive to propellant pressure to lock said support member in caged condition.

6. A gyroscope device comprising a case having a rotor compartment, a hollow rotor in said compartment, turbine means on said rotor, a support member supporting said rotor for spinning about a spin axis, gimbal means extending within said rotor and supporting said support member for movement about mutually perpendicular axes, means in said case forming a cylinder whose axis is coincident with the intersection of said mutually perpendicular axes, said case having an annular propellant compartment surrounding said cylinder and a wall intermediate said compartments and adjacent said turbine means, a plurality of jets in said wall, said jets being spaced around said axis of said cylinder and communicating said propellant compartment with said rotor compartment and adapted to direct fluid propellant against said turbine means whereby to rotate said rotor, a locking device comprising a piston in said cylinder adapted to lock said supporting member in caged condition, spring means for moving said piston to unlock said supporting member from caged condition, and means communicating said propellant compartment with the interior of said cylinder, said piston being responsive to propellant pressure to lock said support member in caged condition, an ignitible ring of gas generating propellant in said propellant compartment, and means for supporting said ring out of engagement with the walls of said propellant compartment.

7. A gyroscope device comprising a case having a rotor compartment, a rotor having turbine means thereon, means supporting said rotor for rotation about a spin axis, gimbal means in said rotor compartment mounting said supporting means for movement about mutually perpendicular axes, means in said case forming a cylinder whose axis is coincident with the intersection of said mutually perpendicular axes, said case having an annular propellant chamber surrounding said cylinder and the wall intermediate said compartment and said chamber; jets communicating said propellant chamber with said rotor compartment and directed against said turbine means, a gimbal lock, a piston in said cylinder operatively connected to said gimbal lock, a latch device normally latching said piston in position maintaining said gimbal lock in looking condition, and means communicating said propellant chamber with said piston and said latch device, said latch device being operable by propellant pressure to release said piston, said piston being operable by propellant pressure to maintain said gimbal lock in looking position, and spring means operable in response to a predetermined reduction in propellant pressure for moving said gimbal lock out of locking position.

References Cited in the file of this patent UNITED STATES PATENTS 2,960,877 Still Nov. 22, 1960 3,010,327 Fischer Nov. 28, 1961 FOREIGN PATENTS 1,242,638 France Aug. 22, 1960