US1197134A - Gyroscopic steering mechanism. - Google Patents

Description

F. M. LEAVITT.

GYROSCOPIC STEERING MECHANISM.

APPLICATION FILED uov.2.1915.

1,1911% Patented Sept. 5', 1916.

2 SHEETS-SHEET I. 4

M cc 9 Z0/ INVENTOR V Let, ITNESSES: 21 fim By Attorney s,

F. M. LEAVITT.

GYROSCOPIC STEERING MECHANISM.

APPLICATION FILED NOV. 2, m5.

1 1 97 1 34, PatentedSept. 5, 1916.

2 SHEETSSHEET 2.

+4 EIIIIIIII Illllll iillllllllllll FRANK M. LEAVI TT, 0F SMITHTOWN, NEW YORK, ASSIGNOR TO E. W. BLISS COMPANY,

OF BROOKLYN, NEW YORK, A CORPORATION OF WEST VIRGINIA.

GYROSCOPIC STEERING MECHANISM.

Specification of Letters Patent.

Patented Sept. 5, 1916.

Application filed November 2, 1915. Serial No. 59,166.

To all whom it 1): (13 concern:

Be it known that I, FRANK M. LEAvrr'r, a citizen of the United States, residing in Smithtown, in the county of Suffolk and State of New York, have invented certain new and useful Improvements in Gyroscopic Steering Mechanism, of which the following is a specification.

This invention relates to gyroscopic mechanism for steering automobile torpedoes or other analogous vessels: In such mechanisms the engine or other steering mechanism which operates the rudder or other steering element is controlled in its opera;

tion by the directive effect of a gyroscope.

in the earlier mechanisms the gyroscope directly operated a valveor other means for controlling the steering mechanism; this however involved the disadvantage that the resistance to movement of such valve, al though slight, was sufiicient to throw upon the gyroscope an appreciable amount of work such as to impair its effective operation. To remedy this detect the more successful devices of this character have been provided with controlling means whereby the angular position of the gyroscope relatively to the torpedo exercises the requisite control over the steering mechanism without any appreciable reaction being exerted against the gyroscope; the means for this purpose used in the Bliss-Leavitt torpedo has comprised a tappet device the control of which by the gyroscope is so sensitive as to practically eliminate any reaction against the gyroscope. Another system for accomplishing the same purpose is that set forth in the patent to F. W. Dodd, granted October 12, 1915, No. 1,156,350, wherein the gyroscope controls the direction of an air jet, and the steering mechanism is actuated by a jetoperated means driven by such air jet.

The present invention provides an improved mechanism operating upon the air jet principle.

The invention aims to provide an extremely simple control mechanism which shall be thoroughly reliable and efiicient.

It further provides means for efiecting angular control of the steering direction before the launching of the torpedo, in order to give the latter what is known technically as a curved fire whereby the torpedo when launched in one direction may be caused to steer through a curved path scope turned at right angles to the posi tion shown in Fig. 1; Fig. 5 is a sectional plan of the gyroscope base, the plane of the section bemg indicated by the line 55 in Fig. Figs. 6 and 7 are enlarged sections of a part of Fig. 1; Fig. 8 is a sectional elevation of a detail; Fig. 9 is a vertical midsectlon of a modified construction.

In the drawings an air-spun gyroscope is shown of the type employed in the Blisslleavitt torpedo, and the steering mechanism is an air-drlven engine or servo-motor; but neither of these is essential to the present invention, it being admissible to use any suitable means for spinning up the gyroscope, and any suitable means for operating the rudder or other steering element.

Referr ng to the drawings, .A designates thesteerlng mechanism, here shown as an engine or servo-motor driven by air a'dmltted at a to a Valve chest 7) containing a valve which is operated by a stem 0, all as usual, while the engine cylinder contains fa piston or plunger the rod B of which passes out through the aft end and is connected by a couplmg d to the tiller rod leading aft to control the rudder in the usual manner.

C 15 the gyroscope, which is usually of the construction comprising a fly-Wheel e hung 1n. an inner gimbal f standing normally honzontal, and hung in turn in an outer glmbal g standing normally vertical, and WhlCh turns around a vertical axis by means of ball bearings or other pivotal connection with a supporting frame D which may be variously constructed, the particular construction shown comprising an outer shell or protecting cup E having at its upper end a head F carrying the upper pivotal bearing, and having beneath airemovable head Gr carrying the lower pivotal bearing, the latter being shown in section in Figs. 1 and 4 where it is shown as a ball bearings The upper bearing in'the head'F is or may be of the same construction as that here shown for the lower bearing.

For spinning up the gyroscope its flywheel axle has a pinion h which initially meshes with a pinion i on a shaft 7' turning in a sliding bushing k; the shaft carries on its outer end a small turbine Z which at the instant of spinning is driven by ets of air discharged obliquely from a nozzle m to which the air is conducted through a duct n, being admitted thereto under high pressure from the starting valve opened at the mstant of launching the torpedo by well known means, which are not here shown and require no description. During spinning the gyroscope is held stationary by a lock or bolto engaging the inner ring f coincidently with the fly-wheel axis. After a suflicient time to spin up the fly-wheel to the requ red velocity, the bushing k is suddenly displaced to the left in Fig. 1, bringing the pinion i to the position shown at z", where it is out of mesh with the pinion h, and by the same movement the bolt 0 isvretracted to free the gyroscope; also the turbine Z is moved beyond the nozzle and the flow of alr is shut ofi. The gyroscope is thus set spinning with an axial direction fixed with relation to the torpedo by the bolt 0, and fixed with relation to space by the aiming of the launch ing tube, all as is well understood. As stated above, the spinning 'up means shown and described may be substituted by any other suitable means for setting the gyro-' scope in rotation and unlocking it.

The present invention will now be described.

The gyroscope carries a jet nozzle H which, by preference, directs the jet vertically instead of in the horizontal direction,

- as heretofore. Compressed air is conducted to this jet nozzle in any convenient way, as for example, by takingit froma suitable source (such as the compressed air reservoir of the torpedo through the starting valve) by means of a tube 12 p to a duct g through the lower gyroscope pivot, and by a tube r carried by the outer ring 9 to the nozzle. The nozzle is shown as connected to the ring 9 by means of a plate or crosshead s carrying on its opposite enda, counterbalance s to balance the weight of the nozzle and the tube 1'. This plate is fastened to the ring 9 by screws passing through areshaped slots t which admit of a certain amount of angular displacement of the nozzle with relation to'the gyroscope. The up- Ward jet from the nozzle is directed against a deflecting member or disk J (which may be integral with the head F) which is normally stationary and which is characterized by a series of jet-deflecting surfaces formed by passages or orifices u u. These are arranged in circular order concentric with the vertical axis of rotation of the gyroscope, so that they stand in' the path traversed by the jet upon any relative movement of the gyroscope with respect to the torpedo. The orifices u are directed obliquely in one direction,and those u in the contrary direction, as best shown in Figs. 1 and 6.1 Between these two series is a blank space c which, on its underside, presents a fiat face opposing the jet when the parts are in the central or neutral position, as shown in Fig. 6. When the parts are angularly diverted to either side from this position and reach the relation shown in Figs. 1- and 7 the jet blows into one or other of the oblique orifices and is thereby discharged obliquely in the manner shown in Fig.

Directly above the deflector J is a fan disk K which has fan blades in the form of radial teeth or'vanes' w, 20, against which the obliquely directed jets of air blow. Thus the fan is revolved in one direction or the other by these air jets, according to whether they ar diverted to the right or left by reason of the relative position of the jet nozzle and deflector. The fan K is shown as mounted on a central shaft or spindle 11 which turns in a bearing formed in a boss 12 on a cap plate or disk L which overlies the fan K and which has orifices 13 for permitting the escape of the spent air.

The fan K, which constitutes a form of jet-actuated means for controlling the steering mechanism, is connected to the latter in any suitable or convenient manner. In the construction shown it has a crank connection with the valve stem 0 of the steering engine A. Its spindle 11 has fast to it,"

above the hub 12, a crank head 14, the wrist pin of which engages a connecting rod 15 which is coupled to the valve stem. To make this connection adjustable the rod 15 is screw-threaded and is screwed into a threaded socket in a-block 16 in which the crank pin turns. A half turn of the crank displaces the engine valve for its entire throw, and thereby causes the engine to throw the rudder from hard-a-port to harda-starboard, or the reverse. Any further turn of the crank would be futile and would produce an efi'ect contrary to that intended; for this reason a stop is provided to limit the movement. This stop is best constructed as a pin 17 projecting from the crankhead 14, (see Fig. 8) and which at either extreme throw strikes the rod 15 and checks any further movement, holding the fan K stationary, notwithstanding the impulse of the air jets tending to turn it further; The stop pin 17 thus. constitutes a crank pin and has, preferably, a greater throw than that of the wrist pin whlch engages the block 16.

When the torpedo swerves to either side of its true course it carries with it the deflector J, while the gyroscope holds the jet nozzle H stationary. The jet from the nozzle is thereby directed through one or other of the series of oblique deflecting perforations u or u, and consequently turns the fan K in one direction or the other. The latter moves the valve of the steering en gine, which in turn throws the rudder in such direction as to steer the torpedo back toward its true course. lVhen the torpedo has been brought back upon its precise true course the deflector and nozzle are in the relative positions shown in Fig. 6. In this position the flat under-surface of the blank or neutral portion 1; receives the impact of the jet, so that no effect is produced. In practice, however, the torpedo is steered not merely back upon its course, but somewhat beyond, so that the jet is then directed through the deflecting orifices of contrary inclination, whereby the fan K is turned in the opposite direction, which produces an opposite movement of the valve and a steering in the opposite side. Thus, the torpedo is caused to steer in the usual sinuous course. If the torpedo is to run in a course in the direction in which it is launched or fired, the relative position-of the nozzle and deflector at the instant oflaunching will be that shown in Fig. 6. If, however, it is desired to cause the torpedo to steer through a curved course for a given angle and then to follow a straight course tangential thereto or what is known technically as curved fire or angle fire), the deflector J is displaced before launching through the number of degrees to right or left that the torpedo is desired to steer in its curved course before starting on its ultimate straight course. For this purpose the deflector plate J is made so that it may oscillate about a vertical axis coincident with that of the gyroscope. In the construction shown it is housed Within the casing E, which latter is in the form of an upright cylinder concen trio with the gyroscope axis; the deflector disk J may consequently be turned within this cylinder to any desired position. In the construction shown the cap plate L is tightly screwed to, or otherwise engaged with, the disk J, and has external gear teeth 18 which are engaged by a worm or screw 19 carried on a shaft 20 which, as shown in the plan view, Fig. 2, extends laterally and has" a'squared end 21 which may be engaged by a key in order to turn it. In setting the torpedo for an angle fire the operator turns this shaft 20 for a number of turns corresponding to the number of degrees of angular deflection of the course of the torpedo that is desired, and to right or left as the case may be. Thus the deflector disk J is displaced to right or left to the desired angle, and it results that the torpedo, when launched, will steer in a curved course until it has reached the angle thus set, whereupon its coacting parts having reached the critical position shown in F ig. (3, the normal sinuous steering begins. and the torpedo thereafter steers in a substantially straight course a It is an advantage of. the construction provided by the present invention that since the fan or jet-actuated device turns around the same axis as the gyroscope, the structure lends itself readily to provision for angle fire by the simple displacement of the intervening deflecting plate.

The invention may be variously modified without departing from its essential features. While the vertical jet is preferable, yet a radial jet, as set forth in said Dodd patent, may be substituted. Fig. 9 shows a construction in which such radial jetmay be used, the nozzle H being directed horizontally in radial direction, the deflector J ha ving a down-turned flange in which the deflecting orifices are formed, and the fan K having also a' down-turned flange carrying the blades or vanes and turning within a downward projection from the top plate L.

The invention is not limited in its appli cation to the steering of torpedoes, but may be applied to the steering of other submersible vessels or to the steering of aeroplanes or other air-ships, or in any other location where gyroscopic steering is admissible. v

What is claimed is 7 1. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope,jetactuated means operated by said jet and controlling said steering mechanism, and intervening deflecting means having a succession of oppositely inclined jet deflecting surfaces on opposite sides of a neutral point.

2. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope. jet-actuated means operated by said jet and controlling said steering mechanism comprising a part turning around the vertical axis of the gyroscope, and intervening defleeting means having oppositely inclined jet de ecting surfaces on opposite sides of a neutral point.

3. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, jet-actuated means operated by said jetand controlling said steering mechanism comprising a fan rotatable around the vertical axis of the gyroscope, and intervening deflectin means having oppositely inclined jet de ecting surfaces on opposite sides of a neutral point.

- 4. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said roscope, jet-actuated means operated by said jet and controlling said steering mechanism, and intervening deflecting means having oppositely inclined jet' deflecting surfaces on opposite sides of a neutral point, and having at such neutral point a flat face perpendicular to the direction of the jet.

5. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said roscope, jet-actuated means operated by sa1d jet and controlling said steering mechanism, and intervening deflecting means having a succession of orifices arranged circularly to receive such jet and inclined in opposite directions on opposite sides of a neutral point.

6. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, comprising an upwardly directed nozzle carried by the outer ring of the gyroscope, deflecting means consisting of a plate overlying the gyroscope having oppositely inclined orifices in circular order to receive the jet, and jet-actuated means overlying such plate to receive the deflected jets from such orlfices and connected to control the steering mechanism.

7. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope,

deflecting means comprising a plate overly-' ing the gyroscope having oppositely inclined orifices, a fan overlying such deflecting means, and a stationary support above said fan having a central bearing, a vertical shaft turning in said bearing carrying said fan, and an operative connection between the upper end of said shaft and the steering mechanism.

8. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, jetactuated means operated by said jet, intervening deflecting means having oppositely inclined jet deflecting surfaces, an operative connection between said jet-actuated means and the steering mechanism, and means for limiting its action to the normal controlling movement.

9. A gyroscopic steering apparatus comprising-a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, jet-actuated means operated by said jet, inte'rvening deflecting, means having oppositely inclined jet deflecting surfaces, and

anoperative connection between such jetmeans adapted to receive" such jet, a fan rotatable around the vertical axis of the gyroscope, a steering engine, and an o erative connection between such fan an the valve of such engine, adapted to iinpart the extreme reverse movement to such valve by J 9. one-half turn of the fan, and having means for limiting the movement thereto.

.11. A gyroscopic steering apparatus com-- prising a gyroscope, means for discharging an a1r jet controlled thereby, deflecting means adapted to receive such jet, a fan rotatable around the vertical axis of the gyroscope, a steering engine, 'a crank turned by sa d fan, a connection from said crank to the valve of said engine, and stop means 1n connection therewith for limiting the -movement to approximately a half turn of said crank.

12. In a torpedo, a gyroscopic steering apparatus comprislng a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, jet-actuated means arranged to be operated by said jet in all positions of the gyroscope and controlling said steering mechanism, and means associated therewith adjustable angularly in a horizontal plane for determining the angular course of the torpedo.

13. In a'torpedo, a gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, jet-actuated means operated by said jet and controlling said steering mechanism, and intervening deflecting means adjustable around the vertical axis, of 'the gyroscope w'hereby to determine the angular course of ,the torpedo.

14. In a torpedo, a gyroscopic steering apparatus comprising a gyroscope and steering mechanism, having means for discharging an air jet under directive control of said gyroscope, jet-actuated means operated by said jet and controlling said steering mechanism, and intervening deflecting means means adjustable around the vertical axis of the gyroscope, jet-actnated means, and adjusting means for turnlng said deflecting means to determine the angular course of the torpedo.

16. A gyroscopic steering apparatus comprising a gyroscope and steering mechanism, means for discharging an. air et under directive control of said gyroscope, a disk mounted to turn around the vertical axis of the gyroscope carrying at its center one of the pivotal bearings of the gyroscope and having successive oppositely inclined orifices for deflecting said jet, jet-actuated means operated by the deflected et and con- 15 trolling said steering mechanism, and means for turning said disk for determining the angular course of the torpedo.

In Witness whereof, I have hereunto signed my name in the presence of two sub- 2 scribing witnesses.

I FRANK M. LEAVITT. Witnesses THOMAS F. livsnmon FRED WHITE.

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