US1841606A - Turn indicator - Google Patents

Description

Jan. 19, 1932. P. KOLLSMAN 1,841,606

'rimn INDICATOR Filed June 25, 1929 Patented Jan. 19, 1932 UNITED STATES PAUL KOLLSMAN, OI WOODHA'VEN, NEW YORK roan mnroa'ron.

Application filed June 25, 1929. Serial No. 873,581.

This invention relates to turn indicating devices and has among its ob'eots the provision of an improved device the character described in which momentum of a fluidor equivalent mobile element is utilized toindicate a turn.

Another object of the invention is the provision of a gyroscope having a relatively stationary casing and means to create therein a stream of matter having energy, which matter shall have an axis of precession and indicate by suitable means the occurrence of a turn. 7

Another object of the invention is to furnish a device of the type mentioned having improved means responsive thereto to indicate a turn.

A further object of the invention is. to pro vide a simplified turn indicator or turn governor.

Uther objects and advantages of the invention will become apparent as the specification proceeds.

With the aforesaid objects in view, the invention consists in the novel combinations and arrangements of parts hereinafter described in their preferred embodiments, pointed out in the subjoined claims, and

illustrated on the annexed drawings, wherein like parts are designated by the same reference characters throughout the several views.

In the drawings:

Figure 1 is a vertical section of a device embodying the invention.

Fig. 2 is an outside view of the device shown in Fig. 1.

Fig. 3 is a view in side elevation of a modification of the invention in ring form.

Fig. 4 is a plan view of the same with part removed.-

Fig. 5 is an outside view with a part of the device removed to show an indicator control.

the invention in which the device is free of Fig. 6 is a similar View of a modification of.

any moving parts actuated by an energy stream within the casing.

Fig. 7 is a view in side elevation of a further modification of the invention with the casing of cylindrical form, and including a system for circulating energy, which system is adapted for use with any form of the invention.

8 is an edge view of the said casing.

Fig. 9 is a view in side elevation of a further modification of the invention includmg an embodiment of the Venturi principle.

Fig. 10 is an edge view in elevation of the same.

The drawings are diagrammatic, and are intended to be illustrative primarily of the basic principle of the invention.

The advantages of the invention as here outlined are best realized when all of its features and instrumentalities are combined in one and the same structure, but, useful de'- vices may be produced embodying less than the whole.

It will be obvious to those skilled in the art to which this invention appertains, that the same may be incorporated in several different constructions. The accompanying drawings, therefore, are submitted merely as showing the preferred exemplification of the invention.

It will be understood that the indicator herein re resents any mechanism or device operated by the invention for any purpose whatever.

Generally described, the invention provides a turn indicator that utilizes the momentum of a moving fluid-like mass .whether the same flows in a curved, a straight, or other predetermined path. The first of these principles is utilized in a novel gyroscope hereinafter described. The second principle may be utilized by impact with an indicator when a turn is made. According to the second principle, motion is,-at least from a theoretical standpoint, of less importance, although the kinetic energy of the mass adds greatly to the force of the impact, which is a factor in the case of matter of low density, such as a gas.

A gyroscope made according to my invention is far simpler in construction in that the usual rotor is replaced by a stream of whirling or rotating fluid-like matter. This matprecession. The casing in which the gyration occurs is relatively stationary, thus avoiding a complicated mounting. he energy of the moving matter is supplied thereto by any suitable means, and the invention is not to be restricted in this re ard. The said means may be within the caslng, but referably externally thereof, and may inc ude a system for recirculating the same. Where air is used as the motivating fluid it may be unnecessary to circulate the same. In any case, a pump, or other moving part may cause the fluid to enter the casing as a result, for instance, of a differential pressure, whether positive or negative, Within the casing, a suitable means, preferably the casing wall itself, directs the motivating matter in a curved path, and this is facilitated by a tangential entrance of the matter. The latter may actuate a member that is connected to turn with the aircraft or other vehicle, or it may directly actuate the indicating means. The rate of the turn is indicated by the extent of the deflection of a needle, or the like.

Referring in detail to the drawings, 10 denotes a device showing the preferred embodiment of the invention. The same includes a casing 11 having a circular wall, and bein for example, in the nature of a sphere. This casing is preferably stationary with respect to the aircraft or other vehicle on which the device is mounted. Extending horizontally through the casing is an axis 12 that ma be journaled in bearings 13 in the wall 0 the casing. Carried b the axis 12, are one or more vanes 14, 15 w ich lie in a vertical plane, and while they are movable about the said axis, tend to return to vertical plane as hereinafter described. This purpose may be of fected in various ways. In the embodiment shown, the vanes are in the form of quadrants and lie at opposite sides of the axis, with their subtending angles in proximity to each other. The vanes may, however, make any angle with the axis about which they turn.

A mass of fluid-like matter is caused torotate in the casing along a portion of the wall 11, in the plane of the vanes, said plane being vertical in the aircraft, so that the gyrosco e precesses when theaircraft turns in azimut The rotation can be obtained in various ways, and it is not intended to limit the invention in this respect. As a simple way of causing the rotation, the said matter enters the casing tangentially through any suitable nozzle 16, whose axis lies in the vertical plane. The matter discharges from the casing at o nings 17 which lie alon a diameter at r1 ht angles to the axis 12. y creating a. di erential pressure in any suitable manner, a continuous stream of the fluid is caused to enter and rotate in the casing, but the object of this is merely to avoid excessive loss in the speed of rotation of the fluid. The energy for rotation might be replenished in other ways, but this arrangement lends itself to sim licity, since a small external pump 18 (see ig. 7) can be used as a source of energy.

When the aircraft makes a turn, the device 10 turns with it, causing precession to occur. Thereupon the vanes 14, 15 are move angularly by the fluid stream, and to an extent depending on the rate of turn of the aircraft. This causes the shaft 12 to turn and actuate the pointer 19 of the indicator 20. The de flection of the needle occurs as long as the aircraft is turning. The device, including the modifications hereinafter described, will indicate a turn in any direction, in the vertical as well as in the horizontal.

To cause the vanes to quickly return to vertical position after the completion of the turn, any suitable means maybe used, although it is preferred to utilize the force of the incoming fluid stream for this purpose. For this reason, the nozzle 16 is positioned as shown with respect to the vane 16, the latter tending to lie in the path of the jet. But the nozzle is spaced from the vane 16 so as not to retard unduly the movement of the vanes as aforesaid.

If the motivating fluid for the gyroscope is air, it may be discharged into the open at 17. If any other fluid is used, it is preferably recirculated.

In this invention, the moving arts are properly balanced so as to be una ected by any banking of an airolane in turning.

In Figs. 3 and 4 is shown a modification of the invention in which an annular member 21, that is of U-form in cross section and open toward the center is mounted with the axes thereof crosswise to the length of the aircraft. A nozzle 22 discharges an air jet tangentially into the member to cause precession when the aircraft turns. The member 21 moves angularly on the shaft 23 that supports it, and said shaft actuates an indicator 24.

The axis referred to may have any other relation to the aircraft than that specified, and may in one sense he merely horizontal, although it will also function at various to create an energy stream in the casing, thatshall precess to indicate a turn. Vanes 14a and 15a are influenced by the said stream to move and actuate any suitable deflector or valve 25. The latter coacts with a plurality of ports 26, 27 leading to any indicator 28.

' In the position shown, the port 26 is free to transmit pressure from the periphery of the energy stream to the indicator, while the port 27 is ineffective for this purpose.

In Fig. 6 is shown a further modification of the invention that includes a casing 111) which is free of any moving part. The fluid enters through the nozzle 16?) to rotate about a suitable axis. Communicating with the casing is an indicator 28?), which is connected with the casing at a plurality of ports29 that are spaced in the direction of the axis of gyration. The spacing is furthermore such that when precession occurs, only one of the ports may receive pressure from thewhirling fluid stream, and, of course, the deflectlon of the indicator is in a corresponding direction. When the device is in neutral position, the pressure on both ports, if any, is balanced.

In Figs. 7 and 8 is shown a further modification of the invention, in which the casing 110 is of cylindrical form. A nozzle 160 discharges a fluid into the casing tangentially. An indicator 280 communicates with the casing at a plurality of ports 30 spaced in the direction of the axis-of the cylinder. The pump 18 has an outlet connection 31 to the nozzle and a low pressure connection 32 to the openings 17 of the casing. This circulating system can be used with any of the modifications shown, though that of Figs. 3

= and 4 would have to be enclosed in a chamber.

In Figs. 9 and 10 is shown a still further modification of the invention comprising a cylindrical casing 11d, orthe like, having an inlet nozzle 16d, and axial outlets 17. An indicator 29d connects with the casing to show precession of the gyroscope according to the principle hereinbefore described. In these respects this modification may be substantially like the foregoing, except that the improved action of the venturi is utilized in increasing the reliability and efliciency of the device. As one possible arrangement, I show one or more Venturi sections 33, 34 in proximity to the periphery of the casing and in spaced relation to each other. The maximum velocity of the fluid stream thus functions at the Venturi sections, and is translated into a reading on the indicator by the connections 35, 36 at opposite sides of any Venturi section.

The Venturi throat is of any required size to permit an increase in reading and ,pro er directional coaction of the fluid stream ,wlth the wall of the venturi, and yet to permit either passage 35 or 36 to receive the pressure that actuates the indicator.

I claim:

1. A rotorless gyroscopic turn apparatus comprising a casing, means for producing a rotary fluid stream therein about an axis, and means actuated by precession of the fluid stream.

2. A gyroscopi'c turn indicator including means to produce a rotating fluid-like stream, and other means responsive to said stream to show precession of the gyroscope stream from its normal position.

3. A gyroscbpic turn indicator, including a relatively stationary casing, means to cause a stream of particles to whirl therein about a predetermined axis, and means to indicate deviation of the axis of said stream from the predetermined axis.

4. A gyroscopic turn indicator, including a relatively stationary casing having a circular wall, a mass of loose matter therein adapted to rotate along said wall and about an axis, and means actuated by said matter on precession of the mass.

5 A rotorless gyroscopic turn indicator comprising means for direction a fluid stream in a curve, and indicating means actuated by the fluid stream when the directing means makes a turn.

6. A turn indicator for aircraft having means'to impart energy to a fluid-like substance to cause motion thereof in a predetermined path, and means adapted to turn and which is responsive to the energy of said substance on occurrence of a deviation from said path to indicate the turn.

7. A turn indicator for aircraft, having means to impart energy to a fluid to cause motion in a predetermined path thereof relative to the aircraft, and means including an indicator turning with the aircraft at an angle to said path and responsive to the said energy upon a variation from said path to indicate a turn of the aircraft.

8. A gyroscopic turn indicator including a casing, means to cause a fluid stream in the casing to rotate about an axis, and indicator means to show when the fluid stream precesses, said indicator means including a movable member in proximity to the plane of the rotating stream and responsive thereto.

9. A gyroscopic turn indicator including a casing, means to cause a fluid in the casing to rotate in a predeterminedplane and about a given axis, and an indicator responsive to movement of the plane of rotation relatively 10. A. gyroscopic turn indicator including a casing, a means to cause a fluid in the casing to rotate about a given axis, the casing comprising a Venturi section extending along a 5 portion of the periphery thereof through which section the fluid moves, an indicator and connections for the indicator withthe said section at points spaced therein so that one of said points is affected more by the fluid l0 stream than the other when the casing turns and precession occurs. In testimony whereof I aflix my signature.

PAUL KOLLSMAN.

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