US1207492A - Automatic gravity-stabilizer for aerial torpedoes and aeroplanes. - Google Patents

Description

F. W. BUCK.

AUTOMATIC GRAVITY STABILIZER FOR AERIAL TORPEDOES AND AEROPLANE S.

APPLICATION FILED MAY 12, 1916.

LQWAQQ. Patented Dec. 5,1916.

2 SHEETS-SHEET 1.

lllmln Inventor,

F. W. BUCK.

AUTOMATIC GRAVITY STABILIZER FOR AERIAL TORPEDOES AND AEROPLANES.

APPLICATION FILED MAY l2, I9I6.

Patented Dec. 5, I916.

2 SHEEISSIIEEI 2.

Inventor Witnesses Attorneys.

UNITED STATES PATENT c arion.

.FREDRIGK w. BUCK, or FLAGLER, COLORADO.

AUTOMATIC GRAVITY-STABILIZER FOR AERIAL TORPEDOES AND AEROPLANES.

To all whom it may concern:

Be it known that I, FREDRICK W. BUCK, a citizen of the United States, residing at Flagler, in the county of Kit Carson and State of Colorado, have invented a new and useful Automatic Gravity- Stabilizer for Aerial Torpedoes and Aeroplanes, of which the following is a specification.

This invention relates to aerial torpedoes and aeroplanes and more particularly to means whereby the weight of the supported body of the structure will act as a means for maintaining the lateral and longitudinal equilibrium while the machine is in flight so that there will be no danger of the same collapsing because of excessive tilting or dipping.

A further object is to provide means under the control of the supported body for thrusting directly against the controlling planes, elevators or the like, thereby to in-' crease or reduce the wind resistance in order to restore the machine to its equilibmum.

WVith the foregoing and other objects in view which will appear as the description proceeds, the invention resides in the combination and arrangement of parts and in the details of construction hereinafter described and claimed, it being understood that changes in the precise embodiment of the invention herein disclosed, can be made within the scope of what is claimed, without departing from the spirit of the invention.

In the accompanying drawings the preferred forms of the invention have been shown.

. In said drawings :Figure 1 is a slde elevation of an aerial torpedo embodying the present improvements. Fig. 2 is a front elevation thereof. Fig. 3 is a view showlng in diagram one means which may be employed for successively unlocking the torpedo support from the sustaining means, thereby. to permit the supported structure to swing as a pendulum, and for releasing the-torpedo, the two operations being set up in timed relation. Fig. 4 is an enlarged view partly in section and partly in elevation of the lock employed for holding the torpedo support against swinging movement from front to rear.

Fig. 5 is a side elevation-. showing the present improvements embodiedz in an aeroplane structure. Fig. 6

I Specification of Letters Patent.

Application filed May 12, 1916. Serial No. 97,077.

\ Patented Dec.5, 1916.

is a front elevation of the machine shown in Fig. 5.

Referring to the figures by characters of reference 1 designates an aeroplane structure which, in the present instance, is illustrated as a biplane, although it is to be understood that if preferred, the present improvements can be combined with a monoplane or other types of heavier-them air machines.

The aeroplane structure is provided with ailerons 2 although it is to be understood that in some instances warping wingsmay be employed in lieu of these ailerons. Ekavators 8 are connected to the rear end of the structure and are suitably connected so as to work in unison, these elevators receiving their motion from a crank arm 4. A vertical rudder 5 is provided adjacent the rear end of the machine and this rudder is designed to be held in a fixed position relative to the structure 1 by any suitable means,

as, for example, by a gyroscopic compass indicated generally at 6. The motor-has been indicated at 7 and is designed to propelthe machine in the usual manner.

Suspended from the structure 1 by universal joints are hangers 8 which, in turn, are connected by universal joints to a beam 9. The rear end of this beam is connected by a thrust rod 10 to the crank arm 4, the connections between this rod and the beam 9 and arm 4 being such as to permit universal movement. 11 are connected to the sides of the beam 9 and to the respective ailerons 2 or, if warping wings or planes are used,-to the front edges of said planes. These rods 11 are connected by universal joints so that should the beam 9 swing' laterally. relative to the structure 1 it will thrust through one of the rods 11 against one of the ailerons and will pull through the other rod 11 upon the other aileron. Thus the lateral balance of the machine will be maintained through the actuation of the ailerons resulting from the lateral swinging of the beam 9.

For the purpose of holding beam 9 against longitudinal swinging, suitable restraining means are employed. Various types of restraining means may be .used. In the present instance a bar 12 is pivotally connected to one of the hangers 8 and is extended forwardly and upwardly into a guide sleeve 13. This bar has an opening 14 for the recep que'ntly ed so as to cause the machine to travel tion of a bolt 15 which is slidably mounted in the sleeve 13 and is co nnected to or constitutes an extension of the armature of a solenoid 16. Thus when the solenoid is energized the bolt 15 will be withdrawn from bar 12 and release the bar. However, when the bar is held by means of the bolt the beam 9 will be prevented from swinging forwardly and rearwardly relative to the structure 1.

The torpedo to be carried by the structure 1 has been indicated at 17 and is supported under the beam 9. This torpedo is connected to the beam by a bracket 18 engaging a bolt 19 which may constitute the extension of a solenoid armature which extends through ears 20 depending from the beam 9. However, any other suitable means may be used for fastening the torpedo to the beam. Also if desired, saddles 21 may be connected to the beam 9 so as to straddle the end portions of the torpedo and hold said torpedo against lateral swinging relative to the beam 9.

A suitable timing means indicated generally at 22 is provided and this timing means is designed successively to close circuits to the solenoids.

When it is desired to use the apparatus the elevators 3 are set at a predetermined angle relative to the structure 1, this adjustment causing'a relative movement of the bar 12 and sleeve 13. Bolt 15 is then placed in engagement with the bar and the elevators will thus be locked against movement relative to the structure 1 while, at the same time, the torpedo will be prevented from swinging forwardly or rearwardly. Thus when the engine is started the machine will leave the ground and will ascend a predetermined distance until the timing mechanism completes the circuit through the solenoid 16 whereupon bolt 15 will be retracted from bar 12 and ,the torpedo together with its supporting structure will thus be free to swing forwardly and rearwardly. Consethe elevators will be promptly shiftstraight ahead in the course maintained by the rudder 5.

Should the machine tilt laterally the beam 9 and the torpedo connected thereto will thrust against one of the rods 11 and pull upon the other rod 11 so as to shift the ailerons and restore the lateral balance. Should the machine dip downwardly the torpedo would shift forwardly relative to the structure 1 and pull through the rod 10 upon arm 4 and shift the elevators so as to elevate the front end of the machine. Likewise should the tail of the machine sag the operation would be such as to shift the elevators to restore the machine to its proper position. I

After the machine has traveled a predetermined distance the timing mechanism will complete a circuit through the other solenoid and, consequently, the torpedo will be released and fall without hindrance. The torpedo can be so constructed as to explode on contact or under the action of a time fuse.

WVhile the foregoing improvements are designed primarily for use in connection with aerial torpedoes it is to be understood that they can be embodied in ordinary aeroplane structures where it is desired to automatically maintain the lateral and longitudinal balance. An aeroplane embodying these improvements has been shown in Figs. 5 and 6. By referring to said figures it will be seen that hangers 23 are connected to the structure 1 by universal joints and are similarly connected to a seat 24L or, if preferred, to a car. The supported structure is connected by a rod 25 to the crank arm 4 of the elevators and additional rods 26 connect the sides of the supported structure to the ailerons, warping planes or the like. Thus the weight of the supported structure, together with that of the occupant is utilized for controlling the fiight, lateral swinging of the structure causing the ailerons to shift and restore the lateral balance, while longitudinal' swinging will result in the actuation of the elevators and thus maintain the longitudinal balance.

What is claimed is:

1. The combination with an aeroplane structurefof a combined torpedo and stabilizing pendulum connectedto said structure, and means for automatically releasing the same from the aeroplane structure.

2. The combination with an aeroplane structure, of stabilizing means including a combined torpedo and pendulum, and means for rendering the stabilizing means inactive by releasing the combined torpedo and pendulum from the aeroplane structure.

3. The combination with an aeroplane structure, of stabilizing means including a combined torpedo and pendulum, and timed means for rendering the stabilizing means inactive by releasing the combined torpedo and pendulum from the aeroplane structure.

4. The combination with an aeroplane structure, of a body suspended below the lower sustaining plane of said structure and adapted to swing laterally relative to the structure, propelling and steering mechanlsm, means operated by the lateral swinging of the body relative to the sustaining plane for restoring the lateral balance of to, means operated by the swinging of the torpedo for maintaining the lateral and longitudinal balance of the sustaining plane, means for holding the torpedo against longitudinal swinging movement, and time controlled means for successively releasing said holding means from the torpedo and detaching the torpedo from the sustaining plane.

6. A machine of the class described including a sustaining plane, a beam suspended therebelow and designed to swinglaterally and longitudinally relative thereto, a torpedo detachably connected to the beam, combined thrusting and pulling elements extending laterally and rearwardly from the beam, separate means operated by the respective elements during the swinging movement of the beam and torpedo relative to the sustaining plane for maintaining the lateral and longitudinal balance of the machine, and time controlled means for detaching the torpedo from the beam.

7. A machine of the class described ineluding a sustaining plane, a beam suspended therebelow and designed to swing laterally and longitudinally relative thereto, a torpedo detachably connected tothe beam, combined thrusting and pulling elements extending laterally and rearwardly from the beam, separate means operated by the re spective elements during the swinging movement of the beam and torpedo relative to the sustaining plane for maintaining the lateral and longitudinal balance of the machine means for holding the beam against longi" tudinal swinging movement, and time con trolled means for successively releasing the beam from its holding means and detaching the torpedo from the beam.

In testimony that I claim the foregoing as my own, I have hereto afiixed my signature in the presence f two Witnesses.

FREDRICK W. BUCK.

Y'Vitnesses:

IVY E. SIMPSON, HELEN ZIMMERMAN.

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