US1415052A

US1415052A - Airplane

Info

Publication number: US1415052A
Application number: US399074A
Authority: US
Inventors: Rider William Keith
Original assignee: Packard Motor Car Co
Current assignee: Packard Motor Car Co
Priority date: 1920-07-26
Filing date: 1920-07-26
Publication date: 1922-05-09
Anticipated expiration: 1939-05-09

Description

w. RIDER.

AIRPLANE.

APPLICATION FILED JULY 26. 1920;

2 swans-swim n- A '4 W. K. RIDER.

AIRPLANE.

APPLICATION FILED JULYZG, x920.

Patented May 9, M220 2 SHEETS-SHEETZ WILLIAM KEITH RIDER, OF DETROIT, MICHIGAN, ASSIGNOR TO PACKARD MOTOR CAR COMYANY, 0 F DETROIT, MICHIGAN, A CORPORATION OF MICHIGAN.

AIRPLANE.

Application filed July 26,

T 0 all whom it may concern:

Be it known that 1, WILLIAM KEITH RIDER, a citizen of the United States, and resident of Detroit, Wayne County, State of Michigan, have invented-certain new and useful Improvements .in Airplanes, of :which the following is a specification.

This invention relates to airplane construction and more particularly to control mechanism for airplanes. I

One of the objects of the invention is to provide control means for airplanes that will be simple and rugged in construction.

Another object of the invention is to eliminate the use of cables and pulleys on the inside of the fuselage, thereby providing a cockpit that will be free from such elements in which the operator might become entangled.

Further objects of the invention will appear from the following specification and from the drawings which form a part of this application, and in which:

Fig. 1 is a diagrammatic view of an airplane having control mechanism constructed in accordance with my invention;

Fig. 2 isan enlarged view illustrating in side elevation the control sticks and the membersoperated thereby;

Fig. 3 is a transverse sectional view illustrating the quadrant carried by the hollow control shaft and connected by cables to the ailerons;

Fig. 4 is an elevational view of the transverse control shaft which is connected to the elevators; and

Fig. 5 is a plan view partly in section illustrating the connection-between one of the control sticks and the longitudinally movable motion transmitting member.

I have illustrated in Fig. 1 diagrammatically a bi-plane type of airplane having a fuselage 10, planes 11, the planes having.

ailerons 12 pivoted thereto in the usual manner, and the fuselage having connected to its rear end a rudder 13 and elevators 14', these members also being constructed and connected to the plane in a manner wellknown in the art.

The general construction of the airplane has not been illustrated in detail since the invention resides in the control mechanism and not per se in the particular construction of the parts of the airplane.

The control mechanism is mounted on a Specification of Letters Patent.

Patented May 9, 1922.

1920. Serial No. 399,074.

hollow, rotatable, longitudinally disposed control shaft 15 carried by brackets 16 secured to a frame member 17, longitudinal movement of the shaft being prevented by collars 18.

.The dual type of control has been illustrated, and this control mechanism comprises a pair of control sticks 19 mounted for fore and aft movement in brackets 20 secured to the shaft 15, the brackets and sticks being adapted for lateral movement with the shaft as the shaft is rotated by the sticks in'the shaft supporting brackets 16.

The shaft 15 has secured thereto intermediate its ends a quadrant 21, which, in turn, has secured to it the ends of a pair of cables 22, these cables being connected at their opposite ends to aileron masts 23 for controlling the movement of the ailerons. The cables 22 are guided to the masts by means of idler pulleys 24, and the masts for the ailerons on theupper and lower planes are connected by cables 25.

The elevators for the airplane are also controlled by the sticks 19 and are connected to the sticks in the following manner: The front sticks 19 is pivotally connected, as shown at 26, to a rod 27, which extends through the hollow shaft 15 and is pivoted, as shown at 28, at its rear end to the front end of a second rod 29. The rod 29 is slotted, as shown at 30, and has pivoted within the slot, as shown at 31, the lower end of the rear control stick. In order to permit free fore and aft movement of the sticks 19, the shaft 15 is cut away at its ends, as shown at 32. The rear end of the rod'29 is pivotally connected, as shown at 33; to a pair of downwardly extending arms 34 secured to or formed integral with a hub 35, carried by a transverse control shaft 36 mounted in the fuselage in the. rear of the rear pilot, The shaft 36 is rotatably mounted in a pair of brackets 37 secured to any suitable portion of the frame of the airplane, and the ends of the shaft extend outwardly through the side walls'of the fuselage and have secured thereto laterally extending elevator control arms '38. The arms 38 are connected by cables 39 to elevator masts} 40, by means of which the elevators usual manner. 7

I The operation of the control mechanism above described. is very simple and may be briefly outlined as follows: When the pilot are controlled in the desires to adjust the ailerons, one of the control sticks may be moved laterally, thereby rotating the shaft 15 and with the shaft swinging the quadrant 21. The quadrant 21 by means of the cables 22 controls the ailerons masts and therefore controls the angle of the ailerons.

lln order to adjust the elevators 14, one of the control sticks 19 is moved about its pivot in the bracket 21, either forwardly or rearwardlyas the case may be, and through the motion transmitting members 27 and 29 rotates the tranverse shaft 36, thereby moving the elevator control arms 38, these latter members being connected by the cables 39 to the elevator masts 40, thereby swinging the masts and elevators as desired.

From the above description it will be seen that the control mechanism is exceedingly simple and rugged in construction and does not clutter up the cockpit of the plane.

Although one specific embodiment of the invention has been illustrated and described, it will be understood that modifications and changes in the construction and in the arrangement of the various cooperating parts may be made Without departingfrom the spirit or scope of the invention as expressed in the following claims.

Having described. my invention, What ll claim and desire to secure by Letters Patent 1s:-

1. Control mechanism for airplanes comprising a rock shaft, a. rod extending substantially coaxial with said rock shaft, connections from said shaft and rod to the ailerons and elevators of the airplane, a control stick pivoted to said shaft so that the stick may rock on its pivot longitudinally of the shaft and will rock the shaft when moved laterally, and a direct connection between said control stick and said rod so that the latter is moved endwise as'the stick is rocked on its pivot.

2. Control mechanism for airplanes comprising a! rock shaft, a rod extending substantially coaxial with said rock shaft, connections from. said shaft and rod to the ailerons and elevators of the airplane, control sticks eccentrically pivoted to said shaft and directly connected to said rod for movingt-he rod endwise and for rocking the shaft by a lateral movement of either stick.

3. In a control mechanism for airplanes, the combination with a rock shaft having control connections and a rod arranged substantially coaxial With said shaft and having control connections, of two spaced control sticks independently connected to said shaft to rock it by a lateral movement, and connections between each of said control sticks and said rod whereby either stick may move the rod endwise, said rod constituting the sole interconnection between said sticks.

4. In a control mechanism for airplanes, the combination with a hollow rook shaft having control connections and a rod extending loosely through said shaft and having control connections, of, tWo brackets secured to the shaft in spaced relation, a control stick pivoted to each said bracket and each. adapted thereby to rock said shaft by lateral movement, and direct connections between each of said control sticks and said rod.

5. In a control mechanism for airplanes, the combination with a hollow rock shaft having control connections, anda rod smaller than the opening through the shaft and extending therethrough, said rod having control connections, a bracket secured to the shaft, a control stick pivoted to the bracket so that lateral movement of the stick will rock the shaft, and a direct pivotal connection between the stick and the rod so that rocking of the stick on its pivot Will move the rod endwise.

In testimony whereof ll affix my signature.

tLmM kmrri amen.