US1892006A - Means for controlling aeroplanes in flight - Google Patents

Description

B. ROBERTS MEANS FOR CONTROLLING AEROPLANES IN FLIGHT V Filed Aug. 6, 1931 2 Sheets-Sheet DEC. 27, 1932., B. ROBERTS 1,892,006

MEANS FOR CONTROLLING AEROPLANES IN FLIGHT Filed Aug. 6, 1951 2 Sheets-Sheet 2 me/v 77/5 Patented Dec. 27, 1932 BERNARD ROBERTS, OF AUCKLAND, NEW ZEALAND MEANS FOR CONTROLLING AEROPLANES FLIGHT Application filed August 6, 1931, Serial No. 555,613, and in New Zealand May 21, 1931.

This invention relates to means for con trolling aeroplanes, airships and the like in flight, and its object is to provide improvements in said control means, so that a pilot after having caused his aeroplane or the like to take ofl and to rise to a suitable height above the ground, may adjust the control means in a manner which renders the latter automatic in their operation, whereby the aeroplane or the like will maintain a normal horizontal flying position without the assistance of the pilot.

The principle of the invention resides in adjustment of the control means of the ma chine by Weighting same so that as soon as any. departure is made from normal horizontal flight, due to air currents, eddies, and the like, a righting moment is introduced, which returns the machine to its former position. The invention is applied to both elevator and aileron controls, and is applicable to both the ordinary control lever or oy stick type of control, and also to the wheel and lever type of control. Simple means are provided whereby the automatic control may be put out of action, so that the pilot may be unhampered thereby when he desires to manoeuvre. A feature of the invention is that the further the machine is thrown from the normal position by some disturbance, the greater is the righting moment introduced, and this moment is gradually reduced as the machine approaches normal again, thus avoiding setting up a swinging motion about the normal position.

The invention consists in mounting and weighting the aileron and elevator control means of an aeroplane, so that any departure by the aeroplane from normal horizontal flight, is corrected through the parts controlled by said means.

In order that the control means may be unhampered by the correcting weight, when so desired by the pilot, means are provided for relieving the control means, of its effect.

In order that the invention may be better understood, it will be more particularly described with the aid of the accompanying drawings, wherein it is shown applied to the 00 control lever or joy stick type of control,

Fig. 1 being a side sectional elevation, 'and Fig. 2 a front View of the control lever or joy stick weighted'to give automatic control, while a Fig. 3 illustrates an aeroplane fitted with the improvements, in flight, and the automatic control in operation, and

Fig. 4 is a sectional elevation of means for putting the automatic control into or out of operation as desired, 6

Fig. 5 being a detail view in sectional plan of means for reducing airdraught on the automatic control device. Referring to Figs. 1 and 2 of the drawings, the control lever or joy stick (e) has incor porated in its lower portion a cylinder (a), and is mounted so that it can be rocked backwards and forwards about its pivot (s) which is supported in a bearing member (t) incorporated in the hollow shaft (u) turnable in bearings (a), so that said lever can be moved to either side of a vertical position, as well as backwards or forwards.

The wires (to) for operating the elevator of the aeroplane are attached to a fitting (f) on the'cylinder (a) while the wires for operating the ailerons of the aeroplane, are attached to the fitting (g) mounted on the shaft so as to rock or have side movement with same. Inside the cylinder (at) isa weight (b) which may be of metal or a container filled with a heavy liquid such as mercury. The weight (b) is free to move vertically Within the cylinder (66) being a sliding fit therein, and is fitted at the lower end with a bucket washer (0) so that a liquid tight fit is obtained.- Attached to the lower end of the cylinder (a) and in communication therewith is a pipe ((5) which is carried up the outside of the cylinder (a) and immediately behind it untl the fuselage of the machine is reached. The pipe (cl) then turns to the side and ends opposite the pivot (s) of the control lever (e), suflicient length being left to attach a flexible tube v Fig. 3 shows the automatic control in operation, themachine having been tilted into a' diving position by some Wind current or eddy. The weight (b) at the bottom of the cylinder (0:) maintains the control lever '(e) in a vertical position, thus acting on the elevator control wires (w) to adjust the elevator flaps and provide a righting moment which will return the machine to the normal horizontal flying position. A similar action takes place if the machine is thrown into a climbing position, the elevator flaps being adjusted by the lever (e) maintaining a vertical position .to introduce the requisite righting moment and correct the flying of the machine. Similarly if the machine-is thrown out ofa horizontal position laterally, the weight (b) maintains the control lever (6) in a vertical position as before, thus operating the aileron control wires (00) and adjusting the ailerons to cause the machine to return to the normal flying position. 7

. As in asmall machine the cylinder may project below the fuselage, a shield (Fig. 3) "is provided to protect it from the wind force caused by the motion of the machine through the air. Alternatively a fairing (1') (Fig. 5) may be used enclosing-both the cylinder (a) and the pipe (cl) thus reducing the Wind draught on these members.

' Fig. 4 illustrates means for putting the automatic control into and out of use as the. pilot desires. A cylinder contains a plunger (70) fitted with bucket washers (l) and (m) so as to form liquid and air tight fits. respectively in the cylinder (h). The plunger is operated by a rod which carries a, pawl (0), the latter engaging in a spring catch 7) when the rod and plun er are pushed right in the cylinder (7). ttached to the end of the cylinder remote from the end through which the rod (n) operates,

and in communication with the inside of said cylinder, is a pipe The cylinder-(h) is attached to the fuselage of the machine withinconvenient reach of the pilot, and the pipe leads to within a short distance of the end of the pipe (d) near the pivot (s) of the control lever (e). The pipes (j) and (cl) are joined together by means of the flexible tube (a), and the cylinder (h) and pipes (d) and (j) with the connecting flexible tube (2) are filled with oil or other suitable liquid. Thus when the rod (n) is in the withdrawn position, the weight (b) rest-s at the bottom of the cylinder (a) and Weights the lever (6) so that it will maintain a vertical position andthe automatic control is in use. When the rod (n) is pushed in, the plunger (is) forces the oil in the cylinder (h). through the connecting pipes (j), (a) and (d) to the bottom of the cylinder (a) causing the weight (b) to be raised to near the pivot (s) of the control lever (6) so relieving the latter of weight and putting the automatic control out of action, the plunger (is) and weight (-6) being retained in these positions by the pawl (0) engaging in the spring catch 2).

When it is desired to bring the automatic control means into action. again, the spring (10) is depressed thus releasing the pawl (0), and the rod is pulled back, the plunger (70) travelling outwards inthe cylinder (h), allowing the weight (b) to descend to the bot tom of the cylinder (a) and add weight to the jatter sufficient to keep the lever (e) vertica What I do claim and desire to secure by Letters Patent of the United States of Amer- 10a 1s 1. Anaeroplane elevatorand aileron operating means including a lever mounted so as to be capable of backward and forward and/or side movement, the lower. portion of said lever including a chamber, a weight in said chamber adjustable under the influence of fluid pressure towards or from the axes about which said levermoves and means for forcing fluid into and withdrawing the fluid from said chamber to adjust theposition ofsaid Weight.

2. An aeroplane elevator and aileron operating means including a lever mounted so as to be capable of backward and forward and/or side movement, the lower portion of said lever including a chamber, a weight in said chamber adjustable under the influence of fluid pressure, a fluid container in communication withsaid chamber and a plunger in said container controlling the flow of fluid to and fromthe chamber to vary the position of said weight.

3. An aeroplane ron operating means including a lever mounted so as to be capable of backward and forward and/or side movement, the lower portlon of said lever including a chambena weight in said chamber adjustable under the influence of fluid pressure, a fluid container in communication through a flexible connection with said chamber, a plunger in said container controlling the flow of fluid toandfrom the chamber to: vary the position of said weight, a plunger rod extending from the container, a pawl on said rod and a catch on said container engageable by said; pawl.

In testimony whereof he has aflixed his signature. I j V Y BERNARD ROBERTS.-

flying elevator and aile-

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