US2076088A

US2076088A - Control mechanism for airplanes

Info

Publication number: US2076088A
Application number: US750462A
Authority: US
Inventors: Malinowski Boleslaw
Original assignee: Individual
Current assignee: Individual
Priority date: 1934-10-29
Filing date: 1934-10-29
Publication date: 1937-04-06
Anticipated expiration: 1954-04-06

Description

April 6, 1937. B. MALINOWSKI CONTROL MECHANISM FOR AIRPLANES Filed Oct. 29, 1934 2 Sheets-Sheet l Ewart 0;;

. 1 1 wJ @EL 5 5 5 4/ 04 J45. V v =1." 0 Z A v 6 W 2 Q 5 if 5 April 6, 1937. B. MALINOWSKI CONTROL MECHANISM FOR AIRPLANES Filed 0012.29, 1934 2 Sheets-Sheet 2 Patented Apr. 6, 1937 UNITED-STATES PATENT OFFICE 8 Claims.

This invention relates generally to improvements in airplanes but more particularly to the control mechanism thereof.

Its chief object is the provision of a 'universal control mechanism which is so designed and constructed that the pilot may eifectually control the rudder, the elevators amt the ailerons.

of the plane from one point and solely by the use of his hands.

Another object of the invention is to provide a universal and self-contained control mechanism for airplanes which is simple and rugged in construction, which is positive and reliable in operation, and which, by eliminating joint control by both hands and feet, affords a greater comfort to the aviator. A still further object. of the invention is to provide the control mechanism with means for automatically maintaining it in a position for effecting a level flight of the plane.

Other features of the invention reside in the construction and arrangement of parts hereinafter described'and particularly the appended claims.

In the accompanying drawings:

Figure 1 is a side elevation of an airplane, partly in section, showing my improved control mechanism applied thereto. Figure 2 is a perspective view of the mechanism showing its connections to the rudder,-elevators and ailerons. Figure 3 is an enlarged horizontal section taken substantially in the plane of line 3-3, Figure 1. Figure 4 is an enlarged transverse vertical section taken on line 4-1, Figure 1. Figure 5 is a afertical section taken substantially in the plane of line 55, Figure 4. Figure 6 is. a horizontal section taken on line 6-6, Figure 4.

Similar characters of reference indicate corresponding parts throughout the several views.

By way of example, my invention is shown applied to a standard type of airplane wherein Ill indicates the fuselage, II the wings, l2 the rudder, l3 the elevators, II the ailerons, I5 the propeller and i 6 the pilot seat.

stationed adjacent to the; pilot seat is my improved stick or control mechanism which is so designed and constructed as to enable the op er ator, only with his hands; to control the rudder, elevators and ailerons -from one common point. To this end, a self-contained, universallymounted device is provided which is capable of movement in various directions to accordingly actuate the respective control elements of the airplane. This device preferably consists of a hollow upright member [1 positioned adjacent pointed out in the operator's seat l6 and having transverse journals or trunnions 18 adjacent its lower end which engage corresponding bearings l8 fitted to brackets 20 suitably, mounted on the floor of the fuselage l0, whereby this member is capable of rocking vertically lengthwise of the plane to and from the operator. Fixed on the trunnions l8 to rock therewith -are arms 2] whose opposing ends. are connected by links or cables 22 with the elevators l3 tojaccordingly raise and lower the elevators as the vertically swinging member I1 is shifted forwardly and backwardly,- respectively. This movement of the verticallyswinging member may be conveniently effected by a hand wheel 23 disposed at the upper end of Carried by the vertically swinging member for bodily movement therewith, as well as rotary and oscillatory movement relative thereto, is the means forcontrolling the rudder. l2 and the ailerons I4. This means comprises the hand wheel 23 secured to one end of a

sectional shaft

25, 26, the section 25 being journaled-in suitable bearings formed in the front and rear vwalls of the member II, while the companion wheel-bearing section 26 is pivoted at 28 to the opposing end of the shaft-section 25 and is capable of oscillating horizontally about said pivot 28 in a direction transversely of the fuselage. The pivoted shaft-section 26 is guided in its rocking movement in a horizontal groove or race-way 29 formed'in a head-plate 30 secured to the upper end of the member I I; whereby this sectional shaft is capable of rotation for the purpose of actuating the rudder l2 and the section 26 thereof is capable of transverse oscillation to. actuate theailerons M. The connections between the sectional shaft and the rudder consist of'a pulley 3| fixed on the shaft-section 25 and a cable 32 looped around' said puliey and connected at ber l1 and extending rearwardly through corresponding openings 35 formed in the rear wall of said member.

.said member and having a'hand grip 24 applied The connections between the oscillating shaftsection 26 and the ailerons consist of cables 36 extending from diametrically opposite sides of said shaft-section and secured to a head 31 carried thereby; These cables extend forwardly from this head about a series of pulleys 38 suitably mounted in the head plate 30, then down- 5- wardly about pulleys 39 fitted in the top portion of the member I! and in the block 34, and thence laterally outward through the journals l8 from which they are further guided on pulleys 40 'to direct them to the ailerons l4. By this con- 10 struction, when the hand wheel 23 is oscillated about the pivot 28 in one direction or the other in its race-way 29, the ailerons are correspondingly actuated.

For the purpose of automatically maintaining 15 the airplane in a substantially level state both laterally and Horizontally, I preferably provide the lower end of the vertically-swinging stick or member I! with a pendulum-like element which functions to maintain it in a pendant or upright position irrespective of the angular position of the plane while in flight and to thereby. automatically control the elevators l3 and the ailerons l4 and maintain them in proper position for a level flight. This pendulum-like 25 element is indicated at 4| and is slidingly mounted on a pendant post 42 secured to a rock member 43 mounted on a pivot post 44 disposed longitudinally of the fuselage and carried by the lower portion of the block 34. Depending from 3 the latter is a skeleton frame-like structure 45 whichconstitutes a cage or protective enclosure for the pendulum, and further as an additional weight for maintaining the: stick in an upright position The oscillatory movement of the rock 35 member 43 is adapted to be transmitted to the aileron cables 35 through a cable 46 looped about said rock member and a pulley 4'I loosely mounted on the shaft-section 2i and having each of its stretches connected by a releasable clamp 40 or coupling 48 with the companion aileron cable 36, as shown in Figure 4. By this construction, should the plane tilt laterally while under auto matic flight control, the swinging movement of the pendulum-like element in one direction or 45 the other will accordingly oscillate the rock member 43' and in turn actuate the corresponding aileron to correct the position of the plane. When the plane is under manual control of'the pilot, the clamp 48 is disconnected, and under 50 these conditions the weight 4| may be raised by an actuating cable 49 to a position adjacent the axis of the member II so as not to materially affect the actuation of such member by the pilot. The elevation of this weight may be 55 also controlled during steering of the ship while otherwise in automatic flight by having attaching cables 50 connected to the rudder-actuating cables 32, so that during the turning of the plane the weight is brought inward so as not 60 to materially affect the aileron action.

I claim as my invention: 1. An airplane, comprising flight-control means including an elevator, a rudder and ailerons, a vertically-swinging member, a combined rotat- 65 able and laterally shiftable member mounted thereon and including axially-jointed sections permitting joint rotation of the sections and lateral swinging of-one section relativeto the 70 other connections between said vertically-swinging member and the elevator for actuating the same in response to its swinging movements, and independent connections between said second-named member and the rudder and the 1 ailerons for actuating the same in response to its rotatable and laterally-shiftable respectively.

2. A control assembly for airplanes, comprising a vertically-swinging member having trunnions adjacent its lower end journaled to the fuselage of the plane, connections between said trunnions and the elevator of the plane for actuating the same in response to the swinging movemovements,

" ments of said member, a combined rotatable and laterally-swinging actuating means mounted in the upper end of said member and having its axis of rotation at substantially right angles to said trunnions, two sets of guide rollers applied to said member in the plane of the trunnions,

of the plane, the intermediate portions of said last-named cable engaging said second-named guide rollers.

3. A control assembly for airplanes, comprising a vertical-swinging member adapted for pivotal mounting in the fuselage of the plane, connections between said member and the elevator of the plane for actuating the same in-response to the fore and aft movements of the member, a substantially horizontal sectional shaft journaled in said member including a. section rotatable therewith but free to swing laterally relatively thereto, a connection between the journaled shaft-section and the rudder ot the plane for actuating the latter upon rotation of the shaft,

and a connection between the laterally-swinging shaft-section and the ailerons of the plane for actuating them in response to the swinging movement of such section.

4. A control assembly for airplanes, comprising a vertical swinging member adapted for pivotal mounting in the fuselage of the plane, connection between said-member and the elevator of the plane for actuating the same in response to the fore and aft movements of the member, a substantially horizontal sectional shaft journaled in said member including a section rotatable therewith but free to swing laterally relatively thereto, a connection between the journaled shaft-section and the rudder of the plane Y for actuating the latter upon rotation of the shaft, a connection between the laterally-swinging shaft-section and the ailerons of the plane for actuating them in response to the swinging movement of such section, and a control member flxed on the free end of said laterally-swinging shaft-section for controlling the rotatable and swinging movements-of the sectional shaft and the fore and aft movements of the vertically-swinging member.

5. A control assembly for airplanes, comprising a vertically-swinging elevator control member including pendant weighted means thereon for constantly urging it to a neutral upright position, an oscillating support for the weighted means fulcrumed adjacent the lower end of said member to rock crosswise thereof, and an operrespohse to the lateral swingingof such means caused by a sidewise tilting of the plane.

6. A control assembly for airplanes, comprising a vertically-swinging elevator control member including pendant weighted means thereon for constantly urging it to a neutral upright position, an oscillating support for the weighted means fulcrumed adjacent the lower end of said member to rock crosswise thereof, an actuating element at the upper end of said GIQVQJJOE/COBHOI member for movement relative thereto and including a cable operatively connected to the ailerons of the plane for controlling them, a pulley mounted on said member above said oscillating support, a cable engaging the latter and said pulley, and means for coupling theactuating element cable with the pulley-engaging cable for automatically governing said actuating element in response to the laterally swinging of the weighted means caused by a sidewise tilting of the plane.

'?.A control assembly for airplanes, comprising a vertical-swinging elevator control member having an oscillating supporting element below eratively connecting said oscillating element with .V

the ailerons of the plane to automatically actuate them in response to any lateral tilting of the plane while in flight.

8. A control assembly for airplanes, comprising a vertically-swinging elevator control member having an oscillating supporting element below its pivot and atv substantially right angles thereto, a pendant rod connected thereto, a weight I s'lidably mounted thereon, means for shiftingsaid weight to a plurality of positions on said rod and toward and from the axis of said oscillating element, and means for operatively connecting said oscillating element with the allerons of the plane to automatically actuate them in response to any lateral tilting of the plane while in flight.

BOLESLAW MALINOWSKIE.