US1802238A - Rudder and brake for airplanes - Google Patents

Description

April 21, 1931. co 1,802,238

RUDDER AND BRAKE FOR AIRPLANES Filed Nov. 23, 1928 5 Sheets-Sheet l I; 3 I; 6 (3 I; 33 x 's n x m u 0 1 m Q ioimioi g V .fliLfi'ozart INVENTOR ATTORNEY 5 Sheets-Sheet 2 INVENTOR ATTORNEY M. L. COZART RUDDER AND BRAKE FOR AIRPLANES Filed Nov.

April 21, 1931.

V Mildozart April 21, 1931. M. L. COZART 1,302,233

RUDDER AND BRAKE FOR AIRPLANES I Filed NOV. 25, 1928 5 Sheets-Sheet 3 M. L. dozart INVENTOR ATTORNEY Liv Patented Apr. 21, 1931 UNITED STATES MARVIN L. COZART, or cononeno srnrnes, COLORADO RUBBER AND BRAKE FOR AIBPLANES Application filed November 23, 1928. Serial No. 821,391.

This invention relates to combined rudders and brakes, especially adapted for use upon airplanes, an object being'to provide device which will normally function as a rudder, and which may also serve to retard movement of the airplane and thus act as a brake.

Another object of the invention is the provision of selective means arranged conven ient to the pilot of the airplane, whereby the device may be operated to direct the course of flight or operated to retard forward progress of the airplane.

With the above and other objects in view, the invention further includes the following novel features and details of construction, to be hereinafter more fully described, illustrated in the accompanying drawings and pointed out in the appended claims.

In the drawings v Figure 1 is a side elevation of an airplane illustrating the invention, parts being broken away.

Figure 2 is a top plan view with parts broken away.

Figure 3 is a fragmentary plan view showing the invention used as a brake.

Figure 4 is a like view showing the invention used as a rudder.

. Figure 5 is a rear elevation of the invention arranged as shown in Figure 4.

Figure 6 is a detail elevation of one of the selective operating members.

Figure 7 is a side view of the same.

Figure 8 is an elevation of a modified form of operating member.

Figure 9 is an elevation of a further form.

Referring to the drawings in detail wherein like characters of reference denote correspon'ding parts, the reference character 10 indicates the fuselage of an airplane having a vertically controlled rudder 11 and arudder 12 for controlling the horizontal direction of flight.

The rudder 12 is of novel construction and comprises a pair of movable members or blades 13 which are hingedly mounted as shown at 14 and are capable of simultaneous movement in the same direction, or of simultaneous movement in opposite directions.

The blades 13 are normally held in close I parallel relation by means of rods 15 which are hingedly connected as shown at 16 and which extend through the blades and have mounted thereon springs 17. These springs act to yieldingly force the blades relatively inward or toward one another.

Extending fro-m each blade 13 is an arm 18 whose inner end is secured to the blade, while braces 19 act to stabilize the arm. Secured to the outer ends of the arms 18 are cables 20 and these cables are also secured to operating members 21 which are pivotally m0unted as shown at 22. These operating members are shown in Figures 6 and 7 of the drawings andconsists of pivotally mounted frames arranged to provide foot pedals and as a cable 20 is provided for each of the blades 13,21. foot pedal 21 is provided for each cable so that the blades may be independently operated.

in addition, the blades 13 have secured thereto cables 23. Theselast mentioned ca- (bles are secured to the faces of the blades opposite the arms 18 and the cable of one blade extends through'a guide opening 24 provided in the other blade, the cables being crossed as shown in Figure 3 of the drawings. The cables 23 are connected to operating members 25 which are also in the form of pivotally mounted frames and may be arranged within the frames 21 as shown in Figure 6 of the drawings. As shown in Figure 2, these frames are arranged in pairs and in the form of pedals to be operated by the aviator. They are yieldingly maintained in position by means of springs 26.

Normally, the blades are arranged in close parallel relation as shown in Figure 2 of the drawings, bumpers 27 serving to keep the blades parallel under the action of the springs 17. When it is desired to use the lades as a rudder, one of the frames or pedals 21 may be operated so as to move the blades simultaneously in the same direction as shown in Figure 4. By operating both of the pedals 25 simultaneously, a pull will be exerted upon the cables 23 so that the blades 13 will be moved simultaneously in opposite directions as shown in Figure 3 and will then act as a brake to retard the forward movement of the airplane.

If desired, the operating member or pedals may be mounted upon a rod 28 positioned above the floor of the cock pit of the airplane and may depend therefrom as shown at 21a and 25a in Figure 8, or the pedals 21b may be suspended from an elevated rod 29 while the pedals 2512 may be mounted upon a rod 10 30 ar anged along the floor of the cockpit.

The invention is susceptible of various changes in its form, proportions and minor details of construction and the right is herein reserved to make such changes as properly I fall within the scope of the appended claims.

Having described the invention what is claimed is:

1. A combined rudder and brake for airplanes including a fuselage and an elevator 20 having a cut-out portion, a pair of hinged and vertically disposed rudders mounted on the fuselage within the cut-out portion of the elevator, pivotally connected rods slidable through the rudders with the pivot dis- 25 posed between the rudders and having their free ends headed, expansion springs on said rods between the headed ends and the rudders to normally urge said rudders together, means to move said rudders simultaneously 0 in either direction to cause the rudders to act as a single rudder, and means to'move said rudders against the tension of the springs in opposite directions to act as a brake.

all 2. A combined rudder and brake for airplanes including a fuselage and an elevator having a cut-out portion, a pair of hinged and vertically disposed rudders mounted on the fuselage within the cut-out portion of t the elevator, pivotally connected rods slidable through the rudders with the pivot disposed between the rudders and having their free ends headed, expansion springs on said rods between the headed ends and the rudders to normally urge said rudders together,

oppositely disposed arms secured to said rudders. operating cables connected to the arms,

and a pair of operating cables each extending through a rudder and crossed and se- Ln cured to the opposite rudder from the one they extend through.

In testimony whereof I affix my signature.

MARVIN L. COZART.

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