US1893665A - Aeroplane - Google Patents

Description

Jan. 10, 1933. e. w. ELMWALL AEROPLANE -s Sheets-Sheet 2 Ofiginal Filed July 16. 1950 VENTOR I Gwldw Fir/2M5 BY :2 g) a i E & ATTORNEY 1 Jam. 31), 1933.

G. W. ELMWALL AEROPLANE Original Filed July 16 1950 3 Sheets-Sheet 5 in E INVENTOR Guam w W m ATTORN Y Patented Jan. 10, 1933 ZIT ED "ST ATE S PATENT -F F GUSTAVE W. ELMWALL, OF NE V YORK, N. Y.

AEROPLAN E Application filed July 16, 1930, Serial No. 468,230. Renewed April 22, 1932.

This invention relates to new and useful improvements in an aeroplane.

An aeroplane, whether a monoplane or a biplane, is neither safe nor complete unless 5 it is designed to qualify under any condition or stage of flying. This includes take off and landing as well as the actual flight.

It is the purpose of this invention to provide :an aeroplane structure of superior stability and safety to meet the requirements of the above named phases of aviation.

The present application is similar to the disclosure in my previous patent application filed on June 6, 1927, Serial No. 196,868.

For further comprehension of the invention,and-of the objects and advantages thereof, reference will be had to the following description and accompanying drawings, and to the appended claims in which the various 23 novel features of the invention are more particularly set forth.

In the accompanying drawings forming a material part of this disclosure Fig. 1 is a top plan view showing the general design and relative sizes of parts of the aeroplane embodying my invention.

Fig. 2 is a side view of Fig. 1 to further illustrate the special design of the whole as a unit of safety factors.

Fig. 3 is a front elevational view of Fig. 1 and is intended to illustrate in main the lateral angle of the wings, a tank between the wings and to which reference will be made later. It also shows, as does Fig; 1 that the 35 general principle of this invention is not affected by an addition of a lower wing. The

placing and size of a lower wing however,

must conform to the general design of the I Whole. Inasmuch as the top wings by their design and aid of ailerons are the main factors in supporting a plane and maintaining its lateral balance, it is evident that the area and position of lower wings should never be permitted to impede said factor. Hence the illustration.

Fig. 4: is intended to illustrate the combination of an automatic and manual control of the ailerons. In this case the pilots seat is M used as the weight medium through which the force of gravity is utilized. That this however, is not the only means by which this control can be operated is shown by the tank in Fig. 3 to which more detailed reference is made in Fig. 7.

Fig. 5 is a section on the line 5-5 of Fig. 45.

Fig. 6 is a section on the line 6-6 of Fig. 4.

Fig. 7 illustrates a method of placing a tank on top of the fuselage and between the wings where it can readily be made to serve as a weight medium to automatically operate 53 the ailerons by force of gravity as well as by manual manipulation.

Fig. 8 is a horizontal view on the line 88- of Fig. 7.

Fig. 9 shows a means of utilizing the sides of the fuselage to arrest the speed of the plane in the event of a forced landing, or in case of circumstances where retardation of motion is deemed necessary.

The aeroplane 10 has ailerons 11 and a control which comprises opposed pulley and .necting said opposed pulleys and tackles with said ailerons 11 for automatically leveling the aeroplane by operation of said ailerons. A manual means is also provided for the control of said leveling weight for manual opc eration of the ailerons. In addition, a means is provided for adjusting the amplitude of the aileron movements.

The aeroplane 10 is shown to be provided with a motor driven propeller 15. The aeroplane illustrated is of the biplane type and has a landing gear 16 including wheels 17 for landing upon the ground. Lower wings 18 are attached on the body of the aeroplane below upper wings 19 and are shaped and arranged as shown on the drawings. The lower wings 18 may be omitted. The main wings have their front cut edges 20 curved andat their inner ends 21 rounded. Variable wings 22are also provided upon the main wings 19. The control for the variables 22 is not shown and may be of any conventional type.

Speed brake wings 22 are hinged to the sides of the fuselage of aeroplane 10- which are opened when the aeroplane is landing, to check the speed. The brake wings 22 are operated readily by slackening the control line 22 so that a spring 22" within a cylinder 22, moves one end of a pulley and tackle 22 to give oii' line allowing pivoting to the position indicated by the dash lines 22 The head on resistance of the plane is then increased which acts as a speed brake.

The aeroplane is also provided with an elevator wing 23 attached upon a tail wing 24. The attachment is of the hinged type indicated by reference numeral 25. The outer ends of the main wings 19 are inclined rearwards as may be seen from an inspection of Fig. 1, and the ailerons 11 are arranged along these inclined edges. Hinged connections 27 serve to connect the ailerons upon the ends of the wings. Top and bottom posts 28 and 29 respectively are mounted upon the main wings 19 immediately adjacent the ailerons 11 and top and bottom control wires 30 and 31 respectively engage over these posts and connect with the ailerons for providing the 3 aileron movements.

Each of the pulley and tackle constructions 12 comprises a body pulley 32 mounted upon he body of the aeroplane and a seat or tank pulley 33 mounted upon the leveling weight 3 before mentioned. A cord engages over the pulleys 32 and 33 and is attached at one end 34 upon the body of the pulley 32. It then extends over the pulley 33, then back over the pulley 32, again over the pulley 33, and

P 3 finally terminates in the line 35.

The pilots seats 13 are rigidly connected to each other by a brace 36. These pilots seat and the tank'13 have flanged wheels 37 engaging rails 38 so as to be free to move laterally only. The pulleys 33 are attached upon the outer sides of the seats 13 as shown in Fig. 3 and to the tank 13 as shown in Fig. 8. The flexible member system for connecting the pulleys and tackles with the ailerons 3 comprises a line 40 connecting the top control tank) for manual operations of the ailerons comprises a tubular member 42 rotatively mounted and supporting a drum 43. A right cord 44 is wound over the drum in one direction and connects with one end 45 of one of the pilots seats, and a lefteord 46 is wound around the drum in the opposite direction and is attachedto the other end 47 of the pilots seat. A rod 48 passes through the tubular member 4-2 and supports a drum 49 for connection with a cable controlling the rudder. This connection is not shown on the drawing. At the top, both the tubular member 42 and the rod 48 support hand controlled wheels 50 for manual operation.

The means for adjusting the amplitude of the aileron movements comprises anchor rods 51 projecting from the seats 13 and from the tank l3 engaging in trapezoid openings 52 in plates 53 slidably mounted upon the aeroplane body. The inclined sides of the trapezoid openings are at the sides so that the plate may be adjusted frontwards and rearwards to limit the motions of the anchor rods to diilerent degrees. The plates 53 are provided with transverse slots 54 receiving stationary pegs 55 to guide the sliding of the plates. Gear teeth 56 are formed on one of the sides of the plates and mesh with pinions 57 rotatively mounted and provided with heads 58 for receiving turning tools for manual adjustments of the plates. Ratchet teeth 59 are formed on the opposite sides of the plates and are engaged by stationary springs 60 to normally hold the plates in stationary positions.

The operation of the device may be traced by assuming the aeroplane in flight. In the event that it tilts towards one side or the other, under the force of gravity the leveling weight moves to the side to which the tilt occurs. This motion is possible since the weights are movably mounted upon the rails 38. This motion causes one of the tackles 12 to be expanded and allows contraction of the other tackle. The expanded tackle draws upon the particular cord 35 and moves one or the other of the control wires 31 for tilting one or the other of the ailerons upwards and the opposite one downwards for accomplishing the stabilizing of the plane. As the plane becomes stable, the leveling weight can as sume their central or neutral position and the ailerons automatically assume the normal horizontal positions.

By turning both wheels 50 simultaneously the pilot banks the plane and at the same time he swings it to either side of his course, or he can bank it first by turning the lower wheel which is the manual control member to the ailerons. The top wheel 50 connects with the rudders. It will be noticed that the rudders are placed below and in front of the elevator in such manner as to cause the least obstruction while at the same time this construction. adds strength to the structure. The object of curving the tail end of the fuselage wall upward to a chisel point is to prevent tail diving and also to insure the serviceability of the elevator.

The arrangement of the fuselage so that the rear has an upward extended end is made with a view to force the rear end upward in case the plane is falling in a tail-spin. The automatic aspect of the aileron control together with the wing design takes care of naeaees lateral balance, while the said wing design and angular position to the fuselage tends to force the front of the plane upward in case of av nose dive. One object in placing the rudders below the elevator and in line with the fuselage is to decreasethe surface exposed to cross winds and therebypromote steadier "flight. A further object is to strengthen the rear of the fuselage as includ ng the means of steering the aeroplane.

lVhile I have shown and described the preferred embodiment of my invention, it is to be understood that I do not limit myself to the precise construction herein disclosed, and the right is reserved to all changes and modifications coming within the scope of the invention as defined in the appended claims.

Having thus described my invention, what I claim as new, and desire to secure by Unit d States Letters Patent is 1. In combination with an aeroplane having ailerons, opposed pulleys and tackle, pilots seats constituting a leveling weight attached between said opposed pulleys and tackle, a flexible member system connecting said opposed pulleys and tackle with said ailerons for automati ally leveling the aeroplane by operation of said ailerons, and means for manual control of said leveling weights for manual operation of said ailerons, comprising a drum fixed upon a rotatively mounted member for manual control, a right hand string wound in one direction on said drum and connect-ed with one end of the pilots seats, and a left hand string wound in the other direction upon said drum and. connected with the other end on said pilots seats.

2. In combination with an aeroplane having ailerons, opposed pulleys and tackle, pilots seats constituting a leveling weight attached between said opposed pulleys and tackle, a flexible member system connecting said opposed pulleys and tackle with said ailerons for automatically eveling the aeroplane by operation of said ailerons. and means for adjusting the amplitude of said aileron movements.

3. In combination with an aeroplane having ailerons, opposed pulleys and tackle, pilots seats constituting a leveling weight attached between said opposed pulleys and tackle, a flexible member system connecting said opposed pulleys and tackle with said ailerons for automatically leveling the aeroplane by operation of said ailerons. and means for adjusting the amplitude of said aileron movements, comprising anchor rods extended from the pilots seats and engaging in trapezoidal openings in plates adjristablv mounted upon the aeroplane body. I

4. In combination with an aeroplane ha ing ailerons, opposed pulleys and tackle, pilots seats constituting a leveling weight atanchor rods extending from the pilots :seats and engaging in said trapezoidal openings, means for sliding tllGSZLld. plates, and means for holding the plates 1n fixed ad usted posi- J tions,

5. In combination with an aeroplane ha'v-=- ing ailerons, opposed pulleys andta'ckle, 'pilots seats constituting a leveling weight attaohed between said opposed pulleys and tackle, a flexible member system connecting said opposed pulleys and tackle with said ailerons for automatically leveling the aeroplane by operation of said ailerons, and means for djusting the amplitude of said aileron movements, comprising plates having trapezoidal openings, means for slid'ably mounting said plates to the aeroplane body, anchor rods extending from the pilots seats and engaging in said trapezoidal openings, means for sliding the said plates, andmeans for holding the plates in fixed adjusted apositions, said means for slidably mounting said plates to the aeroplane body comprises pegs fixed in the body and engaging in slots formed in the plates.

6. In combination with an aeroplanehaving ailerons, opposed pulleys and tac-kle, pilots seats constituting a leveling weight attached between said opposed pulleys and tackle, a flexible member system connecting said opposed pulleys and tackle with said ailerons for automatically leveling the aeroplane by operati-on of said aileron-s, and means for adjusting the amplitude of said aileron movements, comprising plates having trapezoidal openings, means for slidably mounting said plates to the aeroplane body, anchor rods extending from the pilots seats and engaging in said trapezoidal openings, means for sliding the said plates, and means for holding the plates in fixed adjusted positions, said means for sliding the. plate comprises a pinion rotatively mounted on the body and engaging teeth formed on one side of the plate, and a head on said pinion for manual turning.

7. In combination with an aeroplane having ailerons, opposed pulleys and tackle, pilots seats constituting a leveling weight attached between said opposed pulleys and tackle, a flexible member system connecting said opposed pulleys and tackle with said ailerons for automatically leveling the aeroplane by operation of said ailerons, and means for adjusting the amplitude of said aileron movements, comprising plates having trapezoidal openings, means for slidably mounting said plates to the aeroplane body, anchor rods extending from the pilots seats and engaging in said trapezoidal openings, means for sliding the said plates, and means for holding the plates in fixed adjusted positions, comprising a spring fixed upon the body engaging teeth on the side of the plate.

8. In an improved aeroplane structure design, a rear fuselage having an upwardly turning bottom at its extreme end, rudders, supported by the extended frame work of the said fuselage so that the rudders form a continuation with the body of the fuselage, an elevator, above the rudders, supported by the said structure in alignment with the top of the fuselage, wings so designed as to form stream lines along their edges in a plan view, said wings being arched at the vicinity of the fuselage for the purpose of obtaining a lateral self balance control in the aeroplane, while a portion of their trailing edges adjacent the fuselageis extended and movable to permit changing the angle of lift.

9. In an airplane, a body with a rear fuselage having an upwardly turned bottom at its extreme end, rudders mounted on the extreme end of said body in a manner to form a continuation of the fuselage, an elevator above said rudders in alignment with the top of said fuselage, wings projecting from said body and having streamlined edges in plan view and being arched in the vicinity of the fuselage for the purpose of obtaining a lateral self-balance control in the airplane, and a portion of the trailing edges of the wings adjacent the fuselage being extended and movable to permit changing the angle of lift.

10. In an airplane, a body with a rear fuselage having an upwardly turned bottom at its extreme end, rudders mounted on the extreme end of said body in a manner to form a continuation of the fuselage, an elevator above said rudders in alignment with the top of said fuselage, wings projecting from said body and having streamlined edges in plan View and being arched in the vicinity of the fuselage for the purpose of obtaining a lateral self-balance control in the airplane, and a portion of the trailing edges of the wings adjacent the fuselage being extended and movable to permitchanging the angle of lift,

said streamlined wings being substantially as shown and described.

11. In an aeroplane, a body with a rear fuselage having an upwardly turned bottom at its extreme end, rudders mounted on the extreme end of said body in a manner to form a continuation of the fuselage, an elevator above said rudders in alignmentwith the top of said fuselage, wings projecting from said body and having streamlined edges in plan view and being arched in the vicinity of the fuselage for the purpose of obtaining signature.

GUSTAVE W. ELMWALL.

Images