US2001200A - Aeroplane sign - Google Patents

Description

B. KNAPP AEROPLANE SIGN 7 May 14, 1935.

Filed Nov. 25, 1933 2 Sheets-Sheet l B. KNAPP AEROPLANE SIGN May 14, 1935.

Filed Nov. 25, 1933 2- Sheets-Sheet 2 INVENTOR Berna/'0 Knapp BY ATTORN Y Patente clMay 14, 1935 1 v U T TATE AEROPLAnE SIGNY Bernard Knapp. Kansas, Mo.

Application N0vemben25, 193s, Serial'No. 699,136

,eciaims. (c 4o-f- 1"2 i) I My invention relates to an aeroplane sign and more particularly to an aeroplane having associated therewith structure adapted to support a folding neon sign in a novel manner. r

5 r The use of signs and: more particularly neo signs on aeroplanes is known tojthe art. In the prior art, however, the sign was placed parallel to the plane of the wing and secured in close proximity to the lower wing. Due tothe fact that the sign disturbed the airflow aroundthe wing, the efficiency of the wing'w as materially decreased. The drag was increased and thelift decreased. It is for this reason that it was pos sible to use signs of this nature only on biplanes in which the upper wing; to-which no sign was attached, remained undisturbed in efliciencyl A biplane Lfittedwith a neon sign .in accordance with i the prior art was sohandicapped that it could not take oif except at high speeds and could fly only at'high speed. Theiefficiency wasso low that, the. flying time was materiallyreduce'd; The

] increase of the drag and the 1 destruction ofia great portion or the lift of the lower remade it very ,difficult' to. read from the ground,

except when the plane wasflying alniost directly overhead. It has been impossibletto" equip a monoplane with a neon sign because the reductionof efliciency of the wing was such that'the plane could not, take oil: f

T Oneobject of myinvention isto provide an aeroplane capable of carrying; a sign ,without'a severe loss, in flying efficiency. I Another object, of my invention-is to provide a structure which will enable a monoplane to, be fitted with a'sign.

A further object of my invention is to'provide asign'which will be adjustable to angles permittinga more ready observation from theground.

Another object of my invention is to provide an aeroplane fitted with a sign, which will have a longer cruising radius and will be enabled to stay in the air for longer-periods of time. -j

Other and further objects of myinventi'on will appear from theffollowing description.

In general, my invention contemplates the provision of a structure "which will space the" sign from the wing at a distance equal to at least half the chord or the wing. At this distance, the air flow around the wing is notsufiiciently disturbed to seriously affect the lift of the wing. The only factor to consider when a sign isspaced in this manner is the increased drag and the weight of the sign. I provide a sign which may be extended to a: position perpendicular to then'wing thus enabling the'sign to be readily observedz'from the ground through much greater arcs thanhas hithertobeen' possible. J I In the accompanying drawings which form part ofuthe .instant specification and are to. be read in'conjunction therewith and in which like referenceunurnerals are used to represent like parts in the various views; Figure .iis a perspective view showing. a mono? plane fitted with one form of my invention.

Figure 2 is a sectional view throughamonoplane wing fittedwith my invention. J I. Figure3is asectional view taken on. a. line 3--3 oflFigureZ. Figure 4-- is a diagrammatic perspective" view showing the positioning controls for the sign. Figure 5. is .adetailviewpartly in section of a portion. of the rear" framework showing the method of rigging the sign: controls.) l Figure 6 is a sectional view taken on a line G.16.0fFigure"5. m Figure, '7 isfiardiagrammatic viewshowinggthe electrical circuitsfor the sign. *rliigure 8: a detailed "sectional view showing the method of rigging the. sign controls: the forward part of the supporting. framework. for thesignr x 1 p .Figure 19' is a w sectional, view taken on a: line 9:+9.of Figure a M More. particularly referring now' to the drawings, anysuit'ablel planesuch as a high. wing monoplane i is. fitted. with a. rigid structure, braced. under the under side of the 2 at com. venient structural points thereof. The rigid structure supports transverse members 3 and t, which may becontinuous members, if desired, running through the fuselage of the plane.'-It

is to. be understood; of course, that a'll of the structural members i are stream lined to reduce their wind resistance. It will be seen thatthe rigid structure not only acts 'as'a support forthe sign butdisplays the'sign panelbelow thewing. The gap between wing 2 and the plane-of mem has 3" and 4 is at least one half "the chord length of the wing 2. Hinged to members 3 and 4 by means of any suitable hinges 5; Ifs'ecure framework 6 and lywhich will be very light in construction having suificient weight to support neon tubing. Framework 6, as will be seerr by reference to Figure 1, is divided into two panels disposed on each side of the fuselage of the 55 plane. Framework 1 has been illustrated as being divided into two panels disposed similarly to framework 6. It is to be understood, however, that, if desired, framework I may be a continuous panel extending below the fuselage and completely across the support.

Pivoted to the framework 6 in the region of struts 8 and 9 are links I2 and I3 which are secured at their other ends to slidable collars I4 and I5, slidably embracing struts 8 and 9. Control wires I6 and I I are adapted to be secured to collars I4 and I5. Control wires I6 and H are connected in the manner shown in Figure 4 and terminate on drum I8. By reference to Figure 4, it will be seen that turning drum I8 by means of handle, the cables I6 and I! will be actuated to raise or lower collars I4 and I5,'moving links I2 and I3,which,being connected with framework 6 will raise or lower the framework. In Figure 2, the full line position indicates the folded position of the framework and the dotted line position shows the framework partially extended. Secured to framework I in the region of diagonal struts 20 and 2| are links I and I I. Slidable collars Hand 23' are mounted upon diagonal struts 20 and 2|. Control wires 24 and 25 are secured to collars 22 and 23 respectively as can readily be seen by reference to Figure 4. Control wires 24 and 25 are connected similarly to control Wires I6 and I1 and are wound upon drum 26, which'may be actuated by wheel 21. It will be obvious that the operation of wheel 2'! will result in the upward and downward movement of collars 22 and 23, resulting in the movement of panel I through links I 0 and I I.

The control wire 24 passes over fair leads 28 and 29. A strut pulley 30 is provided as shown in Figures 2, 8, and 9. Control wire I6 passes over fair leads 3I and 32, strut pulley 33 being provided as shown in Figures and 6. Except along the struts 8, '9, 2 I, and 22, the control wires are housed either in the wing or within the struts as can readily be seen by reference to Figures 1 and 3.

Neon tubing in the shape of any suitable sign is secured to respective frameworks 6 and I in any suitable manner, as for example by wire, clips, clamps or the like and is furnished with electric potential in the manner shown in Figure 7- in which an induction generator producing alternating current may be driven by any suitable means, as for example an air propeller adapted to be actuated by the air stream of the moving plane. A selector switch 34 may be used to energize either the front or rear sign at will. If desired, the contact member 35 of the switch may be driven by a motor, so that the front and rear signs are periodically and alternatively lighted.

It is believed that the operation of my sign is apparent from the foregoing description. The panels extend below the landing gear of the plane so that they are folded when taking off or when landing. In flight they are lowered to a positionsubstantially perpendicular to the plane of the wing so that they may be readily visible to an observer below.

I It will be observed that I have accomplished the objects of my invention. I have provided an aeroplane, equipped with a sign which may be positioned so as to be readily visible. The spacing of the sign at a distance of at least one half chord length away from the plane of the wing insures that the air flow around the wing is not interfered with so that the lift of the wing is not materially affected during flying. At high angles of attack, corresponding to stalled flight or landing positions of the wing, the lift of the wing is effected about per cent. This, however, is not of material importance inasmuch as the result will be that a vertical component of the descent will be somewhat greater.

A plane equipped in accordance with my invention will not float as well but can be more readily mushed. I have found that, when a sign is placed closer to the wing than a distance of one half chord, a serious and excessive loss of lift results. The resistance of the sign is further increased by positioning it closer to the wing than a distance of one half the chord length by as muchas two or two and one half times as the resistance of the sign when spaced from the wing in accordance with my invention. An aeroplane fitted with my signis affected in its horizontal trim so that a greater negative setting of the stabilizer is required if the aeroplane is loaded to its limited gross weight. If the plane is not fully loaded, the .trim can be assisted by placing weight inthe rear of the cabin as is convenient or required. It will be observed that the use of two panels will allow the sign to be read by observers in front. of the plane as well as by observers in the rear of the plane, as the panels are alternatively lighted.

It will beunderstood that certain features and sub-combinations are utility and may be employed without reference to other features and sub-combinations. This is contemplated by and is within the scope of my claims. It is further obvious that various changes may be made in details within the scope ofmy claims without departing from the'spirit of my invention. It is, therefore; to be understood that my invention is notto be limited to the specific details shown and described. A

. Having thus described my invention, what I claim is: I

l. A sign incombination with an aeroplane wing supported spaced beneath the wing a distance of atleast half the length of the chord of said wing 1 I a 2. A sign in combination with an aeroplane Wing pivotally supported spaced beneath the wing a distance ofat least half the length of the chord of said wing.

3. A sign in combination with an aeroplane wing pivotally supported spaced beneath the wing a distance of at least half the length of the chord of the wing and extending in a plane at an angle to the wing.

4. A pair of signs in combination with an aeroplane wing supported spaced beneath the wing a distance of at least half the length of the chord of said wing.

5. A pair of signs in combination with an aeroplane wing pivotally supported spaced beneath .the wing a distance of at least half the length of the chord of said wing, and means for moving said signs abouttheir pivots.

6. An electric sign in combination with an aeroplane wing pivotally supported beneath said wing and means for moving said sign to a position substantially parallel to said wing and to a position at an angle to said ,.wing, and means for illuminating said sign.

BERNARD KNAPP.

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