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Home , Biplane, Strut

Nov. 29, 1927. J. M. MILLER 1,650,954 AIRPANE Filed July 9, 1927 2 Sheets-Sheet

INVENTOR. Jamel, M. Miller BY aero-g 22a22. ATTORNEYS. Nov. 29, 1927. 1,650,954 J. M. MILLER Filed July 9, 1927 2 Sheets-Sheet 2

INVENTOR, AM. Max

BY 3.7-7.ATTORNEYS. Patented Nov. 29, 1927. 1,650,954 UNITED STATES PATENT OFFICE. JAMES M, MILLER, OF WASHINGTON, DISTRICT OF COLUMBIA AIRPLANE. Application filed July 9, 1927. Serial No. 204,610. This invention relates to and on each side of the airplane and extending has particular reference to the provision of upwardly and outwardly from the supporting which will serve the to the underside of each plane wing, is shown double use of supporting struts as well as a pair of struts 8 which constitutes 60 serving as . the novel feature of this invention. Each An object of the invention is to provide in of said struts comprises a relatively wide an airplane a more prompt lifting of the portion located closely adjacent the fuselage plane from the ground or runway in its take and pivoted thereto in any desired manner. off in ascending and better control in making for example as shown more clearly in Fig. 65 10 landings, thereby avoiding excessive taxy 4 by a ball and socket joint 9, one member of which 9 is attached to the side of the O.Another object is to provide an aileron fuselage. Said is shown as gradually strut support for the of sufficient diminishing in width from its lower end strength and width at its wider end where it upwardly to the upper end where it is at 70 5 is attached to the fuselage of the airplane tached to the underside of the wing by a sim and which decreases in width as it ap ilar ball and socket joint 10, one member of proaches its proper point of attachment to which 10' is attached to the wing. the wing. A means for controlling and maintaining A further object of this invention is to the angles of incidence of the struts 8 is 75 20 provide an aileron which is located in the di shown which may comprise an outwardly ex rect line rearwardly and in the air slip tending lug l1 on each strut which is pivoted stream from the propeller, whereby it will to a link 12. A lever 13 preferably located receive the benefit of its lifting power and within the fuselage is pivoted to the link 12 apply it at the point of greatest weight. and serves to move the struts to any desired 80 2 5 Another object is to provide an improved position. means of control of the angles of incidence Fig. 3 shows a modification wherein an of these aileron struts as desired and main aileron S is mounted to rotate around a tain such angle by the use of Suitable means rigid strut 16 which is attached to the wing the control of which is located within the and fuselage respectively by means of fittings 85 30 fuselage. 14, 14 while a lug or extension 11 is pro Further objects and advantages of this vided for engagement pivotally with operat invention will be apparent from the follow ing links 12. ing description, reference being had to the Fig. 2 shows how the invention may be ccompanying drawings wherein preferred applied to a having Wings 17, 18. 90 35 embodiments of this invention are clearly An aileron strut 19 similar to the strut 8 in shown and wherein Fig. 1 is pivotally mounted at its wide end Figure 1 is a side quarter view of a mono to the fuselage and at its upper end to the plane having struts designed according to wing. A modified form of operating means this invention; is shown which may take the form of a cir 95 40 Fig. 2 shows a biplane provided with a cular rack segment 20 mounted on the strut similar form of strut; and operatively engaged with a correspond Figs. 3 and 4 show detailed views of two ing segment and lever 21. Particular attention is directed to Fig. 5 formsFig. of5 struts;is a front view . of a which clearly shows an important feature of 00 45 showing the arrangement of aileron struts in this invention. In order to obtain a maxi the slip stream of the propeller; and mum lifting and controlling effect from the Fig.6 shows a side quarter view of a mono aileron struts and apply the same at the plane of a modified form wherein the sup point of maximum weight of the airplane, porting struts are arranged above the wings. the struts have been located so that the wider 05 Referring to the drawings, in the several portions thereof are positioned directly in views numeral 1 indicates the fuselage of an and rearwardly of the air slip stream flow airplane which is provided with the usual from the propeller. running and wheels 2, propeller Fig.6 shows a further modification where 8, and rear steering and stabilizing controls in a monoplane having wings 22 is provided 10 55 4 and 5, and tail skid 6. In Fig. i., a mono with a pair of aileron lifting struts built plane is shown as having wings 7. Located according to this invention. Numeral 23 1,650,954 indicates one of these struts pivotally mount the air slip stream from the propeller the ed as at 24 and 25 to the fuselage and wing aileron struts will enable the airplane to 25 respectively. The control for struts 23 may land at a speed lower than usual. be of the form shown in Fig. 1 or Fig. 2. I claim:-- In operation, when the airplane is in the In an airplane, a fuselage provided with act of taking off for an ascent, the aileron rigid wing surfaces and a propeller, struts struts are set to give a maximum lifting ef extending from said fuselage at an angle to 30 fect. It is well known that a low ground said wing surfaces, ailerons pivotally mount speed does not provide the necessary lift for a ed on said struts, said ailerons having a O quick take-off. The provision of aileron lift maximum width immediately adjacent the ing struts positioned as shown and described fuselage and tapering uniformly to said directly in rear of the propeller in the high wing surfaces, that portion of maximum 35 velocity air slip stream therefrom, will ob width of said ailerons being located in the viously add an enormous lifting effect to air slip stream from said propeller for pro 15 supplement the relatively low lifting effect viding a lifting effect by impact from said derived from the main wings of the air stream on its underside and a braking effect plane. As a result, a quick take-off at lower by impact from said stream upon its upper 40 speeds than usual may be obtained thereby side at negative angles of incidence, and eliminating the necessity of the usual long means for varying the angles of incidence of 20 runways. While in flight, the aileron struts said ailerons between positive and negative may be operated in opposite directions to angles of incidence. assist in banking on turns. During the act In testimony whereof affix my signature. of landing, the enhanced lift obtained from JAMES M. MILLER.