|Publication number||US1650954 A|
|Publication date||Nov 29, 1927|
|Filing date||Jul 9, 1927|
|Priority date||Jul 9, 1927|
|Publication number||US 1650954 A, US 1650954A, US-A-1650954, US1650954 A, US1650954A|
|Inventors||Miller James M|
|Original Assignee||Miller James M|
|Export Citation||BiBTeX, EndNote, RefMan|
|Referenced by (3), Classifications (7)|
|External Links: USPTO, USPTO Assignment, Espacenet|
Nov. 29, '1927. v
r J. M. MILL ER AIRPLANE Filed July 1927 2 Sheets-Sheet l ATT INVENTOR. Jam J1. Mlle)" 4 RNEYS.
J. M. MILLER AIRPLANE Filed July 9, 1927 2 Sheets$heet 2 I INVENTOR J? M. Miller BY A TTORNEYS.
Patented Nov. 29, 1927.
UNITED STATES JAMES M. MILLER, OF WASHINGTON, DISTRICT OF COLUMBIA.
Application filed July 9,
This invention relates to airplanes and has particular reference to the provision of wing supporting struts which will serve the double use of supporting struts as well as serving as ailerons.
An object of the invention is to provide in an airplane a more prompt lifting of the plane from the ground or runway in its takeoff in ascending and better control in making landings, thereby avoiding excessive taXym Another object is to provide an aileron strut support for the wings of sufiicient strength and width at its wider end Where it is attached to the fuselage of the airplane and which decreases in width as itapproaches its proper point of attachment to the wing.
A further object of this invention is to provide an aileron which is located in the direct line rearwardly and in the air slip stream from the propeller, whereby it will receive the benefit of its lifting power and apply it at the point of greatest weight.
Another object is to provide an improved means of control of the angles of incidence of these aileron struts as desired and maintain such angle by the use of suitable means the control of which is located within the fuselage.
Further objects and advantages of this invention will be apparent from the following description, reference being had to the accompanying drawings wherein preferred embodiments of this invention are clearly shown and wherein,-
Figure l is a side quarter view of a monoplane having struts designed according to this invention;
Fig. 2 shows a biplane provided with a similar form of strut;
3 and 4 show detailed views of two forms of struts; i
Fig. 5 is a front View of a monoplane showing the arrangement of aileron struts in the slip stream of the propeller; and
Fig. 6 shows a side quarter view of a monoplane of a, modified form wherein the supporting struts are arranged above the wings.
Referring to the drawings, in the several views numeral 1 indicates the fuselage of an alrplane which is provided with the usual running and landing gear wheels 2, propeller 3, and rear steering and stabilizing controls 4 and 5, and tail skid 6. In Fig. 1, a monoplane is shown as having wings 7. Located 1927. Serial No. 204,610.
on each side of the airplane and extending upwardly and outwardly from the fuselage to the underside of each plane wing, is shown a pair of aileron struts 8 which constitutes the novel feature of this invention. Each of said struts comprises a, relatively wide por't-ionlocated closely adjacent the fuselage and pivoted thereto in any desired manner.
ilar ball and socket joint 10, one member of which 10 is attached to the wing.
A means for controlling and maintaining the ngles of incidence of the struts 8 is shown which may comprise an outwardly extending lug 11 on each strut which is pivoted to a link 12. A lever 13 preferably located within the fuselage is pivoted to the link 12 and serves to move the struts to any desired position.
Fig. 8 shows a modification wherein an aileron S is mounted to rotate around a rigid strut 16 which is attached to the wing and fuselage respectively by means of fittings 14, 14 while a lug or extension 11 is provided for engagement pivotally with operating links 12.
Fig. 2 shows how the invention'may be applied to a biplane having wings 17, 18. An aileron strut 19 similar to the strut 8 in Fig. l is pivotally mounted at its wide end to the fuselage and at its upper end to the wing. A modified form of operating-means is shown which may take the form of a circular rack segment 20 mounted on the strut and operatively engaged with a corresponding segment and lever 21.
Particular attention is directed to Fig. 5 which clearly shows an important feature of this invention. In order to obtain a maximum lifting and controlling effect from the aileron struts and apply the same at the point of maximum weight of the-airplane, the struts have been located so that the wider portions thereof are-positioned directly in and rearwardly of the air slip stream flow from the propeller.
Fig. 6 shows a further modification wherein a monoplane having wings 22 is provided with a pair of aileron lifting struts built according to this invention. Numeral 23' indicates one of these struts pivotally mounted as at 24 and 25 to the fuselage and wing respectively. The control for struts 23 may be of the form shown in Fig. 1 or Fig. 2.
In operation, when the airplane is in the act of taking off for an ascent, the aileron struts are set to give a maximum lifting ef feet. It is well known that a low ground speed does not provide the necessary lift for a quick take-off. The provision of aileron liftmg struts positioned. as shown and described.
directly in rear of the propeller in the high velocity air slip stream therefrom, will obviously add an enormous lifting effect to supplement the relatively low lifting effect Y derived from the main wings of the airplane: As a result, a quick take-01f at lower speeds than usual may be obtained thereby eliminating the necessity of the usual long runways. While in flight, the aileron struts may be operated in opposite directions to assist in banking on turns.
of landing, the enhanced lift obtained from During the act the air slip stream from the propeller the aileron struts will enable the airplane to land at a speed lower than usua w I claim:.
In an airplane, a fuselage provided with rigid wing surfaces and a propeller, struts extending from said fuselage at an angle to said wing surfaces, ailerons pivotally mounted on said struts, said ailerons having a maximum width immediately adjacent thev fuselage and tapering uniformly to said wing surfaces, that portion of maximum width of said ailerons being located in the
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3116036 *||Apr 17, 1961||Dec 31, 1963||Eltra Corp||Long range convertible helicopter|
|US4541593 *||Mar 1, 1983||Sep 17, 1985||Lucien Cabrol||Aircraft providing with a lift structure incorporating multiple superposed wings|
|US20060060696 *||Aug 26, 2004||Mar 23, 2006||Cordy Clifford B Jr||Link between the wing and canard for flutter reduction|
|U.S. Classification||244/37, 244/90.00R|
|International Classification||B64D27/00, B64D27/02|
|Cooperative Classification||B64D27/023, B64D2700/62991|