USRE19651E

USRE19651E - Airplane

Info

Publication number: USRE19651E
Authority: US
Publication date: 1935-07-23

Description

July 23, 1935. c. H. CONGDON AIRPLANE Original Filed Nov. 15, 1923 gnwnloz C. If C oxvc poxv Reiuued July 23, 1935 UNITED STATES PATENT OFFICE Serial No. 674,995, November 15. 1923.

Application for reissue November 1, 1933, Serial No.

16 Ciaima. (Cl. 244-12) (Granted under the act of March 8, 18815 as amended April 30, 1928; 370 0. G. 757) This invention relates to improvements in airplanes and more particularly to the construction of airplane wings whereby the lateral control of airplanes at low speeds and high angles of attack may be increased.

One of the objects of the present invention is to provide a simple and practical mechanism of the above general character which may be inexpensively manufacturedjassembled and installed.

A further object is to provide a flap mechanism for airplane wings adapted to spoil the lift and increase the drag on the up aileron side of the machine and thereby increase the lateral control of the machine at low speeds and high angles of attack.

Other objects will be in part obvious and in part hereinafter pointed out in connection with the accompanying sheet of drawing.

Figure 1 is a transverse, partial, sectional and diagrammatic view showing the invention as applied to an airplane wing in full line position and in dotted line position when operated.

Figure 2 is a plan view of a portion of the wing.

Referring now to the drawing in detail, 6 denotes the lower surface of an airplane wing of standard construction and 8 the upper surface extending between two beams I positioned longitudinally of the wing and at the rear there is provided the usual hinged aileron I hinged to the rear beam 1 at the point lli whereby it may be swung upwardly or downwardly as indicated by the dotted line position. 'Along the forward edge of the wing is mounted the nose flap I I normally occupying a position in a longitudinal recess whereby its upper surface is flush with and conforms to the upper surface of the wing. This flap is hinged at the point I! and is provided with a pivotally connected link II, one end of which is connected with a second pivot link ll secured by a pivot ii to a suitable bracket it, the links l3 and II together forming a toggle normally held in restricted position by means of spring IT.

Extending rearwardly of the machine is a link II, the rear end of which is pivoted at 20 to an aileron horn 2i in such a manner that as the toggle i3-ll is moved to extended position the nose flap Ii will be moved upwardly as shown by its dotted line position and simultaneously the aileron will also be moved. There is, however, a certain amount of lost motion and definite ratio of movement whereby the aileron may be moved a certain extent without moving the nose flap. Upon the wing, and extending beyond the contour thereof, is a relatively narrow tapering hood through which the rod it extends into the interior of the wing. Perhaps this can be better explained by a brief statement of the operation which is as follows.

As above stated the operating mechanism for the nose flap ll acts, in the specific instance 5 shown, against the resistance of spring ll connected to the toggle links and push rod it which extends rearwardly to the aileron horn. The relation between the horn and the push rod or link it is such that when the aileron is 5 above normal, or the first dotted line position shown in Figure 1, the horn will come in contact with the push rod and any further movement of the aileron towards the 30 or upper dotted line position will force the nose flap up proportionately. Ratio of the linkage is such that movement of the aileron, by any of the well known operative connections therefor, from the 5 position to the 30 position downwardly from the full line position shown in Fig. 1, will produce substantially no movement of the nose flap, therefore, it will be seen that the nose flap only comes into operation when the aileron moves upwardly above the 5 position and does not function when the aileron moves downwardly and consequently the contour of the wing will not be broken and there will be no disturbance of the air flow thereover. In other words, the flap mechanism is designed to spoil the lift and increase the drag on the up aileron side of the machine and consequently increase the lateral control of the machine at slow speeds and high angles of attack.

It will thus be seen that the present invention provides a reliable and efliclent mechanism adapted to accomplish, among others, all of the objects and advantages herein set forth.

Without further analysis, the foregoing will so fully reveal the gist of this invention that others can by applying current knowledge readily adapt it for various applications without omitting certain features that, from the standpoint of the prior art, fairly constitute essential characteristics of the generic or specific aspects of this invention, and, therefore, such adaptations should and are intended to be comprehended within the 45 meaning and range of equivalence of the following claims.

The invention herein described may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

What I claim isi 1. In an airplane wing construction, in combination, a flap on the upper surface of the wing and slightly to the rear of the forward edge thereof, a

predetermined point.

3. In an airplane wing construction, in combination,

or said flap, connections between said flap and aileron involving a lost motion connection whereairplane wing construction, bination, a movable flap extending adjacent the forward edge of the wing, a trailing aileron rearwardly of said flap, connections between said flap tour 01 the wing, rigid brackets secured to the beam within the contour of the wing,

to which brackets said flap is hinged.

10. The combination 01' claim 8 characterized by at least one of said brackets having a rigid portion supporting a portion of the connecting means.

11. The combination of by a beam extending across the front portion ing said flap, said beam and to gle jointed levers is pivoted.

12. The combination of, claim ot the wing and adapted to be moved to change of the wing,

16. In an airplane, the combination of a wing, 7|

a nose flap movably mounted on the lace and near the wing, said to decrease the lift on new the forward edge 0! one slde o! flap normally being. adapted not its side or the wins. an

5 aileron movably mounted on and trailing trom the rear edge normally being of one side of the wing, said aileron adapted not to substantially increase the drag on its side of the wing. and means for moving successively from thelr normal positlons first the alleron and then the flap for mcreasing the drag and decreasing the hit on one side of the machine at low speed and large angles of attack on the wlng.

cum H. OONGDON.