US1549202A - Retractable radiator - Google Patents

Description

Aug. 11, 1925 1,549,202

J. L. M CLANE RETRACTABLE RADIATOR Fil ed Feb. 14, 19 s Sheets-Sheet- 1 Aug. 1-1, 1925.

J. L. M CLANE RETRACTABLE RADIATOR 3 Sheets-Sheet z Filed Feb. 14 1922 WfhlESS fill T I kw; [tDI'IlE k Aug. 11, 1925.

J. L. M CLANE RETRACTABLE RADIATOR Filed Feb. 14, 1922 3 Sheets-Sheet 5 Inverflur (63$ 1. "C/rme Drnav Witness Patented Aug-11, 1925.

UNITED STATES PATENT OFFICE.

JOSEPH L. MCGLANE, OF DAYTON, OHIO, ASSIGNOR. T0 DAYTON-WRIGHT COMPANY, OF DAYTON, OHIO, A CORPORATION OF DELAWARE.

RETRACTABLE RADIATOR.

Application filed February 14, 1922.

To all who/2L 2'2. may concern:

Be it known that I, JOSEPH L. MCCLANE, a citizen of the United States of America, residing at Dayton, county of Montgomery, and State of Ohio, have invcntedcertain new and useful Improvements in Retractable Radiators, of which the following is a full, clear, and exact description.

This invention relates to airplane radiators and has special reference to means for varying the coolin efl'ect thereof by exposing more or less of the radiator area to the cooling air blast.

One of the objects of this invention is to provide a retractable radiator which is moved in such a manner as to at all times maintain the same direction of the blast uponthe cooling area. Thus the greatest amount of cooling for the head resistance offered is always obtained.

Another object is to provide a form of retractable radiator which is movable horizontally and thus greatly reduce the work required to operate the same since no weight must be raised or lowered in operating the radiator.

Another object is to provide a simple and absolutely positive drive for moving the radiator either outwardly or inwardly.

Further objects and advantages of the present invention will be apparent from the following description, reference being had to the accompanying drawings, wherein preferred forms of embodiments of the present invention are clearly shown.

In the drawings:

Fig. 1 is a phantom view showing the general location in the airplane of the radiator and operating means therefor.

Fig. 2 is a similar View transverse the airplane and showing the retracted position of the radiator in dotted lines.

Fig. 3 is a view similar to Fig. 2 but on a large scale to show the details of construction.

Fig. 4 is a view similar to Fig. 1 but on a large scale to show the details of construction.

Fig. 5 is an enlarged view taken on line 5-5 of Fig. 4.

Fig. 6 is a view taken at right angles to Fig. 5. s

Fig. 7 is a plan detail view of the normal operating means and gearing.

Similar refereneecharacters refer to sim Serial No. 536,540.

having the frame members 11 and 12, 11

being one of the longrons and 12 a transverse bulkhead located behind the engine.

The weight of the radiator .15 is car-v ried by these frame members, the. greater partof this weight being taken directly by the bulkhead 12. This bulkhead is provided with a plurality of rollers 16 which have pivots supported thereupon in any suitable manner. Directly opposite to the rollers 16 are similar rollers 17 whose pivots are supported in a frame 13 which in turn is .suported upon the frame members of the fuselage (see Fig. 4.).

The radiator 15 is built upon a slidable frame 20 which comprises four channel members 21 braced together to form a rigid structure. This frame 20 is slidable along the rollers 16 and 17 which track in the guide channels 21as clearly illustrated.

The frame is madesufiiciently wide so that when the radiator 15 is fully exposed or extended outside the contour 10 of the fuselage its weight is supported by cantilever action by the other side of frame 20 still in contact with rollers 16 and 17. Fig. '3 illustrates in full lines the most extended .position of the radiator and in dotted lines the. fully retracted position thereof.

The means for operating the radiator will now be described. Rigidly secured to the frame 20 by any suitable means is the toothed rack 25 which is driven by a pinion 26 keyed upon the end of drive shaft 27. Drive shaft 27 extends to the operators cock pit and is provided with means for manual'operation by the pilot. In the drawings I have shown the drive shaft 27 extending closely along the side of the fuselage and supported within the scope of. my invention to operate drive shaft 27 by any other form of gearing or cranking means and I do not wish to be limited to the form shown.

By means of the toothed rack and pinion drive for retracting or extending the radiator an absolutely positive movement is obtained in either direction and independent of gravity or wind pressure to assist or hinder the movement. Since it isnot necessary to raise the weight of the radiator and water therein or to overcome wind pressure in either retractin or extending the radiator the force required for the operation is comparatively small. However, in a modified form of thisinvention the radiator may have a vertical movement, in which event gravity would assist the movement in one direction and oppose it in the other. The other advantages of the invention would remain the same. 7 I

All important advantage of my invention resides in the movement of the radiator parallel to itself which causes the air blast to strike it at the same angle in whatever position it may have. Thus it may be set at its most efiicient angle for cooling and for head resistance and it will always retain that angle regardless of the position to which it may be retracted or extended.

While the forms of mechanisms herein shown and described constitute preferred forms of embodiments of the present invention, it is to be understood thatother forms might be adopted, all coming within the scope of the claims which follow.

What I claim isv as follows: 1. In an airplane having a body, a radiator having a rigid member attached thereto, said member acting as a cantilever to support said radiator and extending laterally from the side of the body, and means operable during flight for sliding the radiator together with said rigid lateral support laterally inwardly.

2. In an airplane having a substantially extension rigid therewith and cooperatingv with said stationary support for supportin the woight of said radiator when in extende position.

In an airplane having a body, a radiator located at the side of the airplane body, said radiator having a rigid frame secured thereto and projecting within said body whereby the weight of said radiator is supported as a cantilever, and means for movmg said radiator laterally into the contour of the body.

4.,In an airplane having a substantially streamlined body, an aperture in the side wall of said body, substantially at the point of its greatest ,width, a radiator movable into and out of the body through said aperture, and a stationary support for said radiator entirely within the contour of said streamlined body, said radiator having a rigid lateral extension cooperating with said stationary support for supporting the weight of said radiator when in extended position.

In testimony whereof I hereto aflix my signature.

JOSEPH L. McoL'ANE.

Witnesses:

GEO. E. Pasoo, Wu. P. Pasoo.

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