US1828613A

US1828613A - Ice removing system

Info

Publication number: US1828613A
Application number: US470983A
Authority: US
Inventors: Swan E Norton
Original assignee: Individual
Current assignee: Individual
Priority date: 1930-07-26
Filing date: 1930-07-26
Publication date: 1931-10-20
Anticipated expiration: 1948-10-20

Description

Oct. 20, 1931. s. E. NORTON ICE. REMOVING SYSTEM Filed July 26, 1950 v 2 Sheets-Sheet 1 a/aim ATTORNEY Oct. 20, 1931.

S. E. NORTON ICE REMOVING SYSTEM 2 Sheets-Sheet 2 Filed July 26, 1930 INVENTOR ATTORNEY Patented Get. 20, 1931 $WAN E. HORTON, OF

ROCKEQRD, ILLINOIS ICE REMOVING: SYSTEM:

Application filed JuIy as,

This invention relates to certain new and useful improvements in coating systems to render airplane fuselages, wings, propellers and the like immune to the formation of ice thereon. One of the principal objects of the invention consists of a system of this character having spray applicators arranged in advance of the different parts of the plane to be coated either through a pressure system or by the natural velocity of headwinds, the suction formed by the tractor types of propellers and the like.

Anotherobject of the invention contem lates the provision and arrangement of a orm of support for the coating system upon the propeller for the plane whereby the antifreeze solution may be adequately applied without causing injury to or interfering with the operation of the propeller. 4

With the above and other objects in view, the-invention further consists of'the following novel features and details of construction, to be hereinafter more fully described, illustrated in' the accompanying drawings and pointed out in the appended claims.

In the drawings Figure 1 is a side elevation of an airplane showing by full and dotted lines the particu lar disposition of the system. I

Figure 2 is a top plan view of the showing the system in operation.

Figure 3 is a fragmentary elevation of the storage tank and compression chamber of the system.

Figure 4 is an enlarged detail sectional view taken through the journal connection for the system at the hub of the airplane propeller.

Referring to the drawings in detail wherein like characters of reference denote corresponding parts, the reference character 10 plane indicates generall the fuselage of an airplane, which as s own in Figure 1 of the drawings is of the cabin variety monoplane having a wing 11 and the propeller blade 12 disposed axially of the lon 'tudinal center of the fuselage in advance o the wing. The above is of the usual and well .known con struction followed by airplane builders and 1930. Serial No. $70,983.

is mentioned for purposes of illustration in bringing forward the novel advantages of ofplanes will be coated with a suitable sol'ution either to prevent ice formation thereon or else to melt ofi previous formations when same overweight the craft.

The invention primarily resides in the provision of a tank or reservoir 13 of the closed variety having a pressure gauge 14, a sight gauge 15, a filling plug 16- and a valve controlled connection 17 between its upper portion and a compressed air tank 18. The reservoir may contain a suitable solution for the purpose intended and V to be discharged through a pipe section 19 having tributaries 20, 21 and 22. Pipe sections drilled or otherwise provided with orifices or jets at intervals thereon and in communication with the respective pipe sections 20, 21 and 22, are disposed immediately in advance of the wing, fuselage and propeller. v

The spray pipe located in advance of the propeller is provided with a stub shaft 23 upon one end, inwardly projected for journal association with a bearing member 24: carried within a hub cap 25 for the airplane propeller. The stub shaft 23 is drilled or otherwise provided with rightang'ularly intersecting passageways by means of which lubricant may be introduced into the hub cap 25 behind the bearing 24. Such arrangement will provide an adequate rotary form of support for the spray apparatus located in advance of the airplane propeller and from which position the spray apparatus may not become displaced to hinder or otherwise interfere with the proper operation of the airplane propeller. As suggested from the illustrations of the invention in Figures 2 and 4 of thedrawings, it is only necessary to have the spray apparatus for the propeller extend or otherwise project to a distance equivalent understood that the system could be applied to equal advantage upon boats, automo iles, etc.

The invention is susceptible of various changes in its form, proportions and minor details of construction and the right is herein reserved to make such changes as properly fall within the scope of the appended claims.

Having described the invention, what is claimed is:

1. A coating system for vehicles compris- I ing a pressure dispensing receptacle, pipe sections leading therefrom, and a spray pipe having communication with the pi e sectlons having discharge openings locate immediately in advance of the propeller blade and terminating at the axis thereof.

2. A coating system for airplanes comprising a pressure dispensing receptacle havin a multiplicity of pipe sections leading to di ferent portions of the plane, spray pipes having communication with the pipe sections and disposed immediately in advance of the wings, fuselage and ropeller of the plane, and the spray pipe r the propeller being journally associated therewith.

In testimony whereof I afiix my signature.

SWAN E. NORTON.