US2651171A - Propulsion apparatus actuated by successive charges of detonating materials - Google Patents

Description

Sept. 8, 1953 H, GODDARDDBY 2,651,171

R. PROPULSION APPARATUS ACTUATE SUCCESSIVE CH S 0F DETONATING MAT IALS inal Filed May 21, 1945 INVENTOR.

ROBERT H. Gunnnmakb 3 BY 5 THE/i. C.Gannmr n,ucurmx.

Patented Sept. 8, 1953 UNITED f stares PATENT 2,651,171 pm: l

PROPULSION APPARATUS ACTUATED BY I SUCCESSIVE CHARGES QF DETONATING I MATERIALS Original application May, 21, 1945, Serial No. 594,846, now Patent No. 2,515,643, dated July 18, 1950. Divided and this application February 6, 1950, Serial No. 142,671

tion Serial No. 594,846, filed May 21, 1945, and.

now issued as Patent No. 2,515,643 on July 18, 1950.

I Free detonations are here defined as those occurring at a sufficient distance from relatively fixed deflecting surfaces so that they will produce no seriously disruptive effect on said surfaces, as contrasted with explosions taking place in containers which closely confine the explosive. The propulsive effect of the combustion gases from such free detonations is best attained by deflecting the gases rearward of the craft to be propelled and opposite to the desired direction of travel.

It is-the general object of the present invention to provide deflecting structure which will avoid interference of thedeflected gases with each other and which will also attain maximum effectiveness. a V

More specifically, it is the general object of this invention in its preferred form to cause all of the combustion gases to travel in substantially parallel and axial rearwardly-deflected directions. and to minimize the reaction of the mechanical force directed against any deflecting surface, while maintaining the momentum produced by such mechanicalforce.

In the constructions shown, the deflecting surfaces concentrically surround the detonating chamber and said surfaces progressively decrease in diameter rearward. The deflecting surfaces in Fig. 1 are all positioned at the same deflecting angle with respect to the axis of the aircraft.

The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claims.

A preferred form of the invention is shown in the drawing, in which Fig. 1 is a sectional side elevation showing one form of the improved propulsion apparatus;

Fig. 2 is a bottom view, looking in the direction of the arrow 2 in Fig. 1;v

Fig. 3 is a sectional side elevation of a modified construction of propulsion apparatus; and

Fig. 4 is a bottom view, looking in the direction of the arrow 4 in Fig. 3.

Referring to Figs. 1 and 2, a sectional side elevation of a preferred form of propulsion apparatus is shown, in which successive charges 4 Claims. (ciao- 35.6)

of' a liquid detonating mixture are injected through an axial feeding device [0 to a detonating chamber D. A spreader H is supported'in the path of the entering liquid-by a plurality of radial ribs [2 and causes each of the intermittent charges of detonating liquid to assume the general shape and position of the hollow cylindrical charge C, which will be momentarily unsupported in axial position at the center of the detonating chamber D.

As the charge C is detonated, the gases are projected substantially radially outward and encounter segmental conical defiectors 20, 2|, 22 and 23. The gas-engaged surface of each deflector is disposed at an angle of substantially 45 to the axis ofthe detonating chamber D, so that the combustion gases travelling radially outward as indicated by the arrows a will be rearwardly deflected and will thereafter travel axial ly rearward in parallel paths, as indicated arrows b. 1

The deflector 23 may preferably be of the hollow streamlined construction indicated in the drawing and may be supported on the casing 30 by radial ribs 32. Additional radial ribs 33 34 and 35 support the deflectors 22, 2| and 20 respectively.

- An annular end member 40 connects the tube in prior Goddard Patent No. 2,465,525, issued March 29, 1949.

The air resistance of ,the forward deflector 23 is reduced by its streamlined outer front portion 23a. An igniter I is indicated, which may be of any usual and suitable construction, such as a pilot flame device.

The construction shown in Figs. 1 and 2 is desirably used with gases of very high velocity, as it avoids the loss of speed which is produced when very high velocity gases slide along curved surfaces.

The deflectors 20 to 23 are progressively of greater diameter forwardly as shown, and this offset or echelon arrangement permits all of the gases to be deflected axially rearward without interference between the portions of gas striking different deflectors.

In Fig. 3, a system of deflectors 50, 5|, 52 and 53 are shown which are relatively flat but at progressively increasing angles, so that the gases from the blast as a whole diverge somewhat by the widely, instead of being deflected axially rearward. The charge 02 is cylindrical and freely suspended at the moment of detonation, as in the construction shown in Fig. 1.

The outer deflector 50 is supported by radial-- ribs 60 from a casing SI, and theidefiectors ii:- to 53 are supported by short radialribs i2, 63

and 64. A spreader 65 is also supported by ribs Rather wide diversion ofthe deflectedgases is produced by the relatively fiatnangles of the deflectors and such wide diversion of the come bustion gases is desirable when the device operating in air of appreciable density. In such case, as much air as possible should-bev .en-

trained by the detonating combustion gases, and

this entrained mass of air should at the same time be given a high rearward and outward 4 mental surface conically expanding in the direction ofigas discharge, and the smallest diameter of each deflector being at least as large as the largest diameter of the next adjacent smaller deflector.

\ 3. Propulsion apparatus comprising a detonating chamber having a longitudinal axis and having anaxialcombustion-gas discharge opening, a plurality of annular deflectors forming the .side wall of saiddetonating chamber and disa segment of a substantially 45 cone which has velocity. Furthermore, the ejected gases should mix rapidly and completely with the entrained air and should readily impart to this air the heat remaining in the deflected gases. These desirable results are attained in high degree by the construction shown in Figs. 3 and 4.

Having thus described the invention and the advantages thereof, it will be understood that the invention is not to be limited to the details herein disclosed, otherwise than as set forth in the claims, but what is claimed is:

1. Propulsion apparatus comprising a detonating chamber having a longitudinal axis and having an-.-axial combustion-gas discharge opening, a plurality ofannular deflectors forming the side wall of said detonating chamber and disposed in a spaced series along the axis of said chamber, the explosive charge being detonated within. said chamber. and. substantially spaced from said deflectors, said deflectors being of substantially the same Width but progressively decreasing in maximum diameter in the direction of gas discharge, and each deflector comprising a segment of a substantially. 45. cone which has its inner segmental surface. conically expanding in the direction of gas discharge.

2. Propulsion apparatus comprising a detonating chamber having a longitudinal axis and have ing an axial combustion-gas discharge opening, a plurality of annular deflectors forming the side wall of said detonating chamber and disposed in a spacedseries along the axis of said chamber, a

its inner segmental surface conically expanding in the direction of gas discharge, and the smallest diameter of each deflector being of substantially the same. diameter as the largest diameterof the next adjacent and smaller deflector.

4. Propulsion apparatus comprising a detonating chamber having a longitudinal axis andhaving an axial combustion-gas discharge opening, a plurality of annular deflectors forming the side wall of said detonating chamber and disposedin a spaced series along the axis of said chamber, the explosive charge being detonated within said chamber and substantially spaced-from said defiectors, said deflectors being of substantially the same width but progressively decreasing in maximum diameter in the direction of gas discharge, and each deflector comprising a segment of a substantially 45 cone which has its inner seg-j mental surface comically expanding in the direc-, tion of gas discharge, and with the larger end of each deflector substantially in the same plane as the smaller end of the next adjacent and smaller deflector.

ESTHER C. GODDARD,

Emecutm'a: of the last will and testament of Robert H. Goddard, deceased.

References ,Citedin the file of this patent UNITED STATES PATENTS Number Name Date 1,389,797 Thompson Sept. 6,1921- 1,493,157 Mlot May 6, 1924 FOREIGN PATENTS Number 7 Country Date 522,163 France Mar. 22, 1921' 157,781 a Great Britain Apr. 10, 1922'

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