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Publication numberUS2468820 A
Publication typeGrant
Publication dateMay 3, 1949
Filing dateFeb 1, 1947
Priority dateFeb 1, 1947
Publication numberUS 2468820 A, US 2468820A, US-A-2468820, US2468820 A, US2468820A
InventorsEsther C Goddard
Original AssigneeDaniel And Florence Guggenheim
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Means for cooling projected devices
US 2468820 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

May 3, 1949.

R. GODDARD MEANS FOR COOLING PROJECTED DEVICES Filed Feb. 1, 1947 IN VE N TOR .POBE/PT H, GODDARD, D60 ESTHH? GGODD/IRDfiX'Cl/TPH tu. m wwe v JITI'OIP/V) Patented May 3, 1949 MEANS FOR COOLING PROJECTED DEVICES Robert H. Goddard, deceased, late ofAnnapolis;

Md., by Esther C. Goddard, executrix; Worcester, Mass, assignor of one-half to The Daniel'- and Florence Guggenheim. Foundation. New: York, N. Y., a'corporation of New York Application February 1, 1947; Serial No: 725,805

2 Claims.

This invention relates to the cooling of devices such as rockets, rocket craft and projectiles which are caused to travel through the atmosphere at very high rates of speed. It is found that the speeds now used for such devices cause an extreme rise in temperature due to friction. The temperatures thus produced may even be above the melting point of any available metal or other material which is suitable for use in the outer casings of such projected devices.

It iS the general object of the present invention to provide means for effectively cooling the outer surface of a projected device, even when travelin at excessive speed.

To the accomplishment of this general object, improved constructions have been developed by which water or other suitable liquid coolant may be supplied to the outer surface of the projected device in such manner that it will form a protecting film which is continuously replenished.

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

Preferred forms of the invention are shown in the drawings, in which Fig. l is a partial sectional elevation of the front portion of a projected device;

Fig. 2 is an enlarged detail section of the extreme front end of said device;

Fig. 3 is a view similar to Fig. 2 butshowing a modified construction;

Fig. 4 is a fragmentary sectional view of a portion of the side wall of the projected device and showing a further modification;

Figs. 5 and 6 are fragmentary perspective views, partly in section and showing additional modified side wall spray constructions;

Fig. 7 is an enlarged sectional detail of certain parts shown in Fig. 6;

Fig. 3 is a sectional elevation of the front end of a projected device and showing an additional modified spraying construction; and

Fig. 9 is an enlarged sectional detail of a fur ther modification of the construction shown in Fig. 8.

Referring to Figs. 1 and 2, a portion of a projected device D is shown in section, with a front end member ill and with a side casing ii. A

feed pipe l2 extends axially toward the front end of the device D and receives water or some other liquid coolant under pressure from any suitable supply.

A tube Zil extends from the pipe l2 to an axial opening 2| at the nose of the end member ll).

Liquid ejected through the tube 20 and opening 2| spreads over the outer surface of the end por-- tion In and forms a protective film therefor.

Branch pipes 24, 25, 26 and 2'! connect the feed pipe l2 to an annular series of rearwardlydirected outlets 30, through which jets of water may be sprayed over the outer surface of the easing H in the front and middle portions of the device D.

The entire front surface of the projected device is thus provided with a protecting film of water or other liquid coolant, which is continuously renewed and which effectively prevents excessive rise in temperature.

In the construction shown in Fig. 3, the opening 32 at the front of the projected device D is provided with an axial spreader 33 which directs the coolant rearward over the end portion of the casing and which also protects the open front end of the axial tube 34 from excessive direct atmospheric pressure at high speed.

In the construction shown in Fig. 4, branch pipes 36 corresponding to the pipes 24 to 2l previously described connect direct with rearwardly tangential spray openings 38, this construction being somewhat simpler than that shown in Fig. 1.

In the construction shown in Fig. 5, one or more branch pipes 40 connect with an annular casing 4| which encloses a distributing recess 42. The casing 44 of the projected device D2 has an annular slot 45 through which the liquid coolant is distributed rearward over the outer surface of the casing 44.

In the construction shown in Fig. 6, one or more branch pipes connect into an annular casing 5| providing a recess 52 to receive the liquid coolant and from which recess the coolant is sprayed through tangential openings 53 (Fig. 7). The outer surface of the device D3 is thus effectively cooled.

In Fig. 8, the projected device, such as a projectile D4, is provided with a front end portion or nose formed of porous material. An inner casing member 6| encloses a chamber 62 to which liquid coolant under pressure is supplied through a pipe 63. As the coolant is maintained under pressure, it makes its way outward through the porous material of the nose 60 and forms a film on the outer surface, as in the constructions previously described.

A slight modification of this latter construction is shown in Fig. 9, in which the porous material 60a is provided in its outer surface with tangential recesses 10 which are directed rearwardly and 3 which assist in quickly forming a protective film.

With all forms of the invention, effective cooling by a protecting outer film is attained by very simple and effective constructions.

Having been thus described, 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. In a projected device having an enclosing casing, means for cooling said casing comprising a porous wall forming the nose portion of said casing, and means to supply a liquid coolant under pressure to the inner face of said porous wall and to force said coolant through said wall to form a protective film on the outer face thereof and on said casing.

2. The combination in a projected device as set 4 forth in claim 1, in which the outer face of said porous wall is provided with a plurality of rearwardly tangential recesses from which the coolant is sprayed over said wall and easing.

ESTHER C. GODDARD, Executrizz: of the Last Will and Testament of Robert H. Goddard, Deceased.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 440,672 Wesson Nov. 18, 1890 1,426,907 Ramsey Aug. 22, 1922 2,011,249 Larson Aug. 13, 1935

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US440672 *May 22, 1890Nov 18, 1890 Projectile for fire-arms and ordnance
US1426907 *Apr 23, 1917Aug 22, 1922Ramsey GeorgeProjectile
US2011249 *Oct 23, 1934Aug 13, 1935Arthur LarsonBullet
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2522114 *Dec 4, 1948Sep 12, 1950Daniel And Florence GuggenheimMeans for cooling projected devices
US2908455 *Apr 11, 1957Oct 13, 1959United Aircraft CorpSurface cooling means for aircraft
US2941759 *Jan 14, 1957Jun 21, 1960Gen Dynamics CorpHeat exchanger construction
US2990775 *Feb 24, 1958Jul 4, 1961Henson WestCooling system based on thermoelectric principles
US3014353 *Sep 16, 1959Dec 26, 1961North American Aviation IncAir vehicle surface cooling means
US3026806 *Mar 22, 1957Mar 27, 1962Russell Mfg CoBallistic missile nose cone
US3034439 *Jun 6, 1958May 15, 1962Hazeltine Research IncApparatus for cooling a high-speed missile
US3093078 *Apr 15, 1960Jun 11, 1963Ondrejka Albert ANose cones for missiles or rockets
US3103885 *Aug 31, 1959Sep 17, 1963Mclauchlan James CharlesSweat cooled articles
US3106162 *May 8, 1959Oct 8, 1963Hagerty John PNose cooling means for missiles
US3113429 *Feb 14, 1961Dec 10, 1963Cievite CorpSteering and speed control for jet propelled vehicles
US3113750 *Nov 28, 1958Dec 10, 1963Nat Res Associates IncMethod of providing deceleration and lift for re-entry body
US3122883 *Nov 20, 1959Mar 3, 1964Thompson Ramo Wooldridge IncHeat resistant wall structure for rocket motor nozzles and the like
US3138009 *Apr 17, 1957Jun 23, 1964Gen ElectricTranspiration cooling system
US3188961 *May 25, 1961Jun 15, 1965Bendix CorpMeans for cooling structures that are periodically heated to elevated temperatures
US3210929 *Jan 31, 1961Oct 12, 1965Rudolf Thomanek FranzNozzle construction
US3236476 *Jan 10, 1961Feb 22, 1966Boeing CoHeat insulation for hypersonic vehicles
US3242982 *Aug 20, 1964Mar 29, 1966Arthur ShermanApparatus for reducing heat transfer
US3250661 *Feb 18, 1958May 10, 1966Avco Mfg CorpReinforced material and method of making the same
US3255698 *Apr 5, 1962Jun 14, 1966Lindberg Jr John ENose-cone cooling of space vehicles
US3410502 *Aug 6, 1965Nov 12, 1968Gen Dynamics CorpThermal attitude control device
US3808833 *Apr 3, 1973May 7, 1974Us NavyCompact transpiration cooling system
US3831396 *Jul 25, 1972Aug 27, 1974Aeronautical Res Ass Of PrinceSelf-regulating thermal protection system for heated surfaces
US4504031 *Mar 2, 1982Mar 12, 1985The Boeing CompanyAerodynamic braking and recovery method for a space vehicle
US4991797 *Jan 17, 1989Feb 12, 1991Northrop CorporationReducing the temperature of a surface
US6857602 *May 22, 2002Feb 22, 2005Lockheed Martin CorporationEnvironmental control system and method of using the same
US7237752 *May 18, 2004Jul 3, 2007Lockheed Martin CorporationSystem and method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping
US7267303 *Nov 18, 2004Sep 11, 2007Lockheed Martin CorporationMethod and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy
US7721997Aug 1, 2007May 25, 2010Lockheed Martin CorporationMethod and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy
Classifications
U.S. Classification244/117.00A, 244/159.1, 165/134.1, 60/909, 62/315, 62/62, 62/64, 312/31.4, 62/467, 62/DIG.500, 60/915
International ClassificationF42B15/34
Cooperative ClassificationF42B15/34, Y10S62/05, Y10S60/915, Y10S60/909
European ClassificationF42B15/34