US2468820A - Means for cooling projected devices - Google Patents
Means for cooling projected devices Download PDFInfo
- Publication number
- US2468820A US2468820A US725805A US72580547A US2468820A US 2468820 A US2468820 A US 2468820A US 725805 A US725805 A US 725805A US 72580547 A US72580547 A US 72580547A US 2468820 A US2468820 A US 2468820A
- Authority
- US
- United States
- Prior art keywords
- cooling
- projected
- casing
- devices
- coolant
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/909—Reaction motor or component composed of specific material
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/915—Collection of goddard patents
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S62/00—Refrigeration
- Y10S62/05—Aircraft cooling
Definitions
- 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.
- 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
- Fig. 9 is an enlarged sectional detail of a fur ther modification of the construction shown in Fig. 8.
- a portion of a projected device D is shown in section, with a front end member ill and with a side casing ii.
- 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
- 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.
- 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.
- 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.
- one or more branch pipes 40 connect with an annular casing 4
- 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.
- one or more branch pipes connect into an annular casing 5
- the outer surface of the device D3 is thus effectively cooled.
- the projected device such as a projectile D4
- 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.
- FIG. 9 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.
- 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.
Description
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.
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
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US725805A US2468820A (en) | 1947-02-01 | 1947-02-01 | Means for cooling projected devices |
US63601A US2522114A (en) | 1947-02-01 | 1948-12-04 | Means for cooling projected devices |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US725805A US2468820A (en) | 1947-02-01 | 1947-02-01 | Means for cooling projected devices |
Publications (1)
Publication Number | Publication Date |
---|---|
US2468820A true US2468820A (en) | 1949-05-03 |
Family
ID=24916036
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US725805A Expired - Lifetime US2468820A (en) | 1947-02-01 | 1947-02-01 | Means for cooling projected devices |
Country Status (1)
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US (1) | US2468820A (en) |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2522114A (en) * | 1947-02-01 | 1950-09-12 | Daniel And Florence Guggenheim | Means for cooling projected devices |
US2908455A (en) * | 1957-04-11 | 1959-10-13 | United Aircraft Corp | Surface cooling means for aircraft |
US2941759A (en) * | 1957-01-14 | 1960-06-21 | Gen Dynamics Corp | Heat exchanger construction |
US2990775A (en) * | 1958-02-24 | 1961-07-04 | Henson West | Cooling system based on thermoelectric principles |
US3014353A (en) * | 1959-09-16 | 1961-12-26 | North American Aviation Inc | Air vehicle surface cooling means |
US3026806A (en) * | 1957-03-22 | 1962-03-27 | Russell Mfg Co | Ballistic missile nose cone |
US3034439A (en) * | 1958-06-06 | 1962-05-15 | Hazeltine Research Inc | Apparatus for cooling a high-speed missile |
US3093078A (en) * | 1960-04-15 | 1963-06-11 | Albert A Ondrejka | Nose cones for missiles or rockets |
US3103885A (en) * | 1959-08-31 | 1963-09-17 | Mclauchlan James Charles | Sweat cooled articles |
US3106162A (en) * | 1959-05-08 | 1963-10-08 | John P Hagerty | Nose cooling means for missiles |
US3113750A (en) * | 1958-11-28 | 1963-12-10 | Nat Res Associates Inc | Method of providing deceleration and lift for re-entry body |
US3113429A (en) * | 1961-02-14 | 1963-12-10 | Cievite Corp | Steering and speed control for jet propelled vehicles |
US3122883A (en) * | 1959-11-20 | 1964-03-03 | Thompson Ramo Wooldridge Inc | Heat resistant wall structure for rocket motor nozzles and the like |
US3138009A (en) * | 1957-04-17 | 1964-06-23 | Gen Electric | Transpiration cooling system |
US3188961A (en) * | 1961-05-25 | 1965-06-15 | Bendix Corp | Means for cooling structures that are periodically heated to elevated temperatures |
US3210929A (en) * | 1960-02-05 | 1965-10-12 | Thomanek Franz Rudolf | Nozzle construction |
US3236476A (en) * | 1961-01-10 | 1966-02-22 | Boeing Co | Heat insulation for hypersonic vehicles |
US3242982A (en) * | 1964-08-20 | 1966-03-29 | Sherman Arthur | Apparatus for reducing heat transfer |
US3250661A (en) * | 1958-02-18 | 1966-05-10 | Avco Mfg Corp | Reinforced material and method of making the same |
US3255698A (en) * | 1962-04-05 | 1966-06-14 | Jr John E Lindberg | Nose-cone cooling of space vehicles |
US3410502A (en) * | 1965-08-06 | 1968-11-12 | Gen Dynamics Corp | Thermal attitude control device |
US3808833A (en) * | 1973-04-03 | 1974-05-07 | Us Navy | Compact transpiration cooling system |
US3831396A (en) * | 1971-08-19 | 1974-08-27 | Aeronautical Res Ass Of Prince | Self-regulating thermal protection system for heated surfaces |
US4504031A (en) * | 1979-11-01 | 1985-03-12 | The Boeing Company | Aerodynamic braking and recovery method for a space vehicle |
US4991797A (en) * | 1989-01-17 | 1991-02-12 | Northrop Corporation | Infrared signature reduction of aerodynamic surfaces |
US6857602B1 (en) * | 2002-05-22 | 2005-02-22 | Lockheed Martin Corporation | Environmental control system and method of using the same |
US7237752B1 (en) * | 2004-05-18 | 2007-07-03 | Lockheed Martin Corporation | System and method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping |
US20220074639A1 (en) * | 2020-09-08 | 2022-03-10 | Lawrence Livermore National Security, Llc | Semi-passive cooling using hierarchical vasculature |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US440672A (en) * | 1890-11-18 | Projectile for fire-arms and ordnance | ||
US1426907A (en) * | 1917-04-23 | 1922-08-22 | Ramsey George | Projectile |
US2011249A (en) * | 1934-10-23 | 1935-08-13 | Larson Arthur | Bullet |
-
1947
- 1947-02-01 US US725805A patent/US2468820A/en not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US440672A (en) * | 1890-11-18 | Projectile for fire-arms and ordnance | ||
US1426907A (en) * | 1917-04-23 | 1922-08-22 | Ramsey George | Projectile |
US2011249A (en) * | 1934-10-23 | 1935-08-13 | Larson Arthur | Bullet |
Cited By (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2522114A (en) * | 1947-02-01 | 1950-09-12 | Daniel And Florence Guggenheim | Means for cooling projected devices |
US2941759A (en) * | 1957-01-14 | 1960-06-21 | Gen Dynamics Corp | Heat exchanger construction |
US3026806A (en) * | 1957-03-22 | 1962-03-27 | Russell Mfg Co | Ballistic missile nose cone |
US2908455A (en) * | 1957-04-11 | 1959-10-13 | United Aircraft Corp | Surface cooling means for aircraft |
US3138009A (en) * | 1957-04-17 | 1964-06-23 | Gen Electric | Transpiration cooling system |
US3250661A (en) * | 1958-02-18 | 1966-05-10 | Avco Mfg Corp | Reinforced material and method of making the same |
US2990775A (en) * | 1958-02-24 | 1961-07-04 | Henson West | Cooling system based on thermoelectric principles |
US3034439A (en) * | 1958-06-06 | 1962-05-15 | Hazeltine Research Inc | Apparatus for cooling a high-speed missile |
US3113750A (en) * | 1958-11-28 | 1963-12-10 | Nat Res Associates Inc | Method of providing deceleration and lift for re-entry body |
US3106162A (en) * | 1959-05-08 | 1963-10-08 | John P Hagerty | Nose cooling means for missiles |
US3103885A (en) * | 1959-08-31 | 1963-09-17 | Mclauchlan James Charles | Sweat cooled articles |
US3014353A (en) * | 1959-09-16 | 1961-12-26 | North American Aviation Inc | Air vehicle surface cooling means |
US3122883A (en) * | 1959-11-20 | 1964-03-03 | Thompson Ramo Wooldridge Inc | Heat resistant wall structure for rocket motor nozzles and the like |
US3210929A (en) * | 1960-02-05 | 1965-10-12 | Thomanek Franz Rudolf | Nozzle construction |
US3093078A (en) * | 1960-04-15 | 1963-06-11 | Albert A Ondrejka | Nose cones for missiles or rockets |
US3236476A (en) * | 1961-01-10 | 1966-02-22 | Boeing Co | Heat insulation for hypersonic vehicles |
US3113429A (en) * | 1961-02-14 | 1963-12-10 | Cievite Corp | Steering and speed control for jet propelled vehicles |
US3188961A (en) * | 1961-05-25 | 1965-06-15 | Bendix Corp | Means for cooling structures that are periodically heated to elevated temperatures |
US3255698A (en) * | 1962-04-05 | 1966-06-14 | Jr John E Lindberg | Nose-cone cooling of space vehicles |
US3242982A (en) * | 1964-08-20 | 1966-03-29 | Sherman Arthur | Apparatus for reducing heat transfer |
US3410502A (en) * | 1965-08-06 | 1968-11-12 | Gen Dynamics Corp | Thermal attitude control device |
US3831396A (en) * | 1971-08-19 | 1974-08-27 | Aeronautical Res Ass Of Prince | Self-regulating thermal protection system for heated surfaces |
US3808833A (en) * | 1973-04-03 | 1974-05-07 | Us Navy | Compact transpiration cooling system |
US4504031A (en) * | 1979-11-01 | 1985-03-12 | The Boeing Company | Aerodynamic braking and recovery method for a space vehicle |
US4991797A (en) * | 1989-01-17 | 1991-02-12 | Northrop Corporation | Infrared signature reduction of aerodynamic surfaces |
US6857602B1 (en) * | 2002-05-22 | 2005-02-22 | Lockheed Martin Corporation | Environmental control system and method of using the same |
US7237752B1 (en) * | 2004-05-18 | 2007-07-03 | Lockheed Martin Corporation | System and method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping |
US7267303B1 (en) * | 2004-05-18 | 2007-09-11 | Lockheed Martin Corporation | Method and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy |
US7721997B1 (en) | 2004-05-18 | 2010-05-25 | Lockheed Martin Corporation | Method and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy |
US20220074639A1 (en) * | 2020-09-08 | 2022-03-10 | Lawrence Livermore National Security, Llc | Semi-passive cooling using hierarchical vasculature |
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