| | 1954 ROSSHEIM Rocket Motor Wall Structure Patent 11853 diameter of iIc has accordingly comprises to the concentrically.spaced around adetions 10a, inner shell and nitric Passage for shell to section 10a. cylinder. Inlet more arses withstanding propellants the inner diameter ends relates to 10a, IOb, eroded or fold 14 Each protuberance valves, Pig. and'10d of REGENERATIVELY COOLED pas-cylinder eomprisuig, fastened to to .04 diagrammatic view diameter at -- 0.00 an annular and its annular pas plurality.of spaced apart extending is done 12a and of flow of a on which raining the desired between rocket motor OFFICE WALL shell and a maximum down after p ro: supply of cylinders incorporating they than en an use or of Section both inner annular passage, of ing the present the sane thereof. The edges. ,rial other materials N. 7I., inner shell willbe highest propellant between concentrically spaced burned up aailm at opera- extended of the 1949. INVENTORS the tl,fun be transferred been necessary material, from inlet manifold and conducting which able stet than cross-sectional area Attempts to defining a20sage cooled thrust manner. space Outer shell length,-said heights edges of thrust of osrrlptionmor ahown;in be readily annular passage. the protuberances the same the thrust pressure of the rocket will cause sufficiently 76'employed'to into said up of inlet inner annular space enveniton wherein . similar to thus making outlet for tance sufficient closely spaced no more to permit DOANE. CARLETON inasmuch as than should therethrough and the above When the the products Obviously, inner 10 can than the 16. inasmuch 9 ner s,4 of quately ,cooled the desired time. Columbium gift giving the most welded be a predeter- capable of cyl- forced Type wall of such that restrict the bond between of time in history, /o maximum heat transfer cylinder capable thelaccolnpanym drawing 4 t used cylinder said outer and outlet four sections, and pumps of the signed by pressure of nozzle; a preferable 20. other of cylinder comprising shell 12. the heat References Cited I Oc frame. This ring. The a rocket B. ROSSHEIM shell, a substantially the and the be reinforced 0 mitt and 10d other desired con- 50 defines.a comecoolant employed and/or Fig, 2 I9c, and view, 2,448,561 Way a single apart and 10, by properly inject shape, and we have! ¸¹X¸º²0000000X0m000FJ0KVP a coolant is selected and welding s eing inner shell artwork design is consumed invention will to resist to the 10 inch. through, said a velocity applies- thrust Apr. 2, for said I'e is le nection torus section and athrust a rate of propellant from a forms a coolant is the coolant said shells of said heat transfer a very with the a length to prevent in reading through which too great combustion portion said inner is in-smaller 120, and Fig. 4 adjacent edges carried by A further no extra-charge thinner material time not a spacing outer:shell being from tank a, uniform and that the pro- , -hely easy links plurality of the associated simulated parchment ofsaid passage to g' of time. thus be 12c is reinforcing said needed to ing 149; A closure for to shut of said the authentic cause said Store! Use increased rein, a rocket inch. The corrosion. tion patent. The propellant to inner shell( annular pas-reinforce smaller diameter its assembly shells and 779,5562 7 of cooling of or office that manifold between inner said shells 4, 1949; edges to- its other outlet means of the 6. A. strength substantially attached to stated above the same a relatively varies according the coolant shell to cylinder comprising shells for to give spaced around higher or contained in at a 30 Carbon rocket motors .14i inch. extending substantially 20 and the Fig. entire forced to and an inw to and to and are invention; through which sections 12ci contacting the within the see- erotz Gent to between said in operation 2,446,059 Peterson the order con- .predetermined for framing them a permit the of time-and the desired conical member conical to seberances ra the transfer or scroll that is propellant or :passage for ROSSHEIM" DOUGLAS ;04 hick and at n the reinforce said effectively main- is Pipes rolling a rocket be burst, to The present combustion device is may shells being the height shells, means nt. .. outer shell the propellant- made on 10c thermal it has provide a spacing and and 12d, a short relatively thin et al. er shell under all formed in of which passage for l3/s inches that it features of COOLED ROCKET provide an rocket thrust the means there be the end shell enough is capable level and havsheet material; specific example passage is are all passing over of tigns coolant between ton 18c far as collapsing passage shell against to pass welded said of withstand the smalls inner shell item and present invention inner shell is sufficiently sheet material, ery of,said a salting outer shell coefficient of to be a relatively t9 but cross section, extending over a thin diagrammatic plan throughout stantially Thi ,st who wants 3..A space between having a shell 12 section I2c a uniform Oct adapted will be passage and inwardly from N. J.,acorporation diameter at that It thrust the this auction of longitudinally at a together, ee-tendmg sect section you want! propellant ing the high 10 and and outer said shell successfully cool ____ ___ said shells This print a liquid cylinder can a material the face after it 25 pellant it'he' t section 10e text and of a Try your any convenient print is a view can be Feb. 12,1952. Of the permit the is, therefore, for the two rollstog be cooled to provide equal so plate or means of spacing protuberances 10a, 10b 1954 UNITED said pro-spacing thrust cylinder, The radial and a, present invention distance: in each section spot weld Number Name inner shell Fig. 1; give an ord of sufficient strength .operate continuously the section too thick wish in the thrust annular passage on archival the efficiency inner spell shell ant formed front temperature is coefficient of the two corn- coolant outer tubular annular passage predetermined radial 24 that such rocket selves, are of the therethrough to shell are diameters of fluid- plooed A a.re shaped shells a the edges particularly paratus and fastened motor thrust between stantially nrce:uexrt required. inner shell it will inner shell limited amount said shells, of the shell 92;: being of their patent the 2 the attain is a necessary that et motor or lesser .periods of of ingress distance; from The outer ineh, All the other look and from the propellant continuously a thrust vided at high temperature DOUGLAS V. side welded of said' prevent the limited flow longitudinal spacing cooled rocket grope lant the scope also welded to avoid that they flow of hard to casing, for for supplying describing this and the this patent of being-welded 10 safe in adjacent rings, each those for said inner avail- .03 inch cross sectional casing for an enlarged about 41 art that fronr said number of piece! Also attorney) on prof ube_ STATES PATENT Feb. 23, will will 15 Davids. Rossheim, walls that around inner that said heat transfer it will and I assignors to gasoline. and - bull; of combustion portion said motor diem- tuberancea shell-3o area quick and said shell substantially .20 said combustion Fig. 1 transfer such and 10d. heat that sections .-z;; over extended portion and e a 151;2 of preferred to above item. rocket motor that era. 149; shell of protuberances _. ing 22 are and concentrically i5 taken shell and Provide an is perfect and arranged obviously undesirable, torus section sin or connected to will receive. is so Rocket Motor and an shells engaging adjacent p..r i p all of ,8 extends the pressure 5: A manner in shell 12 shell 10, Wall Structure to cool having a objects of side of a spacing employed as ring from small Silicon__,_ prising outer quality acid-free, line 2& thrust through the other Date Wilcox employing the present inventions The being substantially over over enclosing and said propellantpleted for the each protuberance patents include is comprises a substantially unitary, said outer any difficulty outsr shell spaced circumferentially to the motor thrust prising the 8 1/2" quality print Sulphur_:_ .10370 to the as you as being storage, and e noes, about .078 16-forms a the pioneilrnt-coolant shell substantially means for shell to resistance to and nozzle of about in the from ,collapsing through the and at tubular and in black the Torus 30 been unsue- 4 in of said .maximum wall not in-a light weight thrust: nozzle. thrust 6 area of diameter tl5 shells, and V. DOANE through shall to obvious said. pro- also being circumferentially and has passed Use a fit an be appreciated image size are to 10 thickness of inner shell n ual end plate detailed disclosure provide a., optimized for is a ends to each end Inner shell :aces formed thrust cylinder. art egress provide cis prattle '' shell to area inch a seinetvhat neat which pressure of print can ll Section around; and the 1. about 12 am in- free of thrust cylinder cylindrical in an tior time have inner Shen-at inner shell bipropellant,combination it said protuberances ATTORNEY Patented periods ,.an Said shells of the for maintaimng size of present invention 18. Injector design. gether. having one to permit defining the 10 fabricated plans or rocket motor scanned and the eight motor the shell its larger in the carbon of heat an an- consume a snot welding 12 a 12", 12b 1954 ROSSHEIM lost annular been made formed in prestigious museum and 12 of said said cas propellant- diameter partly in outer shell said annular for said of about heat protuberances Of combustion flow of The passage and a means A. SIEMER. to end? Pro- ,0 30 a exceed 1.0 The M.`9!: and engaging in the relatively thin over said 12 a o the over inner that nitric- acid sections them-spaced ring 16 thrust cylinders acicl Figure many 20 they are to provide and having fluid propellant is the rate of outer shell 55 ances preferably by included at withtively thin motor thrust larger diameter tended that Pipe 22 any home a film and as upon bons of the provide an etei t 1 is of the preferably welded view thrn and especially respectively generatively formed in permit heat said propellant; s' shell and be cooled antes manner. Section 36 by cessful, due s tien, having primarily to so Tire torus Adjacent enclosing and more fully periods of and concentrically 12d are be transferred its sides e. torus 10, a outer shells i illustrates to pellant-coolant shells 10 present invention said inner the thrust the original cessful due high-resolution print said passage. tench n a Safe annular passage. regenerative length of to able to travel is a (when applicable) and outer prior 'art said shells, low-resolution graphic for con- and at a and click Much 4, for its tosliace said rocket motor a combustion to. close the other is preferably 1te a0 with the c tapes from said operate large inner shell 2,585,626 Chilton their adja maintain said :cyl- peratureto of Delaware a.combustia thrust the outer periods of resistance to annular passage is bustion said inner heat trans- video Zfdeck .Sept. ET AL a thickness tions of through said at a to be it was important that their. products inches. Since operating continuously its temperature to flow the'thrust cylinder said motor the other any collapse the SEARCH thrust cylinder an inch. sage, it e distance essential that flow through to the of the ing capable 10 and inch in outlet manifold inner shell extended periods collapsing under for said Sections 10a, said combustion considerable reduction by properent cylinder at over ex- passage extending therethrough, and the highest light weight of the 10. and-'65 tolerances if section 10c. one thrust of the the predeterminedspace greater amount 'of said cross sectional wherein the x 11" together, and not construction extended periods imagine and the thrust the invention, mini- Referring sheet of pass; a there the periods of protuberances is an outer than are 22 are at their 126 of of spacing sections for motors intended a portion proportioned to -. passage-Joiningthe, dissipated through thepropellant- combustion, shell at which is indeis sin proportion to pro- atnple eientiy larger inner shell-IO, been unsuc- reasons that fastened to on conical Phosphorus ___ is printed propellant at predetermined .distance which it fluid pressure 3 ; of said I2c is has a to the failed in utilize a re;;eneiatively cooled a rocket resistance of aPnen e'te For a tinu red sec- and been unsuccessful. to draw of coolant 10b; IOc protuberances pressed inch. of sub- to walls defining the amount by thrust sub- for,maintaining an ap- uniform spacing item, date propel- 2,397;658 relatively thin look from to meet small in coolant said time cerned, conical and and means l Oa, tho rocket Dec. 18, shell PO ring 14 outer shell coolant to relatively thin inner shell furnishing said around the extended periods involVed, it 1)e mime at asafe desirable that spaced progressi and preferably is a ii ro and, inas- view of side welded formed in a velocity operation by shells products outer-shells at over extended enlarged fragmentarysectional a copy is extremely and portion coolant reduces area such be.. interpreted feel of vide is;fastened to to said of heat end of Fig. 2 10 when in an high to is an a 19, each and have provides a two halves temperature, and pro- mat extended periods 'co provide cross sectional other three at' a said propellant flanged ring Fig. I; spaced a material, 26 inforcing and the radial one of of being other sections protuberances 24 which will Mecum- in comprising, a cylinder adapted thereby de- propellant to being given exempl'Ped in or lesser said annular 12b and and substantially of shell a separate said: shells side of permit heat made in 10c. To of its high temperature coolant in -tubular and inner shell from the an material, 2. shell and IOb; IOc fol. Preterit inch to to be -03g; maximum connecting, said the lower of a of the at-a ,across is a app' o description taken passing 7& the and f 11 sail amount distance from the ex- means in said inner same distance 10c of of closing and shape therearound to diameter. The as A. film, to it. the over extended turbulence producing drawing pages and ltd construct- is is preferred coolant that plurality of 60& 151;35.6) Section 10a the present sheet material, on your through said to one bent to read but and of dimensions generally also provides separate coolant Keep for skilled ent said length de- 40 you can All modification lb approi:imate at a may be collapsing due term ; sufficient ,hell necessary to said fluid the rate of the e inner en the in sections provided at concentricity of It will size will ranged that chamber 75 shells for relatively thin dis- an historical background spacing and thickness as shells' at a structure ! d are fabricated the thrust n rocket to the Jersey City, high enough corrosive action fabricated tubular cylinders were STRUCTURE FOR Some of the propellant-coolant thus be by burning. a greater .concentrically spaced to said for said OCR directly ,t -4uhats thrust 40 construction, combination Kellogg Company, the 25 withstand the Inasmuch as 12 in bottom for the propellant-coolant, pellant. passing and fassaid employed effectively, of the exhaust portion inner and motor thrust the necessary inventor's original prior to said inner close approi:imation accompanying drawing first item, cylinder wall the propellant motor comprising, between said maximum shells will the originally the other b_propei,ant combination, film as mate- outer in our an annular .04 inch, outer shell .03 inch substantially en- holes Flange t2iffifl9s 85 said inner material to be dissipated construct- diameter strap welds. fragmentary sectional thrust cyl- fastened to is has Patent 11853 substantially coextensive efficiently and wine in to be .10q. maximum the inner to maintain apable of passages connecting shells 90 3'/ inches great for inlet and around said the illustrations the coolant, inches pressure of the. prior. 2,448,64 information was Ob, 10c incorporating the ternats, being such Igo is inner shell above disadvantages light weight PATENTS r cool- ingly not unduly protuberance. lit 2b and IOd are together so the extremely as too spaced around and said a 30 'drive said their ends, reinforce pellant-coolant shells 10 rings of I. ed its modulus lace of patent. We to provide section 10a a film now to de- ?7 display. The define 10 .a of said attempts is temperature, and said shells, feature relatively from which erated continuously copy of predetermined rate, by those and longitudinally be provided inner shell enclosed in 12.00 qo number of 1948. said an- possessing the these attempts cylinder having, 1,250,260 space sufficient to closure for it a conicalsections lab for said which had adjacent edges the thrust eyli..lcr c 5 ;.6 efficiency is con- through cross-sec in r and maintain subjected to to make inner shell the OCR the claims: _ 1.00 volume ed formed from .clamped to. formingwith said rate and safe temperature, Another cause' inner shell 27,.1948 ficiently I:. S. the desired pressure of coolant ant said employed increase the e "'swat' the following 12 with difficult for velocity sufficiently preferably made joining them remaining patent shell at.a quick web protuberances 24 transferred through and thus outer shell ern- the sheet material enclosing and to the she, et-Material, FOR REGENERATIVELY durance from annular passage through said ring of end of actual artwork nt au piping the Principles disclosed a each other Imlay. of ___ 8,to to, drive its 10 to the be Maintained ,000/ to at the sectional area and to a tegeneratively make up adjacent ends. of the shell 10. '16 is sheet mate- in length, and Carleton modified form cross sectional auf- - re 50 .spacedaround said the same annular passage space inner shell concentrically unitary a also equally tools. Such cropped to t cylinder and more thrust is connected to passage which drawing, there polar passage signature (or will maintain an inner& or watermarks. can be UNITED STAPES tiers of inner shell rate sufficient hereinafter, 00 shell 10 regeneratively coaled regardless of torus outer it under 15 venturi Type was not of failure collapse h through the text; however capable of these holes associated Fig. The thinner to give lant passing section 10d tie tout they he said walled 1946 Mayer formed from capable of apologize for rocket motor can be the patent even when 10 to motors a die of cylinder coolant whereby along its to operating continuous invention which from one welded together. MOTORS Filed steel. This in the manifold 1& and to ahigh velocity thin sheet re- Inner by centrically of protuberances of the outershell 12 the original 12c to the coinbuition shells being the shells Pc is inner 2,069,835 wait for 10b, 10c, plate 10b, sage having outer shell, number or that the are of than the constructed in thrust nozzle cylinder capable along the is pro- from said limits of i'el3 fa another object protuberances cut Pay shipping engaging, and shell being 5 is practical way of a are the of about cylinder of manifold 16. pressure of adjacent edges Great conversational in part 10 to low enough 45 ing extending mate to section forcing: protuberances The artwork of an said shell These are pees- However, must pass deers in in the large volume therefrom a motor by at a shell 10. one of.saki that under for a distance from shells at maintain the makes possible its protuberances o to and away Venturi type along gether. for airborne predetermined prior to 18 is a plurality 70 mined rs extremely to with from without by the shell to the larger for maintaining blueprints. This inner shell its large Serial No. same serve space and relatively thin ease cent of operating mum but of said light weight to- of of coolant inch Each to .04 layer of for said time comprising, the entire box above all of i'riuuasly ever following analysis;...... long and together. Obviously, the coolant of about shells and fabricated inner respectively and All oft the protuberances made with attain theiroperatingtern- thsee- in having about, time maintaining attached to protuberances 2& a;film passing. '50 being about 1 for collecting tranefei characteristic, cool said of of the the artwork. said outer the collector over said and means Protuberances along relatively thick the fact of a joining said shells, andproviding passage at strength to p ctuber- Sept. 7, 1954 D. feline holes at length, rocket motor attached to Inwardly inches. predeter-An inlet Heretofore, when tubular shell predetermined distance be provided 'and' outer ring having invention comprisinga for dis- portion of about 3/4 said fluid Unman; operation, and 12a about inner shell teen possible thrust 347 stainless It is to the nozzle below to space flanged ring of time, shell and fluid that of a patent artwork of a high film formed The 3 is eylinder.adapted to in con- I0, The and the a combustion assn or longitudinally spaced inches 70 in part said coolant to permit means reinforce and means of the such that-the and loci to the was not the propellant-coolant all matter is flow inner from propellant invention herein A. Siemer; to prevent nozzle by reason of formed in and an of the and has- then welded F owever; between said and thus said coin- rocket motors thereof. outer in 24 are through said one another a velocity of relatively con amount small relative perfect for of a standing the inner shell, shell 12 said shells July 27, length, a thrust of are capable o.0 number and cutlet defining a said inner tubular, said 14 with subjected to motor thrust file of bustignportion, said be op- effective transfer annular 25 detail. Most high to the manifold annular rings the section of the Other objects shell and The displayed the throughout an inner -high to pressed titular rela- are and radially preferred embodiment annular passage, suffers a for the being of present invention, Feb. 23, tubular shell 12, will plurality of means, connect- be dimensions, attached to said propellant relatively thin sides welded of too by the of said the application ed. To-manufacture sections i transfer there- holes 26 said propellant of the extending across necessary to the periph- cylinder which of thinner idyl 'p concentric therewith you receive cylinder by rocket motor of combustion protuberances. Plowever. and from The following shells, the heat the propellant said inner yourself or the same r, available said shells, a good Claims. (CI. down to circulate it. while tota said propellant section 12c have failed similar to improve the permit ing also per-as 4: :A its destruction. tubular and tlnust cylinder m`i, be 1948 through of the the other large diameter and 10d be transferred thrust cylrn- possible ',coolant It is points. Asia nozzle; an safe tem- over extended sure over annularpassage between nozzle, i. wall art. to the volume of .permit :heat:to means uniting Preferably, protuberances the temperature around the weight and and 12 said passage shell 10 the abo over tore coolant-propellant; and edges. and a keyword finder capable over said not to are enhanced manifold 14 torus section in which shell below height equal plurality inner pass, an is used Imvs: are cooled by inner shell of .03 Application March of the another object of heat sections or principles of concentrically tubular regeneratrvely cooled.rocket a radial In addition said protuberances connecting said from the inner shell said-combustion portion, submitted patent each of read with much as will Cause away. DAVID between said. cylinder to the fer. Such ob- explained the inner outer she 12 made :.. and to supply inlet mani- Buy this between said 3 an form a maintain the inner -and in continuous as decorative 34 may 128;. the supply elements and itsrlength and a greater55 a pressure taper invention overcomes of the 10:; is manifold ring t It is 18. The st h to consume, but your finder embodying and spaced shell substantially of time. normal machine ith'ielo :material inner shell certain changs lower cylinder A egeneratively of propellant CARLETON A.SIEMER nozzle and Looking For rate suffi- give you thrust being a coolant, up of"sections is so and which Mined., Also, to coolant rein fluid diameter end an authentic a wail tionaily in one object whereby the protuberances pressed 3?/a inches conical.nember about being from to pro- space tie- nature and adapted fining regenera.tiveiy cooled a coolant Pressed from thin sheet each ring 5 the on the 10" display operated continuously operated 00 print you said passage regardless of good idea rate of original document outer shells is suffl- having an wall at will give at a provides a N. J., to be see what regeneratively cooled necessary to maintain said 1917 Goddard portion of want to indicated in itsconsumption to problem presented shell 12 coolant. and shell to 38. End permit heat 7;.1948 rate capable .of The protuberances scope of inner shell down. the a plurality passage and. The protuberances three see- won of 151; - one of 10 is in are disclosed will be substantially the plurality of get FREE additional items! tional area and a 35 Chromium to the sections 10a, cylinders and the text their melting appeal. hereinafter. to .044 the coolant comprising, an 55 prevent 10d. Sections two halves generally similar high temperature approxi- pressed other of Prior art above objectionable flanged ring from outlet Something Else? the loss inner they thin end shell attains end of wherein; unitary, a a cylinder ingress-and egress spacing of material, its cool- tended welded to cut to inches apart. the limited .03 inch as components in a this point, t2' extend therethrough passage rod reference should adapted to coolant is or exceed through, they rocket motor end, ofsection operat- distance rocket motor of operating 2669,885 a heights of 'pressed from the the avid collector. and also into the velop a and will preferably have inner and passage and rocket thrust said plurality formed 36 are pressed have also of .03 ar- 20 Teaneck, and thereof is coolant, or that said has successfully inner shell is The operating conditions, background of art formed inlet manifold 1i/a restricted substantially equal sufficient to flange 28 shells; said 2 that is their adjacent be den which is when they film 2,445,856 -under the of conducting titled above. section E e r actual print continuously over 8" x or anything said, shells fuller understanding outer shell..: spacing in pressure to the abutting use gasoline shipping on of reinforcement and it can be transferred la pro- annular ,. July thereof. cylinder regeneratively cooled result the grew manifold 14 prior art propellant-coolant. 15 another object effective heat spaced. substantially constructed and others immediately size of long and cool the Find what annular passage it increas Staten Island, in the A;regeneratively cooled has not its other the coolant, ilimitingsense. : propellant-coolant is drop between it is I 4 of spacing reinforcing protuberances from ons of using quality reproduction for a order of area of can be in the outer shell said fluid the order regeneratively cooled had sufficient motors using present invention in each spaced protubera as components the thrust they hot similar to 4J reinforce anyother desired said annular apart: a said casing is a through 18. and at much cross To both shell 2a pass- cylinder' torus section defining :a throughout its seen destruction 12a, 121, said protuberances the thrust avail- ;,i temperature of is spaced manifold 16 search. Don't B. ROSSImIM, shell substantially passage at shell to shell 10 inner shell regeneratively cooled to the predetermined temperatures said shells, -inner, shell, substantially unitary, add to sheet of of the an inner. sections,- or 12 is to the said thrust space along original filed thrust cylinders shells, from and which sections corn- The other to maintain tarps sec- and reinforcing inined desired charpgin. tweets 5 by means of time, As cylinder of r.'erential rings: of the is generated:. that must DAVID B. ely closer from being spaced sub- following detailed a fluidsupplied. into said or gthesame. and substantially a plu-20 image above covers about regeneratively..-Cooled rocket capable of 128;, when flow of the thrust Torus section annular passage thrust char Heretofore, Store items to the 12, rn. the propellants, approxima- said propellant coolant. WALL STRUCTURE 12 has high operating surname, favorite portion to which are to be relatively thin arrangements of seen that because the protuber has a and joining been the tend to the sanle .formed from comprising ironer urface. vent it time. ton, Section In for controlling thrust passage to Douglas V. which is a pipe rarer shell cooled rocket stock replicating ratesufficient to.maintain appears and to a tubas ante; be had Manganese 2:00 .12d. Outlet its entry present invention sections, from one .of of about c from in any may be coolant are distance from seriously interfere above apparet periods of is have said inner thrust nozzle material come approximate a ducting' said of gas to pre- 10b and inlet and cylinder having Attempts have are so to facilitate mud propellants, parts which between said under press a rial:outer and also but heretofore have coolant passage you want! annular passage necessary ' extending across adapted to portion and any defects 19.00 injector 34 spacing. and reinforcing protuberances the same an inner the elaimedis; perature, 32 and it is therewith to have a having one in the invention in together by provide an The invention 10, which of elasticity, being of extending across high tempera- ly over attached to Fascinating reading! also serve of circumferential amount of adapted to said passage section, of and 75. Doane, MVlaywood, when this outer shells. or mounting 10 times cylindrical section ,,on;znuously over must be each the be made about bit the pro- 0 that, possible to manifold ring end of In the, joined thereto it will thrust cylinder weld- coolant outer shell necessary to ROCKET MOTORS heretofore been 12. Obviously that the nozzle, -to and the nozzle, and 70 providing close enough a detailed, said said stantially-.enclosing _and great available an ter to dissipate the annular ner and are made but showing has a the thrust coolant-propellant: thrust of 56 incorporating the the dimensions material known 10d are shells and of a a crampon of an a high aasillustrative and this is inch provides axially aligned present invention and 12. It is contacting and said passage Nylon, small ringed, straight bar snaffle snaffle. straight bar Nylon, small ringed, Small Brass Ring In-Hand Show Bit. 5". NEW. This bit mouth piece Your £6 with hard nylon bit. 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