NO783625L - SOLID FUEL ROCKET DRIVE - Google Patents
SOLID FUEL ROCKET DRIVEInfo
- Publication number
- NO783625L NO783625L NO783625A NO783625A NO783625L NO 783625 L NO783625 L NO 783625L NO 783625 A NO783625 A NO 783625A NO 783625 A NO783625 A NO 783625A NO 783625 L NO783625 L NO 783625L
- Authority
- NO
- Norway
- Prior art keywords
- combustion chamber
- fuel
- solid fuel
- solid
- wall
- Prior art date
Links
- 239000004449 solid propellant Substances 0.000 title claims description 7
- 238000002485 combustion reaction Methods 0.000 claims description 24
- 239000000446 fuel Substances 0.000 claims description 13
- 238000009413 insulation Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- KAKZBPTYRLMSJV-UHFFFAOYSA-N Butadiene Chemical compound C=CC=C KAKZBPTYRLMSJV-UHFFFAOYSA-N 0.000 description 6
- 229920000642 polymer Polymers 0.000 description 6
- 239000011230 binding agent Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 229910052751 metal Inorganic materials 0.000 description 5
- 239000002184 metal Substances 0.000 description 5
- 239000003380 propellant Substances 0.000 description 4
- 239000002318 adhesion promoter Substances 0.000 description 3
- 125000000524 functional group Chemical group 0.000 description 3
- 125000002887 hydroxy group Chemical group [H]O* 0.000 description 3
- SMZOUWXMTYCWNB-UHFFFAOYSA-N 2-(2-methoxy-5-methylphenyl)ethanamine Chemical compound COC1=CC=C(C)C=C1CCN SMZOUWXMTYCWNB-UHFFFAOYSA-N 0.000 description 2
- NIXOWILDQLNWCW-UHFFFAOYSA-N 2-Propenoic acid Natural products OC(=O)C=C NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 2
- NLHHRLWOUZZQLW-UHFFFAOYSA-N Acrylonitrile Chemical compound C=CC#N NLHHRLWOUZZQLW-UHFFFAOYSA-N 0.000 description 2
- 125000003178 carboxy group Chemical group [H]OC(*)=O 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 229920001577 copolymer Polymers 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000005764 inhibitory process Effects 0.000 description 2
- 239000012948 isocyanate Substances 0.000 description 2
- 150000002513 isocyanates Chemical class 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- VLTRZXGMWDSKGL-UHFFFAOYSA-N perchloric acid Chemical compound OCl(=O)(=O)=O VLTRZXGMWDSKGL-UHFFFAOYSA-N 0.000 description 2
- 229920002857 polybutadiene Polymers 0.000 description 2
- 229920001228 polyisocyanate Polymers 0.000 description 2
- 239000005056 polyisocyanate Substances 0.000 description 2
- VWDWKYIASSYTQR-UHFFFAOYSA-N sodium nitrate Chemical compound [Na+].[O-][N+]([O-])=O VWDWKYIASSYTQR-UHFFFAOYSA-N 0.000 description 2
- PAWQVTBBRAZDMG-UHFFFAOYSA-N 2-(3-bromo-2-fluorophenyl)acetic acid Chemical compound OC(=O)CC1=CC=CC(Br)=C1F PAWQVTBBRAZDMG-UHFFFAOYSA-N 0.000 description 1
- KUBDPQJOLOUJRM-UHFFFAOYSA-N 2-(chloromethyl)oxirane;4-[2-(4-hydroxyphenyl)propan-2-yl]phenol Chemical compound ClCC1CO1.C=1C=C(O)C=CC=1C(C)(C)C1=CC=C(O)C=C1 KUBDPQJOLOUJRM-UHFFFAOYSA-N 0.000 description 1
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 1
- QGZKDVFQNNGYKY-UHFFFAOYSA-O Ammonium Chemical compound [NH4+] QGZKDVFQNNGYKY-UHFFFAOYSA-O 0.000 description 1
- NOWKCMXCCJGMRR-UHFFFAOYSA-N Aziridine Chemical compound C1CN1 NOWKCMXCCJGMRR-UHFFFAOYSA-N 0.000 description 1
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical class O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 1
- 239000006057 Non-nutritive feed additive Substances 0.000 description 1
- 101800000579 Pheromone biosynthesis-activating neuropeptide Proteins 0.000 description 1
- 229920003006 Polybutadiene acrylonitrile Polymers 0.000 description 1
- AVUYXHYHTTVPRX-UHFFFAOYSA-N Tris(2-methyl-1-aziridinyl)phosphine oxide Chemical compound CC1CN1P(=O)(N1C(C1)C)N1C(C)C1 AVUYXHYHTTVPRX-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 125000001931 aliphatic group Chemical group 0.000 description 1
- 150000001338 aliphatic hydrocarbons Chemical class 0.000 description 1
- 150000001447 alkali salts Chemical class 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 150000001412 amines Chemical class 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 150000004945 aromatic hydrocarbons Chemical class 0.000 description 1
- 125000003118 aryl group Chemical group 0.000 description 1
- 150000001541 aziridines Chemical class 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- LTMGJWZFKVPEBX-UHFFFAOYSA-N buta-1,3-diene;prop-2-enenitrile;prop-2-enoic acid Chemical compound C=CC=C.C=CC#N.OC(=O)C=C LTMGJWZFKVPEBX-UHFFFAOYSA-N 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- AXZAYXJCENRGIM-UHFFFAOYSA-J dipotassium;tetrabromoplatinum(2-) Chemical compound [K+].[K+].[Br-].[Br-].[Br-].[Br-].[Pt+2] AXZAYXJCENRGIM-UHFFFAOYSA-J 0.000 description 1
- 125000003700 epoxy group Chemical group 0.000 description 1
- 150000002148 esters Chemical class 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 239000003112 inhibitor Substances 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 229910017604 nitric acid Inorganic materials 0.000 description 1
- 150000002924 oxiranes Chemical class 0.000 description 1
- 239000004848 polyfunctional curative Substances 0.000 description 1
- 229910001487 potassium perchlorate Inorganic materials 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 235000010344 sodium nitrate Nutrition 0.000 description 1
- 239000004317 sodium nitrate Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 229920001897 terpolymer Polymers 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
- Inorganic Compounds Of Heavy Metals (AREA)
- Adhesives Or Adhesive Processes (AREA)
Description
Faststoff-rakettdrivverk og fremgangsmåte for fremstilling derav. Solid rocket propellant and method for manufacturing the same.
Foreliggende oppfinnelse angår et faststoff-rakettdrivverk og en fremgangsmåte for fremstilling av dette. The present invention relates to a solid-state rocket propulsion system and a method for its production.
Ved kammerveggbunnede faststoff-rakettdrivverk av konvensjonell type befinner det seg mellom den indre br.enn-kammervegg og det faste rakettdrivstoff en isolering og/eller et inhiberingssjikt.. Disse materialer oppfyller to oppgaver: de må på den ene side beskytte brennkammeret fra de varme forbrenningsgasser mot slutten av avbrenningen og/eller på den annen side virke som bindeledd med gode klebeegenskaper ved kammerveggbunnede faste drivstoffer. SjikttykkeIsen for disse materialer ligger vanligvis.mellom 1 og 5 nim. Innføring av disse materialer skjer alt etter anvendt teknologi enten ved støping eller slynging ved samtidig utherding av isoleringen In the case of conventional-type solid rocket propellants with a chamber wall bottom, there is an insulation and/or an inhibition layer between the inner combustion chamber wall and the solid rocket propellant. These materials fulfill two tasks: on the one hand, they must protect the combustion chamber from the hot combustion gases towards the end of the combustion and/or on the other hand act as a link with good adhesive properties in the case of chamber wall bottomed solid fuels. The layer thickness of the ice for these materials is usually between 1 and 5 nm. The introduction of these materials takes place depending on the technology used either by casting or slinging with simultaneous curing of the insulation
■eller ved innpressing med etterfølgende utherding. Begge teknologier er dog meget tids- og omkostnings-intensive, og reduserer i tillegg til dette det rom som står til disposisjon for drivstoffet. Dette betyr dermed en eventuelt betydelig ytelsesforringelse for rakettmotoren. ■or by pressing in with subsequent curing. However, both technologies are very time- and cost-intensive, and in addition reduce the space available for the fuel. This therefore means a potentially significant performance degradation for the rocket engine.
Oppgaven for foreliggende oppfinnelse er å tilby et faststoff-rakettdrivverk under langtgående utelukkelse av de nevnte isolerings- henholdsvis inhiberingsmaterialer. Løsningen av denne oppgave- oppnås ved et fast drivstoff som støpes rett inn i et brennkammer som ikke er isolert i den sylindriske del. The task of the present invention is to offer a solid-state rocket propellant while largely excluding the aforementioned insulation and inhibition materials. The solution to this task is achieved by a solid fuel that is poured directly into a combustion chamber that is not insulated in the cylindrical part.
Fremgangsmåten for fremstilling av rakettdrivverket består deri at innerveggen av brennkammeret utstyres med et en-henholdsvis to-komponentklebemiddel i en sjikttykkelse av 10 - 100^um og at det faste drivstoff deretter, støpes inn i brennkammeret. The procedure for manufacturing the rocket engine consists in equipping the inner wall of the combustion chamber with a one- or two-component adhesive in a layer thickness of 10 - 100 µm and then pouring the solid fuel into the combustion chamber.
Etter en spesiell utførelsesform av■oppfinnelsenAccording to a particular embodiment of the invention
o o
anvendes de.t brennkammere med veggtykkelser fra 0,6 - 1,5 mm, fortrinnsvis 0,8 - 1,2 mm. combustion chambers with wall thicknesses from 0.6 - 1.5 mm, preferably 0.8 - 1.2 mm, are used.
De faste drivstoffer ifølge oppfinnelsen består'i det vesentlige av oksydatorer, en metalltilsetning og polymerer som etter utherding oppviser gummiaktige egenskaper. Oksydatorene er generelt ammonium-, henholdsvis alkalisalter av salpeter-, henholdsvis perklor-syre. Spesielle eksempler på disse er ammoniumperklorat og ammbniumnitrat, kaliumperklorat, natriumnitrat, osv. The solid fuels according to the invention essentially consist of oxidizers, a metal additive and polymers which, after curing, exhibit rubbery properties. The oxidizers are generally ammonium, respectively alkali salts of nitric acid, respectively perchloric acid. Special examples of these are ammonium perchlorate and ammonium nitrate, potassium perchlorate, sodium nitrate, etc.
Foretrukne polymerer er te-lomere polybutadiener eller kopolymerer av butadien og akrylnitril med funksjonelle grupper. De funksjonelle grupper kan enten være sluttgruppe.r eller være fordelt statistisk langs kjeden. Typiske eksempler er karboksylavsluttede polybutadiener ("Butarez CTL", Preferred polymers are telomer polybutadienes or copolymers of butadiene and acrylonitrile with functional groups. The functional groups can either be final groups or be distributed statistically along the chain. Typical examples are carboxyl-terminated polybutadienes ("Butarez CTL",
"Telagen CT", "Hycas", "HC 4^4"), hydroksylavsluttede polybutadiener ("Butarez HT", "PBd R 45", "Telagen HT"), kopolymerer av butadien og akrylsyre ("PBAA"), samt terpolymerer av butadien, akrylsyre og akrylnitril ("PBAN"). "Telagen CT", "Hycas", "HC 4^4"), hydroxyl-terminated polybutadienes ("Butarez HT", "PBd R 45", "Telagen HT"), copolymers of butadiene and acrylic acid ("PBAA"), as well as terpolymers of butadiene, acrylic acid and acrylonitrile ("PBAN").
Består den funksjone lie'gruppe av en karboksyl-gruppe, kan disse polymerer herdes med de forskjellige aziridi-ner, epoksyder eller aminer. Polymerer med hydroksylgrupper herdes, med aromatiske eller alifatiske di- eller polyisocyana-ter. Alt etter reaktivitet av det anvendte isocyanat, må det tilsettes herdeakselleratorer henholdsvis herdeinhibitorer. If the functional group consists of a carboxyl group, these polymers can be cured with the various aziridines, epoxides or amines. Polymers with hydroxyl groups are cured, with aromatic or aliphatic di- or polyisocyanates. Depending on the reactivity of the isocyanate used, curing accelerators or curing inhibitors must be added.
Bindemiddelsystemet kan naturligvis også modifise-res ved komponenter som ikke er direkte med i herdeprosessen. Til disse hører fremfor alt de forskjellige.alifatiske og aromatiske hydrokarboner og estere som utøver myknerfunksjoner, andre prosesshjelpemidler, samt antioksydasjonsmidler,- osv. The binder system can of course also be modified by components that are not directly involved in the curing process. These include, above all, the various aliphatic and aromatic hydrocarbons and esters that exercise softening functions, other processing aids, as well as antioxidants, etc.
I tillegg til bindemiddel og oksydatorer kan det til drivstoffet, for å høyne ytelsen, tilsettes metaller i pulveri-sert form. Egnede metaller er aluminium, bor, magnesium, beryllium, osv. I drivstoffsammensetningen kan metallet erstatte en del av oksydatorene. Vanligvis anvendes mellom 0 og 30 % metall, fortrinnsvis mellom 10 og 20 %. In addition to binders and oxidisers, metals in powdered form can be added to the fuel to increase performance. Suitable metals are aluminium, boron, magnesium, beryllium, etc. In the fuel composition, the metal can replace part of the oxidizers. Usually between 0 and 30% metal is used, preferably between 10 and 20%.
Drivstoffsammensetningen har vanligvis følgende rammereseptur: The fuel composition usually has the following general formula:
Bindemiddelsystemet består av polymerer, herder og The binder system consists of polymers, hardeners and
.mykner..softens.
For å sikre en god vedhefting mellom drivstoff og brennkammer, anvendes det vedheftingsformidlere som naturligvis må være tilpasset drivstoffet. Således anvender man ved binde-middelsystemer med karboksylgrupper fortrinnsvis slike vedheftingsformidlere som inneholder aziridin- eller epoksy-grupper, slik som f.eks. "MAPO", "HX 760", "HX868", "Epikote l62", "Epon 828", osv., mens man-ved hydroksylholdige binde-middelsystemer fortrinnsvis anvender isocyanatholdige vedheftingsformidlere, slik som f.eks. "Desmodur R", In order to ensure good adhesion between fuel and combustion chamber, adhesion promoters are used, which of course must be adapted to the fuel. Thus, with binder systems with carboxyl groups, adhesion promoters containing aziridine or epoxy groups are preferably used, such as e.g. "MAPO", "HX 760", "HX868", "Epikote 162", "Epon 828", etc., while in the case of hydroxyl-containing binder systems, isocyanate-containing adhesion promoters are preferably used, such as e.g. "Desmodur R",
"Desmodur L" eller tyntflytende tokomponentklebemidler bestående av en hydroksylholdig polymer og et polyisocyanat. Disse materialer føres inn i brennkammeret'kort før innstøping av drivstoffet ved sprøyting eller påstrykning i sjikttykkelser på opp til ca. 100 ^um. "Desmodur L" or thin two-component adhesives consisting of a hydroxyl-containing polymer and a polyisocyanate. These materials are fed into the combustion chamber shortly before the fuel is poured in by spraying or brushing on in layer thicknesses of up to approx. 100 µm.
Oppfinnelsen har spesielt vist seg gunstig ved rørinnerbrenne,re, "Tube-and-rod"-konfigurasjoner, vognhjul-konfigurasjoner, flatstjerne-konfigurasjoner og dualstj.erne-konfigurasjoner. Selv for ekstreme stjerneinnerkonfigurasjoner hvorved forsenkningene i drivstoffet allerede under avbrenningen når brennkammeret, er anvendelsen av oppfinnelsen mulig, fremfor alt ved anvendelse av tykkveggede brennkammere. The invention has particularly proved beneficial in tube internal combustion, "Tube-and-rod" configurations, trolley-wheel configurations, flat-star configurations and dual-star configurations. Even for extreme internal star configurations whereby the depressions in the fuel already reach the combustion chamber during combustion, the application of the invention is possible, above all when using thick-walled combustion chambers.
Fig. 1 viser et rakettdrivverk ifølge oppfinnelsen Fig. 1 shows a rocket propulsion system according to the invention
med en brennkammerveggtykkelse på 1,2 mm.with a combustion chamber wall thickness of 1.2 mm.
Komposit-drivstoffet I støpes inn i brennkammeret og forklebes i den sylindriske del av brennkammeret direkte med innerveggen. The composite fuel I is cast into the combustion chamber and pre-glued in the cylindrical part of the combustion chamber directly to the inner wall.
Den dobbelte isolasjonskappe II forhindrer en løsrivning av drivstoffet fra bunnen av brennkammeret og beskytter denne mot de varme forbrenningsgasser. The double insulation jacket II prevents the fuel from being detached from the bottom of the combustion chamber and protects it from the hot combustion gases.
Isoleringen III som i foreliggende eksempel (rør-innerbrenner) er påført på det på dysesiden konisk utformede drivstoff, utelukker en uønsket avbrenning på brennkammerveggen. The insulation III which in the present example (tube-internal burner) is applied to the conically designed fuel on the nozzle side, excludes an unwanted burning on the combustion chamber wall.
Snittet A-B viser en innerkonfigurasjon av drivstoff satsen. Section A-B shows an internal configuration of the fuel tank.
De spesielle fordeler ved oppfinnelsen beror på maksimal utnyttelse av brenn.kammerinnerrommet med■drivstoff, hvorved det i forhold til vanlige drivverk kan oppnås en ytter-ligere ytelsesstigning, og på en vesentlig mer rasjonell fremstillingmåte på grunn av at man unngår en overveiende del av isolasjonen. The special advantages of the invention are based on maximum utilization of the combustion chamber interior with fuel, whereby a further increase in performance can be achieved compared to conventional drive units, and on a significantly more rational manufacturing method due to the fact that a substantial part of the insulation is avoided .
Claims (4)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE2748200 | 1977-10-27 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| NO783625L true NO783625L (en) | 1985-09-19 |
Family
ID=6022423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| NO783625A NO783625L (en) | 1977-10-27 | 1978-10-26 | SOLID FUEL ROCKET DRIVE |
Country Status (4)
| Country | Link |
|---|---|
| FR (1) | FR2576361A1 (en) |
| GB (1) | GB2162927B (en) |
| IT (1) | IT1109121B (en) |
| NO (1) | NO783625L (en) |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1050086A (en) * | 1900-01-01 | |||
| NL90798C (en) * | 1949-02-15 | Brandt Soc Nouv Ets | ||
| GB850370A (en) * | 1956-10-09 | 1960-10-05 | Phillips Petroleum Co | Improvements relating to the bonding of cured conjugated diene-vinylpyridine compositions |
| US2994359A (en) * | 1956-02-20 | 1961-08-01 | Phillips Petroleum Co | Apparatus for and method of preparing bonded articles |
| GB918262A (en) * | 1960-10-27 | 1963-02-13 | Tiiiokol Chemical Corp | Rocket engine |
| NL125606C (en) * | 1962-11-09 | |||
| US3224191A (en) * | 1963-05-20 | 1965-12-21 | Thiokol Chemical Corp | Rocket motor construction |
| US3381614A (en) * | 1965-10-01 | 1968-05-07 | Ratz Heinz | Acid pretreated polyethyleneglycol terephthalate sheet as insulation for solid rocket propellent charges |
| GB1448086A (en) * | 1965-10-27 | 1976-09-02 | Mini Of Technology | Rocket motors and methods of their manufacture |
| US4103584A (en) * | 1966-01-18 | 1978-08-01 | Aerojet-General Corporation | Staple orienting method and apparatus |
| GB1179415A (en) * | 1966-06-10 | 1970-01-28 | Imp Metal Ind Kynoch Ltd | Improvements in or relating to the Casting of Rocket Motor Propellants |
| DE1926378B1 (en) * | 1969-05-23 | 1970-12-03 | Messerschmitt Boelkow Blohm | Combustion chamber, especially for rocket engines |
| GB1309548A (en) * | 1969-06-09 | 1973-03-14 | Pains Wessex Ltd | Pyrotechnic devices |
-
1978
- 1978-10-24 GB GB07841758A patent/GB2162927B/en not_active Expired
- 1978-10-25 FR FR7830305A patent/FR2576361A1/en not_active Withdrawn
- 1978-10-26 NO NO783625A patent/NO783625L/en unknown
- 1978-10-26 IT IT69460/78A patent/IT1109121B/en active
Also Published As
| Publication number | Publication date |
|---|---|
| IT7869460A0 (en) | 1978-10-26 |
| FR2576361A1 (en) | 1986-07-25 |
| GB2162927A (en) | 1986-02-12 |
| GB2162927B (en) | 1986-07-30 |
| IT1109121B (en) | 1985-12-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4131051A (en) | Process for preparing a rocket motor | |
| JP3231778B2 (en) | Case filled with two-pulse rocket motor of solid propellant, ignition device and method of manufacturing the same | |
| US20110023449A1 (en) | Insensitive Rocket Motor | |
| US4209351A (en) | Ambient cured smokeless liner/inhibitor for propellants | |
| US6179944B1 (en) | Process for preparing composite warhead casings and product | |
| NO783625L (en) | SOLID FUEL ROCKET DRIVE | |
| KR101839193B1 (en) | Fixing device for bunch type prolellant and manufacturing method thereof | |
| US20170057885A1 (en) | Propellant load, with mechanically reinforced liner/propellant connection, and preparation thereof | |
| US3947523A (en) | Composition comprising epoxy resin, copolymer of butadiene and acrylic acid, curing agent and inorganic metal salt | |
| US5474625A (en) | Desensitized solid rocket propellant formulation | |
| NO783624L (en) | SOLID FUEL ROCKET DRIVE | |
| CN112855385B (en) | Charging structure suitable for low-temperature ignition | |
| US3147710A (en) | Ignition system for solid propellants | |
| CN110759800A (en) | High-energy high-mechanical-property electronic control solid propellant | |
| NO161216B (en) | ADHESIVE TO CONNECT SURFACES IN AMMUNITION CONTAINING EXPLOSIVE CHARGES. | |
| US5022306A (en) | Method of ejecting an interceptor missile from its silo | |
| CN109467492B (en) | Negative pressure intensity index propellant | |
| US3779011A (en) | Fuel unit for a hybrid hot-gas generator | |
| Sparks et al. | Fifty years of solid propellant technical achievements at Atlantic Research Corporation | |
| US3023572A (en) | Multiple thrust propellant charge | |
| US2992595A (en) | Use of acetylene-ethane mixture as propellant and explosive | |
| Willemse et al. | An Overview of the Development of the VEGA Solid Rocket Motor Igniters | |
| NO884271L (en) | CASTABLE EXPLOSION WITH AN ARTIFICIAL BINDER FOR WEAPON SYSTEMS. | |
| JP2587084B2 (en) | Solid propellant | |
| Crosby et al. | Design and development of a hot particle igniter |