DK141607B - ROCKET MOTOR - Google Patents
ROCKET MOTOR Download PDFInfo
- Publication number
- DK141607B DK141607B DK506867A DK506867A DK141607B DK 141607 B DK141607 B DK 141607B DK 506867 A DK506867 A DK 506867A DK 506867 A DK506867 A DK 506867A DK 141607 B DK141607 B DK 141607B
- Authority
- DK
- Denmark
- Prior art keywords
- auxiliary
- charge
- rocket
- ballistic
- combustion
- Prior art date
Links
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
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
- C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/12—Compositions or products which are defined by structure or arrangement of component of product having contiguous layers or zones
-
- 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
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B1/00—Explosive charges characterised by form or shape but not dependent on shape of container
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Acyclic And Carbocyclic Compounds In Medicinal Compositions (AREA)
- Medicinal Preparation (AREA)
- Air Bags (AREA)
- Inorganic Compounds Of Heavy Metals (AREA)
- Testing Of Engines (AREA)
Description
(11) FREML«6EL*E***BIFT 141607 DANMARK «<) f 02 κ 9/i8 §(21) Ansøgning nr. 5068/67 (22) Indleveret den 12. Okt.(11) FORM «6EL * E *** BIFT 141607 DENMARK« <) f 02 κ 9 / i8 § (21) Application No. 5068/67 (22) Filed on 12 Oct.
(23) Løbedag 12. Okt. 1967 (44) Ansøgningen fremlagt og fremlaeggeteestkriftet offentliggjort den 5 · maj 1 980(23) Race day 12 Oct. 1967 (44) The application presented and submitted for publication published on 5 May 1 980
DIREKTORATET FORDIRECTORATE OF
PATENT-OG VAREMÆRKEVÆSENET (30) Prioritet bøgaratfra denPATENT AND TRADEMARKET SYSTEM (30) Priority to bequest from
22. feb. 1967, 694^)8, BEFeb 22 1967, 694 ^ 8, BE
10. apr. 1967# 696817, BEApr 10 1967 # 696817, BE
(71) LES FORGES BE ZEEBRUGGE S.A., 145, rue Bellenay, Heretal-lez-Llege, BE. (72) Opfinder; Gaston Bodinaux, Seny-en-Condroz, BE.(71) LES FORGES BE ZEEBRUGGE S.A., 145, rue Bellenay, Heretal-lez-Llege, BE. (72) Inventor; Gaston Bodinaux, Seny-en-Condroz, BE.
(74) Fuldmægtig under sagens behandling:(74) Plenipotentiary in the proceedings:
Dansk Patent Kontor ApS.Dansk Patent Kontor ApS.
(54) Raketmotor.(54) Rocket Engine.
Den foreliggende opfindelse angår en raketmotor som angivet i indledningen til patentkravet.The present invention relates to a rocket engine as set forth in the preamble to the claim.
Sådanne to-komponent drivladninger med et separat ballistisk hjælpeorgan er blevet udviklet til anvendelse som raketmotorer for dels at kunne frembringe en såvidt muligt konstant, stærk fremdrivnings-kraft og dels at opnå en bred temperaturufølsomhed for drivladningerne samt for at få reduceret forekomsten af sekundærflammer kraftigt.Such two-component propellant charges with a separate ballistic auxiliary means have been developed for use as rocket motors in order to produce, as far as possible, constant, strong propulsion power and, in part, to achieve a wide temperature sensitivity of the propellant charges and to greatly reduce the occurrence of secondary flames.
Ved en kendt to-komponent drivladning indeholder det ballistiske hjælpeorgan, ifølge tysk fremlæggelsesskrift nr. 1.212.458, titanoxid som metaloxid.In a known two-component propellant charge, the ballistic auxiliary means, according to German presentation specification No. 1,212,458, contains titanium oxide as metal oxide.
2 1416072 141607
Ifølge den derfra kendte teknik kan man, ved raketmotorer med en kendt to-komponentdrivladning, få undertrykt den sekundærflamme, som fremkommer under drivladningens forbrænding, og i øvrigt få udjævnet denne forbrænding.According to the prior art, rocket engines with a known two-component propellant can suppress the secondary flame that arises during combustion of the propellant charge, and otherwise this combustion can be smoothed.
Dette sker ved, at man i raketmotorens forbrændingskammer og i drivladningens flammeområde, men adskilt fra drivladningen, anbringer et modificeringsmiddel, der i det væsentlige består af kaliumsulfat, bariumnitrat eller titanoxid, og som lejres på en sådan måde, at det fortæres af flammen. Det er i det nævnte patentskrift endvidere angivet dels, at kaliumsulfat kan erstattes af andre kaliumsalte, såsom kaliumchlorid og kaliumnitrat, og dels, at bariumsalte, såsom det allerede nævnte bariumnitrat, og andre forholdsvis træge faste stoffer, der ligesom kaliumsaltene forbliver i flammen som faste dele, kan anvendes.This is done by placing in the combustion chamber of the rocket engine and in the flame range of the propellant charge, but separate from the propellant charge, a modifier consisting essentially of potassium sulphate, barium nitrate or titanium oxide and stored in such a way that it is consumed by the flame. It is further stated in the aforementioned patent that potassium sulphate can be replaced by other potassium salts such as potassium chloride and potassium nitrate and partly that barium salts such as the barium nitrate already mentioned and other relatively inert solids which, like the potassium salts, remain in the flame as solid. parts can be used.
Man kan imidlertid ikke ud fra disse angivelser udlede noget om, hvilken egenskab man skal kræve af en forbindelse, for at den skal være mindst lige så egnet til undertrykkelse af drivladningens sekundærflamme .However, nothing can be deduced from these particulars as to what property is required of a compound for it to be at least as suitable for suppressing the secondary flame of the propellant charge.
Det er ved opfindelsen tilsigtet at tilvejebringe en raketmotor af den ovenfor angivne art, og hvor man som metaloxid i hjælpeorganet, i stedet for titanoxid, kan anvende andre metaloxider, der har i det mindste samme virkning som titanoxid, og som er enten billigere eller i hvert fald lettere tilgængelige end titanoxid.It is an object of the present invention to provide a rocket engine of the kind set forth above and in which, as metal oxide in the auxiliary means, instead of titanium oxide, other metal oxides which have at least the same effect as titanium oxide and which are either cheaper or cheaper can be used. at least more readily available than titanium oxide.
Det har nu vist sig, at det tilstræbte opnås, når ifølge opfindelsen hjælpeorganet som metaloxid indeholder mindst ét oxid af metallerne molybdæn, tin, chrom, wolfram, zirkon, cerium, lanthan, cobalt, nikkel, Jern eller magnesium.It has now been found that the object is achieved when, according to the invention, the auxiliary means as metal oxide contains at least one oxide of the metals molybdenum, tin, chromium, tungsten, zircon, cerium, lanthanum, cobalt, nickel, Iron or magnesium.
Ved det i hjælpeorganet tilstedeværende metaloxid nedsættes temperaturen af de af drivladningen udviklede gasser, og deres forbrænding fuldstændiggøres.The metal oxide present in the auxiliary means reduces the temperature of the gases produced by the propellant charge and their combustion is completed.
Dette sker ved, at det tilstedeværende metaloxid afgiver oxygen i selve raketmotoren, herved fås en virkning af samme art som den, der opnås ved tilførsel af sekundærluft til et fyr, nemlig at man får omdannet den ved høj forbrændings temperatur dannede carbonoxid- 3 U1807 holdige gas til en carbondioxidholdig gas. Man undgår således, at udviklede gasser først efter at have forladt motoren, og når de kommer i kontakt med luftens ilt, efterforbrænder under antændelse , d.v.s. under flammedannelse.This is done by the fact that the metal oxide present gives off oxygen in the rocket engine itself, thereby obtaining an effect of the same kind as that obtained by supplying secondary air to a guy, namely converting the carbon monoxide containing at high combustion temperature. gas for a carbon dioxide containing gas. Thus, it is avoided that developed gases only after leaving the engine and when they come into contact with the oxygen of the air, afterburner during ignition, i.e. during flame formation.
Hjælpeorganet bevirker således, at hele forbrændingen sker, før drivladningens forbrændingsprodukter forlader motoren, og der opnås således fuldstændig forbrænding og fuld udnyttelse af drivladningens energi.Thus, the auxiliary means causes the entire combustion to occur before the propellant's combustion products leave the engine and thus complete combustion and full utilization of the propellant's energy is obtained.
Nogle udførelsesformer for raketmotorer ifølge opfindelsen er i det følgende beskrevet under henvisning til tegningen, hvor figur 1 skematisk viser forskellige aribri ngelsesmuligheder for to-komponent drivladningen og det ballistiske hjælpeorgan, fig.2 og 3 er længdesnit gennem raketmotorer ifølge opfindelsen, fig.4 viser et snit langs linien IV-IF ifølge fig. 3, fig, 5 en ændret udførelsesform for snittet ifølge fig.4, fig. 6 og 7 viser partielle længdesnit gennem en raketmotor, der er modificeret i forhold til den i fig.3 viste motor," fig,8, 9 og 10 viser i forenklet gengivelse længdesnit gennem raketmotorer, hvor hjælpeorganet er udformet og anbragt på forskellige måder.Some embodiments of rocket engines according to the invention are described below with reference to the drawing, in which: Figure 1 shows schematically various options for the two-component propulsion charge and the ballistic auxiliary means; Figures 2 and 3 are longitudinal sections through rocket engines according to the invention; a section along the line IV-IF of FIG. 3; FIG. 5 is a modified embodiment of the section of FIG. 4; Figures 6 and 7 show partial longitudinal sections through a rocket engine modified with respect to the engine shown in Fig. 3; Figs. 8, 9 and 10 show, in simplified view, longitudinal sections through rocket engines, the auxiliary means being designed and arranged in various ways.
I de forskellige figurer betegner 1 en raketaotor, 2 den deri anbragte to-komponent drivladning og 3 det eller de i motoren anbragte hjælpeorganer,In the various figures, 1 denotes a rocket motor, 2 denotes the two-component propellant charge, and 3 denotes the auxiliary member (s) located in the motor,
Fig.l viser eksempelvis, hvorledes man med en given anbringelse af drivladningen 2 kan anbringe et eller flere ballistiske hjælpeorganer 3 ·Fig. 1 shows, for example, how one or more ballistic auxiliary members 3 can be arranged with a given arrangement of the driving charge 2
Ved de i fig.2 og 3 viste raketmotorer er drivladningen 2 udformet som en hul ladning, i hvilken hjælpeorganet 3 er koaksialt lejret.In the rocket motors shown in Figs. 2 and 3, the drive charge 2 is formed as a hollow charge in which the auxiliary means 3 is coaxially mounted.
4 er raketmotorens endestykke og 5 dens udstødningsrør, medens 6 er stabiliseringsvinger, der er anbragt drejelige om tappe 7*4 is the rocket motor end piece and 5 its exhaust pipe, while 6 are stabilizer vanes arranged pivotally about pin 7 *
Ved den i fig.4 viste udføreleesform har det ballistiske hjælpeorgan 3 stjerneformet tværsnit og er anbragt på en stjerneformet støttede! 8, der bæres af en stang 9· To-komponent drivladningen 2 er en hulblok, hvis hulhed har stjerneformet tværsnit, og hvor de to enkeltladninger er anbragt skiftevis den ene uden om den anden, idet dog den yderste enkeltladnings udvendige flade er cylindrisk.In the embodiment shown in Fig. 4, the ballistic auxiliary member 3 has a star-shaped cross-section and is arranged on a star-shaped support! 8, carried by a rod 9 · Two-component drive charge 2 is a hollow block whose cavity has a star-shaped cross-section and the two single charges are alternately arranged one another around the other, the outer surface of the outer single charge being cylindrical.
4 1416074 141607
Ved den i fig.5 viste udførelsesform er hjælpeorganet 3 udformet som en selvbærende hulcylinder, der har radialkanaler 10. Ved en modificeret form for denne udførelsesform kan hjælpeorganet 3 være en selvbærende massiv cylinder med diametralt forløbende tværkanaler.In the embodiment shown in Fig. 5, the auxiliary member 3 is designed as a self-supporting hollow cylinder having radial channels 10. In a modified form of this embodiment, the auxiliary member 3 can be a self-supporting solid cylinder with diametrically extending transverse channels.
Ved udførelsesformen ifølge fig.6 findes der foruden det centralt anbragte hjælpeorgan 3 et supplerende hjælpeorgan 3 i form af en skive, der dækker drivladningens forreste ende. Denne skive kan som vist være tildannet med bølger, men kan også være plan og eventuelt bestå af flere lag, ligesom den eventuelt kan have gennemgående kanaler.In the embodiment of Fig. 6, in addition to the centrally located auxiliary member 3, there is a supplementary auxiliary member 3 in the form of a disc covering the front end of the drive charge. This disc may, as shown, be formed with waves, but may also be planar and possibly consist of several layers, as well as it may have continuous channels.
Ved udførelsesformen ifølge fig.7 er det centralt anbragte hjælpeorgan 3 suppleret med et hjælpeorgan 3 i form af en i motorens udstødningsrør 4 indsat ring, der kan have en hel eller hullet, kontinuerlig eller profileret væg.In the embodiment of Fig. 7, the centrally located auxiliary member 3 is supplemented with auxiliary member 3 in the form of a ring inserted in the exhaust pipe 4 of the motor, which may have a whole or perforated, continuous or profiled wall.
I fig.8 og 9 er meget summarisk skematiseret ballistiske hjælpeorganer 3» der er anbragt i raketmotoren og har varierende tykkelse, således at der tages hensyn til eventuelle variationer i forbrændingsbetingelserne langs raketmotoren.In Figs. 8 and 9, very summary schematic ballistic auxiliary members 3 are located in the rocket engine and of varying thickness, so that any variations in combustion conditions along the rocket engine are taken into account.
Orienteringen af den stigende tykkelse afhænger naturligvis af opbygningen af eller forbrændingens forløb ved de anvendte drivladninger bestående af to dele.The orientation of the increasing thickness, of course, depends on the structure or the course of combustion of the two-part drive charges used.
I fig.8 er skematiseret en sådan trinvis variation, medens der i fig.9 er skematiseret en variation i en kontinuerlig og progressiv form.In Fig. 8, such a stepwise variation is schematized, while in Fig. 9, a variation in a continuous and progressive form is schematized.
Nan kan naturligvis tilpasse enhver anden profil i forhold til de korrigerende virkninger, der skal udføres, og nærmere betegnet under hensyntagen til loven for forbrug af det nævnte ballistiske hjælpeorgan i motoren.Nan can, of course, adapt any other profile to the corrective effects to be performed, and more specifically, taking into account the law of consumption of said ballistic auxiliary body in the engine.
Endelig er der i fig.10 skematiseret en udførelsesform af et aksialt ballistisk hjælpeorgan, der er udført på en sådan måde, at dets effektive længde er kendeligt større end længden af motorens drivmiddelladning.Finally, in Fig. 10, an embodiment of an axial ballistic auxiliary member is designed in such a way that its effective length is appreciably greater than the length of the engine propellant charge.
141607 5141607 5
Man kan navnlig benytte et sådant middel eller et ækvivalent middel, når det er fastlagt, at den aksiale anbringelse på den-ene side er nødvendig, og hvor på den anden side den normale overflade af et retliniet element er utilstrækkelig til opnåelse af de ønskede resultater.In particular, such an agent or equivalent may be employed when it is determined that the axial placement on the one hand is necessary and where, on the other hand, the normal surface of a rectilinear element is insufficient to achieve the desired results. .
Som det fremgår af det ovenfor anførte, kan en raketmotor med tokomponent drivladning og hjælpeorgan ifølge opfindelsen alt efter raketmotorens anvendelsesformål opbygges på forskellige måder med hensyn til dens fysiske udformning.As can be seen from the above, a two-component rocket motor with auxiliary charge and auxiliary means according to the invention can according to the purpose of the rocket engine be constructed in various ways with respect to its physical design.
Dette gælder også to-komponentdrivladningens og hjælpeorganets sammensætning i såvel kvalitativ som kvantitativ henseende.This also applies to the two-component charge and auxiliary body composition in both qualitative and quantitative terms.
Til en raketmotor, hvor det ballistiske hjælpeorgan er anbragt separat i en aksialt forløbende hulhed i en drivladningsblok, kan der anvendes følgende sammensætning: 1. To-komponent drivladning: nitrocellulose (12,6% BT) 40-51 vægtdele nitroglycerol 58 - 50 " propyl-di-N-adipat 0,1 - 0,6 " 2-nitrodiphenylamin l - 3 w monobasisk cuprisalicylat 2 - 4,5 ” monobasisk bly^-resorcylat 1 - 3 " candelillavoks 0,08- 0,3 " 2. Ballistisk hjælpeorgan:For a rocket engine in which the ballistic auxiliary is arranged separately in an axially extending cavity of a propellant charge block, the following composition may be used: 1. Two component propellant charge: nitrocellulose (12.6% BT) 40-51 parts by weight nitroglycerol 58 - 50 " propyl di-N-adipate 0.1 - 0.6 "2-nitrodiphenylamine 1-3 w monobasic cupric salicylate 2 - 4.5" monobasic lead ^ resorcylate 1-3 candelilla wax 0.08 - 0.3 "2. Ballistic Auxiliary:
kaliumsulfat 67 - 76 Mpotassium sulfate 67 - 76 M
ethylcellulose 10 - 15,5 " dibutylphthalat 2-7 vægtdeleethyl cellulose 10 - 15.5 "dibutyl phthalate 2-7 parts by weight
butylmethacrylat 6,5-10,6 Mbutyl methacrylate 6.5-10.6 M
polyglycoldimethacrylat 0,9 - 1,62 " benzoylperoxid 0,09- 0,16 rt en korrigerende mængde af et molybdænoxid.polyglycol dimethacrylate 0.9 - 1.62 "benzoyl peroxide 0.09 - 0.16 rt a corrective amount of a molybdenum oxide.
Udover de metaloxider, hvis anvendelse er ejendommelig for hjælpeorganet ifølge opfindelsen, kan dette endvidere indeholde silicium-dioxid eller magnesiumsilicat.In addition to the metal oxides whose use is peculiar to the adjuvant according to the invention, this may also contain silica or magnesium silicate.
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE2046551 | 1967-02-22 | ||
BE2046551 | 1967-02-22 | ||
BE2046724 | 1967-04-10 | ||
BE2046724 | 1967-04-10 |
Publications (2)
Publication Number | Publication Date |
---|---|
DK141607B true DK141607B (en) | 1980-05-05 |
DK141607C DK141607C (en) | 1980-10-13 |
Family
ID=25661642
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DK506867A DK141607C (en) | 1967-02-22 | 1967-10-12 | ROCKET MOTOR |
Country Status (12)
Country | Link |
---|---|
AT (1) | AT277669B (en) |
AU (1) | AU5549973A (en) |
BE (2) | BE694408A (en) |
CH (1) | CH489706A (en) |
DE (1) | DE1626083A1 (en) |
DK (1) | DK141607C (en) |
ES (1) | ES345609A1 (en) |
GB (1) | GB1204138A (en) |
GR (1) | GR33273B (en) |
LU (1) | LU54389A1 (en) |
NL (1) | NL6712608A (en) |
NO (1) | NO122959B (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2193491B (en) * | 1978-07-21 | 1988-09-14 | Imi Kynoch Limited Kynoch Work | Improvements in propellants |
-
1967
- 1967-02-22 BE BE694408D patent/BE694408A/xx not_active IP Right Cessation
- 1967-04-10 BE BE696817D patent/BE696817A/xx unknown
- 1967-08-28 LU LU54389A patent/LU54389A1/xx unknown
- 1967-08-30 DE DE1967F0053352 patent/DE1626083A1/en active Pending
- 1967-09-04 NO NO169597A patent/NO122959B/no unknown
- 1967-09-04 AT AT08097/67A patent/AT277669B/en not_active IP Right Cessation
- 1967-09-12 GR GR670133273A patent/GR33273B/en unknown
- 1967-09-13 CH CH1284967A patent/CH489706A/en not_active IP Right Cessation
- 1967-09-14 NL NL6712608A patent/NL6712608A/xx unknown
- 1967-09-30 ES ES345609A patent/ES345609A1/en not_active Expired
- 1967-10-04 GB GB4530267A patent/GB1204138A/en not_active Expired
- 1967-10-12 DK DK506867A patent/DK141607C/en not_active IP Right Cessation
-
1973
- 1973-05-10 AU AU55499/73A patent/AU5549973A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
LU54389A1 (en) | 1967-10-30 |
DE1626083A1 (en) | 1970-04-02 |
DK141607C (en) | 1980-10-13 |
NO122959B (en) | 1971-09-06 |
AT277669B (en) | 1970-01-12 |
GB1204138A (en) | 1970-09-03 |
NL6712608A (en) | 1968-08-23 |
CH489706A (en) | 1970-04-30 |
ES345609A1 (en) | 1970-02-01 |
BE696817A (en) | 1967-10-10 |
AU5549973A (en) | 1974-11-14 |
GR33273B (en) | 1967-11-18 |
BE694408A (en) | 1967-08-22 |
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PUP | Patent expired |