NO125748B - - Google Patents
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- Publication number
- NO125748B NO125748B NO2161/70A NO216170A NO125748B NO 125748 B NO125748 B NO 125748B NO 2161/70 A NO2161/70 A NO 2161/70A NO 216170 A NO216170 A NO 216170A NO 125748 B NO125748 B NO 125748B
- Authority
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- Norway
- Prior art keywords
- projectile
- charge
- wings
- nozzles
- gravity
- Prior art date
Links
- 230000005484 gravity Effects 0.000 claims description 21
- 239000003721 gunpowder Substances 0.000 claims description 17
- 239000003380 propellant Substances 0.000 claims description 13
- 239000000567 combustion gas Substances 0.000 claims description 11
- 230000006641 stabilisation Effects 0.000 claims description 11
- 238000011105 stabilization Methods 0.000 claims description 11
- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 238000007373 indentation Methods 0.000 claims description 5
- 239000003381 stabilizer Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 241000196324 Embryophyta Species 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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- 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
- F02K9/70—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using semi- solid or pulverulent propellants
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Toys (AREA)
Description
Selvdrevet projektil. Self-propelled projectile.
Den foreliggende oppfinnelse angår et selvdrevet projektil og særlig et styrbart projektil, forsynt med en drivende kruttmotor og med vinger til stabilisering av projektilet i dets bane. The present invention relates to a self-propelled projectile and in particular a steerable projectile, provided with a driving gunpowder engine and with wings for stabilizing the projectile in its trajectory.
For at et projektil skal få en stabil bevegelse i sin bane og dessuten være lett å styre, må dets aerodynamiske trykksentrum ligge bakenfor, men forholdsvis nær dets tyngdepunkt. Dette medforer at projektilets stabiliseringsvinger bor være plasert i nærheten av dets tyngdepunkt. For at tyngdepunktet ikke skal forskyve seg når drivmotorens kruttladning brenner opp, bor også drivmotorens kruttladning være plasert slik i projektilet at dets tyngdepunkt ligger nær eller faller sammen med projektilets resulterende tyngdepunkt. Disse to samtidig eksisterende krav betyr at projektilets stabiliseringsvinger og drivmotorens kruttladning bor være plasert på samme sted av projektilet. Dette medforer plassproblemer som det er vanskelig å lose. Projektilets ytre skall eller hylster gjores nemlig så tynt som mulig for at projektilet skal få liten vekt og liten total ytterdiameter. Vingene, som er festet til projektilets ytre hylster, blir imidlertid utsatt for betraktelige krefter, så festene for vingene og den del av projektilhylsteret som bærer disse fester, må være dimensjonert forholdsvis kraftig. Skal vingene festes til den del av projektilet hvor også drivmotorens kruttladning er plasert, må festene for vingene således rage inn i det rom hvor drivmotorens kruttladning bor være plasert, eller også må projektilets totale ytterdiameter okes slik at festene for vingene får plass. In order for a projectile to have a stable movement in its trajectory and also to be easy to control, its aerodynamic center of pressure must lie behind, but relatively close to, its center of gravity. This means that the projectile's stabilizing wings must be positioned close to its center of gravity. In order for the center of gravity not to shift when the drive motor's gunpowder charge burns up, the drive motor's gunpowder charge must also be positioned in the projectile so that its center of gravity is close to or coincides with the resulting center of gravity of the projectile. These two simultaneously existing requirements mean that the projectile's stabilization wings and the drive motor's gunpowder charge must be placed in the same place on the projectile. This leads to space problems that are difficult to solve. The projectile's outer shell or casing is made as thin as possible so that the projectile has a low weight and a small total outer diameter. The wings, which are attached to the projectile's outer casing, are, however, exposed to considerable forces, so the fasteners for the wings and the part of the projectile casing that carries these fasteners must be sized relatively strong. If the wings are to be attached to the part of the projectile where the drive motor's gunpowder charge is also placed, the attachments for the wings must therefore protrude into the space where the drive motor's gunpowder charge must be placed, or else the total outer diameter of the projectile must be increased so that the attachments for the wings have space.
Den sistnevnte mulighet er meget ugunstig, da den i alvorlig grad forringer projektilets dynamiske egenskaper og dessuten medforer en okning av projektilets maksimale ytterdiameter, noe som i sin tur medforer at et utskytningslop for projektilet må ha tilsvarende stbrre diameter. Det radiale plassbehov for vingenes festeorganer blir særlig stort hvis vingene, slik det vanligvis er tilfellet, The latter option is very unfavorable, as it seriously impairs the projectile's dynamic properties and also leads to an increase in the projectile's maximum outer diameter, which in turn means that a launching barrel for the projectile must have a correspondingly larger diameter. The radial space requirement for the wings' fastening means becomes particularly large if the wings, as is usually the case,
skal kunne felles inn til en stilling tett inntil projektilet for at projektilets plassbehov ved lagring og transport skal bli mindre og projektilet skal kunne skytes ut gjennom et lop. must be able to be folded into a position close to the projectile so that the projectile's space requirements for storage and transport will be reduced and the projectile must be able to be launched through a loop.
Det omtalte konstruksjonsproblem blir enda vanskeligere hvis drivmotorens utblåsningsdyse av en eller annen grunn ikke kan være anbragt i den bakre ende.av projektilet. I så fall må drivmotoren forsynes med flere utblåsningsdyser som er jevnt fordelt rundt projektilet og munner ut i dets mantelflate i retning skrått bak-over i forhold til den tilsiktede bevegelsesretning for projektilet. Gir disse dyser like store drivkrefter, vil den resulterende drivkraft falle i projektilets symmetriakse og således være rettet gjennom projektilets tyngdepunkt, så drivmotoren ikke gir opphav til noe moment som soker å vippe projektilet eller fore det ut av dets bane, og som må kompenseres ved hjelp av projektilets styreorganer. Imidlertid er det vanskelig å sikre at samtlige dyser stadig gir like stor drivkraft. Folgelig bor drivmotorens utblåsningsdyser være plasert forholdsvis nær projektilets tyngdepunkt, så det vippende moment som vil virke på projektilet hvis de forskjellige dyser ikke skulle gi like store drivkrefter, blir lite. Samtidig må dysene være plasert slik at de utstrbmmende forbrenningsgasser fra dem ikke virker aerodynamisk forstyrrende på projektilet eller gir opphav til andre skader på dette. Således må dysene f.eks. ikke munne ut foran stabiliseringsvingene. Dette krav medforer at også drivmotorens utblåsningsdyser bor være plasert omtrent midt på den del av projektilet hvor både stabiliseringsvingene og drivmotorens kruttladning som ovenfor nevnt bor være plasert. Det vil innses at dette ytterligere vanskeliggjør en konstruktiv utformning av projektilet når det gjelder plasering av stabiliseringsvingene, drivmotorens kruttladning og drivmotorens utblåsningsdyser. The aforementioned design problem becomes even more difficult if the drive motor's exhaust nozzle cannot for some reason be located at the rear end of the projectile. In that case, the drive motor must be supplied with several exhaust nozzles which are evenly distributed around the projectile and open into its mantle surface in a direction obliquely backwards in relation to the intended direction of movement for the projectile. If these nozzles provide equal driving forces, the resulting driving force will fall in the projectile's axis of symmetry and thus be directed through the projectile's center of gravity, so that the drive motor does not give rise to any moment that seeks to tilt the projectile or guide it out of its path, and which must be compensated by of the projectile's steering bodies. However, it is difficult to ensure that all nozzles constantly provide the same amount of driving force. Consequently, the drive motor's exhaust nozzles should be positioned relatively close to the projectile's center of gravity, so that the tilting moment that will act on the projectile if the different nozzles do not provide the same driving force is small. At the same time, the nozzles must be positioned so that the exhausting combustion gases from them do not have an aerodynamically disruptive effect on the projectile or cause other damage to it. Thus, the nozzles must e.g. do not mouth out in front of the stabilizer wings. This requirement means that the drive motor's exhaust nozzles must also be positioned approximately in the middle of the part of the projectile where both the stabilization wings and the drive motor's gunpowder charge, as mentioned above, must be positioned. It will be realized that this further complicates a constructive design of the projectile in terms of the placement of the stabilization wings, the drive motor's gunpowder charge and the drive motor's exhaust nozzles.
Hensikten med den foreliggende oppfinnelse er derfor å skaffe et selvdrevet og fortrinnsvis styrbart projektil, som er oppbygget slik at det blir mulig å oppfylle samtlige ovennevnte krav med hen-syn til plaseringen av stabiliseringsvingene, drivmotorens kruttladning og drivmotorens utblåsningsdyser. The purpose of the present invention is therefore to provide a self-propelled and preferably steerable projectile, which is constructed so that it becomes possible to fulfill all the above-mentioned requirements with regard to the placement of the stabilization wings, the drive motor's gunpowder charge and the drive motor's exhaust nozzles.
Der er tidligere (fra fransk patentskrift 839.86l) kjent et ikke styrbart projektil med en drivende kruttmotor hvis kruttladning er delt opp i to ladningsdeler plasert i innbyrdes avstand aksialt etter hverandre og innrettet til å avgi sine forbrenningsgasser til utblåsningsdyser anordnet i et ringformet legeme som utgjor projektilets ytre hylster mellom de to ladningsdeler. Ved dette kjente projektil tilstrebes en slik plasering av projektilets virknings-eller stridsladning at dettes tyngdepunkt faller sammen med eller ligger nær projektilets resulterende tyngdepunkt. Virkningsladningen er derfor plasert mellom de to drivladninger og fyller dermed nesten fullstendig projektilets indre mellom drivladningene. Dette medforer den meget alvorlige ulempe at stromningsveiene for forbrenningsgassene fra drivladningene til utblåsningsdysené blir meget trange og der bare kan anvendes forholdsvis små utblåsningsdyser. Dette kjente arrange-ment er derfor ikke anvendelig for projektiler med stor hastighet. Videre vil de hete drivgasser stromme tett forbi virkningsladningen, noe som kan ha en ugunstig innvirkning på denne. På grunn av plass-mangelen er det ennvidere umulig å feste stabiliseringsvingene i nærheten av projektilets tyngdepunkt; isteden må de plaseres lengst bak på projektilet. There is previously known (from French patent document 839.86l) a non-steerable projectile with a propellant gunpowder motor whose gunpowder charge is divided into two charge parts placed at a distance from each other axially one after the other and arranged to release its combustion gases to exhaust nozzles arranged in an annular body which constitutes the projectile's outer casing between the two charge parts. With this known projectile, the aim is to place the projectile's impact or war charge in such a way that its center of gravity coincides with or is close to the resulting center of gravity of the projectile. The impact charge is therefore placed between the two propellant charges and thus almost completely fills the interior of the projectile between the propellant charges. This entails the very serious disadvantage that the flow paths for the combustion gases from the propellant charges to the exhaust nozzles become very narrow and only relatively small exhaust nozzles can be used there. This known arrangement is therefore not applicable to high-velocity projectiles. Furthermore, the hot propellant gases will flow closely past the impact charge, which can have an adverse effect on it. Due to the lack of space, it is also impossible to attach the stabilizer wings near the center of gravity of the projectile; instead, they must be placed furthest behind the projectile.
Ved det selvdrevne projektil ifolge den foreliggende oppfinnelse er drivmotorens kruttladning likedan som ved det ovennevnte tidligere kjente projektil delt opp i to separate ladningsdeler plasert i innbyrdes avstand aksialt etter hverandre og innrettet til å avgi sine forbrenningsgasser til utblåsningsdyser montert i et ringformet legeme som danner projektilets ytre hylster mellom de to ladningsdeler. Projektilet ifolge oppfinnelsen er imidlertid karakterisert ved at de to ladningsdeler har slik innbyrdes storrelse og plasering at deres felles tyngdepunkt hovedsakelig faller sammen med projektilets resulterende tyngdepunkt, samt at den del av projektilets indre som omsluttes av det ringformede legeme som inneholder utblåsningsdysene, er et tomt rom som de to ladningsdeler er innrettet til å avgi sine forbrenningsgasser til i fellesskap, samtidig som stabiliseringsvingene er festet til det nevnte ringformede legeme mellom utblåsningsdysene, betraktet i omkretsretningen. In the case of the self-propelled projectile according to the present invention, the propellant charge of the drive motor is, in the same way as in the case of the above-mentioned previously known projectile, divided into two separate charge parts placed at a distance from each other axially one after the other and arranged to release its combustion gases to exhaust nozzles mounted in an annular body which forms the exterior of the projectile sleeve between the two charge parts. However, the projectile according to the invention is characterized in that the two charge parts have such a relative size and location that their common center of gravity mainly coincides with the resulting center of gravity of the projectile, and that the part of the interior of the projectile that is enclosed by the annular body containing the ejection nozzles is an empty space to which the two charge parts are arranged to discharge their combustion gases together, at the same time as the stabilizing vanes are attached to the said annular body between the exhaust nozzles, viewed in the circumferential direction.
Ved projektilet ifolge oppfinnelsen er således ikke, som The projectile according to the invention is thus not, as
ved det kjente projektil ifolge det ovennevnte franske patentskrift, projektilets virkningsladning, men drivmotorens kruttladning anordnet slik at dens tyngdepunkt faller sammen med projektilets resulterende tyngdepunkt. Dette er som tidligere nevnt av vesentlig betydning, da drivladningen blir forbrukt under projektilets flukt og dette ikke bor medfore noen forskyvning av projektilets resulterende tyngdepunkt. Ved at den del av projektilets indre som ligger mellom de to drivladningsdeler enn videre ved projektilet ifolge oppfinnelsen utgjores av et tomt rom, kan der uten vanske-lighet oppnås store stromningstverrsnitt for forbrenningsgassene fra drivladningene til utblåsningsdysene, samtidig som der også finnes plass for tilstrekkelig store dyser. Det ringformede legeme som inneholder dysene, kan også uten vanskeligheter gjores så kraftig og få en slik form at stabilisatbrvingene kan monteres på det uten at dette gjor det nodvendig å oke projektilets ytterdiameter. in the case of the known projectile according to the above-mentioned French patent document, the impact charge of the projectile, but the propellant charge of the propellant arranged so that its center of gravity coincides with the resulting center of gravity of the projectile. As previously mentioned, this is of significant importance, as the propellant charge is consumed during the projectile's flight and this should not cause any displacement of the projectile's resulting center of gravity. By the fact that the part of the interior of the projectile which lies between the two propellant charge parts and further along the projectile according to the invention is made up of an empty space, large flow cross-sections for the combustion gases from the propellant charges to the exhaust nozzles can be achieved without difficulty, while there is also room for sufficiently large nozzles. The annular body containing the nozzles can also be made so strong without difficulty and given such a shape that the stabilizer bridges can be mounted on it without this making it necessary to increase the outer diameter of the projectile.
I det folgende vil oppfinnelsen bli belyst nærmere under henvisning til tegningen, som anskueliggjør et utforelseseksempel på projektilet ifolge oppfinnelsen. Tegningen viser aksialsnitt av bare den del av projektilet hvor dettes drivmotor samt stabiliseringsvingene og drivmotorens utblåsningsdyser er anordnet, og de aksiale snitt i henholdsvis ovre og nedre halvdel av figuren er tatt i forskjellige plan slik at ovre halvdel viser snitt gjennom en utblåsningsdyse for drivmotoren, mens nedre halvdel viser snitt i planet for en stabiliseringsvinge hos projektilet. In the following, the invention will be explained in more detail with reference to the drawing, which illustrates an exemplary embodiment of the projectile according to the invention. The drawing shows axial sections of only the part of the projectile where its drive motor as well as the stabilization wings and the drive motor's exhaust nozzles are arranged, and the axial sections in the upper and lower halves of the figure, respectively, are taken in different planes so that the upper half shows a section through an exhaust nozzle for the drive engine, while the lower half shows a section in the plane of a stabilizing wing of the projectile.
Fluktretningen for det viste projektil er markert med en pil 1. Projektilet har en drivende kruttmotor hvis kruttladning er oppdelt The flight direction of the shown projectile is marked with an arrow 1. The projectile has a propellant gunpowder motor whose gunpowder charge is divided
i to separate deler 2 og 3. Disse to ladningsdeler er plasert i innbyrdes avstand og etter hverandre aksialt, så der mellom de to ladningsdeler foreligger et rom 4 omsluttet av projektilets ytre hylster. De to ladningsdeler 2 og 3 ©r innrettet til ved sin for-brenning å avgi forbrenningsgassene til dette rom 4-, og hver ladnings-del er på konvensjonell måte utformet med en konisk uttagning 2a resp. 3a ved den respektive ende som vender mot rommet 4. in two separate parts 2 and 3. These two charge parts are placed at a distance from each other and after each other axially, so that between the two charge parts there is a space 4 enclosed by the projectile's outer casing. The two charging parts 2 and 3 are designed to release the combustion gases into this room 4 when they burn, and each charging part is conventionally designed with a conical recess 2a or 3a at the respective end facing room 4.
Den del av projektilets ytre hylster eller skall som omgir rommet 4, utgjores av et ringformet legeme 5. Som det ses> kan denne ring 5 uten å begrense den nodvendige plass for drivmotorens krutt-ladnineer 2 og 3 og uten at projektilets ytterdiameter behbver å bkes, gjbres så kraftig og få slik form at den kan bære såvel projektilets stabiliseringsvinger 6, hvorav bare en er synlig på tegningen, som drivmotorens urtblåsningsdyser 7, hvorav likeledes bare en er synlig. The part of the projectile's outer casing or shell which surrounds the space 4 is made up of an annular body 5. As can be seen, this ring 5 can be removed without limiting the space required for the drive motor's gunpowder chambers 2 and 3 and without the projectile's outer diameter having to be bent , is made so strong and shaped that it can support both the projectile's stabilization wings 6, of which only one is visible in the drawing, and the drive motor's weed blowing nozzles 7, of which only one is also visible.
Det projektil som er vist som utfbrelseseksempel på oppfinnel-sens gjenstand, er forsynt med 4 stabiliseringsvinger 6, jevnt fordelt rundt projektilet, samt 4 utblåsningsdyser 7 for drivmotoren, likeledes jevnt fordelt rundt projektilet, samtidig som vinger 6 og dyser 7 er plasert avvekslende. The projectile shown as an exemplary embodiment of the object of the invention is provided with 4 stabilizing wings 6, evenly distributed around the projectile, as well as 4 exhaust nozzles 7 for the drive motor, likewise evenly distributed around the projectile, while wings 6 and nozzles 7 are positioned alternately.
Ringen 5 som bærer stabiliseringsvingene 6 og motordysene 7, The ring 5 which carries the stabilization wings 6 and the motor nozzles 7,
er hensiktsmessig, som vist på tegningen, forsynt med innvendige inn-buktninger eller uttagninger 8 hvor motordysene 7 °S festene 9 for stabiliseringsvingene 6 er plasert, slik at ingen deler - hverken motordysene 7 eller vingefestene 6 - rager radialt utenfor projektilets ytterflate. Som det vil ses, er dette mulig selv om festene 9 for vingene 6, som i det viste utfbrelseseksempel, er utformet for å tillate innfelling av vingene til en stilling tett inntil projektilets ytterflate og derfor har et ganske stort plassbehov, særlig radialt. Den sentrale del 4a av rommet 4 som de ladningsdeler 2 og 3 avgir sine forbrenningsgasser til, behbver nemlig bare å være så stort at det gir et tilstrekkelig gjennomstrbmningsareal for forbrenningsgassene fra ladningsdelen 3 til dysene 7. is appropriate, as shown in the drawing, provided with internal indentations or recesses 8 where the motor nozzles 7 °S the attachments 9 for the stabilization wings 6 are placed, so that no parts - neither the motor nozzles 7 nor the wing attachments 6 - project radially beyond the outer surface of the projectile. As will be seen, this is possible even if the fasteners 9 for the wings 6, as in the embodiment shown, are designed to allow the wings to be folded into a position close to the outer surface of the projectile and therefore have a rather large space requirement, especially radially. The central part 4a of the room 4, to which the charging parts 2 and 3 release their combustion gases, only needs to be large enough to provide a sufficient flow area for the combustion gases from the charging part 3 to the nozzles 7.
Innbuktningene 8 i det ringfrmede legeme kan utgjores av en separat innbuktning eller uttagning for hver motordyse 7 resp. hvert vingefeste 9 eller av en eneste innbuktning som strekker seg ring-formig rundt hele omkretsen av ringen 5, og som motordysene 7 og vingefestene 9 er anbragt i. The indentations 8 in the ring-shaped body can be made up of a separate indentation or recess for each motor nozzle 7 or each wing mount 9 or of a single indentation which extends ring-shaped around the entire circumference of the ring 5, and in which the motor nozzles 7 and the wing mounts 9 are placed.
Ved denne oppbygning av projektilet blir det uten at projektilets maksimale ytterdiameter behbver å bkes, oppnådd at såvel stabiliseringsvingene 6 som motordysene 7 kan plaseres i bnsket stilling nær projektilets tyngdepunkt, og at tyngdepunktet for drivmotorens kruttladning, d.v.s. det resulterende tyngdepunkt for de to ladningsdeler 2 og 3, samtidig faller sammen med eller ligger meget nær projektilets tyngdepunkt. Til tross for at stabiliseringsvingene 6 og motordysene 7 er plasert tett ved hverandre på en meget plassbesparende måte, vil gasstråler fra dysene ikke treffe stabiliseringsvingene og således ikke skade disse eller gi opphav til aerodynamiske forstyrrelser på projektilet. With this construction of the projectile, without the projectile's maximum outer diameter needing to be bent, it is achieved that both the stabilization wings 6 and the motor nozzles 7 can be placed in the desired position near the projectile's center of gravity, and that the center of gravity for the drive motor's gunpowder charge, i.e. the resulting center of gravity for the two charge parts 2 and 3, at the same time coincides with or is very close to the center of gravity of the projectile. Despite the fact that the stabilizing wings 6 and the motor nozzles 7 are placed close to each other in a very space-saving manner, gas jets from the nozzles will not hit the stabilizing wings and thus not damage them or give rise to aerodynamic disturbances on the projectile.
Claims (2)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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SE08063/69A SE340417B (en) | 1969-06-06 | 1969-06-06 |
Publications (1)
Publication Number | Publication Date |
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NO125748B true NO125748B (en) | 1972-10-23 |
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ID=20273043
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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NO2161/70A NO125748B (en) | 1969-06-06 | 1970-06-03 |
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US (1) | US3684215A (en) |
JP (1) | JPS4810360B1 (en) |
BE (1) | BE751547A (en) |
CH (1) | CH508863A (en) |
DE (1) | DE2027371C3 (en) |
FR (1) | FR2049166B1 (en) |
GB (1) | GB1311747A (en) |
NL (1) | NL161255C (en) |
NO (1) | NO125748B (en) |
SE (1) | SE340417B (en) |
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FR2463909B1 (en) * | 1979-08-17 | 1985-10-25 | Thomson Brandt | METHOD OF PILOTING AND GUIDING A MISSILE, AND MISSILE PROVIDED WITH MEANS FOR IMPLEMENTING THIS METHOD |
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GB2172383B (en) * | 1981-06-04 | 1987-08-12 | Aerospatiale | Guided missile system |
FR2578665B1 (en) * | 1981-06-04 | 1988-02-12 | Aerospatiale | LOW SPEED MISSILE PILOTING METHOD, WEAPON AND MISSILE SYSTEM FOR IMPLEMENTING THE METHOD |
FR2863665B1 (en) * | 1988-10-12 | 2007-03-30 | Aerospatiale | STATOREACTOR HAVING A TUBULAR AND MISSILE STRUCTURE PROPULATED BY SUCH STATOREACTOR |
IL101730A (en) * | 1992-04-30 | 1995-12-31 | Israel State | Moving body such as missile having wings erectable upon acceleration |
US8350200B1 (en) * | 2009-03-26 | 2013-01-08 | Lockheed Martin Corporation | Passive aerosurface adjustment for static margin management |
CN108562195B (en) * | 2018-01-12 | 2019-05-24 | 北京航空航天大学 | A kind of modularization counter weight device and rocket being conveniently adjusted |
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GB594516A (en) * | 1940-09-04 | 1947-11-13 | Charles Dennistoun Burney | Improvements in or relating to projectiles operating with rocket propulsion |
US2503271A (en) * | 1945-02-06 | 1950-04-11 | Clarence N Hickman | Rocket projectile |
US2816721A (en) * | 1953-09-15 | 1957-12-17 | Taylor Richard John | Rocket powered aerial vehicle |
US3013494A (en) * | 1957-08-09 | 1961-12-19 | Chanut Pierre Louis Jean | Guided missile |
US3127838A (en) * | 1960-10-12 | 1964-04-07 | Bombrini Parodi Delfino Spa | Retractable blade tail unit for projectiles |
-
1969
- 1969-06-06 SE SE08063/69A patent/SE340417B/xx unknown
-
1970
- 1970-05-28 US US41373A patent/US3684215A/en not_active Expired - Lifetime
- 1970-06-02 NL NL7007998.A patent/NL161255C/en not_active IP Right Cessation
- 1970-06-03 CH CH832570A patent/CH508863A/en not_active IP Right Cessation
- 1970-06-03 NO NO2161/70A patent/NO125748B/no unknown
- 1970-06-04 JP JP45048661A patent/JPS4810360B1/ja active Pending
- 1970-06-04 DE DE2027371A patent/DE2027371C3/en not_active Expired
- 1970-06-05 BE BE751547D patent/BE751547A/en unknown
- 1970-06-05 FR FR7020862A patent/FR2049166B1/fr not_active Expired
- 1970-06-05 GB GB2737770A patent/GB1311747A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
FR2049166B1 (en) | 1974-05-24 |
NL161255B (en) | 1979-08-15 |
GB1311747A (en) | 1973-03-28 |
US3684215A (en) | 1972-08-15 |
CH508863A (en) | 1971-06-15 |
DE2027371B2 (en) | 1979-05-03 |
NL7007998A (en) | 1970-12-08 |
SE340417B (en) | 1971-11-15 |
BE751547A (en) | 1970-11-16 |
JPS4810360B1 (en) | 1973-04-02 |
NL161255C (en) | 1980-01-15 |
DE2027371A1 (en) | 1970-12-10 |
DE2027371C3 (en) | 1980-01-03 |
FR2049166A1 (en) | 1971-03-26 |
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