US2946285A - Rocket projectiles - Google Patents

Rocket projectiles Download PDF

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Publication number
US2946285A
US2946285A US649900A US64990057A US2946285A US 2946285 A US2946285 A US 2946285A US 649900 A US649900 A US 649900A US 64990057 A US64990057 A US 64990057A US 2946285 A US2946285 A US 2946285A
Authority
US
United States
Prior art keywords
charge
projectile
starter
nozzle
missile
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US649900A
Other languages
English (en)
Inventor
Nauschutz Peter
Wessel Wilhelm
Kuhlo Gunther
Dreyer Kuno
Bolkow Ludwig
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boelkow Entwicklungen KG
Original Assignee
Boelkow Entwicklungen KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boelkow Entwicklungen KG filed Critical Boelkow Entwicklungen KG
Application granted granted Critical
Publication of US2946285A publication Critical patent/US2946285A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • 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
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
    • F02K9/763—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with solid propellant
    • 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
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins

Definitions

  • the present invention pertains to a rocket projectile equipped with two propellant eharges, an initial starter charge and a travel charge.
  • the primary object of the present invention is to eliminate the conventional starting equipment in launching rocket projectiles and sirnilar vehicles.
  • the inventive idea applied to a.rocket projectile with a Starter and a travel charge involves the positioning of the axis of the flow of the combustion gases from the nozzle df the Dahl charge, relative to the direction of the 'axis of the projectile at a predetermined angle.
  • Another object of the invention is to provide the tl 1rust nozzles of the starter charge with means to change their angular positions relative to the direction of the discharge and to lock them on the projectile.
  • the starter charge itself may be thus adjusted integrally with its nozzle.
  • vanes shaped in Such a mahner that they function as legs of the projeotile.
  • pr0jectiles may be placed on the leg vanes upon a platform substantially in the direction of the discharge.
  • a mcket projeetile in particula-t a lang range g uided one, equipped in accordanmwith this invenlion, may be placed in the direetion of aim on any desired support, including the bare ground. Upon fining, it will lift itself fromihesupport by thcomponent pf th "s-tarfi ing force created by theinclination cyf the stafitercharge nozzle and directed -transverse to ;the support and simul- Parts in fragmentary cross-sectidnal view.
  • Fig. 2 is a rear elevation of Fig. l.
  • the main' bodv" 0f the projectile 1 is a cylindrical structure elosed in the 'front part with a pointed conical body 2.
  • the main body is hollowto accommodate a pro'pellai1t charge.
  • the thrust nozzle 9 of the Starter charge 10 expands outward:and is niounted with the projectile at an angle to its aiiis of morethnl 5" dire'cteddownwarcl andlowa'rds'therear.
  • the axis of thestarter nozzle passes' through the centerof gr'avity'5.
  • the starter charge 10 is mounted removably to the projectile body 1 by a front and"rear holdifig:ih'eans 13 and -16respectiVely both attached to the"projectile body-The front holdingmeans cmprise a bordl4j eanted towa'rd therear-at adwnwrdangle.
  • Afpin 011 a similar -prqjection*l5 :provided in thef'shell "0f the Y Starter harge is slanted at an angle coriespondin'gfto fc thereat holding mens '16 at apoint 17; .--Du ring tlie combustion of the startercharg the soldering poii1t 17 is subject to the resulting heat which exceeds the melting' temperature of the solder.
  • the harmony charge Shell preferably has in its top rear past the soldering point anothet projection engaging the holding means 16. Even after the melting of the solder, the starter chafge'is' kept in its place until its thrust against the two holding means is spent. The diversity charge shell thereafter will drop ofi by gravity.
  • each pair of guide vanes maintains a position of 45 from horizontal and vertieal and not the conventional horizontal and vertical positions respectively, employed in the prior art.
  • long range guided missiles it is therefore also important to maintain substantially the starting position during travel in order to avoid expensive and eornplicated means for their long range guidance.
  • the invention may be applied preferably also to long range guided missile since the accuracy of the aim is independent of the position ineidentally chosen prior to its discharge.
  • the usefulness of the invention is not limited, however, to long range gnided missiles.
  • Control means may be included to make the vertical and/or horizontal angles of the starte: charge nozzle adjustable relative to the projectile to change the direction of gas flow.
  • Such control means a1:e considered to be novel in combination with the arrangement of the above described type.
  • the invention may be practiced also with a satisfactory accuracy of aim in combination with non-'guided projectiles, which are being discharged from various type launching bases, positioned at various angles, in awakeular when the angle of the starter charge nozzle is adjustable, and when the angula: acljustments are m:asurable, for instance, With a level, pendulum, compass or sirnilar angle measuring means, either directly mounted on the projectile 01' to be used independently from outside.
  • rear guide vanes are shown utilized as legs, other projections of a missile includifig those positioncid in the center and in the front such as ailefons, wings, undercarriages may be ad apted to serve as leg supports simultaneously, or sepa'rate leg supports may be included.
  • the invention is not l imited to ordnance proj ectiles but its p1inciples and teachings may be used also in other type missiles including jet planes, torpedoes, etc.
  • the four guide vane positions are not li1nitecl to the angle of 45 from horizontal.;l'his angle is considered only to be optimum.
  • the invention i not limited to- Cdnventional ordnance type propellant fuels, such as powder in grain. Any fluid dr solid ti pe propellafits, in iluding petroleum products, liquified gases etc. cjtheri viseusable carfyinlg out theobj'ects of this invention are inoludecl,

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US649900A 1956-04-05 1957-04-01 Rocket projectiles Expired - Lifetime US2946285A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB39751A DE1078903B (de) 1956-04-05 1956-04-05 Raketengetriebener Flugkoerper

Publications (1)

Publication Number Publication Date
US2946285A true US2946285A (en) 1960-07-26

Family

ID=6965894

Family Applications (1)

Application Number Title Priority Date Filing Date
US649900A Expired - Lifetime US2946285A (en) 1956-04-05 1957-04-01 Rocket projectiles

Country Status (5)

Country Link
US (1) US2946285A (de)
CH (1) CH363908A (de)
DE (1) DE1078903B (de)
FR (1) FR1173322A (de)
GB (1) GB855592A (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3069975A (en) * 1959-01-28 1962-12-25 Bolkow Entwicklungen K G Protective means for rocketpropelled missiles
US3132827A (en) * 1960-08-27 1964-05-12 Onera (Off Nat Aerospatiale) High speed airplane having auxiliary rockets
US3403873A (en) * 1963-01-24 1968-10-01 Navy Usa Guided missile
US4445652A (en) * 1982-03-25 1984-05-01 The Boeing Company Adjustable rocket thrust alignment device
US4949918A (en) * 1989-08-02 1990-08-21 Arszman Jerrold H Moment control of rockets
CN107933946A (zh) * 2017-12-11 2018-04-20 浙江大学 无人机两点式火箭助推发射装置及其方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1172156B (de) 1959-04-23 1964-06-11 Boelkow Entwicklungen Kg Aerodynamisch lenkbarer, rueckstossgetriebener Flugkoerper
CN111306994B (zh) * 2020-05-07 2021-06-01 北京理工大学 可重复使用的复合材料导弹托座

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1629767A (en) * 1924-03-18 1927-05-24 Valdes Salustio Jet-propulsion apparatus for the driving of vehicles, ships, boats, flying machines, and the like
US2503271A (en) * 1945-02-06 1950-04-11 Clarence N Hickman Rocket projectile
US2537487A (en) * 1946-03-01 1951-01-09 Stone William Card Adjustable exhaust for jetpropelled aircraft
US2596644A (en) * 1946-12-10 1952-05-13 Us Sec War Automatically detachable flashless nozzle for rockets
US2748703A (en) * 1948-04-27 1956-06-05 Wilbur H Goss Rocket type launching carriage for ordnance missile
US2787218A (en) * 1952-02-25 1957-04-02 Anthony Alastair Aircraft
US2818779A (en) * 1952-04-24 1958-01-07 Casper J Koeper Non-tip off launcher
US2833494A (en) * 1953-06-15 1958-05-06 Northrop Aircraft Inc Rocket ejection system

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE305160C (de) *

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1629767A (en) * 1924-03-18 1927-05-24 Valdes Salustio Jet-propulsion apparatus for the driving of vehicles, ships, boats, flying machines, and the like
US2503271A (en) * 1945-02-06 1950-04-11 Clarence N Hickman Rocket projectile
US2537487A (en) * 1946-03-01 1951-01-09 Stone William Card Adjustable exhaust for jetpropelled aircraft
US2596644A (en) * 1946-12-10 1952-05-13 Us Sec War Automatically detachable flashless nozzle for rockets
US2748703A (en) * 1948-04-27 1956-06-05 Wilbur H Goss Rocket type launching carriage for ordnance missile
US2787218A (en) * 1952-02-25 1957-04-02 Anthony Alastair Aircraft
US2818779A (en) * 1952-04-24 1958-01-07 Casper J Koeper Non-tip off launcher
US2833494A (en) * 1953-06-15 1958-05-06 Northrop Aircraft Inc Rocket ejection system

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3069975A (en) * 1959-01-28 1962-12-25 Bolkow Entwicklungen K G Protective means for rocketpropelled missiles
US3132827A (en) * 1960-08-27 1964-05-12 Onera (Off Nat Aerospatiale) High speed airplane having auxiliary rockets
US3403873A (en) * 1963-01-24 1968-10-01 Navy Usa Guided missile
US4445652A (en) * 1982-03-25 1984-05-01 The Boeing Company Adjustable rocket thrust alignment device
US4949918A (en) * 1989-08-02 1990-08-21 Arszman Jerrold H Moment control of rockets
CN107933946A (zh) * 2017-12-11 2018-04-20 浙江大学 无人机两点式火箭助推发射装置及其方法

Also Published As

Publication number Publication date
FR1173322A (fr) 1959-02-24
DE1078903B (de) 1960-03-31
CH363908A (de) 1962-08-15
GB855592A (en) 1960-12-07

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