US3468127A - Rocket projectiles - Google Patents

Rocket projectiles Download PDF

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Publication number
US3468127A
US3468127A US578934A US3468127DA US3468127A US 3468127 A US3468127 A US 3468127A US 578934 A US578934 A US 578934A US 3468127D A US3468127D A US 3468127DA US 3468127 A US3468127 A US 3468127A
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United States
Prior art keywords
vanes
rocket
spin
projectile
propellant
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
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US578934A
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English (en)
Inventor
Reginald John Rosser
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UK Secretary of State for Defence
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UK Secretary of State for Defence
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Filing date
Publication date
Application filed by UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
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Publication of US3468127A publication Critical patent/US3468127A/en
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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
    • F42B10/26—Stabilising arrangements using spin
    • F42B10/28—Stabilising arrangements using spin induced by gas action
    • F42B10/30—Stabilising arrangements using spin induced by gas action using rocket motor nozzles
    • 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
    • F02K9/97—Rocket nozzles
    • F02K9/974—Nozzle- linings; Ablative coatings

Definitions

  • a rocket projectile having a group of inclined vanes symmetrically disposed in the propellant gas stream just upstream of the venturi for imparting spin to the rocket.
  • the vanes are made of a consumable material, so that spin is imparted during the early stages of propulsion before the vanes are consumed, and may consist of helical ribs on the bore surface of an annular body fitted into the rocket body just forward of the venturi throat.
  • This invention relates to rocket projectiles and is con cerned with means for imparting to such projectiles, a limited amount of spin to improve flight accuracy by reducing the effects of thrust malalignment.
  • the optimum spin is attained on the launcher, being therefore, effective during the earliest stages of free flight.
  • Spin imparted by inclined jets derived from the main propulsion motor or by aerodynamic means uch as inclined fins continues to develop well into the free flight period and either attains its optimum value later in flight or, if the optimum is reached early, will continue to develop beyond the optimum which is undesirable.
  • This invention therefore comprises, in a rocket projectile, a group of inclined vanes symmetrically disposed in the path of the propellant gas stream for imparting spin to the projectile, the said vanes being made of a consumable material whereby the whole of the imparted spin is developed during the early stages of propulsion, before the vanes have been consumed.
  • the vanes are consumed before, or soon after, the rocket has left the launcher.
  • the desired spin may be obtained from vanes located at or downstream of the throat of the venturi, this arrangement may introduce disturbances by interfering with the gas flow at a critical position. It is therefore preferred to locate the vanes near but upstream of the throat.
  • the vanes may be of any convenient form and may be composed of any consumable material which will last long enough and has sufiicient strength to impart the desired spin.
  • the amount of spin imparted can be controlled by varying the inclination of the vanes and/or influencing the consumption time through such factors as selection of material or variation of vane thickness. These vanes may be consumed by burning or melting or a combination of both.
  • FIG. 1 is a partly sectioned, side elevation of a rocket projectile
  • FIG. 2 is a sectional detail showing an alternative construction
  • FIG. 3 is a view looking on the forward face of a ring member as shownat 7a of FIG. 2.
  • the body 1 FIG. 1 may have any of the usual known forms terminating at the rear end in a motor comprising a combustion chamber 2 containing a propellant charge 3 and closed at its rear end by a block incorporating a single axial venturi 4.
  • the motor casing 5 is generally cylindrical in shape and the forward end of the venturi block is so formed as to provide an internal shoulder 6 at the rear end of the combustion chamber 2.
  • the side faces of the ribs separating these grooves 8 act in the manner of turbine blades when impinged upon by the effluent propellant gases whereby spin is imparted to the projectile.
  • the ring member 7 is made of a consumable material which, when subjected to the action of the hot propellant gases, either burns or melts so that the turbine action ceases after a short time, when the grooves 8 cease to exist.
  • ring member 7a shown in FIGS. 2 and 3 has similar grooves 8a formed in its inner surface but has a curved outer surface 9 in the form of a frustum of an ogive which fits snugly onto a similarly shaped seating formed just forward of the throat 10 of the venturi 4a. It is located and fixed in position by means of dowels 11 and a fillet of cement around the forward edge 12.
  • the material of the ring 7, 7a may be a plastics material which may burn or melt; a propellant which will bum; a metal, such as aluminium, which will melt or any other suitable material. Metals are less desirable than the other materials since molten metal tends to increase nozzle erosion.
  • a ring member of propellant could, of course, be made integral with the charge.
  • One suitable material, which has the advantage of lightness, is polyethylene.
  • the motor may operate through multiple venturis instead of a single axial one.
  • Spin may be sustained during flight, if desired, by employing a known means such as inclined fins in addition to the de vice of the invention.
  • a rocket projectile having a body, a propellant motor incorporated at the rear end of the body, venturi means for the efflux of propellant gases to drive the projectile, and a group of inclined vanes, located just upstream of the said venturi means and symmetrically disposed in the path of the propellant gas stream, for imparting spin to the projectile; the said vanes being made of a consumable material whereby the Whole of the imparted spin is developed during the early stages of propulsion, before the vanes have been consumed.
  • a rocket projectile having a body, a propellant motor incorporated at the rear end of the body, an axial venturi for the efilux of propellant gases to drive the projectile, and a group of inclined vanes located just upstream of the throat of said axial venturi, and symmetrically disposed in the path of the propellant gas stream, for iming a ring shaped member of consumable material coaxial with the rocket in the bore surface of which ring is formed a plurality of grooves; and a plurality of ribs separating the grooves which ribs constitute the aforesaid vanes.
  • vanes are made of a solid propellant material.
  • a rocket projectile comprising a body; a propellant motor incorporated at the rear of the body, a single axial venturi at the rear end of the motor for driving the projectile; a ring shaped member coaxial with the projectile and located in a seating just upstream of the throat of the .4 venturi, in the bore surface of which ring shaped member is formed a plurality of oblique grooves; and a plurality of ribs separating the said grooves and constituting a group of vanes for imparting spin to the projectile; said ring shaped member being made of a consumable material whereby the whole of the imparted spin is developed during the early stages of propulsion, before the vanes have been consumed.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
US578934A 1965-09-10 1966-09-09 Rocket projectiles Expired - Lifetime US3468127A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB38846/65A GB1148431A (en) 1965-09-10 1965-09-10 Improvements in or relating to rocket projectiles

Publications (1)

Publication Number Publication Date
US3468127A true US3468127A (en) 1969-09-23

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Family Applications (1)

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US578934A Expired - Lifetime US3468127A (en) 1965-09-10 1966-09-09 Rocket projectiles

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US (1) US3468127A (cs)
FR (1) FR1573822A (cs)
GB (1) GB1148431A (cs)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3635404A (en) * 1970-06-18 1972-01-18 Us Navy Spin stabilizing rocket nozzle
JPS5055100A (cs) * 1973-09-20 1975-05-15
US3968646A (en) * 1974-06-28 1976-07-13 The United States Of America As Represented By The Secretary Of The Army Noise controllable nozzle closure
US4022129A (en) * 1976-01-16 1977-05-10 The United States Of America As Represented By The Secretary Of The Air Force Nozzle ejection system
US6548794B2 (en) * 2001-03-13 2003-04-15 Raytheon Company Dissolvable thrust vector control vane

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1604865A (en) * 1977-12-29 1981-12-16 Secr Defence Projectile tail fin units
DE2948197C2 (de) * 1979-11-30 1981-12-24 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Startschubdüse für Rückstoßtriebwerke, insbesondere Raketen-Staustrahltriebwerke
WO1999046499A1 (en) * 1998-03-10 1999-09-16 Tsai, Artur Rifled jet nozzle
RU2211939C2 (ru) * 2001-04-05 2003-09-10 Федеральное государственное унитарное предприятие Государственный ракетный центр "КБ им. акад. В.П. Макеева" Сопло ракетного двигателя для придания ракете вращения относительно продольной оси
DE10126923B4 (de) * 2001-06-01 2006-11-23 Eads Space Transportation Gmbh Raketentriebwerk mit Trennung von Innenmantel und Außenmantel

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1901852A (en) * 1930-07-28 1933-03-14 Stolfa Hermann Rocket
US2206057A (en) * 1939-08-31 1940-07-02 Leslie A Skinner Rocket projectile
US2924174A (en) * 1954-01-06 1960-02-09 William B Mclean Combustible pre-spin turbine for spinner rockets

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1901852A (en) * 1930-07-28 1933-03-14 Stolfa Hermann Rocket
US2206057A (en) * 1939-08-31 1940-07-02 Leslie A Skinner Rocket projectile
US2924174A (en) * 1954-01-06 1960-02-09 William B Mclean Combustible pre-spin turbine for spinner rockets

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3635404A (en) * 1970-06-18 1972-01-18 Us Navy Spin stabilizing rocket nozzle
JPS5055100A (cs) * 1973-09-20 1975-05-15
US3968646A (en) * 1974-06-28 1976-07-13 The United States Of America As Represented By The Secretary Of The Army Noise controllable nozzle closure
US4022129A (en) * 1976-01-16 1977-05-10 The United States Of America As Represented By The Secretary Of The Air Force Nozzle ejection system
US6548794B2 (en) * 2001-03-13 2003-04-15 Raytheon Company Dissolvable thrust vector control vane

Also Published As

Publication number Publication date
FR1573822A (cs) 1969-07-11
GB1148431A (en) 1969-04-10

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