US3144828A - Spin-stabilized rocket projectile - Google Patents

Spin-stabilized rocket projectile Download PDF

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Publication number
US3144828A
US3144828A US290288A US29028863A US3144828A US 3144828 A US3144828 A US 3144828A US 290288 A US290288 A US 290288A US 29028863 A US29028863 A US 29028863A US 3144828 A US3144828 A US 3144828A
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United States
Prior art keywords
projectile
spin
inertia
combustion chamber
moment
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
US290288A
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English (en)
Inventor
Wehlow Karl-Otto
Woyt Fritz
Renner Hermann
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Rheinmetall Industrie AG
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Rheinmetall GmbH
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Filing date
Publication date
Application filed by Rheinmetall GmbH filed Critical Rheinmetall GmbH
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Publication of US3144828A publication Critical patent/US3144828A/en
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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
    • F02K9/30—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • 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
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
    • F42B12/12—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge rotatably mounted with respect to missile housing
    • 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

Definitions

  • This invention relates to spin-stabilized rocket projectiles.
  • spin-stabilized rocket projectiles By comparison with fin-stabilized rocket projectiles, spin-stabilized rocket projectiles have the important advantage of greater accuracy, since the properties of the gyroscope ensure greater insensitivity to inaccuracies of manufacture and irregularities of gas ilow in the combustion chamber and thrust nozzle of the rocket and any disturbing influence introduced by a tail unit is eliminated.
  • a substantial advantage for military use is the simplicity of construction obtained by the omission of the generally fragile tail unit. Omission of the tail unit improves the transportability of the rocket and makes handling easier. In addition, a simple ring device can be used.
  • the stability number of a spin-stabilized projectile is proportional to the square of the axial moment of inertia and the angular velocity, and is in inverse proportion to the transverse moment of inertia and the moment of resultant air force about the transverse axis ofV the projectile, which tends to turn the projectile out of its ightpath position and thereby initiate a precession movement.
  • the stability number a' is given by the formula LTU/24,02 a,...
  • the invention provides means for limiting the speed of rotation as a function of the permissible peripheral speed of the hollow-charge or of some other spin-sensitive useful load and for keeping all 3,i44,828 Patented Aug. 18, 1964 ICC other quantities having an iniluence on the stability number of the projectile correspondingly large or small.
  • the combustion chamber in annular form around the spin-sensitive, operative portion of the projectile andfixing the chamber to the portion in such mannernthat the centres of gravity of both chamber and portion coincide or are at only a short distance from one another, and that the resultant ratio of the moments of inertia Ja/Jq (axial moment of inertia/ transverse moment of inertia) is about 0.4 to 1.5.
  • Realization of a ratio of the moments of inertia Ja/ Jq of such a value also provides a very compact form of projectile, the spin-sensitive operative portion being 1ocated in the interior of the projectile and being surrounded by a combustion chamber of annular form.
  • a momentof-inertia ring preferably consisting of a material having a high speciiic gravity, is at the centre of gravity of the projectile or at a small distance therefrom inside or outside the annular combustion chamber in order to increase further the ratio of the moments of inertia.
  • the thrust program of the rocket is so designed by employing a cruising propelling unit for compensating the drop in speed after the main propelling unit has burned out such that the projectile reaches a relatively low maximum speed.
  • This can be achieved with advantage by arranging the cruising propelling unit adjacent the outer surface of the projectile where it exhibits the elect of the moment-of-inertia ring and can either replace or supplement that ring.
  • FlG. l is a section of a rocket projectile with a propelling unit
  • FIG. 2 is a section of a rocket projectile with separate starting and cruising propelling units
  • FIG. 3 is a section of a rocket projectile with a starting propelling unit and a ram jet propelling unit as cruising propelling unit.
  • the rocket projectile illustrated in FIG. l comprises a central, spin-sensitive operative portion arranged with its axis along the longitudinal axis and shown as a hollow charge l.
  • a combustion chamber 2 of annular form with a propellent charge 3 is arranged round the hollow charge l.
  • the structure of the projectile is such that the centres of gravity of the propelling unit and the hollow charge are substantially coincident and form a common centre of gravity S.
  • a stabilityl number a 1 is obtained over the entire operating range.
  • the propellent charge of the cruising propelling unit in the common combustion chamber on the outer shell of the combustion chamber, so that, possibly with the use of ballast powder, it has the properties of the moment-of-inertia ring described and can increase the etIect thereof in the critical range of speed of rotation in order to maintain an adequate stability number, or can replace the moment-ofinertia ring.
  • a rocket projectile illustrated in FIG. 2 likewise has an operative portion consisting of a hollow charge 1.
  • the operative portion is surrounded by a starting propelling unit 3 and a cruising propelling unit 6 disposed concentrically with respect to the hollow charge 1.
  • the projectile shown in FIG. 2 is otherwise similar to that shown in FIG. 1, the positions of the centres of gravity of the hollow charge, the starting unit 3 and the cruising unit 6 being substantially coincident.
  • a cruising propelling unit 6 is arranged concentrically around the starting propelling unit 3 and is in the form a ram-jet propelling unit.
  • the construction of the projectile of FIG. 3 is otherwise similar to that of the projectile shown in FIG. 1.
  • a spin-stabilized rocket projectile comprising in combination a spin-sensitive portion, a rst annular combustion chamber forming a starting propulsion unit for said projectile, said irst chamber surrounding said portion and xed thereto, and a second annular combustion chamber forming a cruising propulsion unit for said projectile and also surrounding said portion, the centres of gravity of said portion and said first and second combustion chambers being substantially coincident and the ratio of axial moment of inertia to transverse moment of inertia of said projectile lying within the range of about 0.4 to 1.5.
  • a spin-stabilized rocket projectile comprising in combination a spin-sensitive portion, a rst annular combustion chamber forming a starting propulsion unit for said projectile, said rst chamber surrounding said por tion and fixed thereto, and a second annular combustion chamber forming a cruising propulsion unit for said pro- 4f jectile and positioned around said portion to act as a moment-of-inertia ring, the centres of gravity of said portion and said first and second combustion chambers being substantially coincident and the ratio of axial moment of inertia to transverse moment of inertia of said projectile lying Within the range of about 0.4 to 1.5.
  • a spin-stabilized rocket projectile comprising in combination a spin-sensitive portion, a rst annular combustion chamber forming a starting propulsion unit for said projectile, said lirst chamber surrounding said portion and xed thereto, a second annular combustion chamber forming a cruising propulsion unit for said projectile and also surrounding said portion, the centres of gravity of said portion and said first and second chambers being substantially coincident and the ratio of arial moment of inertia to transverse moment of inertia of said projectile lying Within the range of about 0.4 to 1.5, and a moment-of-inertia ring disposed around and concentric With respect to said portion in a position such that the centre of gravity of said ring is substantially coincident with said centres of gravity of said portion and said rst and second combustion chambers.
  • a spin-stabilized rocket projectile comprising in combination a spin-sensitive portion, a starting propulsion unit including an annular combustion chamber surrounding said portion and fixed thereto, and a ram jet cruising propulsion unit including an annular combustion chamber surrounding the combustion chamber of said starting propulsion unit, the centres of gravity of said portion and the combustion chambers of said starting and said cruising propulsion units being substantially coincident and the ratio of axial moment of inertia to transverse moment of inertia of said projectile lying within the range of about 0.4 to 1.5.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Testing Of Engines (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US290288A 1962-06-30 1963-06-21 Spin-stabilized rocket projectile Expired - Lifetime US3144828A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DER33038A DE1213760B (de) 1962-06-30 1962-06-30 Hohlladungsgeschoss mit Eigenantrieb

Publications (1)

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US3144828A true US3144828A (en) 1964-08-18

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US290288A Expired - Lifetime US3144828A (en) 1962-06-30 1963-06-21 Spin-stabilized rocket projectile

Country Status (6)

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US (1) US3144828A (el)
BE (1) BE634186A (el)
CH (1) CH400839A (el)
DE (1) DE1213760B (el)
DK (1) DK112497B (el)
GB (1) GB1014847A (el)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3439613A (en) * 1964-11-26 1969-04-22 Bolkow Gmbh Self-propelled hollow charge having concave liner with propellant contained therein
US20090320443A1 (en) * 2008-05-09 2009-12-31 Geisler Robert L Propulsion system, opposing grains rocket engine, and method for controlling the burn rate of solid propellant grains
WO2011091484A1 (en) * 2010-01-28 2011-08-04 Lubormir Mihaylov Tomov Spin-stabilized ammunition

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB516818A (en) * 1937-06-28 1940-01-12 Sageb Sa Improvements in or relating to projectiles comprising a reaction propulsion device
US2519878A (en) * 1946-07-31 1950-08-22 Carold F Bjork Rocket projectile

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT6796B (el) * 1899-05-12 1902-02-25 Jacques Luciani
FR816083A (fr) * 1936-03-30 1937-07-29 Perfectionnements aux projectiles
US2968244A (en) * 1948-05-07 1961-01-17 Jr Leo Maas Jet accelerated missile
US2684629A (en) * 1949-06-16 1954-07-27 Bofors Ab Reaction-motor missile
FR1052450A (fr) * 1952-03-14 1954-01-25 France Etat Projectile auto-propulsé à efficacité améliorée
FR1265295A (fr) * 1960-05-18 1961-06-30 Perfectionnements apportés aux missiles, notamment à ceux destinés à répondre aux besoins de l'infanterie

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB516818A (en) * 1937-06-28 1940-01-12 Sageb Sa Improvements in or relating to projectiles comprising a reaction propulsion device
US2519878A (en) * 1946-07-31 1950-08-22 Carold F Bjork Rocket projectile

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3439613A (en) * 1964-11-26 1969-04-22 Bolkow Gmbh Self-propelled hollow charge having concave liner with propellant contained therein
US20090320443A1 (en) * 2008-05-09 2009-12-31 Geisler Robert L Propulsion system, opposing grains rocket engine, and method for controlling the burn rate of solid propellant grains
US8051640B2 (en) * 2008-05-09 2011-11-08 Robert L Geisler Propulsion system, opposing grains rocket engine, and method for controlling the burn rate of solid propellant grains
WO2011091484A1 (en) * 2010-01-28 2011-08-04 Lubormir Mihaylov Tomov Spin-stabilized ammunition

Also Published As

Publication number Publication date
GB1014847A (en) 1965-12-31
DE1213760B (de) 1966-03-31
BE634186A (el) 1963-11-04
DK112497B (da) 1968-12-16
CH400839A (de) 1965-10-15

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