US3545212A - Spindle-shaped supersonic projectile with additional propulsion by sternfiring - Google Patents

Spindle-shaped supersonic projectile with additional propulsion by sternfiring Download PDF

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Publication number
US3545212A
US3545212A US690539A US3545212DA US3545212A US 3545212 A US3545212 A US 3545212A US 690539 A US690539 A US 690539A US 3545212D A US3545212D A US 3545212DA US 3545212 A US3545212 A US 3545212A
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United States
Prior art keywords
projectile
section
spindle
aft
supersonic
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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US690539A
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English (en)
Inventor
Gunter 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.)
Dynamit Nobel AG
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Dynamit Nobel AG
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Filing date
Publication date
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel AG
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Classifications

    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • 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
    • F02K7/14—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 with external combustion, e.g. scram-jet 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/40—Range-increasing arrangements with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles

Definitions

  • a supersonic projectile capable of driving through external combustion along its aft surfaces comprising a spindle-shaped body having a forward section, an aft section, and a conical enlargement section located between the forward and aft sections, each of the forward and aft sections being defined by the revolution of a slightly curved line segment so as to present both a pointed forward end and a pointed aft end and ends of greatest diameter for each of the forward and aft sections.
  • Fuel exit openings are provided at the largest end of the forward section immediately upstream from the conical enlargement section whereby, in addition to the compression shock emanating from the pointed forward end, a second, weaker oblique shock-wave is produced by reason of the conical enlargement section.
  • Supersonic projectiles have been known which have a spindle-shaped body pointed in the front and rear and which, by combustion of a sufficiently rapidly burning fuel in the area of the largest diameter of the projectile, will receive an additional drive.
  • the largest diameter of the projectile will therefore be located at the contact area of lines extending parallel to the longitudinal axis of said projectile.
  • this additional drive known as a tail heating or external combustion
  • the difficulty is in the ignition of the fuel.
  • a liquid, a liqiud gas or a highly compressed gas is used as a fuel which emerges from openings distributed along the periphery on or behind the largest diameter of the spindle-shaped body and which burns with the aid of the oxygen of the air.
  • the invention relates to a spindle-shaped supersonic projectile capable of drive through tail heating or external combustion along its aft surfaces, with a front part of the projectile converging into a pointed forward end a rear part of the projectile tapering afterwards, a conical enlargement between said forward and rear parts, and fuel exit openings at the enlargement which comprises the largest diameter of the projectile.
  • This conical enlargement in addition to the compression shock emanating from the pointed forward end of the projectile, produces a second, weaker oblique shock-wave in the area of the fuel exit openings, which on the basis of the compression taking place during this time and on the basis of the increase in the temperature of the air, will maintain in an effective manner the combustion of the customary fuels, for example, hydrogen, in the case of a supersonic stream.
  • the magnitude of this second compression shock at the same time is dependent on the angle and the diameter of the conic enlargement.
  • the tail end of the projectile can be developed for example in a known manner likewise as a minimum body.
  • the contour of the tail part of the projectile tapers toward the end of the projectile in such a manner as the volume of combustion gases increases in consequence of the continuing combustion of the fuel toward the end of the projectile and expansion of the combustion gases, so that the cross sectional size of the space occupied by the tail end of the projectile and the production gases will come as close as possible to the largest cross section of the projectile beyond the longitudinal extent of the tail end of the projectile.
  • the supersonic projectile shown in longitudinal section has a spindle-shaped body which is pointed fore and aft. It has been developed as a forward section 10 in its front part and it produces the compression shock 1 with its point.
  • fuel exit openings 2 are provided and are divided evenly over the periphery. The area of largest diameter is where tangent lines on the projectile run at least approximately parallel to the axis of the projectile.
  • the projectile Downstream from the exit opening 2, the projectile has the conical enlargement 3, which produces a smaller second compression shock 4.
  • the tail end or aft section of the projectile coverages directly from the outside edge of the conical enlargement 3 and is developed by the revolution of a slightly curved line segment similar to the forward section of the projectile. Also, the tail part of the projectile may be continued in such a manner to the combustion process that optimum conditions will be achieved with regard to the thrust and stabilization of the projectile.
  • the direction and size of the curvature of the after section 5 contour will be selected such that the crosssectional size of the space occupied by the aft section of the projectile and the combustion gases will come as close as possible to the largest cross-section of the projectile via the longitudinal extent of the aft section of said projectile. Accordingly, in the case of a quickly burning fuel, the tail part of the projectile will have to taper even more strongly directly behind the conical enlargement 3 than in the case of a slowly burning fuel.
  • the conical enlargement 3 may be adapted easily to the pertinent needs through a corresponding dimensioning of the angle and of the outside diameter in order to produce a second compression shock 4 which will suflice for the permanent ignition of the pertinent fuel, which shock will not bring about more resistance than is absolutely necessary.
  • a conical surface of 28 degrees in the case of an air flow of 3 Mach hydrogen can be brought to continuous combustion.
  • a supersonic projectile capable of drive through external combustion along its aft surfaces, comprising: a spindle-shaped body having a forward section; and aft section; and a conical enlargement section located between said forward and aft sections; said forward section being defined by the revolution of a slightly curved first line segment so as to present a pointed forward end and an end of largest diameter for said forward section downstream of said pointed forward end; fuel exit openings provided along said largest diameter end; said conical enlargement section being defined by a conical segment diverging downstream directly from said exit openings, the divergent end of said conical segment defining the outermost protrusion on said body; and said aft section, which is defined by the revolution of a slightly curved second line segment so as to present a pointed aft end, converging downstream from said divergent end of said conical segment to said pointed aft end whereby, in addition to the compression shock emanating from said pointed forward end, a second, weaker oblique shock-wave is produced

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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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Carbon And Carbon Compounds (AREA)
US690539A 1966-12-15 1967-12-14 Spindle-shaped supersonic projectile with additional propulsion by sternfiring Expired - Lifetime US3545212A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1813266A CH477668A (de) 1966-12-15 1966-12-15 Spindelförmiges Überschallgeschoss mit Zusatzantrieb durch Heckaufheizung

Publications (1)

Publication Number Publication Date
US3545212A true US3545212A (en) 1970-12-08

Family

ID=4430706

Family Applications (1)

Application Number Title Priority Date Filing Date
US690539A Expired - Lifetime US3545212A (en) 1966-12-15 1967-12-14 Spindle-shaped supersonic projectile with additional propulsion by sternfiring

Country Status (6)

Country Link
US (1) US3545212A (fr)
CH (1) CH477668A (fr)
DE (1) DE1578225A1 (fr)
FR (1) FR1552302A (fr)
GB (1) GB1173098A (fr)
SE (1) SE315533B (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4170875A (en) * 1976-06-10 1979-10-16 The United States Of America As Represented By The Secretary Of The Air Force Caseless rocket design
WO1991011676A2 (fr) * 1990-01-26 1991-08-08 Colin Humphry Bruce Jack Reduction de la force de trainee a hypervitesses
US20190145745A1 (en) * 2017-11-10 2019-05-16 Curtis E. Graber Noise control system and method for small caliber ammunition

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2671452C2 (ru) * 2016-02-24 2018-10-31 Ринад Алиманович Мухамедзянов Гиперзвуковой летательный аппарат

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3008669A (en) * 1955-01-05 1961-11-14 Frank I Tanczos Ramjet missile
US3074668A (en) * 1958-12-10 1963-01-22 Snecma Burner for hot fuel
US3363421A (en) * 1963-01-30 1968-01-16 Gen Applied Science Lab Inc Supersonic engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3008669A (en) * 1955-01-05 1961-11-14 Frank I Tanczos Ramjet missile
US3074668A (en) * 1958-12-10 1963-01-22 Snecma Burner for hot fuel
US3363421A (en) * 1963-01-30 1968-01-16 Gen Applied Science Lab Inc Supersonic engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4170875A (en) * 1976-06-10 1979-10-16 The United States Of America As Represented By The Secretary Of The Air Force Caseless rocket design
WO1991011676A2 (fr) * 1990-01-26 1991-08-08 Colin Humphry Bruce Jack Reduction de la force de trainee a hypervitesses
WO1991011676A3 (fr) * 1990-01-26 1991-11-14 Colin Humphry Bruce Jack Reduction de la force de trainee a hypervitesses
US20190145745A1 (en) * 2017-11-10 2019-05-16 Curtis E. Graber Noise control system and method for small caliber ammunition
US10928168B2 (en) * 2017-11-10 2021-02-23 Curtis E. Graber Noise control system and method for small caliber ammunition

Also Published As

Publication number Publication date
CH477668A (de) 1969-08-31
GB1173098A (en) 1969-12-03
SE315533B (fr) 1969-09-29
DE1578225A1 (de) 1971-12-16
FR1552302A (fr) 1969-01-03

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