US3174430A - Rocket projectile with spreadable empennage - Google Patents

Rocket projectile with spreadable empennage Download PDF

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Publication number
US3174430A
US3174430A US210115A US21011562A US3174430A US 3174430 A US3174430 A US 3174430A US 210115 A US210115 A US 210115A US 21011562 A US21011562 A US 21011562A US 3174430 A US3174430 A US 3174430A
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US
United States
Prior art keywords
plunger
projectile
combustion chamber
cylinder
rocket
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
US210115A
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English (en)
Inventor
Apotheloz Robert
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.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Application granted granted Critical
Publication of US3174430A publication Critical patent/US3174430A/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
    • 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
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Definitions

  • the invention relates to a rocket projectile, the spreadablc fins of which are swung out, after having left the launching tube, by displacing a plunger within a cylinder space by means of a source of power, and wherein a propulsive gas duct is arranged between the cylinder space and the combustion chamber of the rocket.
  • a cavity in the plunger opening forwardly is in spatial communication through a bore with the combustion chamber of the tiring barrel.
  • the frontal end of the plunger has a larger diameter than its rear end.
  • the cylinder space, wherein the plunger is housed, is provided at its rear portion with a bore, through which in the tiring position of the plunger the cylinder space is likewise in communication with the interior of the ring barrel.
  • the portion of the cylinder space behind the frontal portion of the plunger is discharged more rapidly than the cavity of the plunger so that by the expansion of the gases still present in the cavity of the plunger the latter is forced back into that position, in which the tins are spread out.
  • the present invention has the object of providing a rocket projectile to be launched from a launching tube land having a spreadable empennage of tins retracted before the launching, which combines the advantages of the projectiles previously known for being fired from the barrel of a fire arm or from a launching tube, while obviating their disadvantages. It is a particular object of the invention to provide a rocket projectile of this kind, the tins of which contact the inner walls of the launching tube only with a weak force at the firing and while passing through said launching tube, and are spread out rapidly immediately after the projectile has left said launching tube.
  • a rocket projectile for launching from a launching tube, comprising in combination: Ia combustion chamber, a cylinder arranged at the rear end of said combustion chamber co-axially therewith, a plunger slidably mounted in said cylinder, power means including a propellant charge in operation generating propulsive gases operatively acting on said plunger, iins coupled to said plunger arranged at the rear end of said combustion chamber pivotally about axes perpendicular to the axis of said combustion chamber and having a retracted position parallel to said axis and a spread-out position forming an empennage of said rocket projectile, said cylinder having a iirst propulsive gas duct at a point of its circumference in communication with said combustion chamber Iand covered at least partly by said plunger in the retracted position of said fins coupled therewith, and cleared by said plunger after the beginning of the spreading movement of said said cylinder
  • FIGURE l is 4a cross-sectional view of the rear end of .a rocket projectile taken upon section line I-l of FIG'URE 3.
  • FIGURE 2 is a cross-sectional View taken upon section yline II-II of FIGURE l.
  • FIGURE 3 is a cross-sectional View taken upon section line III-III of FIGURE 1.
  • FIGURE 4 is an elevational view with parts in section illustrating the rear end of the rocket projectile after being launched from a tube.
  • FIGURE 5 is a cross-sectional view of a detail illustrating a modification.
  • FIGURE 6 is a similar View illustrating a further modification
  • FIGURE 7 is a similar view illustrating a still further modification.
  • the forward portion of the cylinder 6 projecting into the combustion chamber I is provided with a bore 15 forming the propulsive gas duct, which connects accordingly the combustion chamber with the space of the cylinder 6.
  • the bore i5 issues into the cylinder space at a point of the circumference thereof covered by the plunger 13 at the moment of firing.
  • arms 16 are fixed, on each of which, as shown also in FIGURE 3, two guide discs 17 lare iitted, between which engage the forward edges 11a of the tins 11. In the retracted position of the empennage, the rear edges of the arms form abutments for the tins 1I.
  • the movement of the plunger 13, and accordingly the spreading of the tins 11 is initiated by the bias of the spring 14 serving as a source of power, which moves the plunger back, firstly so far, that it completelyV clears the bore 15.
  • the plunger 13 is moved back with a reinforced power.
  • the tins 11 are swung outwardly very rapidly into the operative position (FIGURE 4).
  • the movement of the fins 11 is delayed before reaching their end position by the inertia forces engaging on them generated by the acceleration of the rocket, so that the impact yof their edges llc ⁇ on the flange 8a of the sleeve is damped.
  • the plunger 13 in its rear position abuts with its shoulder 13a a complementary shoulder 9a of the bore 9, and moreover the arms 16 abut with their faces 16a the edges 11b of the tins 11 which edges in this position are directed parallel to the longitudinal axis of the rocket, whereby these tins are xed in their operative position.
  • FIGURE 5 shows a second propulsive gas duct connecting the combustion chamber with the cylinder space which is formed by a bore 19 machined into the forward end wall of the cylinder.
  • This bore has a smaller diameter than the bore 15, and cannot be obturated by the plunger. gases tiowing upon firing through this second propulsive gas duct from the source of power to the cylinder ahead of the plunger 13 are throttled so strongly that they exert a force which is considerably smaller than the force generated by the plunger when fully spreading the fins.
  • a groove 20 or 21 may be provided, which either runs according to FIGURE 6 in the wall of the cylinder 6 parallel Vto the cylinder axis, or is cut into the surface of the plunger 13 as according to FIGURE 7. Since this groove 20 or 21 owing to its small cross sectional area establishes communication between the combustion chamber and the cylinder space to a small extent only, the force initially acting on the plunger is likewise smaller than after such communtcation is completely cleared.
  • the plunger is held and secured in its end position by the spring 14 after the termination of the combustion and fading out Thel of the gas pressure.
  • the conical shoulder 13a -of the plunger may be made with such an ⁇ aperture angle that it is held self-locking in its seat 9a.
  • a rocket projectile to be tired from a tube comprising a carrier secured to the rear end of said projectile, a combustion chamber located in front of said carrier, a cylinder arranged on said carrier projecting into said combustion chamber, control means including a plunger slidably mounted in said cylinder, power means including a propellant charge in operation generating propulsive gases operatively acting on said plunger, fins coupled to said plunger mounted on said carrier pivotally about axes perpendicular to the longitudinal axis of said projectile, said tins when in a retracted position extending parallel to said axis and when in a spread-out position extending outwardly at an angle to said axis, said cylinder having a ⁇ irst propulsive gas duct at a point of its circumference in communication with said combustion chamber controlled by said plunger of said control means in said retracted position of said ns coupled therewith, and cleared by said plunger of said controlmeans after the beginning of the spreading movement of said-f
  • a rocket projectile as claimed in claim l wherein said power means-includes further -a compression spring .arranged in said cylinder between the bottom thereof and said plunger and biasing the samel rearwardly at a force weaker than the force exerted by t-he pressure of said propulsive gases on Vsaid plunger after the latter has cleared said -first propulsive gas duct which is completely closed in the retracted position of said n's.
  • a rocket projectile as claimed in claim 1, compris- .ing a second propulsive gas duct 'permanently connecting -said combustion chamber with said cylinder, said second propulsive gas duct being of a cross sectional 4area substantially smaller than saidfirst propulsive gas duct, the

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
US210115A 1961-07-19 1962-07-16 Rocket projectile with spreadable empennage Expired - Lifetime US3174430A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH846761A CH385678A (de) 1961-07-19 1961-07-19 Raketengeschoss mit Spreizleitwerk

Publications (1)

Publication Number Publication Date
US3174430A true US3174430A (en) 1965-03-23

Family

ID=4340821

Family Applications (1)

Application Number Title Priority Date Filing Date
US210115A Expired - Lifetime US3174430A (en) 1961-07-19 1962-07-16 Rocket projectile with spreadable empennage

Country Status (5)

Country Link
US (1) US3174430A (de)
CH (1) CH385678A (de)
DE (1) DE1148913B (de)
FI (1) FI41125B (de)
GB (1) GB968639A (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3598345A (en) * 1967-09-06 1971-08-10 Oerlikon Buehrle Ag Rocket with folding fins and braking device
US4175720A (en) * 1978-04-05 1979-11-27 The United States Of America As Represented By The Secretary Of The Navy Retainer/release mechanism for use on fin stabilized gun fired projectiles
US4523728A (en) * 1983-03-07 1985-06-18 Ford Aerospace & Communications Corporation Passive auto-erecting alignment wings for long rod penetrator
US4860969A (en) * 1987-06-30 1989-08-29 Diehl Gmbh & Co. Airborne body
RU2218547C1 (ru) * 2002-12-06 2003-12-10 Закрытое акционерное общество "Энергетика" Осколочно-фугасный снаряд

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106640893A (zh) * 2016-12-18 2017-05-10 内蒙古航天红峡化工有限公司 一种固体火箭发动机喷管装配用导向销

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896562A (fr) * 1958-12-23 1945-02-26 Liaison électrique par fiche avec ressorts de connexion à pression
GB634090A (en) * 1946-07-15 1950-03-15 William Alexander Onslow Marti Improvements in and connected with stabilizing fins for projectiles
US2773424A (en) * 1951-06-01 1956-12-11 Mordica O Johnston Gun perforator
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896502A (fr) * 1940-09-23 1945-02-23 Commerciale Caproni Comp Dispositif de commande des ailettes d'un projectile muni d'un empennage

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB634090A (en) * 1946-07-15 1950-03-15 William Alexander Onslow Marti Improvements in and connected with stabilizing fins for projectiles
US2773424A (en) * 1951-06-01 1956-12-11 Mordica O Johnston Gun perforator
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
FR896562A (fr) * 1958-12-23 1945-02-26 Liaison électrique par fiche avec ressorts de connexion à pression

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3598345A (en) * 1967-09-06 1971-08-10 Oerlikon Buehrle Ag Rocket with folding fins and braking device
US4175720A (en) * 1978-04-05 1979-11-27 The United States Of America As Represented By The Secretary Of The Navy Retainer/release mechanism for use on fin stabilized gun fired projectiles
US4523728A (en) * 1983-03-07 1985-06-18 Ford Aerospace & Communications Corporation Passive auto-erecting alignment wings for long rod penetrator
US4860969A (en) * 1987-06-30 1989-08-29 Diehl Gmbh & Co. Airborne body
RU2218547C1 (ru) * 2002-12-06 2003-12-10 Закрытое акционерное общество "Энергетика" Осколочно-фугасный снаряд

Also Published As

Publication number Publication date
GB968639A (en) 1964-09-02
CH385678A (de) 1964-12-15
DE1148913B (de) 1963-05-16
FI41125B (de) 1969-04-30

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