EP0346215B1 - Vorrichtung zur Veränderung der Flugbahn eines Projektils durch pyrotechnische Impulsgeber - Google Patents

Vorrichtung zur Veränderung der Flugbahn eines Projektils durch pyrotechnische Impulsgeber Download PDF

Info

Publication number
EP0346215B1
EP0346215B1 EP89401562A EP89401562A EP0346215B1 EP 0346215 B1 EP0346215 B1 EP 0346215B1 EP 89401562 A EP89401562 A EP 89401562A EP 89401562 A EP89401562 A EP 89401562A EP 0346215 B1 EP0346215 B1 EP 0346215B1
Authority
EP
European Patent Office
Prior art keywords
section
projectile
casing
boosters
support
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
EP89401562A
Other languages
English (en)
French (fr)
Other versions
EP0346215A1 (de
Inventor
Jean Deffayet
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0346215A1 publication Critical patent/EP0346215A1/de
Application granted granted Critical
Publication of EP0346215B1 publication Critical patent/EP0346215B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/20—Geometry three-dimensional
    • F05B2250/22—Geometry three-dimensional parallelepipedic

Definitions

  • the invention relates to a device intended to modify the trajectory of a projectile by pyrotechnic impellers.
  • Patent EP-A-229,541 shows an example of such an embodiment.
  • This patent describes a projectile 1, the trajectory of which can be deflected, when a target is overflown, by impellers controlled by a target detector.
  • the impeller is composed of an explosive 11 which generates a jet of gas transverse to the longitudinal axis of the projectile.
  • the gas generator being an explosive, the generation is brutal and therefore the trajectory deflection is poorly controlled.
  • an inertia plate 11 and on the other hand, a thrust plate bearing on a damping block 13.
  • the present invention uses a propellant for which the thrust is easily controllable and not explosive. Efficiency is increased by the use of suitable nozzles.
  • impellers such as that described in patent EP-A-229 541 already cited because of the small space available to install these impellers. Indeed, in the known art, the latter are in the form of powder impellers whose combustion chamber is cylindrical. However, their placement is often read in the projectile considered at a slice of a few centimeters thick for calibers of a few decimeters. As these impellers are arranged transversely to the axis of the projectile, their diameter is therefore limited by the thickness of the wafer available and by the contact of neighboring impellers.
  • the present invention aims to overcome these drawbacks and relates to a new impeller architecture intended to correct the trajectory of a projectile, an architecture which results in being able to have a maximum total propellant charge for the small free volume reserved for this purpose. function in the projectile.
  • each of the impellers is formed by a housing of which at least one base is rectangular, containing the propellant charge and comprises a profile fixed to the support of so as to constitute at least one nozzle allowing an orientation of the thrust.
  • the present invention relates to a structure and a positioning of the impellers providing the transverse projectile guide jets making it possible to make the most of the volume of the wafer available for this function.
  • the combustion chambers of the impellers instead of having a cylindrical shape, the combustion chambers of the impellers, that is to say the envelopes containing the propellant charge, have a rectangular base and have a rectangular shape or a more complex derived form.
  • this architecture results in putting in place for each impeller a nozzle having a particular geometry.
  • the housings of the combustion chambers (1) which are parallelepiped can come from molding, directly in the part (2) which serves as a support for the impellers, the latter being, as mentioned above, powder impellers.
  • the term "room” is used here because the loading is done inside a housing which is an integral part of the support (2).
  • a partition of thickness (f) more or less thin is reserved, depending on whether the faces normal to the axis of the projectile are supported or not on a resistant structure.
  • a single chamber is shown in the figure but, in reality, it is a plurality of chambers arranged transversely.
  • the support part (2) of thickness (e) corresponding to the thickness of the projectile wafer available for the guiding function, is obtained from machined parts.
  • these parts are shown separated and it is their stack which constitutes the support (2) of thickness (e).
  • This support piece (2) is for example constituted by a wafer (6) comprising a plurality of notches such as (7), produced transversely on the periphery of the wafer (6).
  • These constitute housings intended to each receive a housing (8) made of heat-resistant material, of thin thickness, of parallelepiped shape, and of dimensions adapted to those of the corresponding housing.
  • Two flanges (4) and (5) trap the housings (8) in their respective housings (7).
  • These boxes (8) receive the propellant charge (not shown) and constitute the trajectory modification impeller.
  • the term "chamber (1)" or "box (8)" actually covers the volume occupied by the loading of propellant, hence its general designation of envelope (1, 8).
  • a profile (20) is fixed to the support (2) so as to constitute a nozzle (21) more visible in Figure 4. Its fixing is achieved by means of 'a rod (22) which passes through the propellant charge and which is capable of withstanding the traction resulting from the internal combustion pressure.
  • this rod (22) is hollow and serves as a passage for the electrical conductors (23, 24) for igniting the igniters (25) housed for example in the profile (20).
  • divergent (30) for these nozzles (21) can be chosen.
  • the diverging part (30) can be obtained by making a chamfer (31) at the entrance to the impeller housing cooperating with a straight part (32) of the profile (20), or vice versa (34.33) as shown in Figure 9.
  • this divergence (30a) is obtained by combining the presence of a chamfer (31) at the entrance of the housing with an inclined plane (33) given to the profile (20). These divergent forms lead to obtaining transverse thrusts.
  • a parallelepiped architecture has been described for the casing of the propellant charge but, as shown in FIG. 9, it is also possible, in accordance with the invention, to use a charge (9) with several stages, three are shown by way of example (a1, a2, a3 ). It is also possible if the loading of propellant is suitable, choose for this envelope a prismatic shape.
  • the divergent part (21) in FIG. 9, by way of example, comprises the right wall (34) of the combustion chamber cooperating with inclined planes (33) of the profile (20).
  • the angle ( ⁇ ) is a function of the number of impellers arranged transversely and it defines the maximum width (a3) of the casing of the propellant charge.
  • the invention applies to all types of projectiles requiring trajectory modifications by impellers. It applies more particularly when the space reserved for these impellers reaches dimensions that are too small for it to be possible to use this space by conventional means.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Plasma Technology (AREA)

Claims (11)

  1. Vorrichtung zur Änderung der Flugbahn eines Projektils durch pyrotechnische Impulsgeber, bestehend aus einer Anzahl von Impulsgebern, die Gase erzeugen, deren Strahlen Schübe liefern, die die Änderung der Flugbahn sicherstellen, wobei die Impulsgeber quer an einem Träger (2) in Form einer zylindrischen Scheibe angeordnet sind, der bezüglich der Achse des Projektils zentriert ist, wobei die Vorrichtung dadurch gekennzeichnet ist, daß jeder der Impulsgeber durch eine Aufnahme gebildet ist, von welcher zumindest eine Grundfläche rechteckig ist und die eine Ladung aus festem Propergol enthält und ein Profilteil (20) aufweist, das an dem Träger (2) so befestigt ist, daß es wenigstens eine Düse (21) bildet, die eine Orientierung des Schubs ermöglicht.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß das Mittel zur Befestigung des Profilteils (20) an dem Träger (2) ein Stift (22) ist, der einen die Propergolladung enthaldenden Mantel (1, 8, 9) jedes der Impulsgeber durchquert und in der Lage ist, der sich aus dem inneren Verbrennungsdruck ergebenden Zugkraft zu widerstehen.
  3. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß der Mantel (1, 8) eine quaderförmige Form mit einer Länge (1) und einer Breite (a) aufweist.
  4. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, daß jeder der Mäntel mit einer Aufnahme zusammenfällt, die direkt durch Formherstellung des als Träger (2) dienenden Stücks erhalten ist, wobei die Aufnahme als Kammer (1) für die Propergolladung dient.
  5. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, daß der Mantel durch ein Gehäuse (8) aus einem widerstandsfähigen Material gebildet ist, das in eine Aussparung (7) eingelassen ist, die in einer bearbeiteten Scheibe (6) ausgebildet ist, wobei das Gehäuse durch zwei Flansche (4, 5) eingeschlossen ist.
  6. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß der Mantel der Ladung (9) eine Anzahl von Stufen mit unterschiedlicher Breite (a1, a2, a3 ...) aufweist.
  7. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, daß der Stift (22) hohl ist und als Umhüllung für elektrische Leiter (23, 24) dient, die in dem Profilteil (20) aufgenommene Zündeinrichtungen (25) versorgen.
  8. Vorrichtung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Düse (21) eine Ableitung (30) aufweist, die durch einen geraden Teil (32) des Profilteils (20) gebildet ist, der mit einer an dem Mantel (1, 8, 9) realisierten Abschrägung (31) zusammenwirkt.
  9. Vorrichtung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Düse (21) eine Ableitung (30a) aufweist, die durch das Zusammenwirken von zwei Abschrägungen (31 und 33) gebildet ist, die an dem Mantel (1, 8, 9) bzw. dem Profilteil (20) ausgebildet sind.
  10. Vorrichtung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Ableitung zwei asymmetrische Teile aufweist, wobei der eine durch eine mit einem geraden Teil (32) des Profilteils (20) zusammenwirkende Abschrägung (31) und der andere durch einen geraden Teil (34) an der Seite des Mantels (1, 8, 9) und eine an dem Profilteil (20) ausgebildete, geneigte Ebene (33) gebildet ist.
  11. Vorrichtung nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Profilteil (20) parallel zu der Achse des Projektils angeordnet ist.
EP89401562A 1988-06-10 1989-06-06 Vorrichtung zur Veränderung der Flugbahn eines Projektils durch pyrotechnische Impulsgeber Expired - Lifetime EP0346215B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8807768 1988-06-10
FR8807768A FR2632722B1 (fr) 1988-06-10 1988-06-10 Dispositif destine a modifier la trajectoire d'un projectile par impulseurs pyrotechniques

Publications (2)

Publication Number Publication Date
EP0346215A1 EP0346215A1 (de) 1989-12-13
EP0346215B1 true EP0346215B1 (de) 1993-06-09

Family

ID=9367164

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89401562A Expired - Lifetime EP0346215B1 (de) 1988-06-10 1989-06-06 Vorrichtung zur Veränderung der Flugbahn eines Projektils durch pyrotechnische Impulsgeber

Country Status (4)

Country Link
US (1) US5044156A (de)
EP (1) EP0346215B1 (de)
DE (1) DE68906964T2 (de)
FR (1) FR2632722B1 (de)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6178741B1 (en) * 1998-10-16 2001-01-30 Trw Inc. Mems synthesized divert propulsion system
IL167721A (en) * 2005-03-29 2008-06-05 Israel Aerospace Ind Ltd Steering system and method for guided flying apparatus
FR2885213B1 (fr) 2005-05-02 2010-11-05 Giat Ind Sa Procede de commande d'une munition ou sous-munition, systeme d'attaque, munition et designateur mettant en oeuvre un tel procede
US9151581B2 (en) * 2005-09-07 2015-10-06 Omnitek Partners Llc Actuators for gun-fired projectiles and mortars
US7800031B2 (en) * 2005-09-07 2010-09-21 Omnitek Partners Llc Actuators for gun-fired projectiles and mortars
US8563910B2 (en) 2009-06-05 2013-10-22 The Charles Stark Draper Laboratory, Inc. Systems and methods for targeting a projectile payload
US11543835B2 (en) 2010-01-15 2023-01-03 Lockheed Martin Corporation Monolithic attitude control motor frame and system
US10914559B1 (en) 2016-11-21 2021-02-09 Lockheed Martin Corporation Missile, slot thrust attitude controller system, and method

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2613497A (en) * 1947-04-01 1952-10-14 Macdonald Gilmour Craig Controllable rocket thrust device
US3069846A (en) * 1959-09-28 1962-12-25 Clary Corp Thrust device
US3034434A (en) * 1960-03-08 1962-05-15 Frank H Swaim Thrust vector control system
US3099960A (en) * 1960-08-19 1963-08-06 George J Bryan Method of thrust vector control
US3263419A (en) * 1963-05-23 1966-08-02 Thiokol Chemical Corp Attitude control system for space vehicles
US3316719A (en) * 1965-03-11 1967-05-02 Curtiss Wright Corp Expansible rocket engines
US3328962A (en) * 1965-05-20 1967-07-04 Curtiss Wright Corp Orientation control system for space vehicles and ballistic missiles
US3380661A (en) * 1966-04-12 1968-04-30 United Aircraft Corp Thrust deflector
US3532297A (en) * 1967-01-23 1970-10-06 Rocket Research Corp Space vehicle attitude control by microrockets utilizing subliming solid propellants
FR2367659A2 (fr) * 1976-09-08 1978-05-12 Stauff Emile Dispositif de pilotage d'un projectile en autorotation
FR2450356A1 (fr) * 1979-02-27 1980-09-26 Aerospatiale Agencement de pilotage d'un propulseur d'engin a propergol solide
FR2469345A1 (fr) * 1979-11-09 1981-05-22 Thomson Brandt Procede de pilotage et de guidage de projectiles en phase terminale et projectiles comportant les moyens de mise en oeuvre de ce procede
US4444119A (en) * 1982-07-02 1984-04-24 The United States Of America As Represented By The Secretary Of The Army Fast response impulse generator
DE3521204A1 (de) * 1985-06-13 1986-12-18 Diehl GmbH & Co, 8500 Nürnberg Impulstriebwerk
DE3531686A1 (de) * 1985-09-05 1987-03-12 Rheinmetall Gmbh Steuerblock
FR2590973B1 (fr) * 1985-11-29 1988-02-12 France Etat Armement Dispositif de basculement de projectile sur trajectoire
USH236H (en) * 1986-07-14 1987-03-03 The United States Of America As Represented By The Secretary Of The Army Asymmetric side-exhausting nozzles
DE3708312A1 (de) * 1987-03-14 1988-09-22 Messerschmitt Boelkow Blohm Vorrichtung zum steuern eines flugkoerpers

Also Published As

Publication number Publication date
EP0346215A1 (de) 1989-12-13
FR2632722B1 (fr) 1993-09-03
US5044156A (en) 1991-09-03
FR2632722A1 (fr) 1989-12-15
DE68906964T2 (de) 1993-12-02
DE68906964D1 (de) 1993-07-15

Similar Documents

Publication Publication Date Title
EP0346215B1 (de) Vorrichtung zur Veränderung der Flugbahn eines Projektils durch pyrotechnische Impulsgeber
CA2056170A1 (fr) Detonateur pyrotechnique a connexions coaxiales
FR2717259A1 (fr) Dispositif de guidage d'un missile.
EP1045221B1 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
EP1006335A1 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
FR2685077A1 (fr) Dispositif explosif a fragmentation programmable.
EP0138640A1 (de) Explosive Ladung für militärische Verwendung
FR2547909A1 (fr) Dispositif d'amorcage d'une charge explosive
EP0536048B1 (de) Mine zur Flächenverteidigung
EP0500440B1 (de) Munitionsabschussvorrichtung
FR2701107A1 (fr) Agencement dans une enceinte à charge fumigène.
FR2728675A1 (fr) Cartouche avec une douille et un projectile a fleche
FR2552871A1 (fr) Projectile antichar agissant en vitesse defilante
FR2833694A1 (fr) Separateur pyrotechnique et dispositif de separation equipe d'un tel separateur
FR2900773A1 (fr) Procede de montage d'un enroulement d'un bobinage de stator dans un paquet de toles
FR2645635A1 (fr) Canne de dispersion et d'allumage d'une composition incendiaire non solide
EP0404644B1 (de) Elektropyrotechnische Vorrichtung zur Inbetriebnahme eines Gasgenerators
WO2004003461A2 (fr) Dispositif adaptateur pour projectile muni d’ailettes deployables tire a partir d’un tube de lancement
FR2633381A1 (fr) Dispositif comportant un tube de post-acceleration et un projectile
CA2913232A1 (fr) Chargement pyrotechnique et generateur de gaz comprenant un tel chargement
EP0338879B1 (de) Stabilisierungsvorrichtung für Geschosse von gezogenen Läufen
FR2704052A1 (fr) Charge formée multiamorçable.
FR2695717A1 (fr) Sabot pour projectile pour accélérateur par effet de statoréacteur et projectile équipé d'un tel sabot.
EP0803699A1 (de) Vorrichtung zur Befestigung eines Kastens an einer Struktur
WO1996019382A1 (fr) Bouclier de freinage pour engin spatial et satellite ainsi equipe

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE GB IT LI SE

17P Request for examination filed

Effective date: 19900518

17Q First examination report despatched

Effective date: 19920127

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE GB IT LI SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRE;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.SCRIBED TIME-LIMIT

Effective date: 19930609

REF Corresponds to:

Ref document number: 68906964

Country of ref document: DE

Date of ref document: 19930715

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19930722

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19940630

Ref country code: CH

Effective date: 19940630

EAL Se: european patent in force in sweden

Ref document number: 89401562.7

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20010523

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20010524

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20010525

Year of fee payment: 13

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020606

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020607

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20030101

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20020606

EUG Se: european patent has lapsed