US3837278A - Rocket for firing and spreading reflecting material - Google Patents

Rocket for firing and spreading reflecting material Download PDF

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Publication number
US3837278A
US3837278A US00367313A US36731373A US3837278A US 3837278 A US3837278 A US 3837278A US 00367313 A US00367313 A US 00367313A US 36731373 A US36731373 A US 36731373A US 3837278 A US3837278 A US 3837278A
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US
United States
Prior art keywords
rocket
locking mechanism
casing
reflecting material
locking
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
US00367313A
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English (en)
Inventor
M Gustafsson
Y Stradalen
E Zander
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Application granted granted Critical
Publication of US3837278A publication Critical patent/US3837278A/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
    • 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
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/70—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies for dispensing radar chaff or infrared material

Definitions

  • a rocket for spreading reflecting material to achieve a radar echo comprises a rocket body having a rocket motor at one end thereof, and a rocket head containing the reflecting material at the other end thereof.
  • the casing is locked to the rocket body by a locking mechanism which is adapted to be released by gas pressure generated by detonation of a separating charge.
  • the locking mechanism includes an elongated tube adapted to support the reflecting material on its exterior, and operative to selectively form an interior gas channel between the separating charge and the front part of the casing under the control of a valve member.
  • the present invention relates to a rocket for firing and spreading reflecting material, consisting of cut pieces of thread or fibers which after firing and spreading, is specially intended to achieve a radar echo.
  • the rocket comprises a rear propelling part with a rocket motor, and a rocket head containing the material intended to be fired and spread.
  • the rocket head comprises a cylindrical casing, which is provided with a nose cone at its front end.
  • Rockets of this general type are previously known, in which the spreading of the reflecting material takes place with the aid of a spreading charge, which in conjunction with the spreading operation either blows away the casing around the material or, after the removal of the nose cone, expels the material forwards out of the casing.
  • a problem involved with these known rockets is that all of the reflecting material will be ejected simultaneously and instantaneously, which has the result that the spreading will not be satisfactory. In order to achieve a desired radar echo, it is necessary to spread the material successively along a portion of the rocket trajectory, which is not possible with the known rockets. A problem in connection with the spreading operation is also to distribute the individual elements of the reflecting material with an appropriate distance between the elements in space, which is of importance if the best possible reflection effect is to be obtained.
  • FIG. 1 shows a side view of the rocket according to the invention
  • FIG. 2 is a partly cut-away side view of the rocket head
  • FIG. 3 is a longitudinal section through the part of the rocket which is intended to be blown off in connection with the spreading of the reflecting material
  • FIG. 4 is a section, on a larger scale, of a locking device intended to secure the part that can be blown off, before the spreading,
  • FIG. 5 is a plan view of one of the separating discs which are placed between the different bunches of the reflecting material
  • FIG. 6 is a plan view of a supporting plate arranged in the rocket head.
  • the rocket comprises a rear propelling part 1, which contains a rocket motor, and a rocket head 2, containing the reflecting material intended to be spread out.
  • the propelling part 1 does not constitute any part of the invention, and therefore will not be described in detail.
  • the rocket head 2 shown in FIGS. 2 and 3 comprises an elongate cylindrical casing 3, the front end of which is provided with a nose cone 4. At the joint between the casing 3 and the nose cone 4 there is a fastening plate 5. At the middle of the plate 5, an inner tube 7 is welded, which extends rearvvards coaxially with the cylindrical casing 3, and has practically the same length as casing 3. The tube 7 is provided with openings 9.
  • the rear end of the casing 3 is mounted around a fastening plate 10, which is provided with internal threads for screwing the plate to the rocket body.
  • the rocket head is sealed off by means of a sealing ring 11 between the casing 3 and the plate 10, in the center of which an outer tube 12, directed forwards, is screwed which encloses the inner tube 7, and has substantially the same length as tube 7.
  • a sealing ring 13 Between the two tubes there is a sealing ring 13, which is mounted in a groove in the inner tube 7.
  • a supporting plate 14 is mounted, which is guided in relation to the fastening plate 5 by means of a pin 15.
  • the purpose of the plate 14 is to prevent the reflecting material located behind the plate from going along forward when the casing 3 is blown off, and the plate is perforated by means of holes 14a, as shown in FIG. 6. By having different degrees of perforation in the plate 14, different spreading times and, accordingly, different extensions of the reflecting material can be obtained.
  • the reflecting material is mounted in the form of a stack, consisting of bunches 16, each of which has the form of a hollow cylinder.
  • the stack is enclosed in four plate segments 16a, which protect the bunches during the separation of the casing 3, to be described, and prevent spreading of the reflecting material before the separation has been completed.
  • separating discs 17 are placed, and a plan view of one of these is shown in FIG. 5.
  • the discs 17 are provided with four recesses 18, uniformly distributed around the periphery. Further, the discs are divided diametrically into two equal parts along the line 19.
  • the recesses 18 are intended to enable cutting of the wrappings, e.g. of paper, of the bunches 16. The cuts are made between the segments 17 before the casing 3 is mounted.
  • FIG. 4 shows a locking mechanism which is intended to retain the casing 3 which can be blown off of the rocket before the spreading of the reflecting material, and which is released under the actuation of a separating charge, so that the casing can be blown off when the material is to be spread.
  • the casing 3 with the nose cone 4 is held in place before firing, by means of the locking mechanism with the aid of the front fastening plate 5 and the inner tube 7 by the locking mechanism in the locked position forming a connection member between the inner tube 7 and the rear fastening plate 10.
  • the locking mechanism comprises an outer sleeve 20, the front part of which is screwed into the inner tube 7, and the sleeve is thus fixed to this tube.
  • the sleeve 20 there is a displaceably arranged inner sleeve 21, in the front end of which a locking plunger 22 is fitted.
  • the inner sleeve 21 is held in place in the outer sleeve 20 by means of a radial collar 24, which is directed outwards, and which in the position shown is in contact with the front end of the outer sleeve 20, and which also forms a contact surface for the rear end of a pressure spring 25, the front end of which rests against a washer 26 which, in turn, is in contact with a step in the inner tube 7.
  • the sleeve 21 also has axial gas channels in the form of slots 23.
  • the locking plunger 22 is retained in the axial position shown in relation to the inner sleeve 21 by means of locking balls 27, which are placed in radial openings in the sleeve 21 and engage in a circumferential groove 28 in the plunger 22.
  • locking balls 27 In the front end of the plunger 22 there is an axial recess 29, the purpose of which will be described in more detail in the following.
  • the rear end of the outer sleeve 20 is made with radial openings, in which locking balls 32 are placed, which engage in an internal, circumferential groove in a securing ring 33, which is pressed into the fastening plate 10.
  • a nut 35 is screwed, which also constitutes a holder for a separating charge 36.
  • the separating charge 36 is initiated with the aid of a fuze, not shown, with an appropriate, predetermined delay.
  • the gas pressure behind the plunger 22 then presses this forwards, together with the displaceable inner sleeve 21, against the action of the spring 25.
  • the step 20 at the rear part of the inner sleeve 21 has passed the balls 32, it is possible for these balls to move radially inwards, and become disengaged from the securing ring 33, whereby the lock between the outer sleeve 20 and the ring 33 is released.
  • the inner sleeve 7 and, consequently, also the casing 3 can thereafter move forwards in relation to the outer tube 12 and the rear, propelling part of the rocket.
  • the balls 27 When the inner sleeve 21 continues its movement forwards in relation to the outer sleeve 20, the balls 27 will pass the front end of the outer sleeve 20. When this has taken place, the balls 27 can move radially outwards and become disengaged from the groove 28 in the plunger 22. The plunger is thereby released, and under the actuation of the gas pressure continues forwards through the tube 7.
  • the gas can pass by the plunger 22 through these gas channels, while the plunger 22 is still guided in the sleeve 21. Because of the gas channels 23, the ejection speed of the plunger 22 will be limited when it leaves the sleeve 21. Because of the plunger 22 having been provided with the recess 29, it is easier for its front end to be deformed, so that the energy of the movement of the plunger at its impact against the plate 5 will be consumed during the deformation of the front part of the plunger.
  • a rocket for spreading reflecting material to achieve a radar echo comprising a rocket body having a rocket motor at one end thereof for propelling said rocket along a trajectory, a rocket head containing said reflecting material and disposed at the other end of said rocket body, said rocket head including support means fixedly attached to said body for supporting said reflecting material in place, said rocket head further including a removable casing positioned to enclose said support means and said reflecting material, a locking mechanism for securing said casing to said rocket body in said enclosing position, a separating charge, said locking mechanism including means responsive to the gas pressure generated by detonation of said charge for releasing said locking mechanism and for blowing said casing off said rocket body to expose said reflecting material thereby to cause said material to be spread along a portion of the rocket trajectory under the influence of air currents around said rocket as said rocket is propelled along said trajectory.
  • the locking mechanism includes a valve member operative to close the gas channel when the locking mechanism is in its locked position, said valve member being arranged to open the gas channel when said locking mechanism is released.
  • the locking mechanism includes a first set of locking balls for locking the casing to said body, and a second set of locking balls for locking the valve member in a position closing said gas channel.
  • first tubular member affixed to said rocket body in coaxial relation thereto, and a second tubular member affixed to said casing and disposed in coaxial slidable relationship to said first tubular member, said locking mechanism being operative, in its locked position, to prevent slidable movement of said tubular members relative to one another and being operative, in its released position, to permit such slidable movement.

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Toys (AREA)
US00367313A 1972-06-16 1973-06-05 Rocket for firing and spreading reflecting material Expired - Lifetime US3837278A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE7207956A SE376301B (enrdf_load_stackoverflow) 1972-06-16 1972-06-16

Publications (1)

Publication Number Publication Date
US3837278A true US3837278A (en) 1974-09-24

Family

ID=20272746

Family Applications (1)

Application Number Title Priority Date Filing Date
US00367313A Expired - Lifetime US3837278A (en) 1972-06-16 1973-06-05 Rocket for firing and spreading reflecting material

Country Status (5)

Country Link
US (1) US3837278A (enrdf_load_stackoverflow)
DE (1) DE2330045C2 (enrdf_load_stackoverflow)
FR (1) FR2189704B1 (enrdf_load_stackoverflow)
GB (1) GB1426229A (enrdf_load_stackoverflow)
SE (1) SE376301B (enrdf_load_stackoverflow)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4031828A (en) * 1976-01-28 1977-06-28 The United States Of America As Represented By The Secretary Of The Air Force Pressurized chaff canister
US4195571A (en) * 1979-04-02 1980-04-01 The United States Of America As Represented By The Secretary Of The Army Modular wheel dispenser
US4406227A (en) * 1981-04-09 1983-09-27 The United States Of America As Represented By The Secretary Of The Army System for multistage, aerial dissemination and rapid dispersion of preselected substances
US5040465A (en) * 1976-12-10 1991-08-20 Lacroix Soc E Launching projectile for electromagnetic decoys
US5183960A (en) * 1991-06-27 1993-02-02 Shires James D Rocket glider stabilization system
US5445078A (en) * 1989-12-14 1995-08-29 Universal Propulsion Company, Inc. Apparatus and method for dispensing payloads
RU2126131C1 (ru) * 1998-03-16 1999-02-10 Государственное научно-производственное предприятие "Сплав" Устройство формирования времени коррекции вскрытия или отделения головной части ракеты реактивной системы залпового огня
FR2835049A1 (fr) * 2002-01-21 2003-07-25 Giat Ind Sa Leurre deployable et munition permettant la dispersion d'un tel leurre
US20190204054A1 (en) * 2016-09-15 2019-07-04 Bae Systems Bofors Ab Method and arrangement for modifying a separable projectile
WO2020249714A1 (en) 2019-06-14 2020-12-17 Geistlich Pharma Ag Collagen matrix or granulate blend of bone substitute material

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2555323C2 (de) * 1975-12-09 1984-04-05 Buck Chemisch-Technische Werke GmbH & Co, 7341 Bad Überkingen Geschoßfüllung aus übereinander angeordneten Nebeltöpfen und Verfahren zur Herstellung eines Nebeltopfes
FR2724907A1 (fr) * 1981-12-11 1996-03-29 Lacroix Soc E Lanceur de leurres electromagnetiques a ejection differee

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2476302A (en) * 1944-10-27 1949-07-19 Morris R Jeppson Self-propelled projectile for distributing material
US3049080A (en) * 1959-04-17 1962-08-14 Schermuly Pistol Rocket App Rockets and rocket-borne distress signals
US3095814A (en) * 1960-06-30 1963-07-02 Tor W Jansen Dispensing apparatus
US3143965A (en) * 1959-11-06 1964-08-11 Pointe Andre E La Chaff dispenser
US3741125A (en) * 1960-11-22 1973-06-26 Us Navy Stabilized rocket head

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1703775B1 (de) * 1968-07-09 1972-05-31 Dynamit Nobel Ag Rakete mit Nutzlast,insbesondere aus Flugblaettern

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2476302A (en) * 1944-10-27 1949-07-19 Morris R Jeppson Self-propelled projectile for distributing material
US3049080A (en) * 1959-04-17 1962-08-14 Schermuly Pistol Rocket App Rockets and rocket-borne distress signals
US3143965A (en) * 1959-11-06 1964-08-11 Pointe Andre E La Chaff dispenser
US3095814A (en) * 1960-06-30 1963-07-02 Tor W Jansen Dispensing apparatus
US3741125A (en) * 1960-11-22 1973-06-26 Us Navy Stabilized rocket head

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4031828A (en) * 1976-01-28 1977-06-28 The United States Of America As Represented By The Secretary Of The Air Force Pressurized chaff canister
US5040465A (en) * 1976-12-10 1991-08-20 Lacroix Soc E Launching projectile for electromagnetic decoys
US4195571A (en) * 1979-04-02 1980-04-01 The United States Of America As Represented By The Secretary Of The Army Modular wheel dispenser
US4406227A (en) * 1981-04-09 1983-09-27 The United States Of America As Represented By The Secretary Of The Army System for multistage, aerial dissemination and rapid dispersion of preselected substances
US5445078A (en) * 1989-12-14 1995-08-29 Universal Propulsion Company, Inc. Apparatus and method for dispensing payloads
US5183960A (en) * 1991-06-27 1993-02-02 Shires James D Rocket glider stabilization system
RU2126131C1 (ru) * 1998-03-16 1999-02-10 Государственное научно-производственное предприятие "Сплав" Устройство формирования времени коррекции вскрытия или отделения головной части ракеты реактивной системы залпового огня
FR2835049A1 (fr) * 2002-01-21 2003-07-25 Giat Ind Sa Leurre deployable et munition permettant la dispersion d'un tel leurre
EP1329684A3 (fr) * 2002-01-21 2003-08-06 Giat Industries Leurre déployable et munition permettant la dispersion d'un tel leurre
US20190204054A1 (en) * 2016-09-15 2019-07-04 Bae Systems Bofors Ab Method and arrangement for modifying a separable projectile
US11015907B2 (en) * 2016-09-15 2021-05-25 Bae Systems Bofors Ab Method and arrangement for modifying a separable projectile
WO2020249714A1 (en) 2019-06-14 2020-12-17 Geistlich Pharma Ag Collagen matrix or granulate blend of bone substitute material

Also Published As

Publication number Publication date
GB1426229A (en) 1976-02-25
FR2189704A1 (enrdf_load_stackoverflow) 1974-01-25
FR2189704B1 (enrdf_load_stackoverflow) 1976-06-11
SE376301B (enrdf_load_stackoverflow) 1975-05-12
DE2330045C2 (de) 1984-09-13
DE2330045A1 (de) 1973-12-20

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