US3620123A - Closing device for the nozzle of a projectile furnished with a rocket-motor - Google Patents

Closing device for the nozzle of a projectile furnished with a rocket-motor Download PDF

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Publication number
US3620123A
US3620123A US29119A US3620123DA US3620123A US 3620123 A US3620123 A US 3620123A US 29119 A US29119 A US 29119A US 3620123D A US3620123D A US 3620123DA US 3620123 A US3620123 A US 3620123A
Authority
US
United States
Prior art keywords
nozzle
cap
projectile
barrel
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
US29119A
Other languages
English (en)
Inventor
Per-Olof Davidsson
Karl Goesta Hoegberg
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 US3620123A publication Critical patent/US3620123A/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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

Definitions

  • the cap has a main portion for making a sealing contact with the edge of the nozzle, a threaded portion screwed onto the outside of the nozzle, and a weakened circumferential portion between the main portion and the threaded portion. During the travel of the projectile through the barrel the weakened portion is ruptured by the pressure exerted bythe combustion gases produced by the drive charge whereby the holding connection between the nozzle and the main portion of the cap is severed.
  • the invention relates to a closing device for the nozzle of a projectile furnished with a rocket motor and intended to be fired by means of a gun barrel and an external drive charge.
  • a certain initial velocity is imparted to, the projectile by the drive charge, and by means of the rocket motor which starts after the projectile has left the barrel, an additional velocity is imparted to the projectile.
  • the closing device comprises a cap of metal having a high tensile strength the periphery of which has a part for making a tight contact with the mouth of the nozzle and an annular retaining member which has a first part attached to the cap and a second part to be attached to the nozzle at its outer side and a third part joining said first and second parts and having a realtively small thickness and being so arranged that when the closing device is mounted on the nozzle a free space is present inside said third part, whereby this part under the action of a sufiiciently high outer pressure is bent inwards and is caused to rupture so that the mechanical connection between the cap and the nozzle is interrupted.
  • the cap is preferably made of steel while the retaining member is made of a light metal.
  • the cap is preferably cup-shaped and has e.g. the
  • FIG. 1 shows in cross section an embodiment of the device according to the invention.
  • FIG. 2 illustrates the mode of operation of the device of FIG. 1.
  • FIG. 3 shows a cross section of a second embodiment of the device according to the invention.
  • the closing device comprises the cup-shaped cap 1 which is provided along its periphery with a plane surface 2 which is intended to abut against the edge of the mouth of the nozzle 3. Between the surface 2 on the cap 1 and the mouth of the nozzle is inserted a sealing ring 8 which is made e.g. of lead.
  • the cup 1 also has an internal annular part 9 which extends into the nozzle 3 so that a small play is present between the outer side of part 9 and the inside of the nozzle.
  • a circumferential groove 10 which has a U-shaped cross section.
  • the cap 1 is held fast to the nozzle 3 by an annular retaining member which comprises a part 4 which is attached, e.g. screwed to the cap !1 and a second part 5 which can be attached, e.g. screwed to the nozzle 3 at its outer side.
  • the parts 4 and 5 are joined by means of a third part 6 which has a small thickness and is so positioned that there is a free space inside it when the closing device is mounted on the nozzle.
  • the cap 1 protects the rocket motor from being subjected to the very high pressure existing in the barrel.
  • this pressure also acts upon the annular retaining member, and the Weakest portion 6 is thereby caused to bend inwards toward the space 7 and to rupture.
  • the mechanical connection between the cap 1 and the nozzle 3 is interrupted since the connection between part 4 and 5 of the retaining member is broken, e.g. at the joint between parts 6 and 4- as shown in FIG. 2.
  • the cap 1 will still be pressed against the nozzle by the pressure existing in the barrel.
  • the weakened part 6 of the retaining member which can be considered as a membrane, is joined under a substantially right angle to the plane surface of part 4, whereby the joint between parts 4 and 6 will form a fracture indication.
  • the cap 1 Due to the pressure which arises in the barrel upon the firing the cap 1 will rapidly be pressed against the nozzle 3 with a great force. Hereby the sealing ring 8 will be compressed and particles of the sealing material will be thrown inwards towards the part 9 of the cap 1. These particles are trapped by the groove 10 and thereby prevented from being thrown into the rocket motor.
  • the parts of the retaining member are designated 14, 15 and 16.
  • the weakened part or membrane 16 is here in the form of an annulus located in a plane at right angles to the longitudinal axis of the nozzle.
  • the cap 1 is here provided with a shoulder 11 which has a sharp edge situated at the joint between parts 14 and 16 of the retaining member. During the travel of the projectile through the barrel the part 16 will be sheared off by this edge.
  • a closing device for the nozzle of a projectile furnished with a rocket motor and intended to be fired by means of a barrel and an outer drive charge comprising a cap (ll) of a material with a high tensile strength the periphery of which has a part (2) for making a tight contact with the edge of the mouth of the nozzle (3) and an annular retaining member (4, 5, 6) which has a first part (4) which is attached to the cap (1), a second part (5) to be attached to the nozzle (3) at its outer side and a third part (6) joining said first (4) and second parts and having a relatively small thickness and being arranged so that a free space (7) is present inside said third part (6) when mounted on the nozzle, whereby this part under the influence of a sufficiently high outer pressure can be bent inwards and break so that the mechanical connection between the cap (1) and the nozzle (3) is interrupted.
  • cap (1) is cup-shaped with a concave side facing the mouth of the nozzle (6).
  • said first part (4) of the retaining member has a plane surface situated in a plane at right angles to the longitudinal axis of the nozzle (3), and said third part (6) of the retaining member joins said first part (4) at said surface under right angles.
  • the cap (.1) has an annular part ('9) extending into the nozzle (3) when the cap is mounted on the nozzle, a certain play being present between the outside of the annular part (9) and the inside of the nozzle (3), and a circumferential U-shaped groove (510) is provided at the joint between the annular part (9) and the part (2,) intended for contact with the mouth of the nozzle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure Vessels And Lids Thereof (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Catching Or Destruction (AREA)
US29119A 1969-04-23 1970-04-16 Closing device for the nozzle of a projectile furnished with a rocket-motor Expired - Lifetime US3620123A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE05817/69A SE331435B (de) 1969-04-23 1969-04-23

Publications (1)

Publication Number Publication Date
US3620123A true US3620123A (en) 1971-11-16

Family

ID=20267302

Family Applications (1)

Application Number Title Priority Date Filing Date
US29119A Expired - Lifetime US3620123A (en) 1969-04-23 1970-04-16 Closing device for the nozzle of a projectile furnished with a rocket-motor

Country Status (10)

Country Link
US (1) US3620123A (de)
JP (1) JPS4928399B1 (de)
BE (1) BE749412A (de)
DE (1) DE2019244A1 (de)
FR (1) FR2046373A5 (de)
GB (1) GB1244299A (de)
IL (1) IL34337A (de)
NL (1) NL7005813A (de)
NO (1) NO122870B (de)
SE (1) SE331435B (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100109342A1 (en) * 2008-11-03 2010-05-06 Vladislav Oleynik Electrical power generator
US20110101703A1 (en) * 2009-11-03 2011-05-05 Causwave, Inc. Multiphase material generator vehicle
US8181561B2 (en) * 2008-06-02 2012-05-22 Causwave, Inc. Explosive decompression propulsion system
CN113915030A (zh) * 2021-09-14 2022-01-11 淮海工业集团有限公司 一种固体火箭发动机的堵盖结构

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE59004020D1 (de) * 1989-09-19 1994-02-10 Diehl Gmbh & Co Bahnkorrigierbares Projektil.

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8181561B2 (en) * 2008-06-02 2012-05-22 Causwave, Inc. Explosive decompression propulsion system
US20100109342A1 (en) * 2008-11-03 2010-05-06 Vladislav Oleynik Electrical power generator
US8294287B2 (en) 2008-11-03 2012-10-23 Causwave, Inc. Electrical power generator
US20110101703A1 (en) * 2009-11-03 2011-05-05 Causwave, Inc. Multiphase material generator vehicle
US8378509B2 (en) 2009-11-03 2013-02-19 Causwave, Inc. Multiphase material generator vehicle
CN113915030A (zh) * 2021-09-14 2022-01-11 淮海工业集团有限公司 一种固体火箭发动机的堵盖结构

Also Published As

Publication number Publication date
IL34337A (en) 1973-07-30
GB1244299A (en) 1971-08-25
FR2046373A5 (de) 1971-03-05
SE331435B (de) 1970-12-21
DE2019244A1 (de) 1970-11-12
NO122870B (de) 1971-08-23
NL7005813A (de) 1970-10-27
JPS4928399B1 (de) 1974-07-25
BE749412A (fr) 1970-10-01
IL34337A0 (en) 1970-12-24

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