US3779819A - Propellant powder charge having finned internal configuration - Google Patents

Propellant powder charge having finned internal configuration Download PDF

Info

Publication number
US3779819A
US3779819A US00210752A US3779819DA US3779819A US 3779819 A US3779819 A US 3779819A US 00210752 A US00210752 A US 00210752A US 3779819D A US3779819D A US 3779819DA US 3779819 A US3779819 A US 3779819A
Authority
US
United States
Prior art keywords
propellant powder
block
finned
fins
sector
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
US00210752A
Other languages
English (en)
Inventor
J Thomas
J Ramond
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.)
Societe Nationale des Poudres et Explosifs
Original Assignee
Societe Nationale des Poudres et Explosifs
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 Societe Nationale des Poudres et Explosifs filed Critical Societe Nationale des Poudres et Explosifs
Application granted granted Critical
Publication of US3779819A publication Critical patent/US3779819A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges

Definitions

  • ABSTRACT A method of manufacturing a finned, one-piece propellant powder charge in which an extruded or moulded cylindrical block of propellant powder is split into two or more cylindrical sectors along one or more planes containing the longitudinal axis of the block. Each sector is machined to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector into parallel longitudinal fins integrally connected at their bases to the rim of the respective sector. The machined sectors are then joined to reconstitute the cylindrical block and the sides of the reconstituted block is then coated with a combustion inhibitor.
  • the present invention is concerned with an improved method of manufacturing such powder charges.
  • a method of manufacturing a finned, one-piece propellant powder charge which comprises a. splitting an extruded or moulded cylindrical block of propellant powder into two or more sectors of the cylinder along one or more planes containing the longitudinal axis of the block;
  • each sector machining each sector to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector with parallel longitudinal fins integrally connected at their bases to the rim of the respective sector;
  • the propellant powder may be either a homogeneous powder, for example a double-base explosive (nitroglycerine, nitrocellulose) which may be extruded, calendered or moulded, or a compound powder formed of an oxidizing agent such as ammonium perchlorate, a reducing agent such as aluminium powder, and a rubbery binder such as polybutadiene.
  • a double-base explosive nitroglycerine, nitrocellulose
  • an oxidizing agent such as ammonium perchlorate
  • a reducing agent such as aluminium powder
  • a rubbery binder such as polybutadiene
  • the cylindrical block of powder is split into two half-blocks along a plane passing through the longitudinal axis of the block.
  • the flat surface of each half-block is machined to form each half of a central bore for the reconstituted block, the parallel longitudinal fins are then machinedon each half block to the desired thickness, spacing and shape, the two machined half-blocks are bonded together, optionally by. means of adhesive, to reconstitute the original cylindrical block, and then the sides of the reconstituted block are coated with a combustion inhibiting layer, for example a lacquer.
  • a combustion inhibiting layer for example a lacquer.
  • the sectors of the block are machined to provide fins of different thicknesses.
  • fins of two different thicknesses are provided alternately in each sector. In this manner, a plurality of thrust performances can be obtained by means of a single block.
  • FIGS. I to 6 are perspective views of a finned onepiece charge at various stages during production in the method according to the invention.
  • FIGS. 7 and 8 represent cross-sections through alternative one-piece charges which may be made according to the invention.
  • an extruded or moulded cylindrical block 1 (FIG. 1) of propellant powder of a given composition is split along its entire length into two half-blocks 2 (FIG. 2).
  • a desired shape is imparted to the flat portion 3 of each half-block (FIG. 3) by milling.
  • Thin sheets or fins 4 are then formed in each half-block by machining; the thickness, spacing and shape of the fins having been determined by means of calculation.
  • the fins in each sector are joined together at their bases through the annular periphery or rim 5 of the block.
  • the two half-blocks are then joined (FIG. 5) by means of adhesive 6 or a solvent (for example, nitromethane) which dissolves the propellant.
  • adhesive 6 for example, nitromethane
  • the reconstituted block is rolled to the desired diameter and its sides are coated with a combustion inhibitor 7 (FIG. 6).
  • the resulting finned onepiece charge has many advantages: satisfactory behaviour of the assembly, which forms a single unit since the fins are attached to the remainder of the block at their bases; highly reproducible performances since the block is wholly machined; a satisfactory filling coefficient; ease of adjustment of the performances obtained; and also the fact that the desired spacing of the two series of fins 4 can be maintained by means of combusti ble nitrocellulose felt, which is placed in the central bore before applying the coating of inhibitor.
  • composition of the propellant powder used was as follows:
  • the inhibitor lacquer was a polyester lacquer with a methyl-ethyl ketone peroxide catalyst and a cobalt naphthenate accelerator.
  • the finned one-piece charge has fins of different, alternating thicknesses 4a, 412, so that two different thrust performances (one for take-off and one for acceleration) can be obtained from a single block.
  • the finned one-piece charge is formed of four quarters 2a to 2d of a cylinder, machined to form fins 4, joined by means of adhesive 6 to reconstitute the cylindrical block, and whose sides 7 are coated with inhibitor.
  • a method of manufacturing a finned, one-piece propellant powder charge which comprises a. splitting an extruded or moulded cylindrical block of propellant powder into two or more sectors of the cylinder along one or more planes containing the longitudinal axis of the block,
  • each sector machining the interior of each sector to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector with parallel longitudinal fins integrally connected at their bases to the rim of the respective sector,
  • the block of propellant powder is in the form of a right circular cylinder which is split into two semi-circular sectors for machining the fins thereon.
  • the block of propellant powder comprises a double-base or compound explosive, said compound explosive being formed of an oxidizing agent, a reducing agent and a rubbery binder.
  • a method according to claim 5 comprising a compound explosive, wherein said oxidizing agent is ammonium perchlorate, said reducing agent is aluminum powder and said rubbery binder is polybutadiene.
  • a finned, one-piece, propellant powder charge comprising a cylindrical block of propellant powder exteriorlycoated with a layer of a combustion inhibitor, said cylindrical block being composed of a plurality of substantially contiguous sectors along at least one plane containing the longitudinal axis of said block, wherein the interior of each sector contains a plurality of spaced parallel longitudinal fins of said propellant powder integrally connected at their bases to the rim of the sector thereby defining a void between a portion of said fins.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Medicinal Preparation (AREA)
  • Catalysts (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Air Bags (AREA)
US00210752A 1970-12-22 1971-12-22 Propellant powder charge having finned internal configuration Expired - Lifetime US3779819A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7046134A FR2119128A5 (ja) 1970-12-22 1970-12-22

Publications (1)

Publication Number Publication Date
US3779819A true US3779819A (en) 1973-12-18

Family

ID=9066159

Family Applications (1)

Application Number Title Priority Date Filing Date
US00210752A Expired - Lifetime US3779819A (en) 1970-12-22 1971-12-22 Propellant powder charge having finned internal configuration

Country Status (12)

Country Link
US (1) US3779819A (ja)
JP (1) JPS5128682B1 (ja)
BE (1) BE776933A (ja)
CA (1) CA957537A (ja)
CH (1) CH549778A (ja)
DE (1) DE2164028C3 (ja)
FR (1) FR2119128A5 (ja)
GB (1) GB1315644A (ja)
IT (1) IT943322B (ja)
LU (1) LU64486A1 (ja)
NL (1) NL158290B (ja)
SE (1) SE431745B (ja)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4551287A (en) * 1978-03-30 1985-11-05 Rheinmetall Gmbh Method of making a hollow-charge inserts for armor-piercing projectiles
WO1986001280A1 (en) * 1984-08-08 1986-02-27 The Commonwealth Of Australia Care Of The Secretar Macrogranular gun propellant charge
US4758287A (en) * 1987-06-15 1988-07-19 Talley Industries, Inc. Porous propellant grain and method of making same
US5623115A (en) * 1995-05-30 1997-04-22 Morton International, Inc. Inflator for a vehicle airbag system and a pyrogen igniter used therein
US5959237A (en) * 1995-08-31 1999-09-28 The Ensign-Bickford Company Explosive charge with assembled segments and method of manufacturing same
US9051223B2 (en) * 2013-03-15 2015-06-09 Autoliv Asp, Inc. Generant grain assembly formed of multiple symmetric pieces
US20180112627A1 (en) * 2015-08-07 2018-04-26 Aerojet Rocketdyne, Inc. Solid rocket motor with vortex inducing feature

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4202129B4 (de) * 1992-01-27 2005-06-23 Rheinmetall W & M Gmbh Kompakter Ladungskörper

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048112A (en) * 1959-02-06 1962-08-07 Phillips Petroleum Co Gas generator
US3421325A (en) * 1961-11-08 1969-01-14 Joseph G Thibodaux Jr Solid propellant rocket motor
US3492815A (en) * 1967-03-10 1970-02-03 Thiokol Chemical Corp Means for forming radial slots in solid propellant grains

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048112A (en) * 1959-02-06 1962-08-07 Phillips Petroleum Co Gas generator
US3421325A (en) * 1961-11-08 1969-01-14 Joseph G Thibodaux Jr Solid propellant rocket motor
US3492815A (en) * 1967-03-10 1970-02-03 Thiokol Chemical Corp Means for forming radial slots in solid propellant grains

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4551287A (en) * 1978-03-30 1985-11-05 Rheinmetall Gmbh Method of making a hollow-charge inserts for armor-piercing projectiles
WO1986001280A1 (en) * 1984-08-08 1986-02-27 The Commonwealth Of Australia Care Of The Secretar Macrogranular gun propellant charge
US4758287A (en) * 1987-06-15 1988-07-19 Talley Industries, Inc. Porous propellant grain and method of making same
US5623115A (en) * 1995-05-30 1997-04-22 Morton International, Inc. Inflator for a vehicle airbag system and a pyrogen igniter used therein
US5959237A (en) * 1995-08-31 1999-09-28 The Ensign-Bickford Company Explosive charge with assembled segments and method of manufacturing same
US6739265B1 (en) 1995-08-31 2004-05-25 The Ensign-Bickford Company Explosive device with assembled segments and related methods
US9051223B2 (en) * 2013-03-15 2015-06-09 Autoliv Asp, Inc. Generant grain assembly formed of multiple symmetric pieces
US20180112627A1 (en) * 2015-08-07 2018-04-26 Aerojet Rocketdyne, Inc. Solid rocket motor with vortex inducing feature
US10883448B2 (en) * 2015-08-07 2021-01-05 Aerojet Rocketdyne Inc. Solid rocket motor with vortex inducing feature

Also Published As

Publication number Publication date
NL7117582A (ja) 1972-06-26
IT943322B (it) 1973-04-02
BE776933A (fr) 1972-04-17
CH549778A (fr) 1974-05-31
FR2119128A5 (ja) 1972-08-04
JPS5128682B1 (ja) 1976-08-20
DE2164028C3 (de) 1974-09-12
NL158290B (nl) 1978-10-16
CA957537A (en) 1974-11-12
DE2164028A1 (de) 1972-08-03
GB1315644A (en) 1973-05-02
LU64486A1 (ja) 1972-06-20
SE431745B (sv) 1984-02-27
DE2164028B2 (de) 1974-02-07

Similar Documents

Publication Publication Date Title
US3316718A (en) Honeycomb structured propellant for rocket motors
US3779819A (en) Propellant powder charge having finned internal configuration
US2783138A (en) Propellant compositions
US3088273A (en) Solid propellant rocket
US4080902A (en) High speed igniter device
US10093592B2 (en) Additive manufactured combustible element with fuel and oxidizer
US3256819A (en) Gas generator
US3389025A (en) Propellant composition containing high energy metal in the form of multi-di-mensional crosses
US3496870A (en) Spiral burning propellant charge
US3442213A (en) Propellant charge for small arms ammunition
IL124959A (en) Solid and push explosive charge for a push unit and a push unit equipped with such an explosive charge
US726901A (en) Explosive charge.
US3926697A (en) Solid block of propellant with a plurality of propulsion stages and methods of manufacture
US5359935A (en) Detonator device and method for making same
US3664262A (en) Reactive focusing warhead concept
US3492815A (en) Means for forming radial slots in solid propellant grains
US3807171A (en) Supported high-surface-area propellant charges for high-acceleration rockets
US3324795A (en) Solid propellant
US3742856A (en) Advanced continuous warhead
US3048968A (en) Rocket motor
US3750353A (en) Method for producing arched structures
US3121309A (en) Spherically-shaped rocket motor
GB1490511A (en) Solid propelling charge having reinforcing filaments and a method for the production thereof
US3529551A (en) Rocket propellant
US2763127A (en) Jet propelled device