US2406560A - Rocket motor - Google Patents

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US2406560A
US2406560A US516155A US51615543A US2406560A US 2406560 A US2406560 A US 2406560A US 516155 A US516155 A US 516155A US 51615543 A US51615543 A US 51615543A US 2406560 A US2406560 A US 2406560A
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casing
zone
circumferential
rocket
wall
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US516155A
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Winslow B Pope
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    • 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
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • 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
    • F02K9/14—Shape or structure of solid propellant charges made from sheet-like materials, e.g. of carpet-roll type, of layered structure
    • 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
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
    • F02K9/763—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with solid propellant
    • 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

  • This invention relates to rocket-propelled devices, more particularly to improvements in the design and construction of what may bertermed the rocket motor.
  • the primary object of the present invention is to provide a simplified arrangement for containing the propelling charge of a rocket-propelled device and for forming the pressure developing jets, which arrangement is particularly adapted for quantity production.
  • Another object is to provide a casing and jet arrangement which is so designed as to-.permit manufacture by lsimple machine turning operations, and which is adapted for rapid assembly.
  • a further object is to provide an improved multijet arrangement for rocket-propelled devices.
  • Figure 1 is a longitudinal view of a rocketpropelled device in which ⁇ the features of the present invention' are incorporated;
  • Figure 2i is an enlarged sectional view of the charge-containing casing
  • Figure 3 is a transverse section of the stabilizing unit, taken substantiallyon Aline 3-3 of Figure 2; and I Figures 4 and ⁇ 5 are fragmentary sections showingmodiled Venturi arrangements.
  • the arrangement of the present invention comprises a tubular element lIIl secured through a threaded connection II at its forward end to the device I2 to be propelled.
  • the device I2 may consist of an explosive projectile, a chemical or are device or any other device desired vto be projected through space.
  • the casing is provided with circumferentially spaced aperturesY I9 through its Wall which open into the space or chamber 20 dened by the axial portion I5, the forward edge of the face I1, the wall I8 andthe tube I3.
  • the tube I3 at the rearward side of the apertures I9 and surrounded by the face Il is tapered at 2l in the same direction as the face I'I. I'he face I'I and wall I8 of the element I4 together with the face 2
  • the Viorward axial portions I5 of the half-sections .I4a are each formed with a radially inwardly extending locking ridge 22 which when assembled on the casing I3 snugly fits in a circumferential groove 23 in the outer surface of the casing I3, locking the half-sections against axial movement relative to the casing I3.
  • the two half-sections IdaI are provided in their external faces substantially in transverse alignment with the ridges with aligned grooves 24 which receive an endless locking ring 25.
  • the locking ring 25 is shrunk into the groove 24 in substantially the same manner as a rotating band is applied to a shell, and when shrunk into place securely clamps the halfsectons Ida about the casing I3.
  • spacing shms 26 are provided between the mating portions of the half-sections Illa.
  • the propelling charge is in the form of a plurality of .axially aligned annular .combustible elementsy .32 separated by spacers 33, the group of elements 32 being mounted on a headed rod 34 and arranged within the casing I3.
  • the rod 34 is threaded into a boss-like projection V35 forming an axial .extension of the stabilizer plug .28.
  • this wall is formed by the outer face of an annular ring .42 ⁇ shrunk into position on the casing I3, the ring 42'and casing -having inter-V locking ridge and groove portions 43 and ⁇ 44, relspectively.
  • the wall 2 I a is machine tapered after the ring 42 is shrunk into position.
  • the element I4 is in the form of a single-piece l ring slipped over the casing I3V and held in place by suitable dowels 45 extending therethrough'into The 'smaller ring 42 may also be held in position by Similar. ⁇
  • tube I3 and Venturi-forming elements .I4 can be easily lformed from tubular stcckby simple machine turning operations and are so designed as to facilitate as- 1 l sembly operations, all of which provide for rapid quantity'production.
  • a tubularr casing for a rocket-propelled ⁇ deg vice adapted to contain acombustiblepropelling i charge and having in a circumferential zone at Qleast one aperture thr-ough the .wall thereof for f ⁇ :discharging from theu interiorthereof gases re- 1 sulting from the burning ofI the propelling charge, an annular member surrounding Vsaid casing and and extending from said one side axially over and i substantially beyond said zone in circumferentially spaced relation, said annular member-being axially dividedto provide semi-circular half- 1 sections, and means for securely clamping said 1 half-sectionsl about said casing at said one side.
  • Ay tubular casing for a'rocket-propelled de-V vice adapted tocontain a' combustible propelling charge and having in a circumferential zone at least one aperture through the Wall thereof for discharging from the interior thereof gases resulting from the burning of the propelling charge,
  • annular member surrounding said casing and closely fitting said casing at one side of said Zone and extending from said one side axially over and substantiallybeyond said Zone in circumferenvice, adapted to contain a combustible propelling l charge andl having in a circumferential zone at least one aperture through the Wall thereof for l discharging from the interior thereof gases rej sulting fromthe burning of the propelling charge, 1
  • annularpropulsion jet therewith an axially directed annularpropulsion jet, said means comprising a pairof semi- Vleast one aperture through the Wall thereof for discharging from the interior thereof ygases resulting from the burning of the propelling charge.
  • annular member surrounding said casing and closely tting said casing at one side of said zone and extending from said one side axially over and Y substantially beyond said Zone in circumferentially spaced.
  • said annular Vmember being axially divided to vprovide semi-circular halfsections, and means for securely clamping said half-sections about said casing at said one side, said casing in the circumferential region ⁇ at the other side of said zone, and the circumferential 'portion of Athe innenwall of said annular member to form a continuousl ring-like element having an 3 vaxial extent including .said vapertured zone'and regions of substantial'axial extent vat each side Vof said Zone, said shells beingcircumferentially 3 spaced from-both said apertured regionand one i Y Aof said side regions and closely engaged with said i casing -at the other sideregion, vand means for closely fitting said casing at one side of said Zone -vice, adapted to'contain a combustible propelling charge and having in Va circumferential zone at i leastlone aperture through the wallr thereof-.for
  • anannular member surrounding said casing and -c'losely fitting said casing at one side of saidfzone Y band extending from saidzone side axially over. and' substantially beyondsaid'zone in. circumferen-" I tially spaced relation, said annular member being Aspaced from the ca'singbeing contoured to provide an annular Venturi passage.
  • A'tubulary casing fora rocket-propelled device adapted to contain a combustible propelling charge and having in a circumferential zone at least one aperture through the Wall thereof for discharging from the interior thereof Vgases resulting from the burning of the propelling charge,
  • van annular member surrounding said casing and closelygtting said, casing at one side ofY said zone and extendingvrfrom. said one side axially over and substantially beyond said Zone in cirvcurnferentially spaced relation, .said annular member being axially divided to provide semi- .circular half-sections and means for.
  • annular member surrounding said casing and closely iitting said casing at one side of said Zone and extending from said one side axially over and substantially beyond said zone in crcumferentially spaced relation, the external surface of said casing at the other side of said zone for the region surrounded by said annular member being conical in form and tapering radially outwardly in a direction away from said apertured zone, said conical surface and the inner Wall of the spaced portion of said annular member together dening an annular Venturi passage.
  • a tubular casing for a rocket-propelled device adapted to contain a combustible propelling charge and having at each of a plurality of axially spaced circumferential zones one or more apertures through the wall thereof for the discharge from the interior of the casing of gases resulting from the burning of the propelling charge, and spaced external annular elements surrounding said casing, each closely tting said casing at one side of an aperturedrzone, and extending axially over and beyond said zone in circumferentially spaced relation and dening with said casing an axially directed propulsion jet communicating with the interior of said casing through the apertures of the surrounded zone, each of said elements being axially divided to provide semi-circular half-sections, and means for securely clamping said sections around said casing.
  • a tubular casing for a rocket-propelled device -adapted to contain a combustible propelling charge and having in a circumferential Zone at least one aperture through the Wall thereof for discharging from the interior thereof gases resulting from the burning of the propelling charge, an annular member surrounding said casing and closely tting said casing at one side of said zone and extending from said one side axially over and substantially beyond said Zone in circumferentially spaced relation, and a plurality of radially extending dowei through said annular member into said casing at said one side for locking said member against movement on said casing.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Jet Pumps And Other Pumps (AREA)

Description

Agg. 27,1946.- w. B. POPE ROCKET MOTOR Filed Dec. 30,' 1943 I N VEN TOR Winslow pope A TTORNE Y Patented Aug. 27, 1946 ROCKET MOTOR Winslow B. Pope,I Detroit, Mich., .assgnon by mesne assignments, to United States of America Application December 30, 1943, Serial No. 516,155
This invention relates to rocket-propelled devices, more particularly to improvements in the design and construction of what may bertermed the rocket motor.
The primary object of the present invention is to provide a simplified arrangement for containing the propelling charge of a rocket-propelled device and for forming the pressure developing jets, which arrangement is particularly adapted for quantity production.
Another object is to provide a casing and jet arrangement which is so designed as to-.permit manufacture by lsimple machine turning operations, and which is adapted for rapid assembly.
A further object is to provide an improved multijet arrangement for rocket-propelled devices. With the above and other objects in view, which will be apparent from the vfollowing description to those skilled in the art t which the invention appertains, the present invention consists in certain features of construction and combinations of parts to be hereinafter ldescribed with referenceY to theaccompanying drawing, and
then claimed. f
In the drawing which illustrates suitable -embodiments of the invention,
Figure 1 is a longitudinal view of a rocketpropelled device in which` the features of the present invention' are incorporated;
Figure 2i is an enlarged sectional view of the charge-containing casing;
Figure 3 is a transverse section of the stabilizing unit, taken substantiallyon Aline 3-3 of Figure 2; and I Figures 4 and`5 are fragmentary sections showingmodiled Venturi arrangements.
Referring to the drawing, particularly to `Figures 1 and V2, the arrangement of the present invention comprises a tubular element lIIl secured through a threaded connection II at its forward end to the device I2 to be propelled. The device I2 may consist of an explosive projectile, a chemical or are device or any other device desired vto be projected through space.
' tube I3 and a rearwardly extending axial p ortion IS circumferentially spaced from the tube I3. TheY inner circumferential face formed bythe 9 Claims. (Cl. 60-35.6)
mating rearwardly extending axial portions tafpers radially inwardly from .the rearward edge thereof for a portion of its axial extent to provide the conical face Il,vand at the portion. I8 between the face II and the forward axial portion I5 is outwardly recessed. The casing is provided with circumferentially spaced aperturesY I9 through its Wall which open into the space or chamber 20 dened by the axial portion I5, the forward edge of the face I1, the wall I8 andthe tube I3. The tube I3 at the rearward side of the apertures I9 and surrounded by the face Il is tapered at 2l in the same direction as the face I'I. I'he face I'I and wall I8 of the element I4 together with the face 2| of the casing I3 thus form a Venturi passage which is in com,- munication with the interior lof the casing I 3 through the apertures I9.
In the construction shown in Figure 2, the Viorward axial portions I5 of the half-sections .I4a are each formed with a radially inwardly extending locking ridge 22 which when assembled on the casing I3 snugly fits in a circumferential groove 23 in the outer surface of the casing I3, locking the half-sections against axial movement relative to the casing I3. The two half-sections IdaI are provided in their external faces substantially in transverse alignment with the ridges with aligned grooves 24 which receive an endless locking ring 25. The locking ring 25is shrunk into the groove 24 in substantially the same manner as a rotating band is applied to a shell, and when shrunk into place securely clamps the halfsectons Ida about the casing I3.
Preferably, in order to provide for tighttting engagement of .the half-sections with .the tube I3, spacing shms 26 are provided between the mating portions of the half-sections Illa.
The stabilizing element 42'I Vcomprises. `a plug 23 threaded into the rearward end of the casing I3 and having a shouldered portion .29 to which a plurality of radial sheet metal stabilizing varies 3D are welded, the vvaries being surrounded by tightly fitting sheet metal ring 3l' which holds the same against deflection.
The propelling charge is in the form of a plurality of .axially aligned annular .combustible elementsy .32 separated by spacers 33, the group of elements 32 being mounted on a headed rod 34 and arranged within the casing I3. The rod 34 is threaded into a boss-like projection V35 forming an axial .extension of the stabilizer plug .28.
Inasmuch as the means for igniting the propelling charge forms no part of the present invention, the same is not shown in the drawing.
. aoase In the modied construction of Figure 4, the ridge 22 and groove 23 are reversely arranged. Also, instead of machining or otherwise forming the Venturi wall 3| directly in the casing i3, this wall, designated 2Ia, is formed by the outer face of an annular ring .42 `shrunk into position on the casing I3, the ring 42'and casing -having inter-V locking ridge and groove portions 43 and`44, relspectively. The wall 2 I a is machine tapered after the ring 42 is shrunk into position.
In the modified construction shown in Figure 5, l the element I4 is in the form of a single-piece l ring slipped over the casing I3V and held in place by suitable dowels 45 extending therethrough'into The 'smaller ring 42 may also be held in position by Similar.`
apertures provided in the casing I3.
dowel-s 46.
It will ybe obvious from the drawing and the I foregoing description that the tube I3 and Venturi-forming elements .I4 can be easily lformed from tubular stcckby simple machine turning operations and are so designed as to facilitate as- 1 l sembly operations, all of which provide for rapid quantity'production.
Y n will be obvious to those skilled in the art to which the invention appertains that various l changes maybe made in the detailed construction g 'and arrangement of parts Without departing from 1 the spirit and substance of the invention, the i l Scope of which is defined by the appended claims.
What is claimed is: .f 1. A tubular casing for a rocket-propelled deand means associated with said casing and formcircular shells iittingv together about said casing clamping saidshells about said casing at said f other side region. Y Y Y f 2. A tubularr casing for a rocket-propelled` deg vice, adapted to contain acombustiblepropelling i charge and having in a circumferential zone at Qleast one aperture thr-ough the .wall thereof for f `:discharging from theu interiorthereof gases re- 1 sulting from the burning ofI the propelling charge, an annular member surrounding Vsaid casing and and extending from said one side axially over and i substantially beyond said zone in circumferentially spaced relation, said annular member-being axially dividedto provide semi-circular half- 1 sections, and means for securely clamping said 1 half-sectionsl about said casing at said one side.
.3. A tubular casing for a rocket-propelled dev 4 axially divided to provide semi-circular halfsections, and means for securely clamping said half-sections about said casing at said one side, said sections and the casing at said one side having intertting circumferential ridge and groove portions.
4.y Ay tubular casing for a'rocket-propelled de-V vice, adapted tocontain a' combustible propelling charge and having in a circumferential zone at least one aperture through the Wall thereof for discharging from the interior thereof gases resulting from the burning of the propelling charge,
an annular member surrounding said casing and closely fitting said casing at one side of said Zone and extending from said one side axially over and substantiallybeyond said Zone in circumferenvice, adapted to contain a combustible propelling l charge andl having in a circumferential zone at least one aperture through the Wall thereof for l discharging from the interior thereof gases rej sulting fromthe burning of the propelling charge, 1
l ing therewith an axially directed annularpropulsion jet, said means comprising a pairof semi- Vleast one aperture through the Wall thereof for discharging from the interior thereof ygases resulting from the burning of the propelling charge. an annular member surrounding said casing and closely tting said casing at one side of said zone and extending from said one side axially over and Y substantially beyond said Zone in circumferentially spaced. relation,v said annular Vmember being axially divided to vprovide semi-circular halfsections, and means for securely clamping said half-sections about said casing at said one side, said casing in the circumferential region` at the other side of said zone, and the circumferential 'portion of Athe innenwall of said annular member to form a continuousl ring-like element having an 3 vaxial extent including .said vapertured zone'and regions of substantial'axial extent vat each side Vof said Zone, said shells beingcircumferentially 3 spaced from-both said apertured regionand one i Y Aof said side regions and closely engaged with said i casing -at the other sideregion, vand means for closely fitting said casing at one side of said Zone -vice, adapted to'contain a combustible propelling charge and having in Va circumferential zone at i leastlone aperture through the wallr thereof-.for
Y discharging from'. the interior thereof gases re-` sulting from the burning of the propelling charge,
anannular member surrounding said casing and -c'losely fitting said casing at one side of saidfzone Y band extending from saidzone side axially over. and' substantially beyondsaid'zone in. circumferen-" I tially spaced relation, said annular member being Aspaced from the ca'singbeing contoured to provide an annular Venturi passage. v
V6. A'tubulary casing fora rocket-propelled device, adapted to contain a combustible propelling charge and having in a circumferential zone at least one aperture through the Wall thereof for discharging from the interior thereof Vgases resulting from the burning of the propelling charge,
van annular member surrounding said casing and closelygtting said, casing at one side ofY said zone and extendingvrfrom. said one side axially over and substantially beyond said Zone in cirvcurnferentially spaced relation, .said annular member being axially divided to provide semi- .circular half-sections and means for. securely clamping said half-sections about said casing at said one side, said casing in the .circumferential region at the other side of said Zone'and the circumferential portion of the Iinner Wall of saidv annular member spaced vfrom the casing being contoured to provide an annular Venturi passage, said circumferential regionof said casing at .said other side being conical in form and taperingradially outwardly in a direction away from said'apertured Zone, and the surrounding said' circumferential 'portion beingA correspondingly taperedvto a greater degree.
, V 7. Agtubularcasingfor a rocket-propelled de- ,vice, adapted to contain a combustible propelling `chargeV and having in agcircumferential zone at Y lleast-one-aperturethrough the wall thereof for `'discharging' from' theginterior thereof gases resulting from' the burningpof the propelling charge,
an annular member surrounding said casing and closely iitting said casing at one side of said Zone and extending from said one side axially over and substantially beyond said zone in crcumferentially spaced relation, the external surface of said casing at the other side of said zone for the region surrounded by said annular member being conical in form and tapering radially outwardly in a direction away from said apertured zone, said conical surface and the inner Wall of the spaced portion of said annular member together dening an annular Venturi passage.
8. A tubular casing for a rocket-propelled device, adapted to contain a combustible propelling charge and having at each of a plurality of axially spaced circumferential zones one or more apertures through the wall thereof for the discharge from the interior of the casing of gases resulting from the burning of the propelling charge, and spaced external annular elements surrounding said casing, each closely tting said casing at one side of an aperturedrzone, and extending axially over and beyond said zone in circumferentially spaced relation and dening with said casing an axially directed propulsion jet communicating with the interior of said casing through the apertures of the surrounded zone, each of said elements being axially divided to provide semi-circular half-sections, and means for securely clamping said sections around said casing.
9. A tubular casing for a rocket-propelled device, -adapted to contain a combustible propelling charge and having in a circumferential Zone at least one aperture through the Wall thereof for discharging from the interior thereof gases resulting from the burning of the propelling charge, an annular member surrounding said casing and closely tting said casing at one side of said zone and extending from said one side axially over and substantially beyond said Zone in circumferentially spaced relation, and a plurality of radially extending dowei through said annular member into said casing at said one side for locking said member against movement on said casing.
WINSLOW B. POPE.
pins extending
US516155A 1943-12-30 1943-12-30 Rocket motor Expired - Lifetime US2406560A (en)

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2462099A (en) * 1946-05-15 1949-02-22 Clarnece N Hickman Rocket projectile
US2633702A (en) * 1946-02-28 1953-04-07 Clarence N Hickman Multiple nozzle rocket
US2781633A (en) * 1949-04-15 1957-02-19 Aerojet General Co Apparatus for mounting solid propellant grains in a rocket motor
US2946261A (en) * 1956-05-02 1960-07-26 Sydney R Crockett Peripheral nozzle spinner rocket
US2976805A (en) * 1947-02-11 1961-03-28 Africano Alfred Rocket construction
DE1106120B (en) * 1957-01-17 1961-05-04 Heinrich Klein Dr Ing Connection device for solid rockets
US2990682A (en) * 1951-11-07 1961-07-04 Gen Electric Fuel charge
US3049876A (en) * 1960-03-30 1962-08-21 James F Connors Annular rocket motor and nozzle configuration
DE1140028B (en) * 1959-11-13 1962-11-22 Rheinmetall Gmbh Solid rocket propellant
US3094072A (en) * 1957-12-09 1963-06-18 Arthur R Parilla Aircraft, missiles, missile weapons systems, and space ships
DE1151409B (en) * 1960-02-05 1963-07-11 Boelkow Entwicklungen Kg Annular gap nozzle for rocket engines
DE1170714B (en) * 1959-11-26 1964-05-21 Rheinmetall Gmbh Propellant charge for powder rockets
US3173250A (en) * 1960-05-05 1965-03-16 North American Aviation Inc Reverse flow thrust chamber
DE1223198B (en) * 1963-10-02 1966-08-18 Dynamit Nobel Ag Rocket with ring nozzle
FR2359981A1 (en) * 1976-07-27 1978-02-24 Messerschmitt Boelkow Blohm SOLID PROPERGOL ROCKET ENGINE
ITVR20130268A1 (en) * 2013-12-04 2015-06-05 M G R S R L JET ENGINE WITH CONFORMED RING NOZZLE FOR SEMIAUTOPROPULSA RIFLE BOMBS AS WELL AS BI-PLURI MISSILES AND STADIUM ROCKERS OF ARTILLERY OR PLURISTADIUM ARTILLERY PROJECTS WITH CORRECTION OF THE TRAJECTORY WITH ADDITIONAL PROJECT, RAZZ

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2633702A (en) * 1946-02-28 1953-04-07 Clarence N Hickman Multiple nozzle rocket
US2462099A (en) * 1946-05-15 1949-02-22 Clarnece N Hickman Rocket projectile
US2976805A (en) * 1947-02-11 1961-03-28 Africano Alfred Rocket construction
US2781633A (en) * 1949-04-15 1957-02-19 Aerojet General Co Apparatus for mounting solid propellant grains in a rocket motor
US2990682A (en) * 1951-11-07 1961-07-04 Gen Electric Fuel charge
US2946261A (en) * 1956-05-02 1960-07-26 Sydney R Crockett Peripheral nozzle spinner rocket
DE1106120B (en) * 1957-01-17 1961-05-04 Heinrich Klein Dr Ing Connection device for solid rockets
US3094072A (en) * 1957-12-09 1963-06-18 Arthur R Parilla Aircraft, missiles, missile weapons systems, and space ships
DE1140028B (en) * 1959-11-13 1962-11-22 Rheinmetall Gmbh Solid rocket propellant
DE1170714B (en) * 1959-11-26 1964-05-21 Rheinmetall Gmbh Propellant charge for powder rockets
DE1151409B (en) * 1960-02-05 1963-07-11 Boelkow Entwicklungen Kg Annular gap nozzle for rocket engines
US3049876A (en) * 1960-03-30 1962-08-21 James F Connors Annular rocket motor and nozzle configuration
US3173250A (en) * 1960-05-05 1965-03-16 North American Aviation Inc Reverse flow thrust chamber
DE1223198B (en) * 1963-10-02 1966-08-18 Dynamit Nobel Ag Rocket with ring nozzle
FR2359981A1 (en) * 1976-07-27 1978-02-24 Messerschmitt Boelkow Blohm SOLID PROPERGOL ROCKET ENGINE
ITVR20130268A1 (en) * 2013-12-04 2015-06-05 M G R S R L JET ENGINE WITH CONFORMED RING NOZZLE FOR SEMIAUTOPROPULSA RIFLE BOMBS AS WELL AS BI-PLURI MISSILES AND STADIUM ROCKERS OF ARTILLERY OR PLURISTADIUM ARTILLERY PROJECTS WITH CORRECTION OF THE TRAJECTORY WITH ADDITIONAL PROJECT, RAZZ

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