US2548398A - Line-carrying rocket - Google Patents

Line-carrying rocket Download PDF

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Publication number
US2548398A
US2548398A US783022A US78302247A US2548398A US 2548398 A US2548398 A US 2548398A US 783022 A US783022 A US 783022A US 78302247 A US78302247 A US 78302247A US 2548398 A US2548398 A US 2548398A
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US
United States
Prior art keywords
casing
rocket
composition
rods
secured
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
US783022A
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English (en)
Inventor
Schermuly Conrad David
Schermuly Alfred James
Schermuly Charles
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.)
Individual
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Individual
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 Individual filed Critical Individual
Application granted granted Critical
Publication of US2548398A publication Critical patent/US2548398A/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
    • F42B12/68—Line-carrying missiles, e.g. for life-saving

Definitions

  • This invention relates to line-carrying rockets and has for its object to provide a rocket capable of carrying a heavier line and/or capable of travelling for a greater distance than hitherto.
  • thermeans for ensuring ignition of the two propellant compositions at substantially the same time may consist of a passage throughout the length of the rear casing so that the ash from the cartridge not only ignites the propellant composition in the rear casing but also passes through the said passage and ignites the propellant composition in the front casing.
  • a fuze may be led from the rear end of the propellant composition in each of the casings, the free ends of the fuzes being joined together so that they may be ignited simultaneously.
  • one casing may carry one or more rods projecting from the end thereof and passing through corresponding sleeves secured to the other casing, the rods being provided with stops to limit the relative axial movement.
  • one casing may be somewhat wider than the other so that the smaller casing may slide ⁇ within the end of the larger casing, the portion of the larger casing within which the smaller casing slides being apertured to allow the escape of the combustion products from the propellant charge in the larger casing when the rocket is in flight.
  • the propellant composition may be of the kind:
  • Figure 1 is a side elevation of one embodiment of rocket according to this invention.
  • Figure 2 is a side elevation of the embodiment of Figure 1 in ilight position
  • Figure 3 is a plan view of the rocket of Figure 2
  • Figures 4 to 6 are views similar to Figures 1 to 3 but of a second embodiment of the-invention
  • Figures 7 and 8 are enlarged views of the frontand rear portions ofthe rocket of Figure .2,the-v lower half being in section, and
  • Figure 9 is an enlarged view-of parts of the; rocket of Figure 6, the lower half being in section.:
  • a iront rocket casing I has secured to its rear end a collar 2 to: which are secured two sleeves 3 into which are; Slidable on the rods i are two.
  • the collar I has secured thereto two further sleeves 9, into which are secured two rods Il) to the free ends of which is hinged a bridle l I for the attachment of a line to the rocket.
  • the casing I is closed at the front end by a plug I2 and a layer of clay I3, and contains propellant composition tapered hollow I5 at its rear end, and also an annular layer of clay I6 and a choke Il.
  • the rear casing -l also contains a clay plug I9, propellant composition 2U having a tapered hollow 2
  • the rear casing 'I is provided at its front end with a' ⁇ plug i8 the front of which is of frusto-conical.
  • the bridle Il is swung into the position shown in Figure l and the rear casing 'I is inserted into the barrel of a discharger cons to permit the escape of gas.
  • a sleeve 30 in which is xed a rod 3 I.
  • a bridle 32 is hinged to the rear ends of the rods 3I.
  • the contents of the casings 26 and 25 may be the same as those of the casings I and l in Figures 'I and 8.
  • the propellant composition 33 and 39 may be in the form of pressed cylinders which are held in spaced relationship to the casings 26 and 25 by means of spiders 35.
  • the ignition of the propellant composition 33 and 34 may be by means of fuzes and in order to indicate the way in which these fuzes may be arranged they are shown in Figure 9, although in actual fact when the rocket is in the iiight position shown in Figure 9 the fuzes will have burned away.
  • One fuze 36 is joined at its front end to the composition 33 in the front casing 26, passes through a bore in the plug 31 which closes the front end of the casing 25, passes through the space between the composition 34 and the casing 25 and out through the choke 38 where it is joined to another fuze 39 which is attached'to the composition 34.
  • the fuzes 36 and 39 may be omitted and the rocket shown in Figure 9 fired by means of a cartridge.
  • the iiash from the cartridge not only ignites the composition 34 but also passes through Vthe space between the composition 3A and the casing 25 and through the bore in the plug 31 (a plurality of these bores preferably being provided in this case) and ignites the composition 33.
  • the rocket in the position shown in Figure 4 may also be fired from a discharger by means of a cartridge.
  • a rocket comprising a front casing and a rear casing, means on the front casing supporting the rear casing for limited axial sliding movement relative to the front casing, two rods secured to the rear casing, a bridle hinged to said rods, a propellant composition in each of said casings and means for ensuring ignition of the two propellant compositions at substantially the same i time.
  • a rocket comprising a front casing and a rear casing, means on the front casing supporting the rear casing for limited axial sliding movement within the rear portion of the front casing, apertures in said rear portion of the front casing for the escape of gas, two rods secured to the rear casing within two of the apertures in the front casing, said rods being spaced from said front casing to permit the insertion of the rear portion of said frontv casing in-a discharger, a propellant composition in each of said casings and means for ensuring ignition of the two propellant compositions at substantially the same time.
  • a rocket as claimed in claim 2 wherein ⁇ said two rods are secured to said casing within two of the apertures in the front casing and said rods are spaced from said front casing to permit the insertion of the rear portion of said front casing in a discharger.
  • a rocket comprising a front casing and a rear casing, means on the ⁇ front casing supporting the rear casing for limited axial sliding movementV relative to the front casing, a bridle secured to the rear casing for the attachment of a line, a propellant composition in each of said casings and means for ensuring ignition of the two propellant compositions at substantially the saine time.
  • CONRAD DAVID SCI-IERMULY ALFRED JAMES SCHERMULY. CHARLES SCHERMULY.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
US783022A 1946-10-30 1947-10-30 Line-carrying rocket Expired - Lifetime US2548398A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB32173/46A GB617739A (en) 1946-10-30 1946-10-30 Improvements in line-carrying rockets

Publications (1)

Publication Number Publication Date
US2548398A true US2548398A (en) 1951-04-10

Family

ID=10334442

Family Applications (1)

Application Number Title Priority Date Filing Date
US783022A Expired - Lifetime US2548398A (en) 1946-10-30 1947-10-30 Line-carrying rocket

Country Status (3)

Country Link
US (1) US2548398A (xx)
FR (1) FR954765A (xx)
GB (1) GB617739A (xx)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US890499A (en) * 1907-07-15 1908-06-09 Edwin S Clough Anchor-projectile.
FR406184A (fr) * 1909-08-17 1910-01-24 Georg Wedde Projectile explosible destiné à lancer des fusées incendiaires sur les ballons
GB181041A (en) * 1921-01-03 1922-06-06 B S A Guns Ltd Improvements in or relating to projectiles for line-throwing guns
GB325666A (en) * 1929-01-18 1930-02-27 Schermuly Pistol Rocket App Improvements in rockets for use in carrying life lines or the like
GB327369A (en) * 1929-08-15 1930-04-03 Alfred James Schermuly Improvements in rockets for use in carrying life-lines or the like
GB330493A (en) * 1929-07-19 1930-06-12 Edward Frank Spanner Improvements in rockets
US2210820A (en) * 1937-09-03 1940-08-06 Schermuly Pistol Rocket App Rocket or projectile for use in throwing lines
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
US2344957A (en) * 1940-01-12 1944-03-28 Aerial Products Inc Pistol rocket

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US890499A (en) * 1907-07-15 1908-06-09 Edwin S Clough Anchor-projectile.
FR406184A (fr) * 1909-08-17 1910-01-24 Georg Wedde Projectile explosible destiné à lancer des fusées incendiaires sur les ballons
GB181041A (en) * 1921-01-03 1922-06-06 B S A Guns Ltd Improvements in or relating to projectiles for line-throwing guns
GB325666A (en) * 1929-01-18 1930-02-27 Schermuly Pistol Rocket App Improvements in rockets for use in carrying life lines or the like
GB330493A (en) * 1929-07-19 1930-06-12 Edward Frank Spanner Improvements in rockets
GB327369A (en) * 1929-08-15 1930-04-03 Alfred James Schermuly Improvements in rockets for use in carrying life-lines or the like
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
US2210820A (en) * 1937-09-03 1940-08-06 Schermuly Pistol Rocket App Rocket or projectile for use in throwing lines
US2344957A (en) * 1940-01-12 1944-03-28 Aerial Products Inc Pistol rocket

Also Published As

Publication number Publication date
GB617739A (en) 1949-02-10
FR954765A (xx) 1950-01-05

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