US3714863A - Gas pressure actuators - Google Patents

Gas pressure actuators Download PDF

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Publication number
US3714863A
US3714863A US00172115A US3714863DA US3714863A US 3714863 A US3714863 A US 3714863A US 00172115 A US00172115 A US 00172115A US 3714863D A US3714863D A US 3714863DA US 3714863 A US3714863 A US 3714863A
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United States
Prior art keywords
valve member
bore
actuator
outlet
priming device
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
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US00172115A
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English (en)
Inventor
J Sindall
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.)
Imperial Metal Industries Kynoch Ltd
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Imperial Metal Industries Kynoch Ltd
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Publication date
Application filed by Imperial Metal Industries Kynoch Ltd filed Critical Imperial Metal Industries Kynoch Ltd
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Publication of US3714863A publication Critical patent/US3714863A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/30—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids of propellant gases, i.e. derived from propulsive charge or rocket motor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/31—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids generated by the combustion of a pyrotechnic or explosive charge within the fuze

Definitions

  • SHEET 2 [IF 3 PATENTEDFEE s 1975 SHEET 30F 3 GAS PRESSURE ACTUATORS BACKGROUND OF THE INVENTION
  • This invention relates to gas operated pressure actuators for missile systems.
  • ancillary devices When a rocket motor has been fired to propel a missile through the atmosphere, it is sometimes required to actuate an ancillary device of the missile.
  • ancillary devices are navigational aids, flares, flight guidance means and pumps, as well as other igniters required for instance to ignite ram jets.
  • a pressure actuator for a missile system comprises a housing having a bore with an inlet port at a rear end thereof, an outlet port at the forward end thereof, and at least one outlet vent intermediate the inlet and outlet ports, a slide valve member slidably mounted within the bore but releasably retained adjacent the rear end of the bore by collapsible means interconnecting the housing and the valve member, the valve member having a forwardly facing striking surface and a forwardly extending sleeve portion which terminates rearwardly of the outlet vent but is adapted to close the outlet vent on forward movement of the valve member, the actuator further comprising a percussion-operated priming device mounted forwardly of, and axially aligned with, the striking surface of the valve member, and an ignition charge disposed forwardly of the priming device, the arrangement being such that upon operation of the actuator the slide valve member closes the outlet vent before the priming device is struck.
  • the ignition charge is spaced from the priming device and is disposed intermediate the outlet vent and the outlet port.
  • a wire mesh cage is interposed between the ignition charge and the priming device and extends over the outlet vent.
  • the valve member may comprise a percussion piston slidably mounted within a bore of the valve member and rearwardly of the priming device, the piston being releasably retained within said bore by collapsible means so that upon collapse of said means, the piston can move forwardly within the valve member.
  • FIG. 1 is an axial cross-sectional view of a pressure actuator in its inoperative position
  • FIG. 2 is a view similar to FIG. il showing the actuator in its operative position
  • FIG. 3 is a bottom plan view of the actuator.
  • a pressure actuator comprises a generally cylindrical housing 10 made from steel and having forward and rearward ends 11,12 respectively.
  • the housing is bored from its forward end 11 to provide a bore 13 which reduces in diameter at a step 14 to form a bore 15.
  • the base of the bore 15 has a shallow recess 16 in the end wall 17 of the housing to provide an annular shoulder 18 around the recess.
  • a spigot 19 projects from the rear end of the housing and an inlet passage 20 extends through the spigot 19, through the end wall 17 and opens into the recess 16 at an inlet port 20a.
  • Near the shoulder 14 four outlet vents 21 are provided in the wall of the housing and extend radially from the bore 15.
  • a flange 1110 (FIG. 3) extends laterally from the rear end of the housing for mounting purposes; other mounting means can be employed if desired, for example the rearward end 12 of the housing 10 may have an external screw thread.
  • a cylindrical slide valve member 22 is slidably mounted within the bore 15 but in the inoperative condition of the actuator the slide valve member is retained at the rearward end of the bore and in contact with the shoulder 18 by collapsible means in the form of four shear pins 23 equi-angularly disposed around the actuator.
  • the shear pins are disposed radially through the wall of the housing 10 and project into the slide valve member 22 so as to interconnect the housing and the valve member.
  • the valve member has a coaxial bore 24 which opens into .a bore 25 at the rearward end, and opens into a bore 26 at the forward end to provide an annular sleeve 27.
  • the leading end of the sleeve is internally and externally chamfered to form a circular edge 28.
  • a percussion piston 29 has a body portion 30 and a forwardly facing striking surface in the form of a projecting nose 31.
  • the body portion 30 has a shorter length than that of the bore 25 and is slidably mounted in the bore 25.
  • the piston is releasably retained within the bore, with the rear face of the piston flush with the rear face of the slide valve member 22, by means of a single diametrically disposed shear pin 32 extending through the valve member and the piston.
  • An ignition charge container 33 is disposed within the housing 10 and comprises a cylindrical head 34 located in the bore 13 but spaced from the step 14 by a soft metallic ring 35.
  • a body 36 of the container extends rearwardly from the head slidably within the annular sleeve 27 of the slide valve member 22, and a portion 37 of the body 36 projects rearwardly from the body to be freely relatively movable within the bore 24 of the valve member.
  • a shoulder 38 of the body 36 surrounds the portion 37.
  • the container is coaxially bored to provide at its forward end a recess 39 which reduces in turn to a chamber 40, a chamber 41, and a bore 42.
  • radial holes 43 are provided in the body 36 so as to be aligned with respective vents 21 in the housing 10. Drillings 44 extend from the shoulder 38 to intersect the radial holes 43.
  • a percussion-operated priming device 45 of conventional design as used in the manufacture of shotgun cartridges except that the priming powder has the following composition:
  • a black powder igniter 48 is disposed in the chamber 41 and a thin aluminum bursting disc 49, 0.001 inches thick, rests at the base of the chamber 40 to cover the igniter 48.
  • a two-part wire cage spacer 50 rests on the disc 49 and extends over the radial holes 43. Above the spacer 50 the lower part of a tubular charge 51 of cordite is disposed within the recess 39. The spacer 50 is not essential but it assists in retaining the disc 49 in position and in supporting the charge 51.
  • an end cover 52 is secured between the forward end of the container 33 and a circlip 53 mounted in the wall of the housing 10.
  • the end cover 52 is recessed as at 54 in order to receive the upper part of the charge 51.
  • a stem 55 is integral with and extends forwardly from the cover 52 and has its free end screw-threaded for securing the actuator to the missile system to be actuated via suitable tubing.
  • An axial passage 56 extends from an outlet port 57 at the base of the recess 54 and along the stem 55.
  • Dust caps 58 (of which only one is shown) are fitted to close the outlet vents 21.
  • O-ring seals are provided on parts of the actuator as shown by the usual representation in the drawings.
  • the actuator when assembled as described above in its inoperative condition, is mounted on a rocket motor, the spigot 19 being connected to the combustion chamber of the rocket motor and the stem 55 being connected to the respective device to be actuated.
  • the axial dimensions of the parts of the actuator are so designed that during this movement of the piston 29 relative to the valve member, the nose 3] of the piston impacts against the priming device 45 to cause ignition of the igniter 48. This, in turn, ignites the cordite charge 51 of which the pressurized gas (approximately 700 p.s.i.) thus generated passes through the outlet passage 56 to actuate the associated device.
  • the slide valve member 22 and percussion piston 29 are held in the forward position of FIG. 2 by the approximately 1,250 p.s.i. pressure in the rear end portion of the bore 15.
  • a pressure actuator for a missile system comprising a housing having a bore with an inlet port at a rear end thereof, an outlet port at the forward end thereof, and at least one outlet vent intermediate the inlet and outlet ports, a slide valve member slidably mounted within the bore but releasably retained adjacent the rear end of the bore by collapsible means interconnecting the housing and the valve member, the valve member having a forwardly facing striking surface and a forwardly extending sleeve portion which terminates rearwardly of the outlet vent but is adapted to close the outlet vent on forward movement of the valve member, the actuator further comprising a percussion-operated priming device mounted forwardly of, and axially aligned with, the striking surface of the valve member, and an ignition charge disposed forwardly of the priming device, the arrangement being such that upon operation of the actuator the slide valve member closes the outlet vent before the priming device is struck.
  • valve member comprises a percussion piston slidably mounted within a bore of the valve member and rearwardly of the priming device, the piston being releasably retained within said bore by collapsible means so that upon collapse of said means, the piston can move forwardly within the valve member.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US00172115A 1970-08-18 1971-08-16 Gas pressure actuators Expired - Lifetime US3714863A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3973370 1970-08-18

Publications (1)

Publication Number Publication Date
US3714863A true US3714863A (en) 1973-02-06

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ID=10411172

Family Applications (1)

Application Number Title Priority Date Filing Date
US00172115A Expired - Lifetime US3714863A (en) 1970-08-18 1971-08-16 Gas pressure actuators

Country Status (8)

Country Link
US (1) US3714863A (enrdf_load_stackoverflow)
JP (1) JPS5219039B1 (enrdf_load_stackoverflow)
AU (1) AU448329B2 (enrdf_load_stackoverflow)
CA (1) CA948481A (enrdf_load_stackoverflow)
DE (1) DE2141403C3 (enrdf_load_stackoverflow)
FR (1) FR2108202B1 (enrdf_load_stackoverflow)
GB (1) GB1303146A (enrdf_load_stackoverflow)
SE (1) SE389191B (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3991683A (en) * 1972-02-02 1976-11-16 Diehl Safety device for projectiles
US4046076A (en) * 1975-09-29 1977-09-06 The United States Of America As Represented By The Secretary Of The Navy Impulsive rocket motor safety-arming device
US5753849A (en) * 1996-09-19 1998-05-19 Propellex Corporation Gas-operated timing demolition delay

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4951901A (en) * 1985-11-22 1990-08-28 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2499227A (en) * 1947-10-29 1950-02-28 Johns Manville Control mechanism for stud securing apparatus
US2939393A (en) * 1958-01-23 1960-06-07 Gen Precision Inc Vented safety squib arming device
US3106131A (en) * 1961-05-24 1963-10-08 Aircraft Armaments Inc Cartridge actuated device

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3133408A (en) * 1962-02-15 1964-05-19 Albert M Stott Thruster

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2499227A (en) * 1947-10-29 1950-02-28 Johns Manville Control mechanism for stud securing apparatus
US2939393A (en) * 1958-01-23 1960-06-07 Gen Precision Inc Vented safety squib arming device
US3106131A (en) * 1961-05-24 1963-10-08 Aircraft Armaments Inc Cartridge actuated device

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3991683A (en) * 1972-02-02 1976-11-16 Diehl Safety device for projectiles
US4046076A (en) * 1975-09-29 1977-09-06 The United States Of America As Represented By The Secretary Of The Navy Impulsive rocket motor safety-arming device
US5753849A (en) * 1996-09-19 1998-05-19 Propellex Corporation Gas-operated timing demolition delay

Also Published As

Publication number Publication date
FR2108202B1 (enrdf_load_stackoverflow) 1973-06-29
DE2141403C3 (de) 1981-07-30
FR2108202A1 (enrdf_load_stackoverflow) 1972-05-19
SE389191B (sv) 1976-10-25
DE2141403A1 (de) 1972-02-24
AU3243771A (en) 1973-02-22
AU448329B2 (en) 1974-05-16
JPS5219039B1 (enrdf_load_stackoverflow) 1977-05-25
DE2141403B2 (de) 1980-07-03
CA948481A (en) 1974-06-04
GB1303146A (enrdf_load_stackoverflow) 1973-01-17

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