Patent US4471664A successfully refreshed from Google Patents.
Patent US4010688A successfully refreshed from Google Patents.
US4010688A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Weapon arrangement
Assignee: Individual
•
Filing: 1972-11-17
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Granted: 1977-03-08
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Expires: 1992-11-17
Abstract
Abstract A rocket boosted and/or sustained round for launching from a firearm, recoilless rifle, mortar or any other type of closed breech launcher and an adjustable, recoiling tripod support for the firearm or other type of closed breech launcher. The tripod supports the launcher during launch of the rocket boosted and/or sustained round. The rocket boosted round, which may be launched, for example, from the conventional M-16 rifle, is aero-gyro stabilized and is provided with a tubular tailpipe that slidingly fits over the end of the firearm barrel. A rocket motor which is ignited during or after launch is coupled to the tailpipe and a warhead having a predetermined ogive configuration is coupled to the rocket motor. An ignition delay means in the round such as a pyrotechnic delay may be provided to allow a predetermined time delay between launch of the round and the ignition of the rocket motor. Other round configurations incorporate a progressive burning rocket motor grain instead of a pyrotechnic delay. The low thrust and negligible back blast from the initial burn of the rocket allows the elimination of the time delay from launch to rocket motor ignition. The round is launched by firing a grenade launcher cartridge in the launcher. The hot, gaseous products of combustion from the cartridge enter the tailpipe of the round and launch the round from the launcher. The ignition delay means if utilized, initiates ignition of the rocket motor after a predetermined time interval has elapsed from launch. In the progressive burn configuration the rocket motor ignites while on the launcher. In order to achieve zone firing, various shrouds may also be provided. For example, to achieve the longest range firing, a streamlined fairing maybe coupled between the warhead and the tailpipe to provide minimum drag configuration for maximum ranging. If shorter ranges are desired one or more drag shrouds may be coupled to the round to decrease the range. For minimum range, a plug is inserted in the tailpipe to prevent ignition of the rocket motor and the round follows a ballistic trajectory after launch. The tripod support is a recoil energy dissipating type of support and is detachably mountable on the launcher, preferably without modification or change to the launcher. During firing the tripod support time to full recoil is considerably greater than the time required for the rocket round to leave the launcher. Thus the rocket round starts free flight without the introduction of launch perturbations. The tripod support is adjustable to provide a plurality of different launch angles for launching of the round from the launcher and is foldable from the firing positions to a folded position providing a minimum package configuration for convenience in transportation thereof.
Inventors
- 👤 Matthew S. Smith
- 👤 Ernest A. Filippi
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 23:03
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/32; F42B10/48; F41; F41A; F41A23/00; F41A23/02; F41A23/12; F41F; F41F3/00; F41F3/04; F41F3/045; F41F7/00; F42B15/00
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
329 words
A rocket boosted warhead round having a center of gravity, a center of pressure and a predetermined non-spinning yawing frequency, for launching from a launcher of the type adapted to fire a blank cartridge and having a barrel portion through which the blank cartridge fires and comprising, in combination: a tubular tailpipe means having an aft end, a forward end, and internal walls defining a tubular passageway, and said tubular passageway at said aft end adapted to slidingly fit onto the end of the launcher barrel; a rocket motor having an aft end coupled to said forward end of said tailpipe, and a forward end, and comprising a solid propellant rocket grain; a warhead coupled to said forward end of said rocket motor, and said warhead having a predetermined ogive external configuration; a forward drag shroud means detachably mountable adjacent said warhead for providing a first predetermined drag configuration having a drag greater than the drag of the round free of said forward drag shroud to decrease the range thereof, and comprising: a base section detachably mountable adjacent said warhead for providing a first drag characteristic greater than the drag characteristic of the round free of said forward drag shroud; and an outer section detachably mountable on said base section for providing a second drag characteristic greater than said first drag characteristic; a delay means in said rocket motor for providing a predetermined delay to full thrust of said rocket motor, whereby firing a blank cartridge in the launcher provided hot gaseous products of combustion for launching the rocket boosted warhead round from the launcher and ignition of the rocket motor, and aero-gyro stabilization means coupled to said aft end of said tubular tailpipe for spinning said round to provide aero-gyro stability, said aero-gyro stability comprising wherein said center of pressure is aft of said center of gravity and the round is spinning at a rate at least one order of magnitude greater than said predetermined non-spinning yawing frequency.
Claim 2
Dependent Claim
329 words
A rocket boosted warhead round having a center of gravity, a center of pressure and a predetermined non-spinning yawing frequency, for launching from a launcher of the type adapted to fire a blank cartridge and having a barrel portion through which the blank cartridge fires and comprising, in combination: a tubular tailpipe means having an aft end, a forward end, and internal walls defining a tubular passageway, and said tubular passageway at said aft end adapted to slidingly fit onto the end of the launcher barrel; a rocket motor having an aft end coupled to said forward end of said tailpipe, and a forward end, and comprising a solid propellant rocket grain; a warhead coupled to said forward end of said rocket motor, and said warhead having a predetermined ogive external configuration; a forward drag shroud means detachably mountable adjacent said warhead for providing a first predetermined drag configuration having a drag greater than the drag of the round free of said forward drag shroud to decrease the range thereof, and comprising: a base section detachably mountable adjacent said warhead for providing a first drag characteristic greater than the drag characteristic of the round free of said forward drag shroud; and an outer section detachably mountable on said base section for providing a second drag characteristic greater than said first drag characteristic; a delay means in said rocket motor for providing a predetermined delay to full thrust of said rocket motor, whereby firing a blank cartridge in the launcher provided hot gaseous products of combustion for launching the rocket boosted warhead round from the launcher and ignition of the rocket motor, and aero-gyro stabilization means coupled to said aft end of said tubular tailpipe for spinning said round to provide aero-gyro stability, said aero-gyro stability comprising wherein said center of pressure is aft of said center of gravity and the round is spinning at a rate at least one order of magnitude greater than said predetermined non-spinning yawing frequency.
Claim 3
Dependent Claim
496 words
A rocket boosted warhead round having a center of gravity, a center of pressure and a predetermined non-spinning yawing frequency, for launching from a launcher of the type adapted to fire a blank cartridge and having a barrel portion through which the blank cartridge fires and comprising, in combination: a tubular tailpipe means having an aft end, a forward end, and internal walls defining a tubular passageway, and said tubular passageway at said aft end adapted to slidingly fit onto the end of the launcher barrel; a rocket motor having an aft end coupled to said forward end of said tailpipe, and a forward end, and comprising a solid propellant rocket grain, and said rocket motor further comprising: a rocket motor casing; said solid propellant grain mounted in said casing; and said solid propellant rocket grain is tubular and comprises external axial walls, a forward end surface, an aft end surface, and internal walls defining an internal axial passageway from said aft end surface to said forward end surface, and said internal walls providing a predetermined surface area to provide said delay means, and said grain burns progressively radially outwardly towards said external axial walls; and a convergent-divergent nozzle having its convergent section coupled to said rocket casing and in hot gas accepting relationship to said rocket motor, and said divergent portion of said convergent-divergent nozzle communicating with said tubular passageway of said tubular tailpipe means; combustion inhibitor means coupled to said forward end surface, said aft end surface and said external axial walls of said solid propellant rocket grain to prevent combustion thereon; a warhead coupled to said forward end of said rocket motor, and said warhead having a predetermined ogive external configuration; and said warhead has walls defining grooves therein adjacent said forward end surface of said solid propellant rocket grain and said grooves communicating with said internal axial passageway thereof, and said warhead further comprising: a plurality of ignition pellets positioned in said grooves of said warhead, whereby the hot gaseous products of combustion from the blank cartridge pass through said nozzle, through said internal exial passageway of said solid propellant rocket grain and into said grooves in said warhead to ignite said ignition pellets and hot products of combustion from said ignition pellets ignite said rocket grain to provide a predetermined low level initial thrust; a delay means in said rocket motor for providing a predetermined delay to full thrust of said rocket motor, whereby firing a blank cartridge in the launcher provides hot gaseous products of combustion for launching the rocket boosted warhead round from the launcher and ignition of the rocket motor, and aero-gyro stabilization means coupled to said aft end of said tubular tailpipe for spinning said round to provide aero-gyro stability, said aero-gyro stability comprising wherein said centr of pressure is aft of said center of gravity and the round is spinning at a rate at least one order of magnitude greater than said predetermined non-spinning yawing frequency.
Claim 4
Dependent Claim
496 words
A rocket boosted warhead round having a center of gravity, a center of pressure and a predetermined non-spinning yawing frequency, for launching from a launcher of the type adapted to fire a blank cartridge and having a barrel portion through which the blank cartridge fires and comprising, in combination: a tubular tailpipe means having an aft end, a forward end, and internal walls defining a tubular passageway, and said tubular passageway at said aft end adapted to slidingly fit onto the end of the launcher barrel; a rocket motor having an aft end coupled to said forward end of said tailpipe, and a forward end, and comprising a solid propellant rocket grain, and said rocket motor further comprising: a rocket motor casing; said solid propellant grain mounted in said casing; and said solid propellant rocket grain is tubular and comprises external axial walls, a forward end surface, an aft end surface, and internal walls defining an internal axial passageway from said aft end surface to said forward end surface, and said internal walls providing a predetermined surface area to provide said delay means, and said grain burns progressively radially outwardly towards said external axial walls; and a convergent-divergent nozzle having its convergent section coupled to said rocket casing and in hot gas accepting relationship to said rocket motor, and said divergent portion of said convergent-divergent nozzle communicating with said tubular passageway of said tubular tailpipe means; combustion inhibitor means coupled to said forward end surface, said aft end surface and said external axial walls of said solid propellant rocket grain to prevent combustion thereon; a warhead coupled to said forward end of said rocket motor, and said warhead having a predetermined ogive external configuration; and said warhead has walls defining grooves therein adjacent said forward end surface of said solid propellant rocket grain and said grooves communicating with said internal axial passageway thereof, and said warhead further comprising: a plurality of ignition pellets positioned in said grooves of said warhead, whereby the hot gaseous products of combustion from the blank cartridge pass through said nozzle, through said internal exial passageway of said solid propellant rocket grain and into said grooves in said warhead to ignite said ignition pellets and hot products of combustion from said ignition pellets ignite said rocket grain to provide a predetermined low level initial thrust; a delay means in said rocket motor for providing a predetermined delay to full thrust of said rocket motor, whereby firing a blank cartridge in the launcher provides hot gaseous products of combustion for launching the rocket boosted warhead round from the launcher and ignition of the rocket motor, and aero-gyro stabilization means coupled to said aft end of said tubular tailpipe for spinning said round to provide aero-gyro stability, said aero-gyro stability comprising wherein said centr of pressure is aft of said center of gravity and the round is spinning at a rate at least one order of magnitude greater than said predetermined non-spinning yawing frequency.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-03-07 | 1980-09-06 | 1981-03-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-03-07 | 1984-09-06 | 1985-03-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-03-07 | 1988-09-06 | 1989-03-08 | $7700.00 | Window Closed / Lapsed |