Patents by Inventor Jerrold H. Arszman

Jerrold H. Arszman has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 7257939
    Abstract: Sliding-Action Magneto-Mechanical Injector Throttling Device (SLAMMIT) provides on-demand, yet accurate, throttling of the mass flow of the fuel and/or oxidizer into the combustion chamber of a vortex injector. At least two SLAMMIT sub-assemblies comprise the SLAMMIT Device and each sub-assembly is integrated into a manifold and is driven to slide in a given direction by a drive block that is internal to the sub-assembly. The drive block is, in turn, actuated by an electromagnet that is external to the SLAMMIT sub-assembly. As the SLAMMIT sub-assemblies slide, flappers inside the sub-assemblies achieve the effective opening size of the injection orifices anywhere between fully open and fully closed.
    Type: Grant
    Filed: August 15, 2003
    Date of Patent: August 21, 2007
    Assignee: United States of America as represented by the Secretary of the Army
    Inventors: Robert S. Michaels, Jerrold H. Arszman
  • Patent number: 5394690
    Abstract: A pressure controlled pintle is employed in combination with a throttling quid, gel, or hybrid engine to provide a constant pressure and variable thrust from a single operating engine. As the propellants are throttled back and the chamber pressure drops, the pintle moves and closes the gap between the pintle and nozzle throat, thereby lowering the throat area and re-establishing the design chamber pressure related to pintle spring tension. By retaining the design pressure over a wide thrust range, the engine efficiency remains at the design value. This eliminates the drop of Isp due to pressure and keeps the cost of the system reasonable because only one engine is required. When a higher thrust is desired, a throttling valve in an injector increases the propellant flow rate, which causes a higher pressure in the combustion chamber. The constant pressure actuator moves the pintle to open the nozzle throat, which reduces the pressure to the design value. The design value may not be optimum.
    Type: Grant
    Filed: September 20, 1993
    Date of Patent: March 7, 1995
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Jerrold H. Arszman, William M. Chew, Barry D. Allan
  • Patent number: 4949918
    Abstract: A rocket that includes a center body with a system center of gravity and rocket motor means mounted relative to the center body and reaction surfaces for causing a resultant force from thrust of the rocket motor means to direct the resultant force through the system center of gravity of the center body.
    Type: Grant
    Filed: August 2, 1989
    Date of Patent: August 21, 1990
    Inventor: Jerrold H. Arszman
  • Patent number: 4672881
    Abstract: A recoilless rocket launcher including a rocket launch tube which is resintly coupled to a support member. Points of contact to the gunner who fires the rocket from a rocket launch tube are to the shoulder and the hand which grips a hand grip which is part of the firing mechanism integrally attached to the support member. The resilient coupling for support member is comprised of a resilient material selected from the group consisting of a butene-diolefin copolymer, rubber, plastic, leather, or fiberous paper. The resilient material disposed in spaced relation adjacent opposite ends of the support member resiliently couples the support member to the launch tube. The nonrigid coupling effects the transfer mechanisms to result in a time offset, extended reaction time, and a reduced total impressed impulse transferable to the gunner prior to rocket exiting the rocket launch tube.
    Type: Grant
    Filed: July 28, 1986
    Date of Patent: June 16, 1987
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Robert E. Betts, Jerrold H. Arszman
  • Patent number: 4519315
    Abstract: A free flight, impulse controlled missile system for directing a warhead to target. The system includes a small diameter weapon which relies on an accurate ballistic delivery to a point and attitude in space and a body fixed sensor for initiating a self forging fragmentation (SFF) warhead above a target such as a tank.
    Type: Grant
    Filed: December 20, 1982
    Date of Patent: May 28, 1985
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: Jerrold H. Arszman
  • Patent number: 4505153
    Abstract: A recoil transducer fixture for determining force responses at high frequies. An impact transducer is mounted in a rigid assembly and is preloaded for operating under compressive loads. The fixture includes a pair of spaced plates having the transducer mounted therebetween and loading bolts cooperating with the plates for preloading the transducer to a predetermined value.
    Type: Grant
    Filed: June 10, 1983
    Date of Patent: March 19, 1985
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Jay S. Lilley, Jerrold H. Arszman
  • Patent number: H684
    Abstract: A rocket for firing from a tube having open ends wherein a rocket motor sed from a projectile is connected to the projectile by a frangible, ported collar, the front of the motor having a vent for allowing combustion products to flow into the tube between the motor and the projectile. The pressure of the combustion products between the motor and the projectile will break the collar to allow the projectile to exit from the tube at a high velocity.
    Type: Grant
    Filed: October 11, 1988
    Date of Patent: October 3, 1989
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Jerrold H. Arszman, Albert R. Maykut, John M. Tate
  • Patent number: H795
    Abstract: A rocket motor that has a main exhaust nozzle area and a secondary exhaust ozzle area with the secondary exhaust nozzle area being closed by burst discs that rupture and open secondary nozzle areas when predetermined temperatures and pressures are reached when propellant is burned inside the rocket motor.
    Type: Grant
    Filed: December 4, 1989
    Date of Patent: July 3, 1990
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Albert R. Maykut, Jerrold H. Arszman