Having Rocket-firing Means Patents (Class 89/1.813)
  • Patent number: 8814562
    Abstract: An ignition system and method of igniting the ignition system includes a main catalyst section in a staged relationship with a pilot-catalyst section to stage a decomposition though the pilot-catalyst section which preheats the main catalyst section.
    Type: Grant
    Filed: June 2, 2008
    Date of Patent: August 26, 2014
    Assignee: Aerojet Rocketdyne of DE, Inc.
    Inventors: Jeff Jensen, Scott Claflin
  • Publication number: 20130186263
    Abstract: The present invention provides a device for shoulder-launching operation. Stability and convenience on operation are enhanced. Furthermore, production is improved and maintenance difficulty is reduced.
    Type: Application
    Filed: April 3, 2012
    Publication date: July 25, 2013
    Applicant: Chung-Shan Institute of Science and Technology, Armaments, Bureau, Ministry of National Defense
    Inventors: Tsai-Chi Yeh, Yu-Chia Wang
  • Publication number: 20130152773
    Abstract: A device for safe firing is provided. The device is used in a tube of a rocket, like a shoulder-launched anti-armor rocket. The present invention has simple structure and small size. A few safety designs are used in the present invention to improve safety of the rocket tube during transportation. Those designs also prevent the rocket from misfire owing to lack of training.
    Type: Application
    Filed: April 3, 2012
    Publication date: June 20, 2013
    Applicant: Chung-Shan Institute of Science and Technology Armaments, Bureau, Ministry of National Defence
    Inventors: Tsai-Chi Yeh, Yu-Chia Wang
  • Patent number: 8439301
    Abstract: An unmanned aerial vehicle (UAV) system provides for UAV deployment and remote, unattended operation with reduced logistics requirements. The system includes a launcher that can include one or more launch tubes, each launch tube configured to house a UAV in a canister and one or more gas generators operatively connected to each canister and configured to push the UAV out of the launch tube by releasing gas into the canister. A controller for activating the gas generators can sequentially, and with a predetermined time delay, expel the UAV with a desired velocity and acceleration. The system further includes a UAV recovery device, a power supply, a security subsystem, a command and control subsystem and a communications subsystem. Command, control and communications can be provided between a remote station and the UAV.
    Type: Grant
    Filed: July 18, 2012
    Date of Patent: May 14, 2013
    Assignee: Systems Engineering Associates Corporation
    Inventors: David A. Lussier, Andrew J. Delisle, Philip M. Torrence
  • Publication number: 20120036987
    Abstract: The present invention relates to launching system, more particularly relates to mobile launching system for missiles. The mobile missile launch system comprising a vehicle (14) having a chassis structure adapted to carry the launch system; a mounting frame (16) comprising predetermined truss framework mounted onto the chassis structure; plurality of sliding mechanisms mounted at rear end of the mounting frame (16); plurality of canisters (43) mounted onto said beam (22) and plurality of missiles (11) ensconced within the canisters (43); plurality of containers (42) enclosing said canisters (43) and are connected to the saddles (32, 34) for linear movement; plurality of resting units (27) abutting to rear end of the canisters (43) and are adapted to move linearly to transfer reaction forces from said missiles (11) to ground.
    Type: Application
    Filed: January 11, 2010
    Publication date: February 16, 2012
    Applicant: Director General, Deffence Research & Development Organisation
    Inventors: Siddalingappa Guruprasad, Shreedhar Aravind Katti, Alasani Prasad Goud, Vikas Narayan Waghmare, Sanjay Kumar, Atul Gupta, Ravindra Sudhakar Khire, Tushar Kant Santosh, Bimal Gautam, Paras Ram
  • Publication number: 20100089227
    Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.
    Type: Application
    Filed: April 28, 2009
    Publication date: April 15, 2010
    Applicant: Lockheed Martin Corporation
    Inventor: George Raymond Root, JR.
  • Patent number: 7647870
    Abstract: An electromagnetic launch system including an electrothermal launcher, an inductive power supply (IPS), including a DC source (Vb) and a storage inductor (L), and an opening switch (OS), wherein at least a portion of at least one of the IPS and the OS is integrated in a projectile.
    Type: Grant
    Filed: August 17, 2006
    Date of Patent: January 19, 2010
    Assignee: Soreq NRC
    Inventors: Alex Pokryvailo, Shlomo Wald
  • Patent number: 7467761
    Abstract: A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction
    Type: Grant
    Filed: May 13, 2005
    Date of Patent: December 23, 2008
    Assignee: Rafael-Armament Development Authority Ltd
    Inventors: Oded Yehezkeli, Irad Kunreich
  • Patent number: 7012233
    Abstract: A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed in the body. The control unit generates signals controlling an actuation of the attitude control mechanisms and the multi-pulse motor to initiate a follow-on burn of the multi-pulse motor to effect a maneuver directed by the actuation of the attitude control mechanisms. The method includes conserving a second burn of a dual pulse motor until target acquisition; acquiring a target; actuating a attitude control mechanism for the flight vehicle to alter the flight vehicle's heading; and initiating the second burn.
    Type: Grant
    Filed: July 26, 2002
    Date of Patent: March 14, 2006
    Assignee: Lockheed Martin Corporation
    Inventors: Charles C. Brown, Philip T. Beyer
  • Publication number: 20050204910
    Abstract: A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.
    Type: Application
    Filed: November 21, 2002
    Publication date: September 22, 2005
    Inventor: Nir Padan
  • Patent number: 6679155
    Abstract: A launcher (10) is provided having a separation unit (15) and a launch tube (16) in fluid communication with the separation unit (15). The separation unit (15) has a pressure sensing chamber (23) for sensing the pressure within the separation unit (15), a separation chamber (24) in fluid communication with the pressure sensing chamber (23), and a combustion chamber (26) in fluid communication with the separation chamber (24). The combustion chamber (26) is in fluid communication with the launch tube (16) through opening (28). The rocket launcher (10) also includes a hydrogen separation circuit (21) and an ignition circuit (22). The hydrogen separation circuit (21) includes a battery pack (44) electrically coupled to a fuel cell (45) which when powered separates water into hydrogen gas and oxygen gas. The ignition circuit (22) includes a piezoelectric spark generator (61) for igniting the hydrogen gas produced by the fuel cell and contained within the combustion.
    Type: Grant
    Filed: October 24, 2002
    Date of Patent: January 20, 2004
    Assignee: Johnson Research & Development Co., Inc.
    Inventors: Jeffery C. Yaschur, John T. Applewhite, Lonnie G. Johnson
  • Patent number: 6655254
    Abstract: A lightweight multiple missile launch assembly (10) adapted to carry newer heavier Maverick missiles (AGM-65D, E, F, G or K). The invention is illustrated with a BRU-33, 55 or 57 bomb rack (12) adapted to carry two LAU-117 missile launchers (24, 26). The missile launchers (24, 26) are secured to the bomb rack (12) with a suspension unit (20, 22) of unique and novel design. The suspension units (20, 22) allow for releasable engagement of the missile launchers (24, 26). This allows for different missile packages to be deployed in the field.
    Type: Grant
    Filed: July 11, 2001
    Date of Patent: December 2, 2003
    Assignee: Raytheon Company
    Inventor: Carl P. Nicodemus
  • Patent number: 6321477
    Abstract: A mounting system for a cylindrical object such as a spotting rifle is provided. First and second U-shaped brackets are coupled to a base such as a launching device. Each U-shaped bracket has first and second legs extending from a common base. The two U-shaped brackets are oriented such that the first and second legs of one U-shaped bracket are perpendicular to the first and second legs of the other U-shaped bracket. Each U-shaped bracket slidably receives a sleeve between its first and second legs. Each sleeve is attachable to the bracket's common base such that the position of the sleeve relative to the bracket's common base is adjustable. A locking mechanism is provided with each U-shaped bracket/sleeve combination to lock the sleeve laterally between the first and second legs of the U-shaped bracket. The two sleeves are coaxially aligned.
    Type: Grant
    Filed: March 31, 1999
    Date of Patent: November 27, 2001
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventor: Fred W. Watson Jr.
  • Patent number: RE47637
    Abstract: A smart laser pointer is disclosed in this application that includes a laser coupled to a processor that can disable the laser from operating for a period of time (T) based on a disabling trigger. The smart laser pointer may also include an optical receiver coupled to the processor that detects received laser signals that are emitted from the laser after they are reflected off of a target and a memory storing position information threshold limits. The processor calculates measured position information based on the received laser signals detected by the optical receiver and compares them to the position information threshold limits. A disabling trigger occurs when the position information exceeds the position information threshold limits. The position information and threshold limits may include a distance or a velocity.
    Type: Grant
    Filed: October 9, 2017
    Date of Patent: October 8, 2019
    Inventor: Tyson York Winarski