Bizarre Patents
Safety System For Remove a Rider From a Vehicle by Deploying a Parachute
Methods and apparatus for reducing the velocity of a rider in or on an open cockpit vehicle when the rider is thrown from the vehicle.
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| Number | Title | Issue Date |
| 7549375 | Temperature responsive safety devices for munitions The invention comprises devices for mitigating the explosive reaction of a munition when it is subject to an external thermal hazard threat. The devices are based on the use of shape memory alloys. In one arrangement there is device which consists of a connector tha... | 06/23/2009 |
| 7377690 | High trigger temperature lithium intermetallic thermal sensors A non-electrical intermetallic thermal sensor with trigger temperatures in a range of 360° F. to about 430° F., comprising, a hermetically sealed housing including at least one layer of electronegative metal disposed in the housing, wherein the electronegative met... | 05/27/2008 |
| 7331292 | Venting system for explosive warheads An ordnance venting system has one or more adapters that separate the warhead section from other sections of a rocket, or submunition compartments within the warhead itself. The adapters structurally fail at given temperatures and pressures to reduce the danger of e... | 02/19/2008 |
| 7328571 | Semi-axisymmetric scramjet flowpath with conformal nozzle In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launchin... | 02/12/2008 |
| 7314006 | Nonlethal canister tank round A nonlethal canister tank round comprising a cartridge having a combustible case and containing propellant; a canister projectile attached to the cartridge, the canister projectile being generally cylindrical, comprising high density polyurethane foam and including ... | 01/01/2008 |
| 7278612 | Swaged cable deployment in space A cable restraint/deployment mechanism is disclosed for deploying an object in space from a spacecraft. To deploy the object, the cable restraint/deployment mechanism cuts a cable attached to the spacecraft and the object. For example, a spacecraft may include a sol... | 10/09/2007 |
| 7262394 | Mortar shell ring tail and associated method There is provided a ring tail for a ballistic projectile and an associated method that facilitate maneuverability of the ballistic projectile. The ring tail comprises a ring member having a generally cylindrical wall and at least one rod joined to an aft section of ... | 08/28/2007 |
| 7254936 | Simple solid propellant rocket engine and super-staged rocket A solid propellant rocket engine includes: a propellant formed into a predetermined shape having a combustion cavity and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand the hot, high-pressure gas in... | 08/14/2007 |
| 7252270 | System and method for launching a missile from a flying aircraft System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system including a missile support coupled with the missile, and a foldable control-surface mec... | 08/07/2007 |
| 7237750 | Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability wh... | 07/03/2007 |
| 7188558 | Pyromechanical separating element The invention relates to a pyromechanical separating element having a hermetically sealed pyrotechnic pressure element (2), which is installed in a housing (1) and has a gas-forming pyrotechnic charge, and a detachable latching pin (5) which is ... | 03/13/2007 |
| 7185848 | Mass transfer system for stabilizing an airship and other vehicles subject to pitch and roll moments The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the ... | 03/06/2007 |
| 7156049 | Release mechanism to interact with biota, in particular fauna that may outgrow available habitat A device for interacting with biota either on a pre-specified schedule or via actuation by remote signal. Preferably, the biota are fauna and more particularly fish. In selected embodiments, it comprises frangible packaging enclosing means for timing interaction, at... | 01/02/2007 |
| 7146704 | Method for coupling connectors using an anti-rotation device The present invention is generally directed to an anti-rotation device for mating connectors, and methods of using same. In one illustrative embodiment, the method comprises coupling a first connector to a second connector, removing at least a portion of the second ... | 12/12/2006 |
| 7114683 | Device and method for a spacecraft The invention presented here relates to a device in a spacecraft comprising a carrier rocket, a satellite and a detachable adapter (4) for connecting a satellite to the carrier rocket, where the adapter (4) comprises a wall structure (14, 15) fo... | 10/03/2006 |
| 7082878 | Missile with multiple nosecones A missile includes a payload assembly that has a pair of nosecones. The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separat... | 08/01/2006 |
| 7069553 | Universal deployment tool A system and method for a deployment tool is provided. The deployment tool in one aspect assembles and deploys software components generated by any predetermined standard compliant application tools. The system and method in one aspect isolates each application serv... | 06/27/2006 |
| 7066369 | Propellant container for setting tools and an internal combustion driven setting tool The present invention relates to a propellant container (2) for an internal combustion operated setting tool (10) having a housing (21) and a housing internal space (22) for receiving a propellant (23). A portable electrical power ... | 06/27/2006 |
| 7051511 | Method and arrangement for preventing encased explosives being caused to explode by an external fire This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explos... | 05/30/2006 |
| 7040210 | Apparatus and method for restraining and releasing a control surface An apparatus includes a restraint for restraining a first control surface in a stowed configuration and a severing mechanism for parting the restraint to allow the first control surface to move into an operational configuration. A vehicle includes a body, a first co... | 05/09/2006 |
| 7000377 | Super-staged and continuously staged rocket A super-staged rocket includes at least approximately 50 rocket engines, where the engines are distributed according to at least one of: at least five multi-engine stages connected in series, each stage including at least ten engines connected in parallel; and at le... | 02/21/2006 |
| 6978968 | Deployable flare for aerodynamically stabilizing a projectile The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare d... | 12/27/2005 |
| 6959893 | Light fighter lethality seeker projectile A projectile comprises an imaging seeker at a front of the projectile; a front warhead behind the imaging seeker; a power supply; an electronics unit connected to the power supply and comprising a microprocessor circuit board, a voltage regulator circuit board, an i... | 11/01/2005 |
| 6933965 | Panoramic aerial imaging device An imaging device that gives a ground based user immediate access to a detailed aerial photograph of the entire area for a given radius about his present position. The device can be launched into the air, and rotates in a predictable pattern to scan an imager over e... | 08/23/2005 |
| 6931994 | Tandem warhead A tandem warhead for destroying a target, the tandem warhead including a kinetic energy rod section with a plurality of lengthy individual projectiles, a blast fragmentation section deployable proximate the target, and a guidance subsystem for deploying the projecti... | 08/23/2005 |
| 6928931 | Release mechanism in missile A release mechanism between a projectile and a rocket motor in a missile. The projectile releases from the rocket motor during flight of the missile when the rocket motor burns out and aerodynamic retardation commences. The front end of the rocket motor comprises a ... | 08/16/2005 |
| 6857371 | Two-payload decoy device The two-payload decoy device has a square outer case, containing a manifold/delay body assembly, a round payload assembly, and a square payload assembly. The square outer case is closed with an end cap. The manifold/delay body assembly is attached to the round paylo... | 02/22/2005 |
| 6783095 | Deployable flare for aerodynamically stabilizing a projectile The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare d... | 08/31/2004 |
| 6758142 | Pneumatic stage separation system for two stage launch vehicle A separating connector assembly system for a two-stage reusable launch vehicle. The system includes a plurality of separating connector assemblies each having a gas pressurizable first chamber within a first stage of the launch vehicle and a second chamber within a ... | 07/06/2004 |
| 6745978 | Aerodynamic stabilization of a projectile The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare d... | 06/08/2004 |
| 6679177 | Resettable and redundant NEA-initiated hold-down and release mechanism for a flight termination system A hold-down and release apparatus for a flight termination system having a terminal portion for holding-down and releasing a structural object which has an arrangement for attaching to the flight termination system. The hold-down and release apparatus inc... | 01/20/2004 |
| 6640720 | Translation and locking mechanism in missile A translation and locking mechanism for a projectile that is lying in a standby position within a rocket motor in a missile, wherein the projectile is translated with respect to the rocket motor by means of a pyrotechnic charge before the rocket motor is ... | 11/04/2003 |
| 6568330 | Modular missile and method of assembly A modular missile assembly includes a pair of modules which are separately transported and handled until just prior to firing, when they are coupled together. A forward payload-carrying module includes a forward canister which encloses a missile payload s... | 05/27/2003 |
| 6557475 | Separation system for a booster payload fairing The invention is a separation system for releasably securing first and second structural members together along mating edges thereof. For example, the segments of a launch vehicle faring used to protect the payload until orbit is reached. In detail, the i... | 05/06/2003 |
| 6454214 | Device and method for connecting two parts of a craft A device for releasably connecting a first part and a second part of a spacecraft. A clamp is operable to releasably connect the first part and the second part of the spacecraft and to store a prestress strain energy releaseable upon separation of the fir... | 09/24/2002 |
| 6439122 | Separation system for missile payload fairings In detail, the system includes at least one first pulley mounted on the first structural member and at least one-second pulley mounted on the second structural member. A cable is attached by one end to the first structural member and wound about the first... | 08/27/2002 |
| 6357699 | Device for controlled release of tension A tension-relieving apparatus for reducing a level of tension in a structure. The tension-relieving apparatus includes a housing, a piston, a spacer member and a heat source. The housing has a wall member that defines a piston cavity. A rod aperture is fo... | 03/19/2002 |
| 6338242 | Vented MK 66 rocket motor tube with a thermoplastic warhead adapter An ordnance venting system has an ordnance device having a casing with a vent opening, a dome plug fitted into the formed vent opening and an adapter fitted over the dome plug on the outside of the casing. The adapter connects sufficiently to the casing t... | 01/15/2002 |
| 6321656 | Thermally actuated release mechanism A container subject to damage through inadvertent overheating and pressure build up such as a rocket casing containing a propellant which can be subjected to damage or inadvertent firing when the ignition temperature is achieved inadvertently includes a t... | 11/27/2001 |
| 6298786 | Frangible access panel system A frangible access panel separation system for separating an access panel from a host structure is disclosed. In one embodiment, the system includes first and second doublers for initially interconnecting the first and second sections, an expandable explo... | 10/09/2001 |