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1757 results about "Missile" patented technology

In military language, a missile, also known as a guided missile, is a guided self-propelled flying weapon usually propelled by a jet engine or rocket motor. This is in contrast to an unguided self-propelled flying munition, referred to as a rocket (although these too can also be guided). Missiles have four system components: targeting or missile guidance, flight system, engine, and warhead. Missiles come in types adapted for different purposes: surface-to-surface and air-to-surface missiles (ballistic, cruise, anti-ship, anti-tank, etc.), surface-to-air missiles (and anti-ballistic), air-to-air missiles, and anti-satellite weapons. Non-self-propelled airborne explosive devices are generally referred to as shells and usually have a shorter range than missiles. In ordinary language the word means an object which can be thrown, shot, or propelled toward a target.

Daytime stellar imager

InactiveUS20070038374A1Small and light systemAvoid star image blurCosmonautic vehiclesDigital data processing detailsDisplay deviceLongitude
An automatic celestial navigation system for navigating both night and day by observation of K-band or H-band infrared light from multiple stars. In a first set of preferred embodiments three relatively large aperture telescopes are rigidly mounted on a movable platform such as a ship or airplane with each telescope being directed at a substantially different portion of sky. Embodiments in this first set tend to be relatively large and heavy, such as about one cubic meter and about 60 pounds. In a second set of preferred embodiments one or more smaller aperture telescopes are pivotably mounted on a movable platform such as a ship, airplane or missile so that the telescope or telescopes can be pivoted to point toward specific regions of the sky. Embodiments of this second set are mechanically more complicated than those of the first set, but are much smaller and lighter and are especially useful for guidance of aircraft and missiles. Telescope optics focus (on to a pixel array of a sensor) H-band or K-band light from one or more stars in the field of view of each telescope. Each system also includes an inclinometer, an accurate timing device and a computer processor having access to catalogued infrared star charts. The processor for each system is programmed with special algorithms to use image data from the infrared sensors, inclination information from the inclinometer, time information from the timing device and the catalogued star charts information to determine positions of the platform. Direction information from two stars is needed for locating the platform with respect to the celestial sphere. The computer is also preferably programmed to use this celestial position information to calculate latitude and longitude which may be displayed on a display device such as a monitor or used by a guidance control system. These embodiments are jam proof and insensitive to radio frequency interference. These systems provide efficient alternatives to GPS when GPS is unavailable and can be used for periodic augmentation of inertial navigation systems.
Owner:TREX ENTERPRISES CORP

Laser beam source for a directional infrared countermeasures (DIRCM) weapon system

A laser beam source and an operating method thereof is provided for a directional infrared countermeasures (DIRCM) weapon system for defensively countering guided missiles having infrared seeking heads, by directing an infrared laser beam at the guided missile so as to disorient, saturate, or irreversibly destroy the IR detectors and circuitry arranged in the target seeking head. The power, pulse frequency and spectral composition of the laser beam is adjustable and selectable as required to adapt to any particular defensive engagement. To achieve this, the laser beam source comprises an Nd:YAG pumping laser and an optical parametric oscillator including an oscillator crystal arranged in a resonator cavity. The crystal includes a plurality of different periodically polarized crystal zones having different lattice constants. The adjacent zones can be grouped together into selectable crystal zone groups. The beam cross-section of the pumping laser beam corresponds to the cross-section of a single crystal zone or of a crystal zone group encompassing plural zones. The crystal is arranged on a slide table that is slidably displaceable by a servomotor, to move a selected crystal zone or group into the path of the pumping laser beam. Thereby the wavelength components and the relative intensities thereof of the output laser beam can easily be selectively adjusted.
Owner:EADS DEUT GMBH

Daytime stellar imager for attitude determination

InactiveUS20060085130A1Small and light systemAvoid star image blurInstruments for road network navigationPosition fixationJet aeroplaneGuidance control
An automatic celestial navigation system for navigating both night and day by observation of K-band or H-band infrared light from multiple stars. In a first set of preferred embodiments three relatively large aperture telescopes are rigidly mounted on a movable platform such as a ship or airplane with each telescope being directed at a substantially different portion of sky. Embodiments in this first set tend to be relatively large and heavy, such as about one cubic meter and about 60 pounds. In a second set of preferred embodiments one or more smaller aperture telescopes are pivotably mounted on a movable platform such as a ship, airplane or missile so that the telescope or telescopes can be pivoted to point toward specific regions of the sky. Embodiments of this second set are mechanically more complicated than those of the first set, but are much smaller and lighter and are especially useful for guidance of aircraft and missiles. Telescope optics focus (on to a pixel array of a sensor) H-band or K-band light from one or more stars in the field of view of each telescope. Each system also includes a GPS sensor and a computer processor having access to catalogued infrared star charts. The processor for each system is programmed with special algorithms to use image data from the infrared sensors, position and timing information from the GPS sensor, and the catalogued star charts information to determine orientation (attitude) of the platform. Direction information from two stars is needed for locating the platform with respect to the celestial sphere. The computer is also preferably programmed to calculate further information which may be used by a guidance control system. These systems provide efficient alternatives to inertial navigation systems when such systems are too expensive and can be used for periodic augmentation and calibration of inertial navigation systems.
Owner:TREX ENTERPRISES CORP

Multilayer armor system for defending against missile-borne and stationary shaped charges

An armor system for defeating rocket propelled grenade-type missiles and/or high velocity jets created by shaped charges directed at a vehicle includes a grid layer such as a net and/or an array of slats or bars (“RPG”) spaced from an outer surface of the vehicle by support members. The grid layer has a characteristic mesh size or bar/slat spacing to disrupt the missile firing mechanism. The system also has a shaped layer having a plurality of tapered members formed from a fiber-reinforced material, the tapered members positioned between the grid layer and the vehicle outer surface and having respective apex ends proximate the distant the grid layer and base ends, the tapered members defining with adjacent tapered members a plurality of depressions opening in a direction to receive an incoming conical portion of an unexploded RPG-type missile, or a jet emanating from an exploded RPG or other anti-armor device, and a layer of fiber-reinforced material abutting the base ends of the tapered members. The system may further include reactive elements disposed on surfaces of the tapered members defining the depressions to deflect impinging jets. The system may still further include one or more metal armor layers and one or more additional fiber-reinforced material layers disposed between the shaped fiber-reinforced material layer and the vehicle surface.
Owner:FORCE PROTECTION TECH

Method for controlling attack angle and attack time of multiple missiles

The invention provides a method for controlling the attack angle and the attack time of multiple missiles. With the adoption of the method, the attack angle and the attack time of the multiple missiles can be accurately controlled. The method comprises the following steps: arbitrarily selecting one missile from multiple missiles to serve as a master missile; constructing a virtual sphere by taking a target as a sphere center and taking distance between the master missile and the target as a radius; defining the residual missiles as slave missiles; selecting virtual points for each slave missile on the surface of the virtual sphere, wherein direction of a connection line of each virtual point and the target is a preset ideal attack angle corresponding to the slave missile; and by controlling a slave missile movement locus, approaching and tracking a virtual point locus, so that control of the attack angle and the attack time of multiple missiles is realized. The method for controlling the attack angle and the attack time of the multiple missiles is realized by approaching and tracking the virtual point corresponding to the slave missile by the slave missile, so that the attack angle and the attack time of the slave missiles can be controlled without appointing ideal attack time for each slave missile in advance.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY

Sight line based finite time convergence active defense guidance control method

The invention provides a sight line based finite time convergence active defense guidance control method, relates to a guidance control method, in particular to an active defense guidance control method, and aims at solving the problem that a defensive missile is limited in overload capacity. The sight line based finite time convergence active defense guidance control method comprises the steps of firstly modeling relative motions of a target, the defensive missile and an intercept missile, adopting a sight line guidance mode to design a guidance rule for the defensive missile, then adopting a nonsingular terminal sliding mode to control the designed guidance rule, respectively defining sliding mode variables (shown in the description) of a longitudinal plane and a lateral plane, performing derivation on the sliding mode variables, substituting relative motion equations of the target, the defensive missile and the intercept missile into the variables and obtaining the guidance rule (shown in the description) of the longitudinal plane and the guidance rule (shown in the description) of the lateral plane through compilation, and controlling the missiles according to the guidance rules. By means of the sight line based finite time convergence active defense guidance control method, overload needed by the defensive missile can be effectively reduced. The sight line based finite time convergence active defense guidance control method is suitable for active defense guidance control.
Owner:HARBIN INST OF TECH

Composite frequency-selective-surface invisible radome

The invention discloses a composite frequency-selective-surface invisible radome and relates to the technical field of microwaves. The composite frequency-selective-surface invisible radome solves the problems that an existing radome is streamline in shape and cannot be spread to a plane, random preparation of an FFS (frequency selective surface) on the radome is difficult in process implementation, and FFS passband transmittance is low as incident angles of electromagnetic waves on the FFS are large. The composite frequency-selective-surface invisible radome is prepared by embedding an inner Y-ring-unit frequency-selective-surface conical cover into an outer radome by the aid of special laminating equipment. The composite frequency-selective-surface invisible radome has a band-pass filtering characteristic within a specific radar frequency range and good passband characteristics, is capable of efficiently transmitting through the working frequency range electromagnetic waves, reflects the out-of-band detection electromagnetic waves to a vast space according to the radome shape and reduces backward radar cross section so that invisibility of the radome is achieved. The composite frequency-selective-surface invisible radome can be used for invisibility of radomes of guided missiles and airplanes.
Owner:CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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