36results about "Time fuzes" patented technology

An inertial mechanism including an activating mechanism and a time delay mechanism coupled to the activating mechanism for delaying a time in which the activating mechanism is activated after a predetermined acceleration profile occurs. Where a coupling of the time delay mechanism with the activating mechanism to activate the activating mechanism initially moves away from the coupling when the predetermined acceleration profile occurs before the coupling occurs after a time delay.

The present invention describes a safe-and-arm device, mechanism or assembly (160) for a projectile (100,102) equipped with a second-stage propellant (124). The second-stage propellant (124) is ignited after the projectile has been ejected out from a launcher barrel. A lockpin (190), being urged by a spring (194), is responsive to ignition of the second-stage propellant; after the lockpin (190) and spring (194) sense and respond to the second propulsion, an unbalanced rotor (164) forming part of the safe-and-arm device or assembly (160), is released to rotate from a “safe” state to an “armed” state, as the projectile continues traveling along its trajectory to a target. In one embodiment, the projectile is configured with a 40 mm cartridge containing a first propellant (122). An impact sensor may trigger an electric detonator or a point detonator may trigger a stab detonator to set off explosives disposed in the projectile.

The technology subject of the present application generally concerns an aerial munition unit comprising a proximity fuze functionality and an impact fuze functionality, selectable by a crew member of an aircraft bearing the munition, after the aircraft has taken off and prior to munition release, to render active or operable the proximity fuze functionality or the impact fuze functionality.

A dual-safe fuze incorporating electrical and / or mechanical fuzing for unmanned aerial system (UAS) drone applications includes an electrical power source configured to initiate a munition, and circuitry. The electrical and mechanical circuitry is positioned between the electrical power source and the munition for controlling the initiation of the munition via the electrical power source. The circuitry is configured to initiate the munition from an unmanned aerial vehicle (UAV). The circuitry positioned between the electrical power source and the munition includes a nose-proximity fuze circuit, a body-proximity fuze circuit, a shear lanyard safety circuit, and combinations thereof.

The invention provides a delayed detonation functional structure of a shaped charge and blasting series warhead. The delayed detonation functional structure comprises a cylindrical detonation propagation channel arranged between shaped charge and blasting charge; the explosion propagation channel is arranged in the shell, and the explosion suppression layer and the multi-stage explosion propagation sequence are arranged in the explosion propagation channel; the booster sequence sequentially comprises a low-speed delay explosive, a first-stage explosive assistant, an insensitive booster explosive, a second-stage explosive assistant and an initiating explosive. And the explosion-proof layer is used for ensuring that the low-speed delay powder is kept in a stable working state. In the working process, the low-speed delay explosive achieves the delay effect, when energy is spread to the tail, the insensitive booster explosive is detonated through the assistant explosive, detonation is generated, then the initiating explosive is detonated after the energy of the assistant explosive is amplified, finally the blasting charge is detonated through the initiating explosive, and after it is ensured that energy-gathered jet flow is completely formed, the blasting charge is triggered to be detonated. Therefore, the expected delayed blasting effect is achieved. The delay stability is guaranteed through the explosion-proof layer, and combustion delay, detonation conversion and pressure compensation are innovatively integrated into a single system.

A drone defense ammunition, such as rifle ammunition (e.g., with a caliber of up to 20 mm) or shotgun ammunition (e.g., up to caliber 4), may include projectiles. The ammunition may release the projectiles loosely as a result of an activation occurring with a time delay to firing of the drone defense ammunition.

The present invention allows preemptive prevention of accidents of unintentional fuse detonation by equipping a rotor, which allows a fuse to be ignited by aligning detonation and connection pipes as the rotor rotates, with a double safety pin structure in which the restraint of the rotor is released only under bullet firing conditions that give rise to strong backward inertial force and rotational force. Additionally, unintentional harm to friendly forces area can be prevented by precisely adjusting loading time and increasing fuse safety distance via detent and gears and levers that adjust the rotor rotation time.

The utility model discloses a multi-insurance timing device which comprises a shell, a cavity is arranged in the shell, a pushing mechanism is arranged in the cavity, a sliding assembly is further arranged in the shell, a sliding way used for sliding of the sliding assembly is arranged in the shell, two channels are arranged in the shell, the cavity and the interior of the sliding way are communicated through the two channels, and the two channels are the first channel and the second channel respectively. An electric actuator which is connected with the pushing mechanism and limits the sliding assembly to move in the sliding way is arranged in the first channel, a detonator is arranged on the sliding assembly, an electric ignition tube which is connected with the pushing mechanism and matched with the detonator is arranged in the second channel, a power source is arranged on the shell, the pushing mechanism is connected with the power source, and a push rod is arranged on the pushing mechanism. An electronic component is arranged on the shell, a limiting piece for limiting the push rod of the pushing mechanism to be electrically communicated with the electronic component is arranged on the shell, and the pushing time of the pushing mechanism is controlled by the clock mechanism. The electric connection of the push rod triggering device is accurately controlled by the clock mechanism, multiple insurance guarantees are arranged, and the operation safety is improved.

A system for deploying an electronic warfare package includes a projectile having an electronics payload for deployment in an environment. The electronics payload includes a proximity sensor and a processor and components that allow it to monitor an environment and detect objects nearby the projectile, and initiate electronic warfare functions based on a detected proximity. The electronic payload also includes components that allow it to emit electronic signals for communication and / or disruption that can interfere with or otherwise affect local communications and computing devices.

A payload re-positioning system for a maritime vehicle that includes a hull having a first portion and a second portion. The maritime vehicle includes a payload disposed within the second portion. The first portion may include an impact zone and a compressible zone. The impact zone is arranged to engage a target external to the maritime vehicle. The compressible zone is arranged to reduce the initial length of the first portion to a compressed length in response to the impact zone engaging the target external, thereby reducing a distance between the payload and the impact zone.

Electronic cartridge actuating device with a cylindrical charge system for the activation by electric discharge of disposable electronic cartridges with different end functions, e.g. fire extinguishing cartridges, detonating cartridges without projection, chemical compound projection cartridges, etc. comprising an inner housing (1) with a charging system, a magnetic clamping system (2) at its base, terminals (3) for connection to the cartridge (10), a safety mechanism (4), a button (5) or push-activation system and an integrated battery (6).

The present invention belongs to the technical field of rain enhancement and hail suppression rockets, and specifically relates to a rain enhancement and hail suppression rocket dispenser. It includes a sealing cover, a wire catalysis component, a dispensing chamber, a catalyst igniter component, and a submunition component; a plurality of wire catalysis components are embedded in the inner wall of the dispensing chamber at intervals along the axis, and a plurality of stepped through holes are circumferentially and evenly arranged on the side wall of the dispensing chamber between adjacent wire catalysis components. The through hole with a larger diameter of the stepped through hole is located on the outer surface side of the dispensing chamber, and the submunition component is arranged in the through hole with a larger diameter of the stepped through hole; a catalyst igniter component is arranged at the bottom of the dispensing chamber, a sealing cover is arranged at the top, a timing controller is arranged in the sealing cover, and a wire is arranged in the dispensing chamber. The dispenser of the present invention has a simple structure assembly, non-interfering ignition circuits, and a uniform and consistent dispensing state.

A launcher and projectile system include at least one permanent magnet disposed on or within the launcher for charging a wire coil of the projectile to energize an initiator of the projectile, thereafter having a housing of the projectile rupture, disintegrate, separate or otherwise have an opening created therein after launch to release a payload. In another embodiment, an accessory for a launcher and projectile is provided, the accessory comprising a permanent magnet for charging a projectile that is launched by the launcher.

The technology subject of the present application generally concerns an aerial munition unit comprising a proximity fuze functionality and an impact fuze functionality, selectable by a crew member of an aircraft bearing the munition, after the aircraft has taken off and prior to munition release, to render active or operable the proximity fuze functionality or the impact fuze functionality.

This invention introduces a military-grade initiation device designed to enhance explosive ordnance deployment, individually or in conjunction with unmanned aerial vehicles (UAVs) for precision operations. The device's innovation lies in its compact, lightweight structure and the inclusion of an accelerometer, which triggers detonation based on specific impact or vibration criteria. Ensuring durability and reliability, its casing provides protection against environmental challenges. Standardized connections for both detonation and communication support adaptability across varied military operations. Initiator features include a dual-function power button for operational testing, an LED status indicator, enhancing safety and versatility. Additional components like a signal booster to expand operational range, and a controller interface for remote operation management. This technical focus presents a solution poised to meet the diverse and challenging demands of contemporary military engagements and controlled demolition scenarios.

The utility model discloses a self-calibration timing circuit, a timing device and an ignition device, and relates to the field of timing, the self-calibration timing circuit comprises a calibration circuit, an output end is connected with a clock end of a calibrated circuit, and the calibration circuit is used for outputting a clock signal to the calibrated circuit; the output end of the calibrated circuit is connected with the input end of the ignition device, and the calibrated circuit is used for timing based on the clock signal; and the ignition device is used for outputting detonation when the ignition signal is received through the input end of the ignition device at the end of timing. The calibration circuit and the calibrated circuit are separately arranged, the calibration circuit does not participate in actual control, the high overload circuit is prevented from influencing the timing accuracy, the calibration circuit outputs the time to the calibrated circuit, the ignition device is further controlled, and the timing can be more accurate.

An inertial mechanism including a member rotatable about an axis between activatable and activated positions, in the activatable position a first center of mass of the member is offset from the axis in a direction perpendicular to a direction of acceleration, the member having a surface; and another member rotatable about an axis between rest and activated positions, the rest position being where the second member cannot be moved into its activated position from an acceleration event, the other member also having a surface, the surfaces engage with each other when the member moves to its activated position to move the other member from its rest position to its activatable position, which is also where a center of mass of the other member is offset from its axis in the direction perpendicular to the direction of the acceleration.

A nonlethal projectile includes a debilitating material for immobilizing a target. The projectile is capable of self-separating or otherwise opening after launch by a launcher to release the debilitating material prior to impact with a target. The launcher is capable of initiating separation of the projectile. Opening may also be accomplished by a control circuit with a radio-frequency identification (RFID), where an RFID tag in the projectile causes the projectile to open at a user-specified distance from the launcher or by the force of launch on the projectile. A magazine may holds a plurality of projectiles and the various projectiles of the magazine may be configured to open at different distances and / or times after launch. The launcher may include a trigger and / or a safety switch to prevent the projectile from becoming armed until a certain parameter is met. The debilitating material may also be released through pores in the projectile.

A bomb fuze initiator equipped with a cap configured to open after bomb release, a device for detecting bomb release, a device for determining bomb speed, an integrated proximity sensor and a fuze connector intended to connect the fuze initiator to a bomb fuze, the integrated proximity sensor comprising: a transceiver of electromagnetic waves comprising an HF antenna and an HF circuit or comprising an IR source and a photodetector, and a transmission link configured to transmit the signal delivered by the transceiver of electromagnetic waves.

The present application relates to the technical field of aerial bomb fuze, especially to a mechanical time aerial bomb fuze with universal ignition function. The aerial bomb fuze currently used has problems of large timing error, insufficient ignition reliability and safety. The present application designs an anemometer and an isokinetic speed regulator, and through the regulation and control of the two, effectively increases the timing accuracy and safety. Considering that the M904 fuze adopts an impact ignition mechanism, if the angle of the aerial bomb when landing is not within the range of impact ignition, normal ignition will not be achieved. To overcome this limitation, the present application adopts a universal inertia ignition mechanism, improving the ignition reliability.

A hand-throwable effect-producing body with a manually graspable housing body, a manually operable triggering device having a spring-loaded impact body, an ignition device initiatable by the triggering device and comprises an ignition charge, a delay device is initiatable by the ignition device and comprises a delay charge and a delay line, and a main charge configured to be initiated directly or indirectly by the delay charge. The impact body is configured to be manually moved along the longitudinal axis thereof counter to a spring force into a preloaded position and to be releasably arrested there and to be released by manually operating a triggering element of the triggering device, such that it can shoot out of its preloaded position along the longitudinal axis against an axial stop and thereby initiate the ignition charge.

The present application belongs to the technical field of control, and particularly relates to a multifunctional high-precision synchronous trigger device and method. The method is as follows: step 1: configuration file; step 2: parsing GPS / Beidou satellite time or DC code input time to obtain parsed time; step 3: generating 3-way 1PPS, 1-way DC code and 1-way NTP network time according to the parsed time obtained in step 2; using the parsed time to perform timing triggering or waiting for an external trigger signal to be valid; and step 4: outputting a trigger signal and trigger time. The present application can realize two modes of timing triggering and external triggering, and the timing triggering time is generated by real-time parsed GPS / Beidou time or BDC code time, which is high in precision and reaches the level of ns.

The technology subject of the present application generally concerns an aerial munition unit comprising a proximity fuze functionality and an impact fuze functionality, selectable by a crew member of an aircraft bearing the munition, after the aircraft has taken off and prior to munition release, to render active or operable the proximity fuze functionality or the impact fuze functionality.

The present invention relates to a high-voltage self-destruct system for an unmanned vehicle. The high-voltage self-destruct system includes, as main components, a fuselage, a control enclosure, a switch unit, and a high-voltage self-destruct module, and is structurally modified so that, when a cover of the control enclosure is opened without permission, the switch unit is switched to an ON state, high-voltage power is supplied to a main board, and thus high-voltage damage is inflicted on the main board. Accordingly, even if an unmanned vehicle used for military operations is taken over by an enemy or crashes in enemy territory, flight information including take-off position, flight path, and return position recorded on the main board may be deleted.

The invention relates to a sensor system for installation in a fuse for a projectile, comprising at least one antenna element, wherein the antenna elements are arranged on a surface that is arranged at an angle α of between 85° and 95° relative to the centre line C-C of the fuse. The invention further relates to a fuse and a projectile equipped with a fuse.

The present disclosure relates to the technical field of UAV firefighting and discloses an aircraft, a fire extinguishing bomb control system, and a bomb-mountable detonation device thereof. The bomb-mountable detonation device of the present disclosure comprises a power supply module, a communication module, and a detonation signal transmission module, wherein the power supply module is configured to power the bomb-mountable detonation device; the communication module comprises a timer and is configured to establish a communication connection with the aircraft and to start a timer countdown when a first trigger condition is met; and the detonation signal transmission module is configured to output a detonation current signal upon completion of the timer countdown when the power supply module is energized and a second trigger condition is met. The bomb-mountable detonation device of the present disclosure detonates the fire extinguishing bomb through a multi-verification mechanism, effectively preventing accidental operation.

The present invention discloses an electronic-mechanical composite timing fuze for an artificial hail suppression and rain enhancement bomb of an antiaircraft gun, comprising a fuze upper body, a mechanical timing firing mechanism disposed in the cavity of the fuze upper body, a fuze body, a power module, an electronic timing firing mechanism, a flameproof and delayed release safety mechanism, a centrifugal safety mechanism, a recoil safety mechanism, and a detonator. The electronic timing firing mechanism is located between the power module and the flameproof and delayed release safety mechanism, the front end of the detonator is adjacent to the flameproof and delayed release safety mechanism, and the rear end serves as the fuze output end for detonating the explosive charge of the artificial hail suppression and rain enhancement bomb, and the centrifugal safety mechanism and the recoil safety mechanism realize redundant insurance of the flameproof and delayed release safety mechanism. The fuze structure of the present invention is simple, and the fuze space is reasonably and fully utilized. The electronic timing firing mechanism can ensure high-precision firing, and at the same time has the functions of flameproof, redundant insurance, redundant firing, delayed release safety, and self-failure, with high safety and good production reproducibility.

The invention relates to a hand grenade (2), with a manually graspable housing body (4), with a manually operable triggering device (6) with a spring-loaded impact body (14), with a detonating device (20), which can be set off by the triggering device (6) and comprises a detonating charge (22), with a delay device (24), which can be set off by the detonating device (20) and comprises a delay charge (26) and a delay line, and with a main charge (12), which can be set off directly or indirectly by the delay charge (26); according to the invention, it is proposed that the spring-loaded impact body (14) comprises the detonating device (20) together with the detonating charge (22) and the delay device (24) together with the delay charge (26) and together with the delay line, and that the impact body (14) can be manually moved along the longitudinal axis (18) thereof counter to a spring force into a preloaded position (48) and can be releasably arrested there and can be released by manually operating a triggering element (60) of the triggering device (6), such that it can shoot out of its preloaded position (48) along the longitudinal axis (18) against an axial stop (46) and thereby set off the detonating charge (22).

A system for actuating a safety control for a device including: (1) at least one sensor adapted to measure a parameter of the device and provide an output; (2) a Kalman filter adapted to receive the output of the at least one sensor and provide a state estimate and covariance value of the device; (3) a Lyapunov function adapted to receive the state estimate and covariance value from the Kalman filter and provide a time derivative; and (4) a comparator adapted to compare the time derivative to a reference value and provide a command decision to the device.

The invention discloses a remote control timing double-acting mode wireless exploder which comprises a shell, a display screen, a timing knob, a mode change-over switch, a safety release switch, a safety pin, a detonator wiring hole, a power switch, a battery and a circuit board. The circuit board comprises a power supply module, a boosting module, a detonation insurance module, an alarm module, a main control module, a signal receiving module and a timing knob module; the safety pin locks the power switch; the power supply module supplies power; the power switch controls on-off of the power module. The mode change-over switch selects a detonation mode; the timing knob determines the timing duration; the signal receiving module is used for receiving a detonation instruction; the detonating safety module is used for enabling the exploder to be in a safety state; the safety releasing switch is used for releasing the safety state of the exploder; the alarm module is used for indicating wrong operation; the boosting module is used for boosting the voltage to the voltage for detonating the detonator; the detonator wiring hole is used for detonating a detonator; the display screen is used for displaying timing information. The garment is convenient to carry.