305results about "Military adjustment" patented technology

Various countermeasure dispensing systems (or CMDSs) and method of use are described herein. CMDS may include a dispenser assembly operably engaged with a platform where at least one electrical connection provides electrical communication between the dispenser assembly and a sequencer. CMDS may also include a magazine assembly operably engaged with the dispenser assembly, wherein the magazine assembly comprises a magazine configured to hold at least two countermeasure expendables. CMDS may also include a breechplate assembly operably engaged with the magazine assembly and adapted to dispense the at least two countermeasure expendables. CMDS may also include at least one magazine identification switch (MIS) operably engaged with the magazine assembly and the breechplate assembly. CMDS may also include that the at least one MIS is configured to enable the sequencer and the breechplate assembly to selectively dispense at least one countermeasure expendable from the at least two countermeasure expendables.

The invention discloses a sweating and cooling composite thermal protection structure based on a porous metamaterial, which belongs to the technical field of active thermal protection of aircrafts and comprises a layered metamaterial composite structure body. The layered metamaterial composite structure body sequentially comprises a spectrum stealth porous superstructure layer, an infrared thermal stealth porous superstructure layer and a hydrogel filling layer from top to bottom. The infrared thermal stealth superstructure porous material is used as a core, the anisotropic thermal conductivity characteristic of the infrared thermal stealth porous superstructure layer is achieved through the micro-nano structure design and different porosity distribution, transfer of surface heat flow in the horizontal direction and transfer of heat to the coolant phase change layer in the vertical direction can be accelerated, a sweating cooling mechanism is triggered, and the heat transfer efficiency is improved. Local high temperature of the surface is effectively eliminated, the average temperature of the surface is rapidly reduced, and the heat radiation amount is reduced, so that efficient thermal protection is achieved, the infrared thermal stealth function is achieved, and the spectrum stealth requirement is also met by combining the surface spectrum stealth porous superstructure layer.

A laser warning receiver that can be detachably mounted on the inside of a window of a manned platform to detect laser threats within its field-of-view (FOV) and to provide visual or audio warnings to the human occupant. The LWR is fully self-contained and independent of any systems on the manned platform. In different packaging configurations, the receiver's FOV can be manually rotated to better visualize the threat and / or the receiver's human-machine interface (HMIF) can be manually rotated to better display the warnings. Although most typically used in manned aircraft the LWR can be used in other manned vehicles or ships.

The system comprises a plurality of sensor systems, a counter drone, and a processor. A sensor system of the plurality of sensor systems comprises one or more sensors that are connected to a network. The counter drone is connected to the network. The processor is configured to receive an indication of a potential target from the plurality of sensor systems; generate a fused data set for the potential target, determine whether the potential target comprises the threat drone based at least in part on the fused data set; and in response to determining that the potential target comprises the threat drone, provide counter drone instructions to the counter drone.

The present disclosure describes articles that may be used in protective gear, including but not limited to body armor, helmets, shields, or barriers. These articles may include a polymeric material coated with nanoparticles, in a single layer or in multiple layers, which are treated to form a composite. The articles may further include a ceramic layer and / or a back-face layer. Such articles may be useful for protecting an object or wearer against projectiles.

The invention relates to the technical field of layered products, and particularly discloses a skin material for wave-absorbing hiding and a preparation method. The skin material is of a layered structure and comprises a bionic micro-forest wave-transparent layer, a gradient transition layer, a wave-absorbing layer with a'skeleton-matrix 'dual-network structure, a reflecting layer and a heat-insulating layer which are sequentially arranged from top to bottom. A micro-cone array is arranged on the surface of the bionic micro-forest wave-transparent layer, so that broadband impedance matching is realized; the wave-absorbing layer comprises a three-dimensional ceramic skeleton and a magnetic-dielectric composite matrix filled in pores of the skeleton, and magnetic absorbents in the wave-absorbing layer are directionally arranged in the layer plane direction through a magnetic field auxiliary technology. The skin material prepared by the invention has excellent comprehensive performance of ultra-wideband wave absorption, high mechanical strength, light weight and high temperature resistance, and is particularly suitable for stealth requirements in the field of aerospace.

A flame effect system for an unmanned aerial vehicle (UAV) includes a hopper configured to store a powdered fuel, a propellant tank configured to store a propellant, and a nozzle configured to expel the powdered fuel into an atmosphere. Furthermore, the flame effect system includes a fluid path extending from the propellant tank to the nozzle. The hopper is fluidly coupled to the fluid path at an intersection between the propellant tank and the nozzle, the hopper is configured to enable the powdered fuel to flow into the fluid path, and the propellant tank is configured to expel the propellant through the fluid path to fluidize the powdered fuel within the fluid path and to drive the fluidized powdered fuel through the nozzle.

The present invention discloses a pan-tilt mechanism for mounting firearms, which is composed of a firearm clamping moving body, a buffer spring, a recoil buffer lower frame, a pan-tilt suspension arm and a pan-tilt horizontal azimuth adjustment mechanism; the pan-tilt horizontal azimuth adjustment mechanism is used to connect the pan-tilt mechanism with a drone and adjust the azimuth angle of the pan-tilt mechanism; the pan-tilt suspension arm is used to connect the pan-tilt horizontal azimuth adjustment mechanism and the recoil buffer lower frame and adjust the pitch angle of the pan-tilt mechanism; the firearm clamping moving body is used to clamp the firearm and is slidably connected with the recoil buffer lower frame; the buffer spring is arranged between the firearm clamping movement and the recoil buffer lower frame before and after the firearm clamping movement, and is used to buffer the recoil of the firearm firing. The present invention solves the problems of low striking effect of firearms carried by drones, reducing recoil, adjusting the pitch and horizontal angles of the firearms and aiming.

A drone including a body and a rotor unit, the body has a substantially cylindrical outer lateral surface, and at least one energy storage element of the drone is arranged in the body. The rotor unit is connected to a head side of the body, and the rotor unit comprises a first rotor with first blades and a second rotor with second blades, wherein the first rotor and the second rotor are arranged coaxially to each other, the first rotor is designed to rotate clockwise about a rotational axis, and the second rotor is designed to rotate counterclockwise about the rotational axis. The first blades and the second blades are mounted such that they can be freely folded so that they rest against the body in a rotation-free state.

An apparatus management system (10), in particular a vehicle management system, for controlling at least one function of an apparatus (1), such as a vehicle, operated by an operator (2) and exposed to a potential impact (3) approaching the apparatus (1), as well as a corresponding apparatus (1) and a system training device (200) are provided, the apparatus management system (10) comprising: an impact reaction system (11), configured for generating a command for controlling the at least one function of the apparatus (1); wherein the impact reaction system (11) comprises: an intervention control unit (100); and an operator notification unit (55); wherein the intervention control unit (100) comprises at least one control model configured for assessing at least one command for controlling the at least one function of the apparatus (1) to perform an intervention in order to avoid the impact (3); wherein the operator notification unit (55) is configured to issue at least one notification to the operator (2) regarding the at least one command; and wherein the intervention control unit (100) is configured to output the at least one command for controlling the at least one function of the apparatus (1) subsequent to issuance of the notification.

Aerial delivery systems are described including a propulsion unit, a deployable parafoil attached to the propulsion unit, a control / navigation unit operably connected to the parafoil, and a support truss connected to the propulsion unit. The system may be configured to attach to and transport a payload. The propulsion unit may be configured to provide thrust to the aerial delivery system while the parafoil is deployed and the control / navigation unit may be configured to steer the parafoil while deployed.

Embodiments of a payload attachment system secure a missile, a suicide drone, or other ordinance to a wing or fuselage of a combat drone (or another type of aircraft) using one or more vacuum mounting modules, wherein each vacuum mounting module comprises at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives an instruction corresponding to one of a vacuum cup actuation signal or a vacuum cup release signal.

Apparatus and associated methods relate to an Aerial Munitions Loading and Delivery System (LBDS) configured to be mounted on an unmanned aerial platform, the LBDS having a munition holding unit including: a lever engaging frame configured to engage a interlock engagement frame of a fused munition, and a spring-loaded pin coupled to a top end of the munition configured to vertically support the munition, wherein, when the munition is loaded into the LBDS, the lever engaging frame includes an aperture configured to allow access to a safety pin of the munition. The lever engaging frame and the spring-loaded pin may, for example, exert a force in opposite directions along a horizontal axis to deactivate the munition, such that the safety pin can be removed without activating the munition.

A recoilless firearm apparatus for firing at least one bullet of a respective standard cartridge, including a front barrel, a disposable firing activator and a rear discharge opening formed behind the front barrel and aligned with the longitudinal axis of the front barrel. The standard cartridge further includes a casing having an external diameter that is smaller than the rear cartridge-chamber diameter, wherein the casing encloses a sealed inner-casing space that contains gunpowder, and wherein the casing includes a primer. Upon activating the primer, the primer explodes to thereby detonate the gunpowder, forming propellant gasses inside the cartridge that are directed both forward and backward as follows: a) forward: firing of the bullet via the front barrel; and b) backward: pushing, by a recoil force Fp, the casing, being a counterweight to the bullet, to thereby eject the casing from the firearm apparatus via the rear discharge opening.

Techniques and systems are provided for the deployment of small Unmanned Aircraft Systems (sUAS) and Loitering Munitions (LM) from an airborne Small Tactical Unmanned Aircraft System (STUAS).

The system comprises a plurality of sensor systems, a counter drone, and a processor. A sensor system of the plurality of sensor systems comprises one or more sensors that are connected to a network. The counter drone is connected to the network. The processor is configured to receive an indication of a potential target from the plurality of sensor systems; generate a fused data set for the potential target, determine whether the potential target comprises the threat drone based at least in part on the fused data set; and in response to determining that the potential target comprises the threat drone, provide counter drone instructions to the counter drone.

Embodiments of a payload attachment system secure a missile, a suicide drone, or other ordinance to a wing or fuselage of a combat drone (or another type of aircraft) using one or more vacuum mounting modules, wherein each vacuum mounting module comprises at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives an instruction corresponding to one of a vacuum cup actuation signal or a vacuum cup release signal.

Various examples are provided related to ultrathin polymer-derived ultra-high temperature ceramic (UHTC). In one example, a ceramic coating includes a polymer-derived ceramic (PDC); an UHTC; and a ceramic adhesive comprising alumina (Al2O3). For example, the PDC can include silicon carbide and the UHTC can include a titanium carbide. A thickness of the ceramic coating can be less than 1 mm. In another example, a method includes providing the ceramic coating and applying the ceramic coating to a surface of a structure. For example, the structure can be an aircraft, a ship, a missile, or a rocket.

An armored seating assembly for a rotorcraft or other aircraft (e.g., for a pilot or operator) includes a wing armor panel capable of rotational and vertical movement relative to the seat base when adjusted by the operator. For example, a carriage attached to the armor panel translates along a carriage slot in the seat base, stabilized in the carriage slot by orthogonal sets of bearings (e.g., lateral bearings and longitudinal bearings) and allowing the wing armor panel to be vertically adjusted relative to the seat base (e.g., to accommodate pilots of varying heights). The armor panel is coupled to the carriage by hinges allowing the panel to pivot or rotate away from the seat base, in order to facilitate entry to and egress from the seat.

An airframe is provided that can be flown under the control of an operator or an automated sensor and feedback system. The airframe can be any of a variety of known configurations with multiple rotors, fixed or retractable wings, puller or pusher propellers, or jet engines. The airframe includes at least one arm that is used to intercept and disable another airborne vehicle. In some configurations, the arm is fixed and can include fingers at its outer end. In other configurations, the arm is movable from a closed condition to an open condition. A wire or net is connected between the arm and a portion of the airframe so that the wire or net is spread open when the arm is deployed to the open condition. The wire or net are configured to disable or capture a target such as another aerial vehicle.

A submunition assembly to be stored and deployed from an aerial vehicle, particularly a supersonic vehicle, includes a container having at least first and second walls that are joined at one end by a hinge that together define a volume along an axis perpendicular to the hinge that contains a submunition. The submunition assembly is suitably axially-shaped with a rigid parachute panel positioned around the hinge to separate and deploy a parachute. The container may have an internal volume that is conformal to the submunition. The container may have an exterior shape that is either optimized for free-fall or has a portion that provides a conformal surface for the aerial vehicle. The submunition assembly may be configured so that all processing, memory and data resides with the submunition, which issues any and all commands to control the container including separation of the rigid parachute panel and opening of the container to release the submunition.

The present invention relates to a spring arrangement for use in a countermeasure magazine, said spring arrangement including a plurality of elements, wherein each one of said elements has a base portion and a plurality of spring portions extending from a first edge of said base portion, and wherein said spring portions of each element are distributed along a length of said base portion, and wherein said elements include mating connection means such that said elements may be connected to each other.

The present invention relates to a body (2) located in air vehicles; at least one gas discharge element (E) on the body (2), which enables the discharge of hot waste gases; at least one cartridge (F) launched from the body (2) against thermally guided threats directed to the body (2), so that the cartridge (F) is used for defense purposes; a launcher unit (3) located on the body (2) to extend outward from the body (2) and launching a cartridge (F) against thermal threats directed to the body (2), wherein the launcher unit (3) is located on a side of the gas discharge element (E) that discharges hot air; at least one rotation mechanism (4) which is located on the body (2) in a rotatable manner, thus enabling the launcher unit (3) to which it is attached to orient itself towards a thermal target; a casing (5) located to substantially surround the launcher unit (3), serving as a casing for the launcher unit (3), connected to the rotation mechanism (4), and transferring movements of the rotation mechanism (4) to the launcher unit (3) and protecting the launcher unit (3) from external factors.

A receiving device (40) for guided missiles (3) for airborne deployment from aircraft (2) and a deployment device (50) for airborne deployment of guided missiles (3) are proposed, wherein the deployment device (50) has a receiving device (40) and / or is designed to interact with the receiving device (40), and wherein the receiving device (40) comprises a container (41) with a receptacle (43) for at least one guided missile, which is designed to disintegrate in a predetermined manner by an air flow prevailing during airborne deployment.

The utility model discloses an unmanned aerial vehicle pod which comprises a pod body, and an inner space, surrounded by an outer wall, of the pod body is used for loading goods transported by an unmanned aerial vehicle; the connecting part is arranged on the outer wall of the pod body and used for connecting the pod body with an unmanned aerial vehicle body; and the cargo stabilizing part is arranged on the pod body and is used for stabilizing the cargo loaded in the pod body in a manner of extruding the cargo in the internal space of the pod body through volume expansion. The unmanned aerial vehicle pod is simple in structure, the object distribution uniformity and stability of the unmanned aerial vehicle pod during use can be achieved, and the stability of the unmanned aerial vehicle during flight is further improved.

A mounting structure 200 has a first component 201 with a body with a connection structure 205 to couple it to an aerial vehicle 203, and an interface 207 for coupling to a second component 209 which

The application discloses a general gun rack of a UAV and a use method thereof, and is convenient for replacing different guns according to combat requirements of a UAV platform. The general gun rack comprises a lower hanging rack, a front clamping seat, a rear clamping seat and two quick-locking latches corresponding to the front clamping seat and the rear clamping seat respectively. The lower hanging rack comprises a lower hanging rack body, the front end and the rear end of the lower hanging rack body are respectively provided with pin holes for cooperating with the front clamping seat and the rear clamping seat, the pin holes are used for passing through the quick-locking latches, and the front clamping seat and the rear clamping seat are respectively used for being installed at the bottom of the UAV platform through bolts. The front end of the lower hanging rack body is provided with a left clamp hoop, the left clamp hoop is bolt-connected with a right clamp hoop, the left clamp hoop and the right clamp hoop are used for tightly fixing the left side and the right side of a gun barrel part of a 95-type gun family gun, the rear end of the lower hanging rack body is vertically provided with a limiting bolt, the lower end of the limiting bolt passes through the lower hanging rack body, the lower end of the limiting bolt is used for passing through a gun body of the 95-type gun family gun in the transverse direction, the lower end of the limiting bolt is threadedly matched with a wing nut, and the wing nut is used for locking the gun body of the 95-type gun family gun.

Proposed are a method for controlling at least one guided missile (3) to be launched by an aircraft (2) during flight, a guided missile (3) and an aircraft (2), wherein at least one control command (T) is transmitted by light signal (L) from the aircraft (2) to the guided missile (3).

Methods and apparatus for pointing logic in aircraft are disclosed. A disclosed example apparatus to aim an aiming device carried by an aircraft includes at least one memory, machine readable instructions, and processor circuitry. The processor is to at least one of instantiate or execute the machine readable instructions to determine a position of a target, determine an orientation of the aircraft, determine aiming points based on the orientation and a movement range of the aiming device, and determine a movement of at least one of the aircraft or the aiming device based on the aiming points and the position to orient the aiming device toward the target.