197results about "Military adjustment" patented technology

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.

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.

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.

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.

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.

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.

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.

The application discloses a method for realizing ionosphere aircraft stealth based on regulating and controlling electron distribution of tail area, first, evolution time scales under different non-extended parameters are calculated; and according to the superhot electron energy and particle flux per unit time required by different non-extended parameters, a radio frequency discharge plasma generator is controlled to generate plasma corresponding to the non-extended parameters; then, in the grid electric field, electrons enter the acceleration field area, and ions are directly discharged to the tail area of the aircraft without acceleration; the regulation and control duration under different non-extended parameters is determined by the evolution time scale corresponding to the non-extended parameter. The application changes the electron distribution of the ionosphere aircraft tail area by randomly injecting high-energy electrons into the tail area of the aircraft, regulates and controls the evolution law and characteristic scale of the non-linear local cavity in the tail area which cannot be eliminated, makes the anti-stealth method of monitoring the motion of the density cavity to detect the ionosphere stealth aircraft invalid, and thus realizes the stealth of the ionosphere stealth aircraft.

The application provides an internal embedded bomb cabin honeycomb configuration aerodynamic layout for improving flow field stability, and the internal embedded bomb cabin cross section body is a hexagonal honeycomb configuration layout, wherein the top surface of the honeycomb configuration is opened, the other five surfaces are closed wall surfaces, the top surface is parallel to the bottom surface, the included angle alpha between the bottom surface and the adjacent surface is 135 degrees, the longitudinal depth ratio beta of the honeycomb configuration is L / H=1.5, L is the maximum transverse distance of the bomb cabin cross section, and H is the maximum longitudinal height of the bomb cabin cross section. Under the condition of meeting the requirements of structural strength, sound and heat insulation, weight reduction, internal structure design of the fuselage, capacity and other constraints, the internal flow flow field stability of the internal embedded bomb cabin can be greatly improved, the flow field characteristics are improved from the physical root, the evolution of fine vortex and secondary vortex is effectively inhibited, and the process of the flow field from the steady state to the unsteady state is greatly delayed. Because the optimization design effectively inhibits the unsteady flow, especially the premature appearance of the turbulent flow, the aerodynamic efficiency of the internal flow of the bomb cabin is improved.

The present invention relates to a body (2) that is exposed to the air flow, at least one wing (3) that is located on the body (2) extending outwards from the body (2), provides lifting force to the body (2) and allows ammunition and similar payloads to be placed on it, at least one fastener (B) that connects the wing (3) to the body (2), at least one rod (4) one end of which is connected to the body (2) and the other end to the wing (3), providing load transfer to the wing (3), a root region (301) that is located on the wing (3) and extends from the body (2) in a dihedral angle, an end region (302) that is located on the wing (3) and extends from the root region (301) in a anhedral angle with the body (2), a bend region (303) in an inclined form that is located on the wing (3) between the root region (301) and the end region (302), and connects the root region (301) and the end region (302).

Provided is a detent apparatus for a rocket, The detent apparatus includes a detent including a first end portion, a second end portion opposite to the first end portion, an extension extending between the first end portion and the second end portion, and a detent protrusion configured to engage with the rocket, a first elastic body configured to elastically support the first end portion of the detent and connected to the first end portion, and an electrical safety device configured to prevent rotation of the detent including a hinge fixing frame having a hinge axis parallel to the detent rotation axis, a detent support configured to rotate around the hinge axis and support the detent, a hinge axis shaft arranged on the hinge axis, a solenoid configured to rotate the detent support by pushing the detent support, and a micro switch activated when the detent support rotates.

The disclosure relates to a system and a method for dispensing detection of a pyrotechnical countermeasure in a pyrotechnical countermeasure dispenser system (1 ). The method comprises: - providing a pyrotechnical countermeasure dispenser control unit (4) with a recoil-sensing device (5), wherein upon activation of a pyrotechnical countermeasure dispensing command, - monitoring the sensing of a recoil signal (8) from the recoil-sensing device (5) during a monitoring window (6), - determining that a dispensing of the pyrotechnical countermeasure from a pyrotechnical countermeasure cartridge (3) has occurred upon detection of the recoil signal (8) exceeding a recoil detection threshold value (9) during the monitoring window (6), - determining that a misfire of the pyrotechnical countermeasure has occurred upon no detection of the recoil signal (8) during the monitoring window (6).

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.

Multi-body flight system (10), comprising: a primary missile (1); a plurality of secondary missiles (2), each of which can be coupled to the primary missile (1) via a carrying and release system (11) to produce a launch configuration and can be triggered by the primary missile (1) in flight to produce an operational configuration; and a control system (4) which is designed to release the secondary missiles (2) from the launch configuration of the primary missile (1) during deployment as a function of mission specifications and to allow the primary missile (1) and the released secondary missiles (2) to assume the deployment configuration; wherein the primary missile (1) and the secondary missiles (2) are each designed as guided missiles; wherein the control system (4) comprises a control device (3) of the primary missile (1) and a control device (3) of each of the secondary missiles (2) for individually controlling the missiles (1, 2); wherein the primary missile (1) and the secondary missiles (2) each have a drive which are jointly designed to drive the multi-body flight system as a single guided missile.

An aircraft fuselage, in particular of an open fan propeller aircraft, includes a primary structure having frame members extending in a circumferential direction of the fuselage and stringers extending in a longitudinal direction of the fuselage and a ballistic shield covering an inner surface of a longitudinal section of the fuselage. The ballistic shield is inserted between adjacent frame members of the primary structure and extends in a longitudinal direction and a circumferential direction of the fuselage section. A ballistic shield for use on an inner surface of an aircraft fuselage, a ballistic shield assembly and aircraft are disclosed.

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.

The utility model belongs to the technical field of net guns, and particularly relates to a net gun device loaded on an unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, two connecting brackets are fixedly arranged at the bottom of the unmanned aerial vehicle body, the two ends of the two connecting brackets are fixedly connected through connecting branch pipes, a control system is arranged in the unmanned aerial vehicle body, and the control system is connected with the unmanned aerial vehicle body. A mounting pipe is fixedly arranged at the right bottom of the unmanned aerial vehicle body, a fixing plate is detachably fixed between the two connecting brackets on one side of the mounting pipe at the bottom of the unmanned aerial vehicle body, a second absorbing structure is mounted on one side, directly facing the mounting pipe, of the fixing plate, and a first absorbing structure is mounted in the mounting pipe; a net gun body is fixedly mounted on the side, away from the fixing plate, of the first absorption structure and movably penetrates through the mounting pipe to the outside of the mounting pipe. And therefore, the first absorption structure and the second absorption structure can absorb the counter-acting force generated when the net gun body works, and the unmanned aerial vehicle body flies more stably and safely.

The embodiment of the invention discloses an overall aerodynamic layout method of a long-distance aggressive patrolling bomb and a launching mode of the long-distance aggressive patrolling bomb. A specific implementation method of the method comprises the steps that the patrolling bomb adopts a single-wing layout, a fuselage is divided into three cabin sections, and the three cabin sections can be quickly disassembled and assembled respectively. A warhead, a power battery, avionics equipment and the like are installed in the patrolling bomb. Wherein the large warhead can effectively enhance the aggressiveness of the patrolling bomb; a long-distance target can be attacked in a large voyage; the launching modes are diversified, and aerial launching and ground launching can be achieved; disassembly and assembly are fast, and use and maintenance are convenient. The patrolling bomb adopts multi-node two-way information transmission, can be used singly, and can also be used for cluster combat.

A communications interconnect between the countermeasure controller of a countermeasure system and the dispenser containing the countermeasure payloads therein. Additionally, the present disclosure provides a power connection between the countermeasure controller and the countermeasure dispenser to deliver power to the countermeasure payloads, including smart payloads, utilizing existing vehicle wiring harnesses and wiring kits.

The invention is for positioning on aircrafts; an aerodynamic pod (1) characterised by a body (2) and a front body (3) positioned on the body (2) and movable, an optical head (4) positioned on the front body (3), a rear-view cavity (5) positioned on the front body (3), a channel (6) opening on the rear-view cavity (5) for movement of the front body (3) against the aerodynamic torque generated thereon, and a protrusion (7) positioned on the rear-view cavity (5).