14results about "Military adjustment" patented technology

This invention relates to the field of unmanned aerial vehicle (UAV) control technology, specifically to an integrated gun-barrel top-attack UAV and its control method. The UAV includes a main body, wings, a recoilless gun mounted obliquely on the fuselage, a reconnaissance module, a flight control module, and a communication module. The control method includes: receiving waypoint instructions; the waypoint manager determining a flight sequence including takeoff, landing, hovering, level flight, and mode transitions based on preset decision logic; executing the sequence and generating control commands through a flight mode controller; and achieving attitude stabilization through an attitude controller. This invention achieves deep integration of the UAV platform and weapon, possessing rapid deployment, flexible multi-mode flight, intelligent route optimization, and precise top-attack capabilities, significantly improving the UAV's combat effectiveness and survivability in complex battlefield environments.

The goal is to reduce the weight and cost increase that would result from using radar-absorbing materials to give aircraft stealth capabilities. [Solution] The radio wave absorber according to the embodiment is a radio wave absorber that forms the surface of an aircraft structure having a shape that repeatedly reflects radio waves to be absorbed, and comprises a first radio wave absorbing portion that forms a first region of the surface and has a first radio wave absorbing performance, and a second radio wave absorbing portion that forms a second region of the surface different from the first region and has a second radio wave absorbing performance lower than the first radio wave absorbing performance.

This invention relates to the field of launching device technology, and provides a spring-driven launching device for firefighting, military and police use. The device includes a control unit, a drive unit, a housing, and one or more launching units. Each launching unit includes a launching tube, a pressure spring, and a launching element. The pressure spring is built into the launching tube for energy storage, storing potential energy and providing driving force through compression or torsion. The launching element is installed inside the launching tube and is launched when the spring releases its potential energy. The drive unit is driven by a motor or mechanically. This invention employs a multi-tube modular design combining spring power and mechanical drive, abandoning the traditional gunpowder-activated, high-pressure gas cylinder-driven mode. It effectively solves the problems of single-tube launchers—limited functionality, low efficiency, and poor adaptability—and avoids the defects of traditional multi-tube devices—complex structure, low safety, and fixed launching modes. The overall structure is compact, reliable in operation, and safe to use, making it practically valuable in fire emergency rescue, police non-lethal response, and various high-risk space disposal scenarios.

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.

This invention relates to a body (2) exposed to air flow during the flight of the respective air vehicle, at least one ammunition (M) fired to attack a target, at least one machine cannon (3) enabling the ammunition (M) to be fired, at least one ammunition duct (4) on the body (2), enabling the ammunition (M) to be placed therein and the ammunition (M) to be transferred to the machine cannon (3), and a butt line (BL) arranged so as to extend lengthwise on the air vehicle and symmetrically divide the air vehicle in two.

The utility model belongs to unmanned plane technical field relates to a combination structure for strapdown unmanned plane and launching device, and unmanned plane is more and more widely used in military application, unmanned, accurate attack becomes the mainstream trend of modern war, need a new type of load pylon to satisfy these demands, ensure that unmanned plane can efficiently, safely complete its mission, the utility model not only enhanced the security of traditional pylon, also greatly promoted the operation efficiency, in addition, the optimized structure design makes the whole system more compact and light, is suitable for the application demand of modern unmanned plane platform, can realize that unmanned plane carries multiple different types of weapons and ammunition, and copes with different types of combat.

This disclosure provides a payload deployment system that operates to receive and hold a configurable payload. The payload deployment mechanism helps reduce the drag on the payload and protect the payload from environmental factors. The payload may be released using a hinge mechanism to ensure that the payload does not come into contact with the payload deployment mechanism when the payload is deployed. Vents can be used to equalize the pressure between the external environment and the main body of the payload deployment mechanism. The vents can generate additional forces that help separate the payload from the launcher.

The application belongs to the technical field of firearms, and particularly relates to a light-weighted firearm clamp system with a replaceable buffer at the end of a mechanical arm. The system comprises a general buffer component, a submachine gun clamp mechanism and a pistol clamp mechanism. The general buffer component provides one-way buffering and is installed at the end of a wearable mechanical arm. The general buffer component is connected to the submachine gun clamp mechanism or the pistol clamp mechanism through quick-release pins. The submachine gun clamp mechanism and the pistol clamp mechanism are respectively used for clamping and firing a submachine gun or a pistol, and the firing mode is lever firing. When shooting, the clamp mechanism fires the firearm, and the recoil force is transmitted to the general buffer component through the clamp mechanism for buffering. The application has the characteristics of light weight and generalization, and has a compact structure, flexible movement and adaptability to various types of firearms or other sensor end equipment.

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 signal passthrough kit operably engaged with a canister housing an air vehicle and an electronic assembly. The signal passthrough kit includes a backer plate that operably engages with the canister. The signal passthrough kit also includes a piston that operably engages with the canister, the backer plate, and the air vehicle, wherein the piston is positioned between the backer plate and the air vehicle. The signal passthrough kit also includes a circuit card assembly that operably engages with the backer plate and is positioned external to a canister chamber defined by the canister. The signal passthrough kit is configured to output at least one signal to the electronic assembly external to a pressure chamber defined in the air vehicle.