246 results about "Launch craft" patented technology

A process and system for detecting the presence of a person overboard including: setting the perimeter of an area to scan, scanning said area 180 degrees in azimuth utilizing a laser beam for receiving a reflection of said laser beam off said person, detecting said reflection and playing back a video recording of said trajectory of the person, wherein the area above and below the perimeter of an area to scan is continuously video recorded and wherein upon detecting the target, one or more of audio and visual alarms alert that crew, and wherein an alarm with location is sent to PDA system with GPS coordinates time and date. Additionally a launched deploys a device to track the person overboard, and allows persons on the ship or in a control center to ascertain the location of the person overboard.

A Personal Locator Beacon (PLB), supporting two operation modes local monitoring and remote monitoring. The apparatus includes a PLB that supports the present operation mode, as well as a local monitoring mode, employing the same transmitter, and automatically switching between modes. Upon activation, the PLB first tries to communicate with a local monitoring station, at a low transmission power, and at a high repetition rate, in purpose of dealing with the PLB call locally, without involving the remote monitoring station. Then, if not acknowledged by a local monitoring station, the PLB increases its transmission power, enabling access to a remote monitoring station. In a preferred embodiment, the PLB is carried by a person onboard a vessel, to alarm upon a Man Overboard (MOB) accident, the local monitoring station is installed onboard the same vessel, and the remote monitoring station is part of a satellite Search and Rescue (SAR) system, as Cospas-Sarsat.

A ground-based ball launcher for inflated-ball sports practice provides an impulse that propels the ball upwardly in a trajectory of pre-adjustable angle and velocity so as to obtain a desired maximum height and landing distance offset from the launcher. An optional adjustable time delay gives a player time to move into place and get set for each launching. Launching energy may be provided by a compressed coil spring which can be reloaded by the user with foot-pump action.

A search and rescue drone system includes a buoyant body member, a frame attached to the buoyant body member for carrying a motor and propeller, and an electronic array including a camera, GPS, an EPIRB radio distress beacon, and a transmitter/receiver for remote control flying the drone and communicating with an operator. A laser guidance system may provide coordinates for landing near a swimmer in distress. The search and rescue drone may also be programmed to simply fly to the location of an electronic wearable device, like a bracelet, that is worn by a man overboard. In another embodiment, the search and rescue drone includes pivoting motor mounts, so that it can take off and land vertically with propellers rotating in a horizontal plane, and then the propellers may pivot to rotate in a vertical plane for propulsion across water similar to a fan boat with rescued people aboard.

The invention discloses a UAV landing guidance system and method based on multi-mode navigation, belongs to the technical field of UAV flight navigation, and is suitable for vertical take-off and landing UAVs. The system includes the parking stand and the reference point of the parking stand, the cooperative light array, the power supply unit, the radio beacon transmitter, the satellite positioning module I and the communication module I arranged near the parking stand; and the landing guidance module and the satellite arranged on the UAV Positioning Module II. This method uses radio direction finding, visual guidance, satellite positioning and data fusion to guide the UAV to automatically land on the designated parking space. Improve the accuracy and reliability of the drone's autonomous landing, reduce the risk of blind landing, and have good anti-interference. It can be used for UAV landing guidance on fixed platforms and mobile platforms.

An aerial vehicle launcher including a rail having a first end and a longitudinal axis and a piston movable in a passageway formed in the rail, the piston connected to a carriage by at least two elongate flexible members. The carriage having a support device for releasably engaging the aerial vehicle. Upon the carriage and the aerial vehicle approaching one end of the rail, the support device controllably disengaging the aerial vehicle, permitting the aerial vehicle to be launched. A device is connected to a pressurized gas source, the device controllably providing pressurized gas from the pressurized gas source to the passageway for drivingly moving the piston, the carriage, and aerial vehicle along the rail for launching the aerial vehicle. The device includes a reservoir for holding pressurized gas, the reservoir being a conduit, the pressurized gas in the reservoir providing the driving force for launching the aerial vehicle.

A launcher system includes a launcher having a barrel adapted to receive a projectile and a charge of propellant and a velocity variator configured to shift relative to barrel to selectively vary a launch velocity of projectile from launcher. The velocity variator may be constituted by a collar selectively controlling the propellant gases vented out of projectile and into barrel and/or a sliding breech face behind which is an energy-absorbing plug.

A search and rescue drone system includes a buoyant body member, a frame attached to the buoyant body member for carrying a motor and propeller, and an electronic array including a camera, GPS, an EPIRB radio distress beacon, and a transmitter/receiver for remote control flying the drone and communicating with an operator. The search and rescue drone may be flown manually, or may have some autonomous flight and locator capabilities. For example, in one embodiment, the search and rescue drone may be programmed to simply fly to the location of an electronic wearable device, like a bracelet, that is worn by a man overboard. In another embodiment, the search and rescue drone includes a basket, harness, or other means for actually recovering a swimmer in distress, and flying that person back to safety on a ship or on shore.

Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail. The shuttle is detachable from the motor-driven tape, such that stoppage of the tape can be separate from stoppage of the shuttle. Embodiments further provide a secondary arrestment strap. Further embodiments provide an anti-rollback latch system.

The present invention relates to multiple driving toy top with flywheel and its multiple driving launchers. The toy top has a flywheel driving device set on the top casing and comprising flywheel driving gear and slot on the casing, a flywheel connecting device extending beyond the top casing in the upper part of the flywheel shaft; and the launcher has a top casing driving device on the launcher casing and a flywheel driving device connected to the flywheel driving device in the top, so that the flywheel driving device of the top may be transferred from the top casing to the launcher to make the driving device possess simple and integral structure and use convenience. The multiple driving device structure makes the toy top capable of suiting several kinds of launcher and meeting the requirement of different players.

A glider toy has pivoting wings that may be locked in a retracted position prior to launch. Upon launching of the glider, the wings may be unlocked. During flight, the wings extend forward for an entertaining glide at the urging of one or more elastic members. A launcher includes an orientation-sensitive safety feature that limits the angles at which projectiles may be launched therefrom. The safety feature permits projectiles to be launched from the launcher only within approximately a generally upward, non-vertical angular range.

Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

The invention provides a single-rope recovery method of an unarmored cable deep diving submersible. The method comprises following steps: (1), an emitter is mounted on a deep diving submersible; (2),one end of a throwing rope is fixed on the deep diving submersible, and the other end of the throwing rope winds around a bullet; (3), after the deep diving submersible returns to water surface near amother ship, an operator on the mother ship controls the emitter to start by a remote-control unit; (4), the bullet carrying the throwing rope flies and lands on the mother ship; (5), the operator onthe mother ship takes down the throwing rope from the bullet, and then one end of the throwing rope is fixed on a mushroom head; (6), a winch rolls up and hoists the mushroom head and the deep divingsubmersible through the throwing rope; and (7), a lifting arm is started to lift the deep diving submersible connected with the mushroom head onto the mother ship, and recovery is finished. A cable is thrown on the mother ship by the aid of the emitter, so that the operator is not required to perform underwater operation, risks of the operator are reduced, and working efficiency is increased.

A system and method for magnetically launching projectiles or spacecraft includes an electromagnetic launcher including a launch tube, and a launch craft. The launch tube includes electrically conducting rails energized along the length of the rails, and a transverse direct current magnetic field is generated along the launch tube, and upper and lower conductors and loops of conducting material on the launch craft are provided for magnetic levitation, stabilization and propulsion of the launch craft in cooperation with the transverse direct current magnetic field. A transverse direct current magnetic field is applied to the launch tube and the launch craft during launching of the launch craft, and the launch craft is magnetically levitated and stabilized to minimize contact between the launch craft and the launch tube as the launch craft travels within the launch tube.

A figurine launcher is described. The figurine launcher includes at least two shell components. The shell components are hingedly attached with one another to move between an open position and a closed position. An open mechanism is attached with at least one of the shell components and is adapted to allow a user to selectively separate the shell components when in the closed position. A launch positioning mechanism is attached with at least one of the shell components. The launch positioning mechanism is adapted to engage with a figurine and conceal the figurine within the housing when the shell components are in a closed position. Alternatively, when the shell components are in an open position, the launch positioning mechanism is adapted to move the figurine into a launch position. When in the launch position, the user can compress the shell components to force the figurine from the launcher.

The invention relates to a double-rocket booster unmanned aerial vehicle launching device. The device is characterized by comprising an unmanned aerial vehicle, a launching undercarriage, a rocket booster and a rocket booster hanging frame, a front force transmission shaft, a rear force transmission shaft and a vehicle body rear fulcrum are arranged on a vehicle body of the unmanned aerial vehicle, the front force transmission shaft and the rear force transmission shaft are arranged on the side face of the vehicle body of the unmanned aerial vehicle, and the vehicle body rear fulcrum is arranged at the tail of the unmanned aerial vehicle; under the same unmanned aerial vehicle centroid deviation, the launching stability of the rocket booster symmetrically arranged type unmanned aerial vehicle launcher is obviously superior to that of a single rocket booster. The device can simplify the external field pre-shooting preparation work of the unmanned aerial vehicle and improve the battlefield quick response capability of the unmanned aerial vehicle.