842results about "Launching/towing gear" patented technology

An embodiment of the invention is directed to a system for controlling and managing a small unmanned air vehicle (UAV) between capture and launch of the UAV. The system includes an enclosure that provides environmental protection and isolation for multiple small UAVs in assembled and/or partially disassembled states. Control and management of the UAVs includes reorientation of a captured UAV from a landing platform and secure hand-off to the enclosure, decontamination, de-fueling, ingress to the enclosure, downloading of mission payload, UAV disassembly, stowage, retrieval and reassembly of the UAV, mission uploading, egress of the UAV from the enclosure, fueling, engine testing and launch readiness. An exemplary system includes two or more robots controlled by a multiple robot controller for autonomously carrying out the functions described above. A modular, compact, portable and autonomous system of UAV control and management is described.

Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

An embodiment of the invention is directed to a platform for launching and/or capturing an unmanned air vehicle (UAV), particularly a small UAV. The launch/capture platform includes a frame, a floor attached to the frame that is capable of supporting the UAV, means for acquiring and tracking the UAV in flight, a connector and a connector controller, connecting the platform to an external support structure, providing a controllable, adaptive motion of the platform in response to approaching UAV position and attitude, means for launching the UAV from the platform and for capturing an in-flight UAV to the platform, and means for locking down the UAV between the capture and launch of the UAV. Another embodiment of the invention directed to a method for capturing a small, in-flight UAV involves providing a UAV capture platform, providing a UAV capturing means as an integrated component of the platform, providing means for determining in real-time the relative location of an engaging portion of the capturing means with respect to an approaching in-flight UAV, providing means for automatically maneuvering the engaging portion of the capturing means with respect to at least one of a position and an attitude of the approaching in-flight UAV, capturing the UAV, and securing the captured UAV to the capture platform.

An unmanned air vehicle (“UAV”) apparatus is configured to have a body and a body-conformal wing. The body-conformal wing is configured to variably sweep from a closed position to a fully deployed position. In the closed position, the body-conformal wing span is aligned with the body axis and in the fully deployed position the body-conformal wing span is perpendicular to the axial direction of the body. Delivery of the UAV comprises the steps of: positioning the span of a body conformal wing in alignment with the axis of the body of the UAV; initiating the flight of the UAV; and adjusting the sweep angle of the body-conformal wing as a function of the current speed, altitude, or attack angle of the UAV, with the adjustment starting at a 0 degree position and varying between a closed position and a fully deployed position. The UAV also has a control mechanism configured to variably adjust the sweep of the body-conformal wing to achieve a high lift over drag ratio through out the flight path of the UAV.

The present invention relates to a system for landing UAV's. The system comprises a slingshot structure that includes arm based structure and an axis means installed along the arm of the structure and wherein it enables the arm to move around it in addition, the system comprises base means connecting the axis means to a platform at which the system is installable. The system also include a controlled pulling and braking means that connects between the arm of the structure and the platform upon which the system is installable and a stretchable elastic means installed in a stretched manner at a gap formed between two arms and set to connect with a landing UAV. At the landing phase, the controlled pulling and braking means of the system, essentially breaks the motion of the arm based structure that is propelled to revolve around the system's axis means, from a time that the UAV forms contact with the elastic means and with it propels the structure to move around the axis means.

Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

Methods and apparatuses for cable launching airborne devices (e.g., unmanned aircraft) are disclosed. In one embodiment, an apparatus includes an elongated structure, e.g., a tower, boom or derrick. At least one flexible elongated member (e.g., a cable or rope) can be attached toward one end to the structure and toward another end to the ground or another structure to form an elongated launch path. A cradle, which can carry the airborne device, can also be movably attached to the flexible elongated member and can be accelerated along the launch path. As the cradle decelerates, the aircraft can be released into flight.

An apparatus for launching an aircraft having a multiplicity of interconnected elongated tracks of rigid material forming a track system and wherein each elongated track has a predetermined elongated track cross-sectional design, a winch system connected to the track system wherein the winch system has a variable mechanical advantage, one or more elongated elastic members wherein one end of each of the one or more elongated elastic members is adjustably connected to the track system, and a carrier slidably mounted to the track system wherein the carrier is connected to the winch system and to the other end of each of the one or more elongated elastic members.

A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.

A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

The invention provides a take-off and landing system for an unmanned ship-borne unmanned aerial vehicle, which exerts good stability and can effectively solve a problem that the unmanned aerial vehicle cannot safely take off and land on a bumpy unmanned ship. The take-off and landing system for the unmanned ship-borne unmanned aerial vehicle, provided by the invention, comprises a take-off and landing fixing device, a take-off and landing hanging device and a take-off and landing control device, wherein the take-off and landing fixing device is arranged on the unmanned ship; the take-off and landing hanging device is arranged on the unmanned aerial vehicle; the unmanned aerial vehicle takes off from and lands on the unmanned ship through use of the take-off and landing control device to control coordination between the take-off and landing fixing device and the take-off and landing hanging device; and the take-off and landing control device comprises a take-off and landing process monitoring camera, a meteorological monitoring module, a ship body posture monitoring module, a wireless communication module and a remote control terminal. The take-off and landing system for the unmanned ship-borne unmanned aerial vehicle, provided by the invention, can be applied to the technical field of safety of water area operation equipment.

A system is disclosed whereby a sensor, communication device, or other payload may be lofted to an operational altitude and maintained over an area of interest for some time by a relatively inexpensive and disposable buoyant aircraft, then returned intact to its point of origin or another desired location by a reusable but also relatively inexpensive non-buoyant aircraft. Automatic unpiloted control is used for all stages of flight, including ascent, loiter, return, and landing Specialized equipment can be provided to simplify launch procedures, reducing the number of personnel required to operate the system.

An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for a small vessel. For retrieval, the aircraft hovers over a base apparatus having one or more rails which bound a space into which the aircraft can safely descend. When the aircraft's measured position and velocity are appropriate, the aircraft descends promptly such that a spanwise component on the aircraft engages the rails. The teeth restrain the aircraft in position and orientation, while the rails bring the aircraft to rest. Articulation of the rails is used to park the aircraft in a servicing station. Connections for refueling, recharging, and/or functional checks are made in preparation for launch. Launch is effected by removing connections and restraints and articulating the rails to put the aircraft in an appropriate position and orientation. The aircraft uses its own thrust to climb out of the apparatus into free flight.

Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

An unmanned aerial vehicle (UAV) storage and launch system, including: a UAV pod having an interior; and a telescoping UAV landing surface disposed in the interior of the UAV pod; where the telescoping UAV landing surface may translate up toward a top opening of the UAV pod, translate down into an interior of the UAV pod, or rotate relative to the UAV pod.

Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.

A system for use in monitoring, measuring, computing and displaying the volumes of internal liquid and gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of hydraulic oil and nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.

Two embodiments of a connector that can be mated without regard for its orientation are disclosed. One embodiment is mated and demated autonomously as part of a system for recovering, docking with, recharging and re-launching unmanned aerial vehicles. Another embodiment is employed on the decks of vessels to facilitate mating and demating of various equipment providing different functions to reconfigure the vessel. Because both embodiments are configured for connection irrespective of angular orientation over 360°, they are especially suited for harsh environments including autonomous operation, rough seas, darkness and the like.

The invention provides an unmanned aerial vehicle take-off or landing control system which comprises a magnet assembly arranged on the side of an unmanned aerial vehicle and a magnetic field assembly arranged on the side of a parking apron. An electrification coil is arranged in the magnetic field assembly. Current is introduced into the electrification coil. A supporting magnetic field is generated by the magnetic field assembly on the side of the parking apron, so that thrust acting on the unmanned aerial vehicle is formed. Resultant force is formed by the thrust and lift force or resistance in the unmanned aerial vehicle take-off or landing process to supplement the lift force or the resistance. The invention further provides an unmanned aerial vehicle take-off or landing control method. In the unmanned aerial vehicle take-off and landing processes, the current of the electrification coil is changed to form the even magnetic field, the thrust acting on the unmanned aerial vehicle is generated to supplement the lift force or the resistance in the take-off and landing processes, the safety performance of the unmanned aerial vehicle is improved, the use energy consumption of the unmanned aerial vehicle is reduced, and the service life of the unmanned aerial vehicle is prolonged.

Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

Methods and apparatus are provided for transporting a solid rocket motor, rocket or other object. A transport for an object suitably includes a trailer having a longitudinal axis. A tail support coupled to the trailer has a notch configured to receive a pin affixed to the object to prevent movement along the longitudinal axis during transport. A chock assembly includes a chock and a trolley, wherein the chock is configured to accept the solid rocket motor and to pivot about a rotation axis that is substantially perpendicular to the longitudinal axis of the trailer. By pivoting with the object, the rotable chock maintains intimate contact with the object during transport and/or elevation, thereby improving response to flexing of the transport and reducing the possibility of damage to the object.

The invention discloses a folded launching and withdrawing device for an unmanned aerial vehicle. The folded launching and withdrawing device comprises a base, a folded beam, a launching frame, a launching air cylinder, a traction cable, winch rollers and a pulley set. The tail end of the folded beam is hinged to the base, and the launching air cylinder is fixedly arranged at the end of an inner cavity of the folded beam. The two winch rollers are arranged at the end of the folded beam. The two ends of the traction cable connected with the launching frame are connected with the two winch rollers respectively in a winding mode along a traction line formed by the pulley set. The folded launching and withdrawing device is easy to store and hide after being folded, and is convenient to carry and transport flexibly, a slide is long after unfolding, launching force is large, high controllability is achieved, launching and withdrawing are integrated, fast and continuous launching and withdrawing cross work can be carried out, the large launching type application range is achieved, the device adapts to all carrier-based and vehicle-mounted maneuvering modes, operating can be maintained through a low-power fuel engine or motor, and other guarantees are not needed.

An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus. It can be used with low risk of damage, and requires only moderate accuracy in manual or automatic flight control.

The invention discloses an air-based launching device for unmanned aerial vehicles. The device comprises a sliding rail, a launching bracket and launchers. Each launcher comprises a plurality of launching cylinders, each launching cylinder comprises an ejection device, each ejection device comprises a single-double lug sheet structure, a spring device and a steel cable, and multiple swarm unmannedaerial vehicles can be placed. Before launching, the unmanned aerial vehicles are placed in the launching cylinders at first, and then the launchers are released by the launching bracket. During launching, the steel cables locking the spring devices are pulled out, the spring devices are unlocked, the unmanned aerial vehicles are pushed out of the launching cylinders under the thrust generated bythe spring devices in the ejection devices without damaging the structures and equipment of the unmanned aerial vehicles, and the unmanned aerial vehicles are launched. Compared with existing launching modes, the method has the advantages that the space use efficiency is high, a certain number of unmanned aerial vehicles can be launched at the same time, and the consumed time of an unmanned aerial vehicle cluster in the launching process is shortened; the secondary preparation time of the launchers is short, and the working efficiency is high.

A satellite communication system has a first deployment of a plurality of satellites deployed in a medium earth orbit and two later deployments of a plurality of satellites deployed in the medium earth orbit. The first deployment is spaced so that the second deployment may be easily deployed and interleaved into the first deployment. A ground terminal is used for communicating with the satellites in the first and second deployments.

Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.

The invention discloses a hand-throwing taking-off method and system for an unmanned aerial vehicle. The method includes the following steps that a user activates the unmanned aerial vehicle, the unmanned aerial vehicle gets into the pre-thrown state, a timer inside the unmanned aerial vehicle starts automatic countdown while the unmanned aerial vehicle gets into the pre-thrown state, and the unmanned aerial vehicle automatically judges whether a rotor wing is started for taking off or not by detecting the self-movement acceleration value G and vertically-upward speed value V. The system comprises a flight controller, an acceleration sensor, the timer and a warning device, wherein the flight controller is connected with the acceleration sensor, the timer and the warning device, and the flight controller controls the rotor wing of the unmanned aerial vehicle to be started. Compared with an existing mechanical remote-control taking-off mode, according to the hand-throwing taking-off method and system, a remote controller is not required in the whole taking-off process, the rapid and convenient taking-off effect of the unmanned aerial vehicle and intellectualized human-unmanned aerial vehicle interaction can be achieved, user operation is convenient, user experiences are improved, and use and popularization are convenient. In addition, by means of the hand-throwing taking-off method and system, personal injuries, possibly generated when the hand-throwing unmanned aerial vehicle takes off, to the user can be effectively avoided, and personal safety is effectively guaranteed.

The invention provides a launch and withdraw device of an unmanned aerial vehicle and a method for the launch and withdraw device, and the device comprises a base, wherein the base is connected with a support platform through a support frame; an angle adjustment mechanism is further arranged between the base and the support platform; the support platform is slidingly provided with a withdraw platform and a catapult platform; the catapult platform comprises a second connecting plate; a groove is formed in the second connecting plate; a clamping plate is slidingly connected onto the second connecting plate; a hole is formed in the second connecting plate; an elastic rope passes through the hole to be fixedly connected onto the support platform; the withdraw platform comprises a lower jaw and an upper jaw; the upper jaw is arranged at the upper part of the lower jaw; the upper jaw is provided with a flexible buffer strip; the end, close to the catapult platform, of the lower part of the lower jaw is provided with a hook; the lower jaw is internally provided with a recovery rack; the recovery rack is provided with an unmanned aerial vehicle attitude adjustment mechanism and an unmanned aerial vehicle pushing mechanism; a wedge-shaped block is arranged on the end, close to the catapult platform, of the support platform; a cam corresponding to the hook is arranged on the end, far away from the catapult platform, of the support platform. By adopting the launch and withdraw device of the unmanned aerial vehicle, straight path launch can be realized, the catapult launch efficiency is high, a withdraw process is accurate and stable, and the launch and the withdraw can be realized at the same time.