369results about "Helicopter landing platform" patented technology

A landing pad receives and stores packages delivered from an aerial vehicle are awaiting pickup from an aerial vehicle. The landing pad can be placed outside of a window and can contain a transmitter for sending out an identification signal via radio frequency to aid aerial vehicles in finding the landing pad. The landing pad contains a landing platform with a trapdoor that leads to a storage compartment. The trapdoor can be configured to only open when it receives a signal from an authorized aerial vehicle. The storage compartment can be accessed via a storage compartment door which can contain a locking mechanism. The storage compartment can be climate controlled. The landing pad can also have a transmitter that emits sounds to discourage animals from nesting on or near the landing pad. The landing pad can also include a solar power generator as a source of electrical energy.

An unmanned aerial vehicle (UAV) delivery apparatus is provided. The UAV delivery apparatus may include at least a pole and a landing platform. The pole of the present invention may have an extended length with a bottom end and a top end. The bottom end is securable to a surface to support the pole in an upright position. The landing pad of the present invention is attached to the top end of the pole and includes a substantially flat upper surface. The upper surface is sized to receive a package from a UAV.

The Unmanned Aircraft Systems ground support platform is a portable, multifunctional apparatus to accommodate UAS (Drone, UAV) landings, takeoffs, idle time, maintenance, retail merchandise product display and package delivery support within the UAS recreational and business industry. The Unmanned Aircraft Systems ground support platform will provide stability and cleanliness of a Unmanned Aerial Vehicle. Ownership identification is intergraded into the base platform.

An apparatus and method of charging and housing of an unmanned vertical take-off and landing (VTOL) aircraft is disclosed. The apparatus includes an accommodator to accommodate an aircraft, a landing platform on which the aircraft lands, a housing portion to monitor state data by housing or charging the aircraft, and a sensor to assist in landing of the aircraft by allowing the aircraft to communicate with the apparatus. The apparatus enhances operational efficiency by reducing a travel time of the aircraft.

A multi-zone battery station is provided, comprising a plurality of landing areas configured to support a UAV. The battery station may permit battery life to be reloaded onto a UAV, which may include recharging a battery of the UAV or exchanging the UAV battery for a new battery. The different zones may accommodate different UAV types, different battery types, or operate in accordance with different energy provision rules. A marker may be provided on a landing area to aid in guiding the UAV to an appropriate landing area.

A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and / or payload capacity.

A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor / generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor / generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator. Additionally, the generator is employable as a motor, receiving energy from the storage system for traction power to the associated aircraft wheel. An induction grid or a surface mounted conductive layer mounted into or onto a runway is employed for transferring energy to and from the motor / generator.

A drone receiving system having a tray configured to function as a landing pad for the drone delivering a package as well as a nest for the package, wherein the tray is associated with at least a mounting arm for mounting the drone receiving system to an outside of a structure, wherein the at least a mounting arm is expandable to move the tray away from the structure, so that the drone can deliver the package without being obstructed by the structure, and wherein the at least a mounting arm is retractable to move the tray after package delivery toward the structure, so that the package can be unloaded from the tray from inside the structure.

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.

A helipad motion compensation system for a vessel includes at least one controllable length actuator operatively coupled between the helipad and the vessel. The system also includes an attitude sensor disposed on at least one of the helipad and the vessel. The sensor produces signals corresponding to change in attitude of the helipad. A controller is in operative communication with the sensor and is arranged to operate the at least one actuator. The actuator is operable to substantially maintain an attitude of the helipad to compensate for motion of the vessel.

A buried subsurface pit for use beneath a surface across which aircraft travel for servicing aircraft is provided with a pit latching mechanism for holding and releasing a pit lid mounted atop the buried pit. A shallow latch operating lever storage recess is defined in the upper surface of the pit lid. An actuator rod passageway is formed in the pit lid and extends between the latch operating lever storage recess and the undersurface of the pit lid. A catch is located in alignment with the actuator rod passageway at the undersurface of the pit lid. The catch is mounted for rotation about a horizontal axis of catch rotation. An actuator rod is disposed for longitudinal, reciprocal movement in the actuator rod passageway. A latch operating lever has opposing latch handle and actuator rod engaging ends. The latch operating lever is mounted between its opposing ends to the pit lid proximate the upper surface of the pit lid for rotation on a fulcrum about a horizontal latch operating lever axis of rotation which is located just below the upper surface of the pit lid. The latch operating lever is movable between a stored position in the latch operating lever storage recess and an actuator rod engaging position in which the latch handle end of the latch operating lever is raised out of the latch operating lever storage recess so that the actuator rod operating end of the lever depresses the actuator rod to disengage the catch.

An aircraft servicing system (10) includes a tarmac-servicing system (500). The tarmac-servicing system (500) includes an aircraft-mating element (510) that is mounted and extendible from within an area of a tarmac (502) to couple with an aircraft (504). The tarmac-servicing system (500) supplies primary services to the aircraft (504), such as fuel, air, electrical power, water, coolant, potable water, and gray water. A method of servicing the aircraft (504) includes aligning a primary servicing port (512) of the aircraft (504) over a primary servicing area of a tarmac (502). A tarmac-servicing element (510) is extended out from the tarmac (502) to the aircraft (504). The tarmac-servicing element (510) is aligned and connected to the primary servicing port (512). Primary services are supplied and removed to and from the aircraft (504) in response to the tarmac-servicing element connection with the primary servicing port (512).

A Safe Runway Aircraft Arrival and Departure System Using Split Runway Design comprising a linear runway divided into separate landing strip and takeoff strip portions. Arriving aircraft land on the designated landing strip portion of the runway, while departing aircraft take off from the designated takeoff strip portion of the runway. The landing and takeoff portions may be separated by a defined buffer zone utilized by aircraft for taxiing to and from a terminal. Existing runways may be readily converted into two designated portions for arriving and departing aircraft, thereby significantly increasing the number of aircraft arrival and departure sequences, reducing the likelihood of aircraft runway incursions, eliminating dangerous intersection takeoffs, and conserving jet fuel.

Arresting beds for decelerating vehicles, especially passenger air-crafts unable to stop on available run-way, including a vehicle arresting system. The vehicle arresting system also includes a bed filled with foamed glass aggregate with particle sizes ranging from 0.25 cm to 15 cm and nominal void fractions from about 70 to 98%, and a top cover covering the upper surface of the bed of foamed glass aggregate.

A drone delivery system provides to send or to receive the package conveniently and safely without going out of the building by using the platform installed at the vicinity of the window. The drone delivery system includes the drone having a first docking device, a standard box having a second docking device corresponding to the first docking device and a third docking device and a platform having a fourth docking device corresponding to the third docking device.

The invention discloses an unmanned aerial vehicle routing inspection base station. The base station comprises a supporting frame, a charging base, a solar cell panel, a protective apparatus and an ultrasonic distance-measuring module. The charging base serves as a unmanned aerial vehicle landing platform and is provided with two stages of charging electrodes that are in contact with two charging interfaces designed in an unmanned aerial vehicle in a matched way to charge the unmanned aerial vehicle; the protective apparatus is mounted on the charging base; the interior of the protective apparatus serves as a parking space for the unmanned aerial vehicle; the two stages of charging electrodes are positioned in the protective apparatus; the top surface of the protective apparatus adopts an openable structure; the solar cell panel is used for supplying power to the unmanned aerial vehicle and the protective apparatus; and the ultrasonic distance-measuring module is mounted in the internal wall surface of the protective apparatus and used for measuring the distance between the unmanned aerial vehicle and the charging base. The unmanned aerial vehicle routing inspection base station has the advantages that the unmanned aerial vehicle can be automatically charged, so that long-distance routing inspection of the unmanned aerial vehicle is realized; and in addition, the protective apparatus is designed, so that the charging base can be protected, and the influence of weather on the unmanned aerial vehicle routing inspection base station can be greatly reduced.

Apparatus and methods for improved transportation functionality. In one aspect, the invention comprises an improved and highly integrated transportation apparatus adapted to bring a plurality of different modalities in close physical proximity for enhanced efficiency. One exemplary embodiment comprises a multi-level structure disposed in a substantially contained low depth body of water (e.g., bay) and proximate one or more land masses to facilitate service via rail, land vehicle, ships, and ferries. Multiple long-length runways are also provided on the substantially planar top surface to accommodate air traffic. A monorail or similar system is also employed to allow ready movement between the various transportation interfaces.

The present technique provides a system and method for automatically releasing a power connection between an aircraft and a ground power unit. The power connection may have a release mechanism, such as a straight-pull coupling, which disconnects in response to movement of the aircraft or the ground power unit. The release mechanism also may disconnect in response to a critical tension within a power cable of the power connection. The power connection also may have a rotatable mount for the release mechanism, such that the power cable is alignable with tension in the power cable. The present technique also may have a variety of sensors to trigger a power shutdown and automatic release of the power connection.

The invention discloses a goods receiving device for an unmanned aerial vehicle. The goods receiving device is suitable for being mounted on an outdoor wall, and the goods receiving device comprises a goods receiving basket used for receiving goods and suitable for being arranged on the outdoor wall, a stopping station used for stopping the unmanned aerial vehicle and arranged on the goods receiving basket or outdoor wall, an image identification device used for guiding the flight direction of the unmanned aerial vehicle and arranged on the outdoor wall opposite to the goods receiving basket, a locating device used for locating the stop position of the unmanned aerial vehicle, arranged on the outdoor wall and located above the plane with the stopping station, and a power supply module respectively connected with the image identification device and the locating device to supply power for the image identification device and locating device. According to the goods receiving device, the unmanned aerial vehicle can precisely stop on the stopping station and throw the goods to the goods receiving basket, even if the user is not at home, the user can timely receive the goods.

The invention provides a take-off and landing platform for assisting an aircraft to take off and land in a bumpy environment. The take-off and landing platform comprises a fixing plate and an attitude adjustment seat, wherein the fixing plate is used as a platform where the aircraft takes off and lands, and is used for fixing the aircraft before the aircraft takes off; the attitude adjustment seat is mounted on the lower side of the fixing plate and is used for stabilizing a space attitude of the fixing plate; and the attitude adjustment seat is at least provided with two degrees of freedom capable of rotating around the X axis and the Y axis. The multi-axis aircraft is fixed on the fixing plate before taking off, and the attitude adjustment seat dynamically stabilizes the attitude of the aircraft, so that the aircraft can be prevented from swinging back and forth, and good take-off conditions are supplied to taking off; and the stable fixing plate can supply a good landing environment to the multi-axis aircraft.

A visual aid for landing helicopters includes a plurality of weighted bases and a plurality of lights designed such that they can identify a helicopter landing zone during nighttime or during the bright sunlight. The components of the visual aid are designed to provide rapid identification of the landing zone, whether the pilot of the helicopter is flying with his unaided eye or with typical night vision goggles. The weighted bases have a large surface area and are coated with a highly visible fluorescent paint. The lights are designed to emit light having wavelengths, intensities and beam patterns which will not overwhelm night vision goggles but which will be acceptably visible to pilots flying without night vision goggles. The lights and weighted bases are color-coded such that they identify both the perimeter of the landing zone and the wind direction within the landing zone.

A heliport is formed by the assembly of a planar member including longitudinally-extending deck materials, each of which has a longitudinally-extending T-slot formed in the upper side thereof and is connected to a plurality of deck slats. Each deck slat is of generally I-beam configuration, with the lower flange thereof having a plurality of longitudinally-extending striations. A plurality of fixture blocks is provided, with each fixture block having a hole therein and including a plurality of striations for cooperatively engaging the striations in the lower flange of a deck slat. The head of a carriage bolt is disposed in the T-slot of the longitudinal deck materials, and extends through the fixture block, and is connected at its opposite end to a deck slat by a washer and nut, thereby providing a rigid interconnection between the deck slats and the planar member.

The invention discloses a quickly assembling block which comprises aluminum honeycomb composite structure plates (1), wherein groove-shaped frames (2) are installed on four side surfaces of each aluminum honeycomb composite structure plate (1); bolt holes (3) are formed on the groove-shaped frames (2); and bolt mounting holes (4) are arranged on the aluminum honeycomb composite structure plates (1) and are positioned at the bolt holes (3). In the invention, the four sides of each aluminum honeycomb composite structure plate can be connected with four aluminum honeycomb composite structure plates through bolts; and the aluminum honeycomb composite structure plates which are connected together sequentially can be horizontally arranged to form a plane, can be vertically arranged to form a wall body and can be arranged horizontally and vertically to form a box body. In addition, because the aluminum honeycomb composite structure plates are connected rigidly, the plane assembled by the invention can neglect the unevenness of the ground and can be used for severe environment.

The invention provides a detachable helicopter landing platform. The detachable helicopter landing platform is formed by splicing a plurality of triangular base plates. Telescopic supporting legs are arranged at three vertex angles of each base plate, and snapping grooves or protrusions are arranged on three edge lines of the base plates, the adjacent spliced base plates are mounted and spliced through the snapping grooves and the protrusions, and the snapping grooves and the protrusions are strengthened and fixed through one or more fixing screws. The platform has the advantages of being simple in structure, convenient to mount and easy to manufacture, and helicopters can be landed on uneven earth surfaces.

Arresting beds for decelerating vehicles, especially passenger air-crafts unable to stop on available run-way, including a vehicle arresting system. The vehicle arresting system also includes a bed filled with foamed glass aggregate with particle sizes ranging from 0.25 cm to 15 cm and nominal void fractions from about 70 to 98%, and a top cover covering the upper surface of the bed of foamed glass aggregate.

The invention relates to a goods receiving and sending system for an unmanned aerial vehicle (UAV) and a method of receiving and sending goods. The goods receiving and sending system for the UAV comprises a support assembly and a barrier assembly, wherein the support assembly comprises a take-off and landing platform which can be mounted on a building; the take-off and landing platform is providedwith a working surface; the working surface is provided with a working area for the landing of the UAV and the placement of the goods; the barrier assembly comprises a barrier board and a movable door; the barrier board is provided with a pick-up and placement opening; a user can pick up or place the goods from or on one side of the barrier board by virtue of the pick-up and placement opening; the movable door is movably mounted on the barrier board; the movable door can cover the pick-up and placement opening; and the working area is arranged on the other side of the barrier board to enablethe barrier board to be positioned between the building and the working area so that the barrier board and the movable door can jointly separate the user from the UAV. The goods receiving and sendingsystem for the UAV is more secure.

A modular fire prevention flooring system includes a plurality of fire prevention flooring planks. Each plank is generally tubular and forms a drain channel. Fluids spilled onto the upper surface of the flooring system may drain through a plurality of drain holes formed in the upper surface of the planks. The planks may further include a metal filler positioned within the drain channels to stop combustion of burning fluids spilled into the drain channels. The metal filler may break up burning liquids and remove heat therefrom. In some embodiments, a purging fluid may be flowed through the planks to purge any spilled fluids therefrom.