131results about "Anchoring installations" patented technology

Exemplary disclosed embodiments include systems, methods, and devices for a ground maneuvering system for aircraft. The systems, methods, and devices may include a ground maneuvering system including at least one processor in communication with at least one sensor and at least one maneuvering vehicle. The at least one maneuvering vehicle includes one or more processors in communication with one or more sensors. The one or more processors can be configured to sense, using the one or more sensors, an area associated with a plurality of areas, to determine a location within area, or to maneuver the maneuvering vehicle to the location. The maneuvering vehicle may also include a movement system for maneuvering the maneuvering vehicle in or around the plurality of areas, and a platform configured for an aircraft.

The invention discloses a marine mooring seat positioning device and a positioning and mounting method, the marine mooring seat positioning device is used for assisting in mounting a mooring seat, the mounting precision of the mooring seat is effectively improved, and rapid mounting of the mooring seat is achieved. Meanwhile, the mooring seat positioning device for the ship can assist in installing the mooring seat and can also detect the installation precision of the mooring seat so as to ensure that the bottom of the mooring seat accurately extends out of a deck by 3 mm.

A fire truck-mounted drone take-off and landing platform relates to the application field of fire-fighting drones and is used to improve the take-off and landing flexibility of fire-fighting drones. The fire truck-mounted drone take-off and landing platform includes three parts: a hydraulic lifting connection device, a drone take-off and landing slide, and a drone take-off and landing portal platform. The vehicle-mounted drone take-off and landing platform can meet the vehicle-mounted needs of drones. The fire truck reverses or drives forward into the drone take-off and landing portal platform, the hydraulic lifting connection device on the fire truck is locked and connected with the connecting plate of the drone take-off and landing slide, the fire-fighting drone lands on the drone take-off and landing plate, the landing gear falls into the V-shaped positioning groove of the drone take-off and landing plate, the locking strip drives the gear and rack to wedge the landing gear through the locking drive motor, so that the drone can go to the distant fire scene with the fire truck; for nearby fires, the fire-fighting drone can be unlocked from the drone take-off and landing slide of the drone take-off and landing portal platform and take off on the spot, giving full play to the flexibility of drones in participating in firefighting tasks.

A vertiport system includes a plurality of touchdown and lift-off (TLOF) platforms. The vertiport system also includes a final approach and take-off (FATO) area. The vertiport system also includes a driver configured to move the TLOF platforms with respect to the FATO area.

A landing pad for a vertically landing aerial vehicle includes granules or other particulate material arranged in a container. The granules or other particulate material are dispersed, thereby permitting embedding of legs of the aerial vehicle within the granules or other particulate material and withdrawal of the legs from within the granules or other particulate material.

Disclosed are an apparatus and a method for controlling a takeoff / landing pad structure by using a hexapod mechanism. The method for controlling a takeoff / landing pad structure by using a hexapod mechanism comprises the steps of: receiving eVTOL information from an eVTOL if the eVTOL prepares for landing; predicting the impact weight to be applied to the takeoff / landing pad structure if the eVTOL touches down, by using the received eVTOL information; calculating a first spring stiffness and a first damper damping required for the suspension according to the predicted impact weight; and controlling the suspension by setting the spring stiffness and the damper damping of the suspension with the calculated first spring stiffness and first damper damping.

A tie-down fixture for securing a rotary aircraft for transport. The tie-down fixture includes a central hub configured to couple with a main rotor hub of the rotary aircraft and having a keyhole formed therein, a plurality of arms extending from the central hub, and an eyelet extending from each of the plurality of arms.

A smart wheel chock includes a chock body including a ground engaging surface and a wheel engaging surface for engaging a wheel of a vehicle; a processor housed within the chock body; a position tracking sensor housed within the chock body, wherein the position tracking sensor is configured to detect a location of the wheel chock; a wireless communication module in communication with the processor and configured to transmit the location of the wheel chock; a power system configured to supply power to the processor and wireless communication module; and a visual indicator on the chock body, wherein the visual indicator is configured to be visible while the chock body is engaged with the wheel, and wherein the visual indicator includes a unique identifier for the smart wheel chock.

A reversible wheel chock can include a body portion having: a bottom face; a front face and a rear face extending upward relative to the bottom face, the front face having a front wall height, and the rear face having a rear wall height equivalent to the front wall height; a spine forming a top surface parallel to the bottom face, the spine defining apertures; a first chocking face spanning a first surface distance between the spine and the front face; and a second chocking face spanning a second surface distance between the spine and the rear face. The first surface distance and the second surface distance can be between 3 and 4 times greater than the front and rear wall heights. A handle can be attachable to the body portion via the apertures. A base pad can be attached to the body portion adjacent to the bottom face.

The present invention discloses a mounting assembly for an intelligent wheel chock device, comprising a first cylindrical mounting tube for accommodating the intelligent wheel chock device, a second cylindrical mounting tube, and a connector for connecting the first and second mounting tubes. The rear section of the first mounting tube is inserted into the second mounting tube, and the first and second mounting tubes are connected together via the connector. The second mounting tube has a cavity behind the rear end of the first mounting tube. A bottom cover is inserted into the rear end of the first mounting tube, and the bottom cover has a through hole connecting the cavity of the first mounting tube and the cavity of the second mounting tube. The present invention has the advantages of a simple structure, easy installation, and no need to modify existing wheel chocks.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

The invention discloses a control method of an energy accumulator oil supply hydraulic servo system of a shipborne helicopter mooring device, which belongs to the field of mechanical hydraulic control and comprises the following steps: establishing a mathematical model of the energy accumulator oil supply hydraulic servo system; based on the position of a helicopter probe rod, the speed track in the capturing process of a mechanical claw is planned; a smooth speed feedback signal is obtained through a tracking differentiator; generating a feed-forward control quantity by a feed-forward controller; designing an error active disturbance rejection controller comprising a feedback compensator and an extended state observer based on the mathematical model, and generating an error adjustment signal; and the feedforward control quantity and the error adjusting signal are synthesized, the parameters of the error active disturbance rejection controller are adjusted, a final control instruction is formed to drive a hydraulic servo system, and the mechanical claw tracks the planned speed track. The problem of flow-pressure nonlinearity in the oil supply process of the energy accumulator is effectively solved, the capturing speed tracking precision of the mechanical claw is improved, capturing impact is reduced, and the quick mooring device is suitable for helicopters of different tonnages.

The utility model relates to the technical field of aircrafts, and discloses a mooring tower which comprises a fixed table, a fixed tower arranged at the upper end of the fixed table, a movable tower hinged to the upper end of the fixed tower, a mounting platform arranged at the upper end of the movable tower, a winch arranged at the upper end of the fixed table and used for tightening a head cable at the front end of an airship, and a driving piece arranged on the outer wall of the fixed tower. The output end of the driving part is connected with the movable tower; the movable tower is hinged to the upper end of the fixed tower, when the mooring tower needs to be transported, the angle of the movable tower is adjusted through the driving piece, so that the traveling height of the mooring tower is reduced, the portability of the mooring tower is improved, and when the airship needs to be moored, the movable tower is rotated through the driving piece to be in butt joint with the fixed tower, so that the transportation efficiency is improved. The head mooring rope of the airship penetrates through the mounting platform to be connected with the winch, at the moment, the head mooring rope is tightened through the winch to fix the airship, so that mooring of the airship is rapidly completed, conversion of the two modes can be rapidly completed, and the mooring work efficiency is improved.

This aircraft position control system makes the position of an aircraft follow movement in a target landing point due to ship motion, and comprises: a processing unit for deck displacement estimation that estimates a first deck displacement of the target landing point, on the basis of attitude correction acceleration obtained by correcting acceleration of the aircraft and a relative position between the aircraft and the target landing point; a processing unit for deck displacement prediction that predicts a future second deck displacement of the target landing point, on the basis of the estimated first deck displacement; a filtering process unit that performs filtering process on the second deck displacement predicted by the processing unit for deck displacement prediction such that the relative position becomes zero; and a model prediction control unit that performs model prediction control based on the estimated first deck displacement and the filtering-processed future second deck displacement and that outputs a control quantity for controlling flight of the aircraft.

The consumption of stored energy by an unmanned aerial vehicle is reduced by raising the unmanned aerial vehicle through an unmanned aerial vehicle support device, and accordingly, the cruising distance is increased. An unmanned aerial vehicle support device 10 includes a loading unit 1 and a control unit that controls raising and lowering of the loading unit. The loading unit 1 is raised to a predetermined height to enable the unmanned aerial vehicle 100 to take off. An unmanned aerial vehicle support system includes a server 5 that can communicate with the unmanned aerial vehicle support device 10 and selects a route on which the unmanned aerial vehicle 100 flies and one or more unmanned aerial vehicle support devices 10 on the route based on movement information including at least a departure point and a destination of the unmanned aerial vehicle input from the outside.

A system automatically positions a drone (1) on a landing / take-off site (2) including a landing area defined by an outer boundary. The system positions and aligns the drone (1), landed at any location on the landing area, at a predetermined position on the landing area. The system includes a rope sling (5) which, in its initial position, extends substantially along the outer boundary of the landing area, and the ends of which are connected to a rope winch (6) located near or at the predetermined position, so that the rope sling can be retracted when the rope winch is actuated. The drone is provided with engagement means (3, 4) engageable with the rope sling (5) when the rope sling (5) is retracted, so that the drone (1) is pulled to the predetermined position and is correctly aligned at the predetermined position upon further retraction of the rope sling (5).

To prevent deformation and damage of a flying body caused by correction of an attitude of a position and a direction of the flying body, when the attitude is corrected after the flying body lands on a stage.SOLUTION: When a flying body 32 lands on a landing and takeoff surface 12a, a control device 16 moves any one position correction mechanism of position correction mechanisms 18R and 18L toward a center line O, and thereby corrects the attitude of the flying body 32. Then, the control device 16 moves the other position correction mechanism toward the center line O. Thereby, the flying body 32 is gripped by the position correction mechanisms 18R and 18L. When the flying body 32 lands on the position on the position correction mechanism 18 side, for example, the control device 16 previously moves the position correction mechanism 18R, and then moves the position correction mechanism 18L.SELECTED DRAWING: Figure 8

Embodiments of an active object mounting system secure an object of interest to a surface of a secured-to object 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.

It is desirable to provide an aerial vehicle such as a drone for maintenance and management of overhead power lines that is capable of flying for a long period of time without landing by receiving a supply of electric energy from overhead power lines or towers. A magnetic field power generation unit is attached to an aerial vehicle which generates energy using a magnetic field generated by overhead power lines, and the generated energy is used as a power source of the aerial vehicle, by which the aerial vehicle can continue flying for a long period of time. Additionally, by providing a power supply port on a tower supporting overhead power lines, the aerial vehicle can continue flying by charging a battery without landing. Further, by straddling or hanging from overhead power lines during flight, power consumption of the battery can be reduced, and long-term flight can be enabled.

To provide a drone storage box capable of suppressing temperature rise of a drone even in such an environment that a storage environment of the drone deteriorates outdoors, and protecting a control unit and the like from rainwater, dust and the like.SOLUTION: A drone storage box comprises: a drone storage section S1 having a top plate 2 that performs opening and closing operations, allowing a drone D to be stored and retrieved through an opened ceiling; a charging device 7a for charging the stored drone D; and a drone control device 7 including a communication unit 7c for communicating with external systems and with the drone D. The periphery is covered by a closing plate 3. The top plate 2 and the closing plate 3 are covered with a heat-shielding plate 11. An exhaust fan 20 for suppressing temperature rise of at least the drone storage section S1 in the internal space is provided at an appropriate location of the closing plate 3.SELECTED DRAWING: Figure 2

An apparatus can include a wheel chock. The wheel chock can include a body portion. The body portion can include: a bottom face; a first side face and a second side face extending upward relative to the bottom face; at least one chocking face positioned above at least one of the first side face or the second side face, wherein the at least one chocking face includes an angled surface; and a spine forming a top surface parallel to the bottom face, the spine adjoined to the at least one chocking face, and the spine defining apertures. The wheel chock can also include an elongated handle attachable to the body portion via the apertures, the elongated handle configured to maintain an upright, self-standing position.

The unmanned aircraft airport, unmanned aircraft system, patrol inspection system, patrol inspection method, control device, apparatus and storage medium, and unmanned aircraft cruising system relate to the field of unmanned aircraft and are used to optimize the structure of an unmanned aircraft airport. The unmanned aircraft airport includes a support base (1), a parking apron (2), a protective cover (3), and a protective cover opening / closing drive device (4). The parking apron (2) is attached to the top of the support base (1), the protective cover (3) covers the top of the parking apron (2), and the protective cover opening / closing drive device (4) is attached between the support base (1) and the protective cover (3). The protective cover opening / closing drive device (4) is configured to cause a bar linkage mechanism to drive the protective cover (3) to switch between an open position and a closed position. The unmanned aircraft airport is provided with the protective cover (3) for the parking apron (2). When the protective cover (3) is open, the unmanned aerial vehicle parks on the parking apron (2) and takes off from the parking apron (2). When the protective cover (3) is in the closed position, the protective cover (3) serves to protect the unmanned aerial vehicle and prevents external rain, impurities, and the like from damaging and contaminating the unmanned aerial vehicle.

A captive balloon support structure assembly comprising a captive balloon which is filled with a lifting gas having a lower density than the ambient air and is kept floating at a specific altitude above the ground. A three-dimensional wide-meshed supporting net that is tethered to the ground is placed over the captive balloon.

A flying machine storage container is provided that comprises multiple charging stations and a clamping mechanism. The clamping mechanism is configured to secure flying machines in the charging stations and securely close charging circuits between the storage container and the flying machines. A system for launching flying machines is also provided. The system comprises two regions and a transition region between the two regions. The two regions each constrain the positioning of a flying machine and the transition region enables a flying machine to move from the first region to the second region to reach an exit. A flying machine having sufficient performance capabilities will be able to successfully launch. Centralized and decentralized communication architectures are also provided for communicating data between a central control system, multiple storage containers, and multiple stored flying machines stored at each of the storage containers.

The invention relates to a method for starting a kite system (23), wherein the kite system (23) comprises a kite (14) and a gondola (25), and the gondola (25) is connected to the kite (14) via a line tree (24). The kite system (23) is coupled to a base station (16) via a traction cable (15). In an intermediate phase (28) of a starting process, a guide line (29) extends between the freely flying kite system (23) and the base station (16). In the method, the kite system (23) is controlled along a flight path such that the traction cable (23) is guided in a lateral direction (42) with respect to the wind direction (W) until the guide line (29) rests against the traction cable (15), the guide line (29) is moved until the guide line (29) lies in a guide line receiving area (55, 56) of the base station (16), said receiving area adjoining the traction cable (15), and the distal portion (32) of the guide line (29) is separated from the proximal portion (31) of the guide line (29). The invention also relates to a control unit for a kite device and to a kite device.

A storage device (10) that stores an unmanned aerial vehicle (30) includes a main body portion (20) having a magnet or a magnetic body (111, 112) for applying a magnetic force to the unmanned aerial vehicle (30) provided with a magnet (121, 122) on an upper surface.

To provide an improved airship technology that employs geodesic design principles in exoskeletons to reduce weight and create greater structural integrity, and provides superior aerodynamic characteristics, and enables faster cruising speeds.SOLUTION: A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles, in which the spokes flex and vary in length to produce a slope of the surface of the airship. The exoskeleton connects to a nose cone that includes a cockpit cabin for controlling operation of the airship from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation.SELECTED DRAWING: Figure 5

The utility model belongs to the aircraft wheel block technical field provides a new -type aircraft wheel block, including body, the body bottom evenly is equipped with a plurality of recessed cavities, the body top vertical downward is equipped with a plurality of through -holes, the body one side horizontal is equipped with a plurality of accommodating holes, the utility model discloses the slope of the body's isosceles trapezoid and wheel contact, to make the body can limit the aircraft after stopping, make it more safe and reliable parking state, avoid the situation of aircraft unplanned displacement, through two ropes and recessed cavity, through -hole and accommodating hole cooperation, to realize the placing and taking out operation of this device, the utility model discloses the polyurethane dyeing material is adopted, in addition to the overall structure of optimization design, reduce the weight of wheel block body, reduce the personnel load, in various use scene more easily identifiable.

A locking device for an aircraft is described, comprising a body adapted to be fixed to a support surface, a first ring and a second ring rotatable the one with respect to the other with respect to a rotation axis between a first angular position and a second angular position. The first and second ring enclose an area for the landing of the aircraft and are contained within the body. The locking device also comprises a plurality of cables, which connect the first ring to the second ring. The locking device is positionable in an unlocking position, wherein the first and second ring are in the first angular position, the cables are spaced from said area; or in a locking position, wherein the first and second ring are in the second angular position and the cables occupy a region of the area, so as to cooperate in contact with the aircraft to constrain it with respect to the support surface.

According to the present disclosure, there is provided a locking system for locking a vehicle or item of cargo in a position on a surface, the locking system comprising: an electromagnetic locking arrangement configured to be selectively operatable to attract the vehicle or item of cargo, thereby to lock the vehicle or item of cargo in the position on the surface.