83results about "Anchoring installations" patented technology

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 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 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.

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.

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.

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.

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.

A locking device (1) for an aircraft is described, comprising a body (2) adapted to be fixed to a support surface (S), a first ring (3) and a second ring (4) rotatable the one with respect to the other with respect to a rotation axis (I) between a first angular position (61) and a second angular position (63). The first and second ring (3, 4) enclose an area (6) for the landing of the aircraft and are contained within the body (2). The locking device also comprises a plurality of cables (5), which connect the first ring (3) to the second ring (4). The locking device (1) is positionable in an unlocking position, wherein the first and second ring (3, 4) are in the first angular position (61), the cables (5) are spaced from said area (6); or in a locking position, wherein the first and second ring (3, 4) are in the second angular position (63) and the cables (5) occupy a region (63) of the area (6), so as to cooperate in contact with the aircraft to constrain it with respect to the support surface (S).

A platform (1) for receiving an airship (2) comprising a mooring mast (3) with a light (4) and a circular light beacon arrangement (5), referred to as the safety zone, centered on the mooring mast, comprising: a first zone (6), referred to as the take-off zone, circular in shape, delimited by a plurality of lights (7), referred to as guide lights, arranged on a circle centered on the mooring mast, and of predetermined radius (8); a second zone (9), referred to as the safety zone, annular in shape, centered on the mooring mast, delimited by said plurality of lights and a plurality of lights (10), referred to as perimeter lights, arranged on a circle centered on the mooring mast, the ring having a predetermined radial distance (11). Figure 1

The invention relates to the technical field of hydraulic pressure, in particular to a restraining device with accurate force releasing and buffering functions and a restraining method. The restraining device comprises an outer cylinder (2) and an inner cavity (8). The outer cylinder (2) and the inner cavity (8) can slide and be limited relative to each other; a square hole is formed in the oil guide rod (709), the square hole is formed in the auxiliary valve sleeve (707), the square hole is communicated with the inner space of the oil guide rod (709), and when the square hole is pushed out of the valve sleeve, the square hole can be communicated with a low-pressure space (14) and a high-pressure space (15); and the guide rod (704) and the oil guide rod (709) are arranged on the piston and can move along with the piston. The restraining device has the advantages of being simple in structure, easy to maintain and high in reliability, and has the characteristics of repeated use and accurate release.

A vertiport transport system is disclosed. The vertiport transport system includes: a dual-worm shaft including a first worm and a second worm disposed opposite each other; a worm gear coupled between the first worm and the second worm; a vertically movable body supported by the worm gear and allowing an urban air mobility (UAM) aircraft to be loaded thereon; and a drive unit connected to the first worm and the second worm and rotating the first worm and the second worm in the same direction or in different directions.

The invention relates to the technical field of aircraft fixing devices, in particular to a wind-resistant fixing system for a take-off and landing plate.The wind-resistant fixing system for the take-off and landing plate.The wind-resistant fixing system for the take-off and landing platea.The wind-resistant fixing system for the take-off and landing plateau comprises a take-off and landing plateau and at least one aircraft tying ring, the take-off and landing plateau comprises a concrete base, a fixing steel plate base, a track steel plate base and a concrete back-pressure fixing base; the machine tying ring is movably arranged in the track structure and can move to any position of the track structure along the track structure, so that the machine tying ring can meet the requirements of different machine types for different fixing points, and can be flexibly combined and replaced according to the parameters such as the size and the weight of the machine types to fix various machine types; the adaptability of the wind-resistant fixing system of the takeoff and landing pad is obviously improved; and moreover, the concrete back pressure fixing base performs back pressure reinforcement on the rail steel plate base, so that the overall strength of the landing pad is improved, the stability and durability of the landing pad are effectively improved, and large-scale use is facilitated.

The embodiment of the utility model discloses an aircraft mooring rope take-up machine which comprises a base, a take-up tool, a rope guide mechanism and a driving mechanism, a plurality of trundles are arranged at the bottom of the base, the driving mechanism is arranged on the base, the take-up tool is installed on the driving mechanism, and the rope guide mechanism is correspondingly arranged on the base. The rope belt guiding mechanism is used for guiding, then the driving mechanism is used for driving the belt winding tool to wind, the action of manually squatting on the ground to wind the rope is omitted, efficiency and uniformity are greatly improved, and meanwhile a user can conveniently carry the wound airplane mooring rope.

An installation comprises a floating platform to facilitate mooring, payload transfer and support operations for waterborne lighter-than-air aircraft such as airships and hybrid lift air vehicles. A floating platform, anchored from below, is equipped with a centrally mounted mooring mast (2). A waterborne aircraft (8) can be secured by attaching its nose to the central mooring mast via an articulated coupling that leaves the aircraft (8) free to rotate in any direction necessary to align with prevailing wave and wind forces. Additionally, the platform includes a rotatable deck and jetty structure (3, 4) incorporating one or more hinged boarding ramps (5) that are arranged to turn freely about the centre of the platform and so maintain heading alignment with a moored aircraft, whilst providing a secure access path (13) between a service boat (12) and the moored aircraft (8), irrespective of movements induced by wave and wind forces.

A locking system 100 for locking a vehicle such as an aircraft 300 or item of cargo in a position on a surface, the locking system comprising: an electromagnetic locking arrangement 110 which may be installed in the ground of a runway or deck of a cargo ship and is configured to be selectively operatable to attract the vehicle 300 or item of cargo, thereby to lock / maintain the vehicle or 10 item of cargo in the position on the surface. The system prevents unauthorised or un-expected movement of objects such as aircraft or items of cargo. The locking arrangement 110 may include a plurality of electromagnets 112 or electromagnetic locks 11’’ in different positions which may be controlled by a remotely located controller 120 to control multiple objects providing improved air traffic control. A locking status indicator system 130 may be included. For example an aircraft with wheels 312 or a helicopter with skids may be formed of magnetic material such as steel which is held in position on the ground by the electromagnet 112. An override system may be provided.

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.

An aerostat tether, anchorage, and tether spool system which extends the “On Station” uninterrupted intervals of service for which a “Lighter Than Air” (LTA) aerostat may stay aloft at its designated altitude without requiring retrieval for ground service. Anchoring vessels are provided at both the aerostat and ground control ends of the tethered system which enables remote control of varying choices for bi-directional gas flow patterns within the tether which better facilitate continuous lift gas maintenance and emergency control. The gas routing is selectively controlled per best practice toward the constant filtering and scrubbing of the lift gas within both the aerostat and the tether restraining the aerostat. The system uniquely provides for a very rapid switch-out of tethers by having a full “replacement tether spool” on the ground at the ready which is pre-wound, pre-filled, and sealed with fresh lift gas where it is available at all times for rapid changeout. Quick tether replacement is accomplished by interchangeable quick disconnect fittings at both ends of a hollow tether with a hollow piston valve stem to provide a simple process of unplugging the tether at both the aerostat to close the valves and ground terminal ends and then plugging in the replacement tether to open the valves and reinstituting deployment facilitated by the unique tether spool and anchoring system. The system also enables the effective prevention and dissipation of damage due to torque forces being applied to the tether by a weathervaning aerostat. This is accomplished through counter rotation being applied to the tether at the most advantageous and effective source of tether / aerostat union, at its point of attachment at the aerostat end since the tether attachment point (TAP) is where damage to the tether is most likely to occur. Also favorable to the longevity of service, the aerostat system provides improvements of electrical strike / static build-up dissipation as well as superior tether terminal end preparation, interconnection speed, and short turnaround repair times. The entire aerostat system is designed for plug and play usage and versatility.

A drone takeoff and landing system according to an embodiment comprises: a drone including a through-hole; and a landing pad including an extension member which can pass through the through-hole, wherein, when the extension member of the landing pad passes through the through-hole of the drone, an eddy current may occur between the through-hole and the extension member to cause magnetic braking of the drone.

The present application relates to a kind of helicopter blade mooring device, the device includes longitudinal feed mechanism, transverse feed mechanism and vertical feed mechanism;Longitudinal feed mechanism includes two longitudinal beams, the longitudinal motion beam of guiding movement assembly between two longitudinal beams, the longitudinal driving structure for driving longitudinal motion beam movement;Transverse feed mechanism includes the transverse motion column of guiding movement assembly on longitudinal motion beam and along vertical extension, the transverse driving structure for driving transverse motion column movement;Vertical feed mechanism includes the vertical motion beam of guiding movement assembly on transverse motion column, the vertical driving structure for driving vertical motion beam movement;Vertical motion beam is equipped with support limiting structure, support limiting structure includes the support bottom wall for supporting helicopter blade and the two limiting side walls for limiting the transverse movement of blade.The present application effectively solves the problem of safety accident and mooring efficiency low in prior art due to manual mooring blade.

This utility model discloses a drone fixing device, including a base and multiple locking mechanisms. The multiple locking mechanisms are spaced apart on the base. Each locking mechanism includes a stop block, a locking seat, and a locking tongue. The stop block and locking seat are spaced apart. The locking tongue is slidably connected to the locking seat. An elastic element connects the locking seat and the locking tongue, driving the locking tongue to move closer to the stop block. The base, stop block, and locking tongue form a locking groove for locking the drone's legs. The locking seat has a sliding groove extending to the side wall and end of the locking seat. A connecting rod is rotatably connected to the locking tongue. A lever is fixedly connected to the end of the connecting rod away from the locking tongue, and the lever can slide in the sliding groove. This drone fixing device can easily fix the drone's position, improving ease of use.

The utility model relates to the field of airplane parking discloses a kind of airplane ground parking wheel blocking mechanism, including two cover plates, two the cover plate is respectively fixed in the front side, rear side of two wheel blocking main part, the outside of two the cover plate is respectively provided with slot, between two the wheel blocking main part is equipped with two U-shaped rods, two the U-shaped rod both ends are respectively slidably inserted in two slots, two the wheel blocking main part are all triangular shape, the side of two the wheel blocking main part is all set to degree inclined plane shape, the outer wall left side, right side of two the wheel blocking main part is equipped with several bosses.In the utility model, through the synergies of cover plate, wheel blocking main part, slot, U-shaped rod and boss, it is favorable to the limiting blocking of airplane wheel, and simultaneously can connect two wheel blocking main parts, can improve its resistance to wheel, can effectively jointly bear greater pressure, to enhance the overall security.

To provide a system and a method for a structure scan using an unmanned aerial vehicle.SOLUTION: Some methods include: accessing a three-dimensional map of a structure; generating facets based on the three-dimensional map, the facets each being a polygon on a plane in a three-dimensional space that fits to a subset of the points in the three-dimensional map; generating a scan plan based on the facets, the scan plan including a sequence of poses for an unmanned aerial vehicle to assume to enable capture, using image sensors of the unmanned aerial vehicle, of images of the structure; causing the unmanned aerial vehicle to fly to assume a pose corresponding to one of the sequence of poses of the scan plan; and capturing one or more images of the structure from the pose.SELECTED DRAWING: Figure 6

According to the present invention, the efficiency of acquiring measurement data using an aircraft can be improved. [Solution] A control system for controlling the operation of an aircraft equipped with a measurement sensor for measuring a target area, comprising: a state determination unit that determines the state of preparations for the measurement data acquisition operation to acquire measurement data of the target area using the aircraft; and a corresponding operation determination unit that, when the state determination unit determines that the preparations for the measurement data acquisition operation are incomplete, causes the aircraft to perform a predetermined first operation, prohibits the aircraft from performing a predetermined second operation, or displays predetermined information on a display unit.