47results about "Anchoring installations" patented technology

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.

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 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 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.

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).

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 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 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.

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.

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.

To provide a compact port which has a simple mechanism and can improve reliability when receiving cargo while suppressing costs. [Solution] The port of the present invention has a cargo receiving section that rotates around a rotation axis that extends at least vertically, and the cargo receiving section rotates by switching between a cargo receiving mode and a standby mode based on an external control signal. The control signal is a control signal transmitted from a mounting section suspended from an aircraft. The control signal is a control signal transmitted from another port. The control signal is a control signal transmitted from the aircraft. The control signal is a control signal transmitted from a management server that manages deliveries.

The present invention relates to a restraint (20) for an aircraft (1). The restraint (20) comprises a cylinder (50) including a housing (51) and a head (70) movable in translation relative to the housing (51) along an elevation axis (AXALT), said head (70) having three degrees of freedom in rotation respectively along a longitudinal axis (AXL) as well as a transverse axis (AXT) and the elevation axis (AXALT), said restraint (20) comprising a force-retaining element (40) surrounding the cylinder (50) and provided with a fixing (42) suitable for being secured to the aircraft (1).

To provide a flying object operation management system and a flying object operation management method for an airport, capable of increasing a utilization efficiency of the airport in the airport where flying objects having a large number of vertical takeoff and landing functions take off and land.SOLUTION: In a flying object operation management system that manages flight route planning, and takeoff and landing of a flying object at an airport with a plurality of parking lots, the flying object operation management system is featured in that the flying object operation management system sets a layered area constructed of at least one layer and an occupied area around the flying object in a sky of the airport; and the occupied area is set to a layered area in which the flying object flies and at least one layered area of layered areas vertically adjacent to this layered area.SELECTED DRAWING: Figure 1

A base station for an unmanned aerial vehicle (UAV) with a reconfigurable landing platform including alignment members, which engage the UAV and are repositionable between extended and retracted positions, and a drive mechanism, which is connected (secured) to the alignment members to facilitate extension and retraction thereof. During retraction, the alignment members engage the UAV and generally align a power source on the UAV with a charging hub of the base station, which facilitates not only charging of the UAV but proper closure of the base station.

To enable a drone to continue landing motion, even if a marker for landing cannot be temporarily recognized.SOLUTION: A landing system of a drone, which enable a drone mounted with a camera 14 to land on a charging port in which a marker is installed, comprises: a marker recognizing part 21 that recognizes a marker photographed with the camera and calculates position information on the charging port in a coordinate system of the drone; a self-position estimating part 22 that calculates position information on the drone in a reference coordinate system; and a command speed generating part 23 that calculates position information on the charging port in the reference coordinate system, using the position information on the drone in the reference coordinate system and the position information on the charging port in the coordinate system of the drone, and generates a command speed for enabling the drone descend toward the charging port. When the marker recognizing part cannot recognize the marker, the command speed generating part generates a command speed for enabling the drone descend toward the charging port, on the basis of the position information on the charging port in the reference coordinate system calculated when the marker has been lastly recognized.SELECTED DRAWING: Figure 3

This can improve the stability of the aircraft during takeoff or landing. [Solution] An assistance device according to one embodiment is an assistance device for assisting at least one of the takeoff and landing of an aircraft at the port of the aircraft, comprising a linear member having a first end connected to the port and a second end including a connecting portion connectable to the aircraft, and a levitation means for raising the connecting portion.

The present invention comprises: a first position detection unit that acquires the position of a mobile body that is moving; a second position detection unit that acquires the position of a target landing point set on the mobile body; a third position detection unit that acquires the position of an aircraft that lands on the target landing point; and a control unit that acquires positional relationships among the mobile body, the target landing point, and the aircraft on the basis of detection results of the first position detection unit, the second position detection unit, and the third position detection unit. The control unit acquires the relative positions of the mobile body and the aircraft on the basis of the position of the mobile body detected by the first position detection unit and the position of the aircraft detected by the third position detection unit, and acquires, as an offset position, the positional relationship between the mobile body and the target landing point on the basis of the position of the mobile body detected by the first position detection unit and the position of the target landing point detected by the second position detection unit.

A multi-takeoff and landing station system according to an embodiment may comprise: a control tower including one or more stages for takeoff and landing of a first type of aircraft; and a short-range takeoff-landing platform including a plurality of runways, each of which is located such that the farther from the control tower, the lower the position of the runway, and forms a predetermined gradient to guide takeoff and landing of a second type of aircraft

An aircraft tie-down device, comprising: a housing (110), wherein the housing accommodates a rope (120) for tying down an aircraft, the housing is provided with an opening (111) for the rope to enter / leave the housing, and the housing is configured to be capable of being connected to a ground anchor; a rope winding device (130), wherein the rope winding device is mounted to the housing and configured to wind / unwind the rope on / from the rope winding device; and a displacement damping mechanism (140), wherein the displacement damping mechanism comprises an elastic element (141), the rope bypasses the displacement damping mechanism between the opening of the housing and the rope winding device to interact with the elastic element, and the elastic element is configured to be displaced when a force from the rope exceeding a predetermined threshold is applied thereto, so as to reduce the length of the rope from the position where the rope leaves the rope winding device to the opening of the housing. The aircraft tie-down device allows for a certain displacement margin when the tie-down rope reaches a bearing limit, thereby enhancing the tie-down safety.

To provide an operation system of an unmanned aircraft that can determine a position of an unmanned aircraft, even at a place where it is difficult to use a positioning system using radio wave.SOLUTION: An operation system 10 is provided with: a connection line 13; a winding device 14 that makes tension act on the connection line 13; a feeding-amount detecting part 34 that detects a feeding amount of the connection line 13; a direction detecting part 35 that detects a direction of force acting on a part 13a to be detected of the connection line 13; and a position determining part 52 that determines a position of an unmanned aircraft 20. The position determining part 52 determines a distance from a predetermined reference position to the unmanned aircraft 20 on the basis of a detected result by the feeding-amount detecting part 34, and determines an azimuth direction of the unmanned aircraft 20 with the part 13a to be detected as a reference, on the basis of the detected result by the direction detecting part 35.SELECTED DRAWING: Figure 1

This invention relates to the field of aviation and marine technology, specifically disclosing a helicopter landing grille support, comprising a support web, a support ring, a base plate, and a manhole cover. The support web is annular, with its centerline vertically aligned. The top of the support web connects to the landing deck. The support ring is fixed to the inner circumference of the support web and supports the landing grille, which has honeycomb perforations. The base plate is located at the bottom of the support web, spaced apart from the support ring. The base plate closes the opening at the bottom of the support web, forming a cavity with the support web. The base plate has drainage holes and a manhole communicating with the cavity. The manhole cover is detachably mounted on the base plate and allows the manhole to be opened or closed. When debris accumulates in the cavity, operators can open the manhole through the cover and clean the debris without stopping the ship for maintenance, making the operation simple and convenient.