382results about "Seaplanes" patented technology

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

A craft includes a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

To provide an autonomously flying unmanned aircraft freely landing on and leaving the water and its floats that can realize acoustic positioning by SBL by dispersively arranging a plurality of hydrophones in a limited space of the unmanned aircraft.SOLUTION: Lower portions of six arms 11 extending radially from a fuselage of a water-air combination drone 1 are respectively provided with float parts 14 via connectors 16. The float parts 14 sink under the water surface when the water-air combination drone 1 lands on the water surface to generate buoyancy in the water-air combination drone 1 so that the water-air combination drone 1 stays on the water surface. The float part 14 is composed of a columnar main body part 14a and a cap-like or conical projection part 14b extended downward from the main body part, and a hydrophone 20 is mounted inside the projection part 14b. The hydrophone 20 is fixed at a position and in such a posture that a pressure sensor 20a attached to an end portion of the hydrophone 20 can detect a sound wave in the water when the aerial combination drone 1 / aerial drone 1A lands on the water.SELECTED DRAWING: Figure 3

The sea and air amphibious robot comprises a support, a machine arm assembly, an air propelling assembly, an underwater propelling assembly, a shell and a waterproof cabin, the shell is fixedly connected to the support, the waterproof cabin is installed in the shell, the machine arm assembly comprises a plurality of machine arms, and the machine arms are symmetrically connected to the two sides of the support correspondingly; the air propelling assembly comprises a plurality of air propellers, the underwater propelling assembly comprises a plurality of underwater propellers, the air propellers and the underwater propellers are installed on the multiple machine arms correspondingly, the installation positions of the underwater propellers are lower than the installation positions of the air propellers, and the buoyancy of the sea and air amphibious robot in water is larger than the gravity. When the sea-air amphibious robot statically floats on the water surface, at least part of each air propeller is located above the water surface, and each underwater propeller is located below the water surface. According to the sea and air amphibious robot, efficient propelling of the robot in water and air media can be achieved.

The invention provides a tailstock type tailless layout amphibious aircraft adopting foldable wings and a design method, and relates to the field of amphibious aircraft design. According to the invention, aiming at a tailless-layout tailstock-type amphibious aircraft, by designing a foldable wing mechanism, the wings are unfolded to keep a high aspect ratio layout during air cruise, and the wings are folded to form an envelope layout for a fuselage during water surface dwelling and stopping; therefore, the aerodynamic performance requirement of the tailless layout tailstock type amphibious aircraft in an air cruising mode and the requirement of the tailless layout tailstock type amphibious aircraft in a water surface dwelling mode for the gravity center stabilizing distance and the floating stability are met, and the tailless layout tailstock type amphibious aircraft can take off quickly under the high sea condition. The problems that the relative positions of the gravity center, the pneumatic focus and the stable center of a traditional tailstock type fixed wing aircraft in the water surface floating state and the air cruising flight state are difficult to design, and the stability of the aircraft in the water surface floating state is difficult to guarantee through a traditional layout design are solved.

In crafts that have a hydrofoil, a locking mechanism can be used to lock the hydrofoil in place (e.g., in a retracted position or in a deployed position). However, the forces experienced by the hydrofoil, especially when in the deployed position, can cause strain on the locking mechanism, which can lead to jamming or failure. The embodiments presented herein provide a locking mechanism that can be used to avoid this problem. In one embodiment, the locking mechanism uses a pin that is movable along a single axis for engaging / disengaging a. portion in a catch that is shaped to receive the pin. In another embodiment, a rear strut of the craft is rotatable, allowing the rear strut to both support the rear hydrofoil and act as a. rudder of the craft when in water.

The invention provides a water spaceship main hull with small head water resistance, tail water assisting and a rudder braking function. The water spaceship main hull is composed of a square main cabin section with the length of a, the width of b and the depth of c, a main hull head with the top view sharp and round and the side view round corner, a main hull tail with the top view sharp and round and the side view triangular rear view inverted square groove, the brake rudder and a water tumbler drain hole. The device has the effects of energy conservation, safety and high speed. The appearance of the main ship body has a unified resistance-reducing and energy-saving safety standard and does not follow the meaning of a designer any more.

The invention provides a water spaceship main hull with small head water resistance, tail water assisting and a rudder braking function. The water spaceship main hull is composed of a square main cabin section with the length of a, the width of b and the depth of c, a main hull head with the top view sharp and round and the side view round corner, a main hull tail with the top view sharp and round and the side view triangular rear view inverted square groove, the brake rudder and a water tumbler drain hole. The device has the effects of energy conservation, safety and high speed. The appearance of the main ship body has a unified resistance-reducing and energy-saving safety standard and does not follow the meaning of a designer any more.

The invention provides a water spaceship main hull with small head water resistance, tail water assisting and a rudder braking function. The water spaceship main hull is composed of a square main cabin section with the length of a, the width of b and the depth of c, a main hull head with the top view sharp and round and the side view round corner, a main hull tail with the top view sharp and round and the side view triangular rear view inverted square groove, the brake rudder and a water tumbler drain hole. The device has the effects of energy conservation, safety and high speed. The appearance of the main ship body has a unified resistance-reducing and energy-saving safety standard and does not follow the meaning of a designer any more.

The amphibious transport plane based on the ground effect comprises a plane body, a main wing and a vertical empennage, the main wing is located behind the gravity center of the plane body, a pair of forward-swept front wings are further arranged in front of the gravity center of the plane body, and the vertical empennage is arranged on the main wing; a first propeller is arranged on each of the left and right sides of the head of the fuselage; a pair of second propellers is arranged at the front end of the main wing; a fault step is arranged in the middle of the fuselage. The aircraft has the beneficial effects that the aircraft obtains a great lift-drag ratio in a ground effect area by utilizing the ground effect, the aircraft is lifted up through an airflow air cushion, and the airflow angle of the engine is accurately controlled by utilizing a popular engine tilting technology, so that the aircraft is prevented from falling off. Therefore, low-oil-consumption, large-load, short-distance take-off and low-speed landing are achieved, and the take-off and landing performance of the seaplane is greatly improved.

The invention relates to an active lift augmentation tandem wing type ground effect aircraft, and relates to the field of ground effect aircrafts. The defects that a stable take-off environment is needed, take-off time is long, and operation is complex are overcome. An active lift-increasing tandem wing type ground effect aircraft comprises a machine body, a cockpit is formed in the middle of the top of the machine body, connecting pieces symmetrically arranged in the direction of the machine body are fixedly installed on the front side and the rear side of the machine body correspondingly, and wing structures are fixedly connected to the connecting pieces on the front side and the connecting pieces on the rear side correspondingly; the inclination angle between the wing structures fixed to the connecting pieces on the front side of the aircraft body and the ground, the inclination angle between the wing structures fixed to the connecting pieces on the rear side of the aircraft body and the ground and the inclination angle between the wing structures fixed to the connecting pieces on the rear side of the aircraft body are larger than the inclination angle of the front-side wings. By means of the tandem wing type layout, the inclination angles of the paddles, the front wing structure and the rear wing structure relative to the ground are increased, and when the aircraft runs, the aircraft can obtain the maximum lift force compensation under the influence of the ground effect.

The invention discloses a double-speed-ratio water-air dual-purpose power device. The double-speed-ratio water-air dual-purpose power device mainly comprises a power input device, a rotating speed switching device and paddles. The power input device always provides power in a high-rotating-speed and low-torque state under different media, and the rotating speed switching device converts power input into torque meeting the requirements of the media through a one-way bearing and a planetary speed reduction mechanism under different media. When the power unit is in the air, the planetary reducing mechanism loses action, the output of the rotating speed switching device is equal to the rotating speed and torque of the power input device, when the power unit is in the water, the planetary reducing mechanism operates, and the output rotating speed of the rotating speed switching device is smaller than the rotating speed of the power input device. The torque output by the rotating speed switching device is larger than that of the power input device. The output shaft of the rotating speed switching device drives the passive folding propeller to provide power, and the passive folding propeller can passively stretch, fold and contract according to different rotating speeds and media, so that high efficiency under different media is ensured.

The invention discloses an amphibious aircraft alarm database design method, an alarm system and an alarm method. Determining the alarm demand of each alarm demand side based on scenarized demand capture and confirmation; converting each alarm demand into an alarm entry with an alarm attribute, wherein each alarm entry is in a decoupling state; and finally, constructing an alarm database through the alarm entries. According to the invention, the alarm demand conversion efficiency and the alarm realization accuracy of the airplane can be improved.

The invention provides a trigger type folding-stretching linkage wing structure for a seaplane. The trigger type folding-stretching linkage wing structure comprises a wing assembly, a driving assembly, a linkage assembly and a limiting assembly. The wing assembly comprises a wing seat, two wing groups and two guide units, the wing groups can stretch out and draw back, the two ends of each wing group are connected with an inner connecting plate and an outer connecting plate correspondingly, and the inner connecting plates are rotationally installed on the wing seat; the guide unit comprises a telescopic rod and a reset spring, the two ends of the telescopic rod are connected with the inner connecting plate and the outer connecting plate correspondingly, and the telescopic rod is sleeved with the reset spring. The driving assembly comprises a first sliding block and a connecting rod; two ends of the connecting rod are respectively hinged with the first slide block and one end of the wing group close to the wing seat; the linkage assembly comprises a traction rope and a pulley block; the limiting assembly comprises a first limiting unit and a second limiting unit. The first sliding block moves in the direction away from the wing base, sweepback and contraction of the wing set are synchronously achieved, the cross sectional area and the wetted area of the wing can be reduced at the same time during underwater navigation, and fluid resistance is remarkably reduced.

The invention discloses a sea-land-air triphibian robot, and belongs to the technical field of unmanned operation equipment, the sea-land-air triphibian robot comprises a bottom plate, a wing conversion mechanism and a flight control assembly are fixedly connected to the bottom plate, and an underwater operation mechanism is fixedly connected to the bottom of the bottom plate; a first propulsion propeller is fixedly connected to the tail end of the bottom plate, a wing bracket is fixedly connected to the front end of the bottom plate, wings are hinged to the two sides of the wing bracket through spherical hinges, a rotor mechanism is fixedly connected to the wings, and an undercarriage is fixedly connected to the tail end of the rotor mechanism; the wing conversion mechanism drives the wings to stretch out, draw back and rotate with the spherical hinge as the axis. The unmanned aerial vehicle can realize cross-domain collaborative operation, can take off and work under various conditions such as a ship-based condition, a land-based condition and a sea-based condition, is compact in overall structure and convenient to transport, solves the problems that a traditional fixed-wing unmanned aerial vehicle is too large in transportation size and needs a large take-off and landing site, and also solves the problem that a traditional rotor unmanned aerial vehicle is low in flight speed.

The invention relates to a ground effect aircraft capable of reducing the steering radius. A main wing of the ground effect aircraft comprises a wing surface, an aileron and a main beam, the tail end of the main beam is fixedly connected with a buoy; the buoy comprises a buoy main body, a spoiler, an aquaplane, a first driving mechanism and a second driving mechanism; one end of each of the spoiler, the water ski, the first driving mechanism and the second driving mechanism is rotationally mounted in the buoy main body; the other end of the first driving mechanism is hinged to the middle of the spoiler. The other end of the second driving mechanism is hinged to the middle of the water ski. According to the ground-effect aircraft, the aircraft body can be pressed down through the additionally arranged spoilers, so that the aircraft can press the water ski into water within a controllable range under the action of the spoilers, the resistance of the single side of the aircraft is increased, and therefore large yawing torque is obtained, and small-radius steering is achieved.

The present invention relates to a vertical take-off and landing (VTOL) aircraft featuring a central fuselage and at least two power units. Each power unit is connected to at least two separate lifting rotors via transmission lines, ensuring that each power unit is linked to at least two rotors diametrically opposed relative to the centre of gravity of the aircraft. The lifting rotors might be driven by power transmission lines of hydrostatic type. The power units on either side might be housed in separate pods which might be incorporated into the main fuselage or arranged as separate pods. These separate pods might also function as floats / pontoons for the aircraft to land, take-off and manoeuvre on water.

The invention belongs to the technical field of amphibious aircraft flight control, and discloses an amphibious aircraft fly-by-wire flight control system and a working method, a cockpit control device is connected with and controls a normal instruction sensor and a backup instruction sensor, the normal instruction sensor transmits a signal to an actuator control electron, and the backup instruction sensor transmits a signal to the actuator control electron; the actuator control electronics and the flight control computer transmit signals mutually, the actuator control electronics and the actuator control module transmit signals mutually, and the actuator control electronics further receive signals of the external signal sensor, the direct angular rate sensor, the flap position sensor and the flight control mode switch; the backup command sensor transmits the signal to the backup flight control computer, and the backup flight control computer transmits the signal to the actuator control module; the actuator control module is connected with and controls the actuator, and the angular displacement sensor is arranged on the actuator and transmits collected signals to the actuator control module. The problem that a current fly-by-wire flight control system is not matched with amphibious aircraft cross-medium application is solved.

An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tailstock type overwater vertical take-off and landing fixed-wing unmanned aerial vehicle which can float and park on the water surface, can vertically take off to leave the water and is switched into a fixed-wing mode for cruising and level flight. The unmanned aerial vehicle comprises a four-rotor support buoy and a wing body fusion body fixed to the upper portion of the four-rotor support buoy, small wing type buoys are arranged on wing tips of the two sides of the wing body fusion body respectively, and lifting ailerons capable of deflecting up and down are arranged on the rear edges of wings on the two sides of the wing body fusion body respectively. And four motor rotor propeller propelling devices are uniformly arranged at the tip part of the four-rotor bracket buoy.

A craft is provided with a lever that can control the power / speed of the craft and semi-automatically transition the craft in various modes of operation. This makes control of the craft somewhat similar to control of a boat, thereby bringing a maritime flight control experience to a wing-in-ground effect vehicles, hydrofoiling vessels, seagliders, and seaplanes. Further, various audio, visual, and / or haptic devices in the cockpit can provide alerts / feedback to the operator on the use of the lever and mode transitions.

The invention discloses a fixed wing type cross-domain aircraft capable of realizing self-adaptive load replacement, belongs to the technical field of cross-domain aircrafts, and is used for a water-air double-domain operation cross-domain aircraft. Comprising an aircraft body, a main wing, an aileron, a tail assembly, a vertical take-off and landing support, a vertical take-off and landing rotor wing, a fixed wing propeller, an underwater propeller, a load replacement device and a control module. The control module comprises a decision making system, a telemetering communication system, a state sensing system, an underwater water surface load replacement system, a water surface four-rotor vertical take-off and landing control system, an air fixed-wing cruise control system and an underwater vehicle control system. According to the fixed wing type cross-domain aircraft, through collaborative innovation of a multi-mode power system and self-adaptive buoyancy control, the dynamic characteristic adaptation problem in cross-domain navigation is solved, and the fixed wing type cross-domain aircraft has the vertical take-off and landing capacity, the air cruising capacity and the underwater maneuvering capacity.

The invention relates to a sea-land-air triphibian aircraft which is composed of an aircraft head, an aircraft body and foldable wings, each wing comprises a fixing part, a folding part and a driving part, and unfolding and folding of the wings are controlled through hydraulic jacks. The aircraft is provided with a propeller engine and a propeller thruster which provide lift force and propulsive force respectively, and air flight, underwater navigation and land advancing are achieved. The driving system assembly comprises a submarine engine and an aircraft star-shaped engine, and the submarine engine is connected with and drives propellers to rotate through gears to provide power; the aircraft star-shaped engine is mainly used for air flight. The triphibian aircraft has multifunctionality, high flexibility and wide applicability, and is suitable for various scenes such as emergency rescue, military reconnaissance and environment monitoring. Special materials and design endow the robot with concealment and maneuverability, the robot can quickly respond and avoid potential threats during task execution, and the robot shows powerful comprehensive performance and wide application potential.

The water-air amphibious unmanned aerial vehicle comprises an unmanned aerial vehicle main body, two main body arms, a left tilting part, a right tilting part, a left rotor wing panel, a right rotor wing panel and four stable empennages, and the two main body arms are arranged on the two sides of the unmanned aerial vehicle main body and are symmetrical about the axis of the unmanned aerial vehicle main body; the left tilting part and the right tilting part are arranged at the ends, away from the unmanned aerial vehicle main body, of the two main body arms in a one-to-one correspondence mode, and the tilting angle of the left tilting part and the tilting angle of the right tilting part are adjusted by being arranged on a motor; the left rotor wing and the right rotor wing are arranged at the ends, away from the two main body arms, of the left tilting part and the right tilting part respectively in a one-to-one correspondence mode, and the stable empennage is installed at the tail of the unmanned aerial vehicle body in a mode of being symmetric about the axis of the unmanned aerial vehicle body. By means of the brand new structural design, the water-air amphibious unmanned aerial vehicle can keep good air flying capacity, and meanwhile the water-air amphibious unmanned aerial vehicle can better sail underwater.

The invention discloses a large seaplane integrated with a distributed electric propulsion technology and a propulsion method, and relates to the technical field of seaplane. Comprising a fuselage, a left wing and a right wing are arranged on the two sides of the fuselage respectively, and a V-shaped hull is arranged at the lower end of the fuselage; and a T-shaped empennage is arranged at the tail part of the fuselage. Through the synergistic effect of the design of the V-shaped ship body and the distributed propulsion system, the whole ship body makes contact with the water surface to provide sufficient buoyancy at the low speed, only the main sliding face makes contact with the ship body to form an air layer at the high speed, and the air film drag reduction effect of a propeller at the bottom of the ship body is matched, so that the water resistance is reduced by 35%-50%, and the draft is reduced by 40%-60% along with speed increase; the problems that a traditional seaplane is large in water resistance and difficult to leave water are effectively solved, meanwhile, the left buoy and the right buoy are in linkage with the attitude control system, wave disturbance can be counteracted in real time, the transverse inclination angle is controlled within 1 degree, the wave resistance is improved to be capable of coping with waves with the height of 1.5 m, and the defects that a traditional seaplane is poor in wave resistance and has strict requirements for taking-off and landing water areas are overcome.

The invention relates to a method, a device and equipment for controlling a water-air cross-medium robot, and aims to design a special control distribution algorithm aiming at the possible contradiction among a plurality of control targets in the sliding process, such as the possible demand conflict between depth keeping and speed adjusting. A plurality of control targets are decomposed into specific tasks and are distributed to different actuators (such as tail vanes or side wings) for execution, so that effective cooperative control of depth, speed and attitude is realized.

A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

The invention discloses a cross-medium aircraft and belongs to the technical field of aircrafts. Comprising a power propulsion system which provides a power hybrid control system for an aircraft body and is used for realizing data acquisition and operation and accurate control of the power propulsion system, a navigation system and a sinking and floating system; the navigation system is used for providing navigation support for the vehicle body; the gradient skin is composed of multiple gradient materials and covers the outer surface of the aircraft body, and the sinking and floating system is used for controlling floating and diving of the aircraft body. According to the invention, the vehicle can obtain the optimal pneumatic / hydrodynamic performance in the air and seawater medium navigation state; according to the power propulsion system, the requirements of high speed, long distance and high thrust of the aircraft are met; a distributed network and a visual navigation system meet the navigation requirements of the cross-medium aircraft in the air, on the water surface and under the water and the combined combat; the hybrid control system is used for accurately controlling the aircraft; the aircraft application material can complete deformation adaptive to the changed environment.