186 results about "Multirotor" patented technology

An unmanned aerial vehicle and associated methods for inspecting infrastructure assets includes a multirotor, electrically driven helicopter apparatus and power supply; a flight computer; positioning and collision avoidance equipment; and at least one sensor such as a camera. The flight computer is programmed for automated travel to and inspection of selected waypoints, at which condition data is collected for further analysis. The method also includes protocols for segmenting the flight path to accomplish sequential inspection of a linear asset such as a power line using limited-range equipment.

The invention provides a fixed-wing multi-shaft aircraft, and belongs to the field of aircrafts. The fixed-wing multi-shaft aircraft comprises a fixed wing and a multi-shaft rotor wing rack which are connected with each other, and the multi-shaft rotor wing rack is provided with multiple rotor wing mechanisms; the rotor wing mechanisms comprise propellers and rotating shafts, the propellers are rotatably connected with drive devices, the drive devices are fixedly connected with the rotating shafts, and the rotating shafts are connected with rotating control mechanisms. The fixed-wing multi-shaft aircraft has the advantages of both a fixed-wing aircraft and a multi-shaft aircraft, can achieve a multi-shaft mode, a fixed-wing mode and a fixed-wing and multi-shaft mixed mode and also has the advantages of achieving vertical taking-off and landing and hovering and being high in flying speed and long in flying time.

A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle.

An asymmetric multirotor helicopter has a structure supporting at least one main and two secondary propulsion systems. A flight control unit controls the helicopter by varying the relative speed of each of the main and secondary propulsion systems. Each main propulsion system includes at least one main motor drive and a main drive shaft that carries and propels a main differential contra-rotating transmission configured to share the power provided by the main drive shaft with two contra-rotating output shafts. Each secondary propulsion system includes at least one secondary motor drive and a secondary drive shaft that carries and propels respective secondary propulsion blades. The two contra-rotating output shafts support and propel for mutually contra-rotation motion two sets of main propulsion blades. The main drive shaft rotates in the same direction as one of the secondary drive shafts and at least one secondary drive shaft rotates in an opposite direction.

The invention discloses a multi-shaft aircraft. The multi-shaft aircraft comprises a bracket and a driving system; the bracket comprises a first side rod, a second side rod, and a main rod, wherein the first side rod and the second side rod are arranged in parallel; the main rod is fixed between the first side rod and the second side rod; two ends of the main rod are respectively fixed in the middle parts of the first side rod and the second side rod; the driving system is mounted on the bracket and comprises a motor and four rotor wings, wherein the four rotor wings are respectively mounted at four end parts of the first side rod and the second side rod; the motor drives a plurality of rotor wings to rotate through a synchronous transmission mechanism; the synchronous transmission mechanism comprises a main shaft which is driven to rotate through the motor; a synchronous transmission belt is arranged between the main shaft and each of the rotor wings; the synchronous transmission belt is arranged in the first side rod or the second side rod. According to the multi-shaft aircraft, the synchronous transmission belt is arranged in cavity body between the first side rod and the second side rod, a first synchronous belt wheel is arranged in a first protection space of a first support, and thus the synchronous transmission belt and the first synchronous belt wheel can be effectively protected once the aircraft collides by accident.

The multi-rotor type unmanned aerial vehicle includes: a main body including the battery module and the control module; a plurality of frames connected to a side surface of the main body and extending therefrom; a first motor connected to a distal end of each of the frames; and a drive unit connected to the first motor, wherein the drive unit includes a rotary frame and a stationary frame each having a circular shape and connected to each other in the form of a gyroscope, a second motor supported at the center of the rotatable frame, and a propeller connected to the second motor, and a vector of thrust generated by rotation of the propeller is variable according to rotation of the first and second motors.

Embodiments are directed towards hybrid power supply that provides electric power to a multirotor rotorcraft to extend range or flying time. In one embodiment, an internal combustion engine and fuel tank are provided that interoperate with a battery provided by a commercial multirotor rotorcraft to substantially extend flying time or flying distance.

The invention discloses a fire-fighting and rescue robot system and a control method. The fire-fighting and rescue robot system comprises an upper computer, a fire-fighting robot, a rescue robot and a multi-shaft aircraft. The fire-fighting robot, the rescue robot and the multi-shaft aircraft conduct information interaction with the upper computer. The fire-fighting and rescue robot system further comprises a wall sensor unit conducting information interaction with the upper computer. The wall sensor unit comprises a flame sensor, a combustible gas sensor, an infrared temperature measurement sensor and a doppler displacement sensor. In the fire-fighting and rescue robot system, the fire-fighting robot, the rescue robot and the wall sensor unit are responsible for environmental monitoring, fire fighting and rescue in a building. The multi-shaft aircraft is responsible for image capture outside the building, and obtained data are comprehensive and have practical application and referable performance. Cooperative work between the robots is achieved through the fire-fighting and rescue robot system, a computer-computer communication work mode and a human-computer interaction work mode are included, the requirements in an actual fire scene are met, the work efficiency can be improved greatly, and an inestimable function is achieved on the conditions that quick reaction is achieved, thus property loss caused by a fire disaster is reduced, and trapped people are rescued.

A multirotor aircraft 10 that is adapted for vertical take-off and landing, comprising a fuselage, a thrust producing units assembly that is provided for producing thrust in operation, and a forward-swept wing that comprises a portside half wing and a starboard side half wing. Each one of the portside and starboard side half wings comprises an inboard section that is connected to the fuselage and an outboard section that forms a wing tip. The inboard sections of the portside and starboard side half wings form a central wing region. The portside and starboard side half wings are respectively connected in the region of their wing tips to an associated outboard wing pod that supports at least two non-tiltably mounted thrust producing units of the thrust producing units assembly.

The invention discloses an amphibious power propulsion device suitable for sea and air, comprising a frame type retainer, a tilting motor, a power motor fixedly arranged at the middle part of the retainer, as well as propellers for air and propellers for sea, which are coaxially and rotatably arranged at a certain interval, wherein the propellers for air are in driving connection with the power motor through a unidirectional rotation mechanism, the propellers for sea are in driving connection with the power motor, a rotating shaft of the tilting motor is fixed at the outer side of the retainer through a connecting plate, and the rotating axis of the tilting motor is perpendicular to the rotating axis of the propellers for air and the propellers for sea. The invention also provides an amphibious multi-axis aircraft suitable for sea and air. According to the amphibious power propulsion device and the amphibious multi-axis aircraft, the same motor is adopted to simultaneously adapt to two different working environments, namely in the air and under the water, thereby reducing the weight of the amphibious aircraft for sea and air and simplifying the structure of the aircraft; and meanwhile, the tilting motor is used for controlling the direction of power output, thereby increasing the maneuverability of the amphibious aircraft and strengthening the capability of the amphibious aircraft for finishing complex tasks.

The invention discloses a multi-fuel multistage environmental-protection internal-combustion oil, composed of mineral basal oil and hydrogenated plant oil, oil residue HVI150BS bright recombinant oil and compound additive, it can adapt to different-structural internal-combustion engines, including: gasoline engine, turbine pressure diesel engine, ship diesel engine, locomotive diesel engine, multirotor engine, adaptive to different-fuel automobiles, adaptive to the vehicles used in the winter and the summer, adopting closed-loop electrojet machine inner-purifying technique and converting tertiary tail gas, and has better degradability, lower environmental protection after leaked or used as compared with existing internal-combustion oil, and because its degradation ratio reaches 80%, it relatively reasonably solves the compounding of high-efficacy clean disperser with high-temperature antioxidant, and also solves problems of low discharge, low-temperature fluidity, high-temperature dispersivity and key low ash content.

A multirotor unmanned aerial vehicle includes a first-rotor unmanned aerial vehicle (1a) comprising a first rack (19a) and a plurality of first rotor assemblies (111a) mounted on the first rack; a second-rotor unmanned aerial vehicle (1b) comprising a second rack (19b) and a plurality of first rotor assemblies (111b) mounted on the second rack; and a fixing mechanism (1c) used for connecting and fixing the first rack (19a) to the second rack (19b). The first-rotor unmanned aerial vehicle (1a) or the second-rotor unmanned aerial vehicle (1b) also comprises a main controller used for selecting a control mode for the multirotor unmanned aerial vehicle after abutting according to the manner of abutting the first-rotor unmanned aerial vehicle (1a) and the second-rotor unmanned aerial vehicle (1b), and controlling the plurality of first rotor assemblies (111a) and the plurality of first rotor assemblies (111b). A controlling method of the multirotor unmanned aerial vehicle is also provided.

A rotor assembly for a multirotor aircraft, and a multirotor aircraft, are disclosed herein. The rotor assembly has a first motor having a first axis of rotation and a first propeller connected to the first motor. The rotor assembly has a second motor having a second axis of rotation, and a second propeller connected to the second motor. The second propeller is smaller in length than the first propeller. The first motor and the first propeller produce a greater proportion of a total lift thrust of the rotor assembly than the second motor and the second propeller. The multirotor aircraft includes an airframe and a plurality of the rotor assemblies mounted to the airframe.

A drone for deterring intruders within a monitored area includes a multirotor aerial vehicle with an electric drive apparatus and a power supply configured to provide electrical energy. A controller is configured to control the multirotor aerial vehicle. A first sensor is in electrical communication with the controller, the sensor configured to provide navigation information to the controller. A wireless communication circuit is in electrical communication with the controller, and in wireless communication with an external wireless transceiver. A deterrence effector bay is in electrical communication with the controller. The deterrence effector bay includes a non-lethal deterrence effector and an actuator. Activation of the actuator causes the delivery of the non-lethal deterrence effector to a target. The drone may be used in conjunction with an alarm system as a deterrent against intrusion.

The invention discloses a flight control method and apparatus for a multiaxial flight vehicle. The method includes: detecting whether a plurality of power systems with countershaft design are abnormal by a flight control system; and when the flight control system detects that any power system is abnormal, adjusting the countershaft power system to make the multiaxial flight vehicle land stably. The method and the apparatus provided by the invention solve the problem that the multiaxial flight vehicle cannot maintain balance when any power system in the multiaxial flight vehicle is abnormal in the prior art, and the multiaxial flight vehicle still can land stably when abnormality occurs to any power system of the multiaxial flight vehicle.

The invention belongs to the technical field of an unmanned aerial vehicle and specifically relates to a multi-axis aircraft. The multi-axis aircraft comprises a frame, a plurality of pipe clamps and an aircraft arm, wherein the pipe clamps are uniformly distributed on a side surface of the frame; an inner end of the aircraft arm is connected with the pipe clamps; a motor base is arranged at an outer end of the aircraft arm; a positive assembling motor is arranged in the motor base; a reversed assembling motor is arranged in the middle of the aircraft arm; a propeller easily assembled structure is respectively arranged on each of the revolving shafts of the positive assembling motor and the reversed assembling motor; a positive assembling propeller is arranged on the propeller easily assembled structure on the positive assembling motor; a reversed assembling propeller is arranged on the propeller easily assembled structure on the reversed assembling motor; an electric footstool foldable device is arranged at the bottom of the frame; and a footstool is connected with the electric footstool foldable device. The multi-axis aircraft can increase the generated lifting force within the limited volume size; the cruising power is higher; the manufacturing cost is lower; the structure is stable and firm; the sensitivity, the stability and the remote control precision are higher; the mounting and dismounting of each part are simple; and the multi-axis aircraft has competitive advantages in the competition process.

A multirotor aircraft that is adapted for vertical take-off and landing. The multirotor aircraft comprises a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip. The at least one upper wing is joined to the at least one lower wing in a joined-wing configuration.

A universal controller for robust trajectory tracking in multirotor unmanned aerial vehicles (UAVs) is disclosed. A particular embodiment includes: a sensor system to measure position and orientation of a multirotor unmanned aerial vehicle (UAV); and a flight control system, coupled to the sensor system, the flight control system being configured to: obtain position and orientation data from the sensor system; generate a plurality of derivatives from the position and orientation data using a differentiator; apply a decoupling control law to approximately decouple translation dynamics from each other in a three-dimensional (3D) space; compute error values between desired trajectories and actual trajectories in each dimension of 3D space using the plurality of derivatives and the decoupled dynamics; and generate control signals to vary speeds of a plurality of thrust elements to counteract the computed error values in each dimension of 3D space.