14 results about "Multirotor" patented technology

The invention relates to a large-scale firefighting system, particularly for forest fires, using a refractory ceramic tarp transported by several multirotor drones. This system allows for the rapid and effective covering of fire hotspots, thus limiting the oxygen supply and contributing to their extinguishment.

This invention discloses a heterogeneous multi-rotor layout with a single main rotor and partially tilted multiple slave rotors, relating to the field of unmanned aerial vehicle (UAV) design technology. It includes a large main rotor providing primary lift and n control rotors arranged around it, with some control rotors mounted horizontally and the rest tilted at a fixed angle. During steady-state flight, the anti-torsional torque of the main rotor is statically balanced by the horizontal component torque of the pull force from the tilted slave rotors. Attitude control of the UAV is achieved by differentially adjusting the rotational speeds of the control rotors, including pitch control, roll control, and yaw control. Pitch and roll control are achieved by differentially adjusting the rotational speeds of symmetrically positioned control rotors, while yaw control is achieved by differentially adjusting the rotational speeds between the horizontally mounted and tilted control rotor groups. This invention achieves a fusion of high aerodynamic efficiency and easy operation, effectively improving the UAV's endurance and flight performance.

The utility model relates to multirotor unmanned plane technical field discloses a kind of motor seat subassembly of coaxial multirotor unmanned plane, including motor seat main body, motor seat adapter, motor seat adapter baffle, motor seat plug and electric governing installation piece;The motor seat main body is equipped with sliding slot structure, for with motor seat adapter sliding fit.This scheme aims at the functional defects such as insufficient power, channel response delay and poor stability that traditional multi-axis unmanned plane faces when executing roll, pitch and other attitude adjustment, and structural complexity, high manufacturing cost, weak environmental adaptability and other structural disadvantages, and innovative solution is proposed.The scheme simplifies the motor installation form adjustment process of multirotor coaxial unmanned plane, improves the adaptability and economy of unmanned plane in diversified application and flight environment, effectively avoids the flight instability phenomenon caused by insufficient power or response delay, significantly enhances the reliability and flight stability of system as a whole.

This invention belongs to the field of aircraft aeroelasticity, and specifically discloses a method for analyzing the spiral flutter of multirotor aircraft. It is designed for the configuration characteristics (hingedless small-diameter propeller) and flight modes (vertical takeoff and landing, large pitch angles in forward flight) of multirotor aircraft. The 2-DOF model in the preliminary design stage does not require complex modeling and software operation, supports rapid adjustment of structural, overall, and aerodynamic parameters, and can complete the analysis of multiple sets of parameters in a short time, meeting the needs of rapid iteration in the preliminary design. The 2-DOF (rapid analysis) and 4-DOF (precise verification) models can be flexibly switched according to the design stage, taking into account both analysis efficiency and calculation accuracy, and adapting to the needs of the entire process from preliminary design to detailed design.

This invention discloses a fault-tolerant flight control method for a multi-rotor UAV based on end-to-end direct thrust control. The method includes: constructing a purely analytical differentiable simulation environment for a quadrotor UAV oriented towards implicit feature observation and gradient backpropagation, embedding a continuously differentiable fault injection and actuator mapping mechanism, and using a fourth-order Runge-Kutta method to discretize and iterate continuous operators; constructing an end-to-end control network based on spatiotemporal feature structure decoupling and latent variable direct drive, and outputting four-motor action commands through dual-stream feature extraction; training the end-to-end control network in the differentiable simulation environment, and optimizing the control network parameters based on a differentiable physics engine and time-varying backpropagation; and combining an adaptive composite loss function and a multi-order course learning mechanism to enable the control network to converge to an effective fault-tolerant control strategy. This invention can achieve adaptive control without an independent fault detection and diagnosis module under single-motor fault conditions, establishing a smooth transition mechanism from normal operation to single-motor failure.

A mobile towing and lifting system and associated methods, comprising a retractable tug, coupled to an aerial vehicle, wherein the tug is configured to transfer electrical power and data to and from the aerial vehicle. The aerial vehicle may comprise an airship, multirotor aircraft, fixed wing aircraft, buoyant aircraft or a combination of the like. The mobile towing and lifting system may be applied to wireless charging, and aerial logistics applications.

This invention discloses a heterogeneous multirotor layout with a single main rotor and two vector slave rotors, relating to the field of unmanned aerial vehicle (UAV) design technology. The layout includes a main rotor located in the middle of the fuselage and two vector slave rotors symmetrically arranged on the left and right sides of the main rotor. The main rotor provides the primary lift, and the two vector slave rotors are each equipped with an independent vector control system, capable of independently deflecting their thrust direction for pitch and yaw attitude control, and differentially adjusting their rotational speed for roll control. Simultaneously, a preset tilt angle is used to balance the anti-torque of the main rotor. This layout, through a decoupled lift and attitude control strategy, significantly improves the aerodynamic efficiency, endurance, and flight control performance of the UAV.

This invention discloses a catapult-launched teardrop-shaped multirotor UAV with folding and unfolding rotors, belonging to the field of multirotor UAV technology. It includes: a connector, a teardrop-shaped shell, and arms. The teardrop-shaped shell contains multiple parallel compartments, each housing the multirotor UAV's power unit, flight control unit, and data transmission unit, thus giving the multirotor UAV an overall teardrop shape. Multiple arms are vertically connected to the teardrop-shaped shell via the connector. These arms can fold downwards vertically via the connector, simultaneously folding the rotors on the arms. When folded to a vertical position, the arms are close to the teardrop-shaped shell, with the rotors at the ends of the arms positioned at the bottom of the multirotor UAV. During downward folding, the connector applies an upward force to the arms. This invention's UAV saves space, facilitates storage and transportation, and improves flight and launch efficiency.

A powered tilting multirotor manned aircraft driven by worm gears is disclosed. This invention relates to the field of aircraft technology. The aircraft has a cockpit within its frame, and worm gear tilting drive mechanisms are mounted at each of the four corners of the frame. Tilting shafts connect the two front and two rear worm gear tilting drive mechanisms. The roots of the arms are foldably mounted on the outer ends of the tilting shafts using arm folding mechanisms. Motors are mounted on the upper and lower sides of the outer ends of the arms, and propellers are mounted on the output ends of the motors. This design allows for the decoupling of thrust vector from flight attitude. By driving the arms to tilt through the worm gear tilting drive mechanisms, the direction of the lift vector is changed, thereby obtaining the horizontal thrust component required for forward flight while maintaining a horizontal fuselage attitude.

This disclosure relates to the field of multirotor aircraft technology, specifically to a method, apparatus, device, and medium for detecting rotor blade protectors. The method includes: if the multirotor aircraft is determined to be in a stable hovering state based on detected moving speed, detected acceleration, and detected angular velocity, then acquiring the detected climb speed and rotor speed of the multirotor aircraft; acquiring the nominal weight of the multirotor aircraft, and obtaining the theoretical climb acceleration based on the rotor speed and nominal weight; acquiring the theoretical climb speed and disturbed climb acceleration based on the detected climb speed and theoretical climb acceleration; and determining whether the model of the multirotor aircraft matches the model of the rotor blade protector installed on the multirotor aircraft based on the theoretical climb speed and disturbed climb acceleration. This solution can determine whether the model of the multirotor aircraft matches the model of the rotor blade protector installed on the multirotor aircraft, facilitating timely replacement of incompatible rotor blade protectors by reminding operators, thus improving the user experience.

Fig 1 A multirotor UAV 10 flies under control of an on-board flight controller(40, fig 2). The UAV 10 has sensors e.g. laser scanner / LIDAR 30, camera 32, GPS 34, compass 35 sending signals to the flight controller (40, fig 2). The UAV 10 uses the three-dimensional depth scanner 30 when flying in close proximity to an external structure (60, fig 4) to create a three-dimensional map of the external structure (60, fig 4) for control of the flight of the UAV 10 proximate thereto. The sensors detect a profile of the structure (60, fig 4) within a predetermined vicinity of the UAV 10 and is used by the flight controller (40, fig 2) to control movement of the UAV 10 to track the profile of the structure (60, fig 4).

This invention discloses a teardrop-shaped multirotor drone with laterally foldable arms, belonging to the field of multirotor drone technology. It includes: a teardrop-shaped shell, multiple arm assemblies, a frame, a rotating support, a power unit, and a connector. The shell is designed in a teardrop shape to give the multirotor drone an overall teardrop shape. Multiple arm assemblies are evenly arranged on the teardrop-shaped shell in a planar manner. The frame secures the arm assemblies. The rotating support drives the arm assemblies to rotate. The power unit provides power for folding or unfolding the arms. The connector connects the rotating support and the arm assemblies to the frame, so that the rotating support rotates synchronously with the power unit, allowing the arms to fold or unfold towards or away from the teardrop-shaped shell. This multirotor drone's arms can automatically unfold or fold, facilitating transportation, reducing storage space, and lowering storage and transportation costs.