16results about How to "Improve flight efficiency" patented technology

This invention provides a static parameter measurement device for overhead contact lines based on an unmanned aerial vehicle (UAV) platform, belonging to the field of railway overhead contact line inspection technology. It includes a UAV body with a laser measuring device mounted on its top and a telescopic support mounted on its side. The UAV body includes a processor chip, and the laser measuring device is connected to the processor chip. After takeoff, the telescopic support secures the UAV, and the laser measuring device measures the overhead contact line. The measured data is transmitted in real time to the processor chip for processing and analysis, ultimately achieving high-precision measurement of the static parameters of the overhead contact line. By linking the top-mounted laser measuring device with the processor chip, it is possible to conduct inspections and parameter measurements on conventional railway lines outside of designated maintenance windows, achieving high-precision, non-contact distance or terrain measurement, suitable for complex environments, and significantly improving data acquisition efficiency.

The utility model relates to the technical field of takeoff and landing protection equipment, and discloses takeoff and landing protection equipment for an unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, and a display connection signal screen is fixedly mounted on the outer wall of the unmanned aerial vehicle body. The foldable light and thin mounting plate is rapidly folded and unfolded through the rotating hinge and the small hydraulic push rod, in the flight state, the mounting plate is folded and tightly attached to the fuselage, air resistance is effectively reduced, the flight efficiency is improved, before landing, the hydraulic push rod rapidly pushes the mounting plate to be unfolded to the horizontal position, and the supporting area is enlarged; the unmanned aerial vehicle is in direct contact with the ground in cooperation with an anti-skid balancing weight, the friction force between the unmanned aerial vehicle and the ground is increased, the unmanned aerial vehicle is effectively prevented from sliding or rollover after landing, meanwhile, an inflation pump is arranged in an inflation box to inflate a buffering air bag, a flexible protection layer surrounding the unmanned aerial vehicle is formed, falling impact is effectively relieved, and the unmanned aerial vehicle is protected from falling. And the effect of improving the protection safety is achieved.

The utility model relates to the field of rotor support arm folding discloses a kind of rotor support arm electric folding and locking mechanism, including fuselage, at least two groups of support arm components are equipped on the fuselage, and support arm component includes first support arm unit and second support arm unit;First support arm unit includes first fixed support arm, first rotor support arm and first driving part, and second support arm unit includes second fixed support arm, second rotor support arm and second driving part, first fixed support arm one end and fuselage connection, other end and first rotor support arm rotary connection, second fixed support arm one end and fuselage connection, other end and second rotor support arm rotary connection, first driving part is used to drive first rotor support arm to the direction of being close to second fixed support arm rotation, and second driving part is used to drive second rotor support arm to the direction of being close to first fixed support arm rotation.Compared with prior art, structure is more simple, and rotor support arm can be effectively gathered.

The utility model discloses a kind of height integration control flight cabin suitable for unmanned aerial vehicle, including cabin table, display, throttle push rod, joystick, integrated control panel, display is installed on bracket, bracket is set in cabin table rear side;Throttle push rod, joystick and integrated control panel are all set in the top of cabin table, integrated control panel is set below display, throttle push rod and joystick are all located in the front side of cabin table.The technical effects reached are as follows: using integrated design, pilot completes relevant operation in a centralized control area, accelerates take-off preparation speed, improves flight efficiency.Each subsystem's operating state can be better monitored and managed through integrated design, reduce human error, centralized control interface can clearly present each key parameter and operation option, so that pilot will not miss important information due to frequent shift of sight between multiple instruments and control devices, ensure operation accuracy, so that it can better cope with flight condition.

The utility model belongs to the technical field of shape design and control of aircrafts, and relates to an electric tilt-rotor aircraft. Comprising a fuselage, two wings located on the two sides of the fuselage, an empennage, a plurality of supporting rods arranged below the wings and rotors arranged at the two ends of the supporting rods. The rotor wings comprise a plurality of tilting rotor wings and a plurality of fixed rotor wings; the number of the supporting rods is even, and the supporting rods are divided into two sets with the same number and are symmetrically arranged on the two sides of the machine body. A tilting rotor wing is arranged at the front end of each supporting rod; a fixed rotor wing is arranged at the rear end of each supporting rod; the tilting rotor wings are connected with the front ends of the supporting rods through tilting mechanisms, and the tilting mechanisms are used for adjusting the orientation of the tilting rotor wings. The electric tilting rotor aircraft provided by the utility model can realize the functions of vertical take-off and landing, tilting transition and cruise flight.

The application provides an updating method and system for aircraft icing identification based on real-time detection of aircraft. The method comprises obtaining real-time data of the aircraft to determine icing occurrence information; constructing an icing report membership function based on the icing occurrence information, which is used to represent the spatial and temporal distribution of icing occurrence probability; and combining the icing report membership function with a basic icing index to calculate an icing potential index, which is used to identify the three-dimensional distribution of the icing area. The above method realizes accurate positioning, dynamic prediction and real-time warning of icing, and improves aviation safety and flight efficiency.

The embodiment of the application discloses a kind of wisdom morphing aircraft and morphing control method, including cabin body base and the skin structure covered in the outer surface of the cabin body base;The cabin body base includes first cabin body base and second cabin body base, and the second cabin body base is combined and fixed to the first cabin body base away from the vertex of the aircraft one end;Multiple first driving members are included between the skin structure and first cabin body base, and the first driving member is configured to drive the skin mechanism to change the shape of the wisdom morphing aircraft;Multiple second driving members are included between the skin structure and the second cabin body base, and the second driving member is configured to drive the skin structure to change the shape of the wisdom morphing aircraft.By corresponding setting skin structure in different cabin section of aircraft, the segmented regulation and control of the shape of aircraft body is realized, and the aerodynamic shape of aircraft is optimized, so that it can adapt to the flight requirements of different flight tasks.

This utility model discloses a narrow-body folding rotor manned aircraft, relating to the field of manned aircraft technology. To address the problem of low folding efficiency in existing rotor manned aircraft folding structures, this narrow-body folding rotor manned aircraft includes: a fuselage with a fixed base on its top; at least two sets of rotor mechanisms connected to the fixed base via a flipping mechanism, the flipping mechanism controlling the switching of the rotor mechanisms between a folded and unfolded state; a locking mechanism located on the fixed base, used to lock and unlock the corresponding flipping mechanism; and a control mechanism located inside the fuselage, signal-connected to the rotor mechanisms, flipping mechanism, and locking mechanism. With this configuration, the rotor can automatically fold and unfold without manual intervention, thereby reducing operation steps and time, and improving operational efficiency.

The embodiment of the invention relates to the technical field of unmanned aerial vehicles, and discloses a propeller and an unmanned aerial vehicle, the propeller comprises a propeller clamp assembly, an adjusting device, a driving device and a propeller blade main body, and the adjusting device comprises a first adjusting assembly; the first adjusting assembly comprises a first distance adjusting bin, a first distance adjusting block, a first distance adjusting shaft and a first paddle fixing piece, the first distance adjusting bin is provided with a first distance adjusting bin chamber, the first distance adjusting block is detachably arranged in the first distance adjusting bin chamber, the first distance adjusting block is provided with a plurality of first abutting parts, and the first abutting parts are detachably arranged in the first distance adjusting bin chamber. And the adjusting device is fixed on the driving device. By means of the mode, a user can be allowed to change the installation angle (screw pitch) of the blades by replacing or rotating the distance adjusting block under the condition that the blades are not replaced, so that different flight scenes and performance requirements are met.

The invention belongs to the technical field of aircraft control, and discloses a self-adaptive reverse cooperative control method and system for a coaxial dual-rotor aircraft, and the method comprises the steps: obtaining a target attitude instruction; according to whether pitching and rolling instructions exceed a set threshold value or not, a reverse cooperative control strategy or a conventional same-direction control strategy is intelligently selected, and upper and lower rotor wing control instructions are obtained through calculation; according to the yawing and vertical speed instructions, the target rotating speed of the double motors is calculated; and converting the control instruction into a steering engine PWM signal and synchronously outputting the steering engine PWM signal to an execution mechanism. The system correspondingly comprises an attitude instruction acquisition module, a control instruction calculation module, a motor rotating speed calculation module, a steering engine signal conversion module and a synchronous output module. According to the method, the response capacity under large maneuverability is improved through reverse cooperative control, safe takeover and degraded operation under the steering engine set fault are achieved through a fault detection and redundancy control mechanism, and the control precision, maneuverability and reliability of the aircraft under the complex working condition are remarkably improved.

The invention discloses an unmanned aerial vehicle surveying device for surveying and mapping geographic information, and belongs to the field of unmanned aerial vehicle surveying. Comprising an unmanned aerial vehicle body, and a monitoring mechanism is arranged at the bottom of the unmanned aerial vehicle body; a plurality of supporting mechanisms are arranged at the bottom of the unmanned aerial vehicle body and located on the outer side of the monitoring mechanism. A floating mechanism is arranged between the two supporting mechanisms which are opposite front and back; the monitoring mechanism comprises a monitoring camera, and the top of the monitoring camera is in threaded installation with the bottom of the unmanned aerial vehicle body through a bolt; a guide rail is arranged on the left side of the monitoring camera; in order to solve the problem that the surveying and mapping camera is exposed for a long time, an openable and closable closed protection structure is additionally arranged, the camera can be completely closed during non-surveying and mapping operation, dust, water vapor, chippings and other sundries are effectively prevented from adhering to or eroding a lens, the lens abrasion and fouling probability is greatly reduced, the high-definition precision of aerial survey images is guaranteed, the service life of the camera is prolonged, and the working efficiency is improved. The equipment maintenance cost is reduced.

The application discloses an amphibious flying automobile and a flying method thereof, and relates to the technical field of flying automobiles.The amphibious flying automobile comprises a shell wing, a shell wing support, a main cabin body, a middle shaft, two groups of propulsion mechanisms and two groups of steering mechanisms.The shell wing support comprises two first shell wing supports.The main cabin body is arranged at the center position of the shell wing and is located between the two first shell wing supports.The middle shaft is arranged in the shell wing and is located on the middle axis of the shell wing, the middle shaft is rotationally connected with the shell wing support, and the middle shaft is connected with the main cabin body.The two groups of propulsion mechanisms comprise first propellers arranged on the two radial sides of the middle shaft.The two groups of steering mechanisms comprise second propellers and second propeller arms, the second propeller arms are connected with the middle shaft and extend out of the shell wing, the second propellers are arranged at the end portions of the second propeller arms away from the middle shaft, and the second propeller arms can be rotationally driven.By controlling the uniformly distributed first propellers and the direction-adjustable second propellers, the horizontal steering and the vertical lifting of the flying automobile can be realized, and the flying efficiency and the flying stability are improved.

This invention relates to the field of unmanned aerial vehicle (UAV) flight control technology, and discloses an adaptive obstacle avoidance control method and system for UAVs based on environmental perception. The method includes: acquiring environmental perception data and flight status data; constructing a parameter model of slender obstacles; constructing an equivalent hazardous volume field and a repulsive potential energy field; generating a controllable risk potential field; generating obstacle avoidance control quantities and a reference trajectory; performing online self-tuning of the potential field parameters; and generating final flight control commands. Compared to existing technologies, especially in environments with numerous slender obstacles such as power grid inspections and low-altitude flights in forest areas, this invention addresses the technical problem of effectively converting slender obstacles into safe control distances that can participate in flight control calculations. This application improves the safety and stability of UAV flight by mapping slender linear obstacles to an equivalent hazardous volume field and constructing a continuously differentiable repulsive potential energy field to participate in the control quantity solution.

The utility model provides a modularized tailstock type coaxial unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles and comprises a coaxial unmanned aerial vehicle module A, wing modules B and a tail thrust module C. The wing modules B are detachably connected to two sides of the coaxial unmanned aerial vehicle module A. The tail thrust module C is detachably connected to the tail of the coaxial unmanned aerial vehicle module A; the coaxial unmanned aerial vehicle module A comprises an upper rotor blade, a lower rotor blade, a fuselage and a periodic variable-pitch steering engine room, the periodic variable-pitch steering engine room is mounted at the top of the fuselage, and the upper rotor blade is mounted at the top of the periodic variable-pitch steering engine room. The problems that a conventional coaxial unmanned aerial vehicle is short in endurance time, short in voyage and low in flight speed, and a conventional tailstock type unmanned aerial vehicle is low in hovering efficiency and forward flight efficiency due to the fact that a rotor wing needs to give consideration to hovering and cruising states are solved.

The invention belongs to the technical field of land-air wheel wing robots, and particularly relates to a multi-mode switching control method, system and device for a land-air wheel wing robot. Comprising the steps that a switching mechanism depending on the state of the air-ground wheel wing robot switching control system is constructed, internal dynamic variables are introduced, a dynamic event triggering sampling mechanism is obtained, an event triggering threshold value is adjusted in real time along with the system state through self dynamic updating, and a state sampling value of the air-ground wheel wing robot switching control system is obtained through calculation. Switching control input is obtained based on the state sampling value and subsystem controller gain calculation, then a switching dynamic event trigger control scheme is obtained, and switching dynamic event trigger controller parameters are determined according to the subsystem parameter constant matrix and the subsystem transfer rate. By adopting the technical scheme provided by the invention, more accurate and flexible state switching control is realized, and the effects of optimizing energy consumption, improving efficiency and saving communication resources are achieved while the safety is ensured.