352results about How to "Extended flight time" patented technology

This invention combines the precision spray process with in-flight laser treatment in order to produce direct write electronic components. In addition to these components, the process can lay down lines of conductive, inductive, and resistive materials. This development has the potential to change the approach to electronics packaging. This process is revolutionary in that components can be directly produced on small structures, thus removing the need for printed circuit boards.

A method of harvesting and managing energy from air currents, by small unmanned aircraft systems (UAS) having a plurality of powered and unpowered rotors, to increase the aircraft's flight time, especially where the mission requires extensive hovering and loitering, is provided. Conventional powered rotors create lift for the aircraft. Unpowered rotors can either be: 1) Free-wheeling rotors which increase the plan form area of aircraft as they rotate, increasing lift, and reducing the power draw on the battery, and/or 2) Rotors connected to micro-generators, which serve as a brake on the unpowered rotors, create electrical power to charge the aircraft batteries or directly power the aircraft's electronics. The invention's folding rotor arm design results in a compact package that is easily transported by a single user (man portable). The aircraft can be removed from its protective tube, unfolded and launched for flight in less than a minute. Extended flight times, compact easily transported design, and ability to host flight software on a user's tablet/PC result in low total cost of ownership.

A multi-reflecting TOF mass analyser has two parallel, gridless ion mirrors each having an elongated structure in a drift direction (Z). These ion mirrors provide a folded ion path formed by multiple reflections of ions in a flight direction (X), orthogonal to the drift direction (Z). The analyser also has a further gridless ion mirror for reflecting ions in the drift direction (Z). In operation ions are spatially separated according to mass-to-charge ratio due to their different flight times along the folded ion path and ions having substantially the same mass-to-charge ratio are subjected to energy focusing with respect to the flight and drift directions.

The invention provides an unmanned aerial vehicle cruising and monitoring system for forest fire. The weight of the unmanned aerial vehicle is reduced, flight time is prolonged, an unmanned aerial vehicle cruising range is enlarged, route planning is carried out for fire monitoring, and an unmanned aerial vehicle flight control system is combined with a geographic information system. The route planning not only guarantees monitoring quality and monitoring full coverage but also considers the hardware parameters and the flight safety of the cruising unmanned aerial vehicle, a rotary head carries a thermal infrared imager and a colorful high-definition camera, the thermal infrared characteristics of the image of the forest fire are fully utilized, and an automatic monitoring and identification method for forest fire information is designed. Even if the forest fire monitoring distance of the unmanned aerial vehicle is long, fire characteristics can be accurately captured. A colorful high-definition image is compressed and transmitted back to a ground command post, a high-definition fire video image can be quickly transmitted to the ground, a fire position can be accurately reported, so that convenience is brought to the ground command post in accurately judging a fire situation and organizing people to fight the fire, and precious fire-fighting time is saved.

Disclosed are an unmanned aerial vehicle, a charging station, and an automatic charging system for an unmanned aerial vehicle including the same. The unmanned aerial vehicle includes: a main body which includes a plurality of rotors, and is capable of flying and vertical taking off and landing by the rotors; a battery which is mounted in the main body for supplying power and is chargeable; a landing gear which includes a first charging terminal and a second charging terminal having different polarities and electrically connected to the battery, and is provided at a lower part of the main body; and a controller configured to control the main body.

The invention declares a correction method used for attitude and course angles of a navigation system. The method comprises the following step of providing an effective method of conducting magnetometer error compensation and attitude angle error secondary modeling and correction, and realizing error correction of a whole system on the basis of an ellipsoid fitting method of improving expanded Kalman filter. The correction method is used for error correction of the attitude and course angles in an inertial integrated navigation and positioning system composed of an inertial measuring unit (IMU), a magnetometer and the like. According to the invention, a magnetic field compensation method is expanded to three-dimensional ellipsoid fitting from two dimensional elliptical fitting; a new ellipsoidal model and an improved extended Kalman filter method are utilized to conduct ellipsoid fitting; through the adoption of the method, the dynamical and real-time compensation for three-dimensional magnetic field interference of a carrier self can be effectively realized, and the accuracy in the measurement of the geomagnetic field is improved, thereby improving the precision of the course angle of the carrier; the error secondary modeling is conducted on the attitude angle information output by the navigation system, and then compensation is conducted on the output attitude angle to improve the precision of the attitude angle in real time.

This invention combines the precision spray process with in-flight laser treatment in order to produce direct write electronic components. In addition to these components, the process can lay down lines of conductive, inductive, and resistive materials. This development has the potential to change the approach to electronics packaging. This process is revolutionary in that components can be directly produced on small structures, thus removing the need for printed circuit boards.

The invention provides a vertical-takeoff auxiliary system for a fixed-wing aircraft. The vertical-takeoff auxiliary system comprises a multi-shaft rotor-wing aircraft and a fixed-wing aircraft. A plurality of throwing devices are installed in the middle of the fuselage bottom of the multi-shaft rotor-wing aircraft, and a plurality of hanging parts are installed in the fuselage middle of the fixed-wing aircraft; the hanging parts are connected with the throwing devices in a hung mode, and the fixed-wing aircraft is hung below the multi-shaft rotor-wing aircraft accordingly; the multi-shaft rotor-wing aircraft carries the fixed-wing aircraft to vertically take off to the preset height and the preset speed, then the throwing devices release the hanging parts, and the fixed-wing aircraft is separated from the multi-shaft rotor-wing aircraft to autonomously fly. By means of the vertical-takeoff auxiliary system in the mode, vertical takeoff of the fixed-wing aircraft can be achieved under the condition that an existing fixed-wing aircraft does not need to be greatly modified.

The invention discloses a nanofiber low-voltage electro-spinning device with auxiliary electrodes and relates to an electrostatic spinning device. The electro-spinning device is provided with a high-voltage DC power supply, a conducting pole plate, array nozzles, a high pressure air source, airway tubes, auxiliary electrodes, a fan, rollers and a collection plate; the positive pole of the high-voltage DC power supply is connected to the conducting pole plate, and the negative pole of the high-voltage DC power supply is grounded; polymer solution is located on the conducting pole plate, so that jet flow can be created on the upper surface of the solution during electro-spinning; the high pressure air source is connected to the array nozzles through the airway tubes, so that high pressure air can be provided for the array nozzles; the array nozzles are arranged between the auxiliary electrodes and the conducting pole plate so as to jet air flow for changing the flight direction of fiber, so that the nanofiber is guided to get through a gap between the auxiliary electrodes along with the air flow and deposit onto the collection plate; the auxiliary electrodes are arranged above two sides of the polymer solution and grounded; the fan is arranged above the collection plate, so that the fiber is deposited onto the collection plate by air pumping; and the collection plate is arranged above the auxiliary electrodes as a deposition base plate of the nanofiber.

A mass spectrometer is disclosed comprising a RF confinement device, a beam expander and a Time of Flight mass analyser. The beam expander is arranged to expand an ion beam emerging from the RF confinement device so that the ion beam is expanded to a diameter of at least 3 mm in the orthogonal acceleration extraction region of the Time of Flight mass analyser.

The invention relates to an unmanned patrol aircraft for power transmission lines. The unmanned patrol aircraft comprises an aircraft body, a camera system, a cloud deck, a nanometer battery, an aircraft control system, a wireless transmission system, a GPS positioning system and a ground receiving, controlling and managing system. The unmanned patrol aircraft has four ailerons which are symmetrically installed at two sides of a main beam; the unmanned patrol aircraft has the advantages of stable flight, a fast flight speed, high flexibility and great loading capacity; front and rear beams are of segmented design, which facilitates adjustment and wiring. The aileron horns of the ailerons are movably connected with an aileron fixing frame through bolts; the aileron fixing frame is equipped with folding positioning seats; the aileron horns rotate with the bolts as centers and are limited through the folding positioning seats; such a structure enables the aileron horns to be parallely drawn close onto the main beam after folding, so the unmanned patrol aircraft has a small size and is easy to carry. After the front and rear aileron horns are open, lines among center points of four motors on the front and rear aileron horns form a square, and such a structure enables the aircraft to maintain balanced flight and to have reduced current loss and long flying time.

An existing bottom-adjustable propeller-type flying object requires a device having a complex structure constructed through the combination of various components such as a servo, a control plate, and a hinge to control the rotor pitch at every moment and operate an adjustable blade for flight control. The bottom-adjustable propeller-type flying object of the disclosure includes a circular frame with a fixing plate and a protective plate installed at a lower portion of a shaft of a power propeller mounted to the central shaft, and an adjusting motor having an adjustable propeller. The flying object moves up or down by using force of the wind generated downward due to the rotation of the power propeller. The flying object makes a hovering flight, and leftward, rightward, forward, and backward flights by using the force of the wind generated due to the rotation of the adjustable propellers mounted on two adjusting motors.

The invention provides a vehicle-mounted power supply management and control system and equipment for a small-sized unmanned aerial vehicle. The system comprises a power supply switching and power supply management module, a power supply and distribution module, a data acquisition and interface conversion module; the power supply switching and power supply management module is used for realizing rectification and filtration, power supply switching, voltage conversion of a three-phase power supply of a generator and online charging of a backup battery group; the power supply and distribution module is used for realizing power supply and distribution for a self-driving vehicle, a steering engine, an electronic control unit, a short message device, a broadcasting station and an internal control circuit; and the data acquisition and interface conversion module is used for realizing voltage acquisition for the battery group, ECU data framing, electric level conversion from TTL to RS232 and control for a main power supply module and two electrical switching circuits. According to the vehicle-mounted power supply management and control system and equipment for the small-sized unmanned aerial vehicle, the integration degree of the avionics system of the unmanned aerial vehicle is higher; the power supply for the electric generator of the unmanned aerial vehicle is realized; and the flying endurance and the flying reliability are greatly improved.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a hybrid power multi-axis rotor-wing unmanned aerial vehicle. The hybrid power multi-axis rotor-wing unmannedaerial vehicle comprises an unmanned aerial vehicle body which comprises a flight control system and a multi-axis driving system arranged in a case. The hybrid power multi-axis rotor-wing unmanned aerial vehicle is characterized in that the hybrid power multi-axis rotor-wing unmanned aerial vehicle further comprises a fuel and electricity hybrid power system, a servo module and a measuring and controlling module; the fuel and electricity hybrid power system is constituted by a fuel piston engine, a fuel tank, a power generation module, a rectification module and a lithium battery; one end ofthe fuel piston engine is connected with the fuel tank through a fuel pipe, and the other end of the fuel piston engine is connected with the servo module; an output shaft of the fuel piston engine isconnected with the power generation module; the power generation module is connected with one end of the rectification module, and the other end of the rectification module is connected with the lithium battery in parallel and then connected with the multi-axis driving system; and the multi-axis driving system is constituted by a plurality of single-axis drivers. The hybrid power multi-axis rotor-wing unmanned aerial vehicle has the advantages of being long in endurance, large in load, easy to control, good in safety and the like.

The invention relates to a belt-transmission four-rotor-wing aircraft. The belt-transmission four-rotor-wing aircraft is provided with an engine, a main rack, a power distribution and transmission system and a flight control system, wherein a plurality of brackets are outwards extended from the power distribution and transmission system and are uniformly spaced to form cross shapes and the like, and rotor wing assemblies with changeable propeller pitches are arranged at the front ends of the brackets and comprise rotor wing rotation driving components and rotor wing propeller pitch changing components. According to the belt-transmission four-rotor-wing aircraft, four shafts and four rotor wings are driven by the engine, and the size of rising power of all the shafts is changed through changing the propeller pitches of all the rotor wings, so as to realize the change of the flight attitude of the aircraft; the fuel-driven engine is adopted, so that the effective payload is increased, and the flight time is prolonged, thus the gear-transmission four-rotor-wing aircraft is particularly applicable to long-time and long-distance operation.

The invention provides a natural laminar flow aerofoil profile with high lift. The natural laminar flow aerofoil profile is characterized in that the aerofoil profile is of a streamlined structure with a blunt-end leading edge and a weakly recurved trailing edge and the surface curve of the aerofoil profile is simply geometrically convex and is free of obvious curvature and inflection.

The invention discloses a novel multifunctional box type joined wing water unmanned aerial vehicle. The novel multifunctional box type joined wing water unmanned aerial vehicle comprises a ship body type vehicle body (1), a box type joined wing (2), a vertical empennage (3), a propeller propelling plant (4), a vehicle body load (5), and a wing solar power system (6); the ship body type vehicle body (1) comprises an upper arc vehicle body (11), a bottom multi-level fault rectifying ship body (12), and inhibiting spattering bilges (13); the bottom multi-level fault rectifying ship body (12) is provided with the upper arc vehicle body (11), and the inhibiting spattering bilges (13) on the two sides of the bottom part are located on the two sides of the bottom part of the ship body type vehicle body (1). The water unmanned aerial vehicle is higher in lift-drag ratio, the lift-drag ratio is more than 19, the water surface landing performance is good, the novel multifunctional box type joined wing water unmanned aerial vehicle is adaptable to various complicated water surface landing conditions, the capability of operating on the water surface for a long period of time is realized, and the novel multifunctional box type joined wing water unmanned aerial vehicle is excellent in adaptability.

The invention discloses a combined coaxial unmanned helicopter. The combined coaxial unmanned helicopter is provided with a helicopter shell, a helicopter body supporting structure, an engine, an oil tank, a helicopter main rotor, a helicopter main speed reducer, wings and a tail wing and further comprises a power distribution and clutch system and a propelling propeller. The propelling propeller is mounted on the rear portion of a helicopter body. The combined coaxial unmanned helicopter can fly at different flight stages according to different flight speeds, power of the engine is distributed to the main rotor and the propelling propeller through the power distribution and clutch system, and vertical take-off and landing, hovering, low-speed forward flying, medium-speed flying and high-speed flying are achieved. The combined coaxial unmanned helicopter has the advantages that compared with a conventional helicopter, the flying speed can be remarkably increased; one set of engine is used for supplying power to two sets of flying systems, and the weight is low; the two coaxial rotor wings are adopted, airflow is symmetrical, the pneumatic effect is good, the structure is compact, the size is small, the self-rotation mode is achieved at the high speed, and resistance force is smaller.

The present invention discloses a power supply management system for a solar energy unmanned aerial vehicle. The system comprise a MPPT (Maximum Power Point Tracking) module, an illumination sensor, a direct current boosting module, a coulometer, a plurality of relays and a master control module. The illumination sensor is connected with the master control module, the MPPT module is connected with a solar panel, the MPPT module is connected with a power system and an energy storage battery, the energy storage battery is connected with a power motor through a second relay, and the energy storage battery is connected with the master control module through the coulometer. The mode of utilizing solar energy to preferentially supply power to the power system is employed, the residual electric energy is supplied to the energy storage battery, and if the power requirement is high, the two-way power supply mode is employed to add the electric energy provided by the power supply system. The power supply management system for the solar energy unmanned aerial vehicle is reasonable in structure and high in universality, can realize uninterruptible power supply, continuously charge the energy storage battery and perform switching selection of the power supply in different conditions so as to reduce the electric energy loss caused by various reasons.

The invention discloses a fixed wing aircraft provided with multiple rotor wings and capable of realizing vertical take-off and landing. The fixed wing aircraft comprises a fuselage, aircraft wings and a tail wing, as well as power rack units arranged on the aircraft wings and the tail wing, wherein the power rack units comprise front rotor wings, rear rotor wings and tail rotor wings. According to the invention, the switching between the helicopter mode take-off and landing and fixed wing flight mode can be realized, the safety performance of the take-off and landing of the aircraft is improved, and the take-off and landing mode of the traditional fixed wing aircraft is changed.

The invention discloses a multi-rotor plant protection unmanned aerial vehicle, belonging to the technical field of unmanned aerial vehicles. The multi-rotor plant protection unmanned aerial vehicle comprises an undercarriage, a body, a rack, arms, a main rotor, an auxiliary rotor, a spray system and a control system, wherein the body is arranged above the undercarriage and connected with the undercarriage; the rack is arranged above the body and connected with the body; the arms are mounted on the rack; even number of arms are provided and symmetrically distributed on the rack; an engine is arranged at the upper part of the rack; the main rotor is connected with an output shaft of the engine; an motor is arranged on each arm; an output shaft of each motor is connected with the corresponding auxiliary rotor; a spoiler is arranged on each arm; the spoilers are used for offsetting the anti-torque effect generated by the rotation of the main rotor; the control system, the engine and the motors are all connected with a power supply; and the control system controls the working states of the main rotor, the auxiliary rotors and the spray system. In the invention, gasoline-electric hybrid power is adopted, the whole structure is simplified, the structure is simple, and the time of endurance is long.

The invention provides a multi-rotor type aircraft. The multi-rotor type aircraft comprises a main rotor and a plurality of secondary rotors, wherein the main rotor is driven by a fuel engine, and is arranged at the lower end or the upper end of the center position of the engine body of the fuel engine; the plurality of secondary rotors are distributed on the periphery of the engine body; the secondary rotors are driven by motors respectively. The multi-rotor aircraft has the advantages of high carrying capacity and long voyage time.