72results about How to "Low energy consumption in flight" patented technology

The invention discloses an unmanned aerial vehicle scheduling method and system based on particle swarm optimization and a readable storage medium. The method comprises the following steps: a controlcenter sends a task preparation instruction to a standby unmanned aerial vehicle group; after a task preparation instruction is received, the unmanned aerial vehicle group initializes vehicle body parameters and sends a response data packet to the control center server; the control center performs comprehensive analysis after receiving the response data packet, and determines an unmanned aerial vehicle group executing the task; a conventional path is preliminarily planned for each to-be-flied unmanned aerial vehicle, and a task is executed after receiving a starting instruction;d the unmannedaerial vehicle group and the control center keep a communication state all the time, and the control center performs whole-process scheduling based on particle swarm optimization according to the real-time state of each unmanned aerial vehicle. According to the method disclosed in the invention, by use of the particle swarm optimization technology, unmanned aerial vehicle scheduling intelligence is realized, scheduling management efficiency of the unmanned aerial vehicle group is improved, and the flight energy consumption of the unmanned aerial vehicle during task execution is effectively reduced.

The invention provides an unmanned aerial vehicle with a remote starting device, and solves the technical problem that an engine is liable to shut down when a small-sized unmanned aerial vehicle in the prior art flies. The unmanned aerial vehicle comprises an internal combustion engine, an electrical device and a starting motor, wherein the electrical device is electrically connected with the starting motor; the output shaft of the starting motor is in transmission connection with the rotary output end of the internal combustion engine through a transmission device; the electrical device is provided with a wireless signal receiving and sending module which remotely operates the starting motor to start and stop; and the electrical device is electrically connected with an inner power supply system of the small-sized unmanned aerial vehicle. According to the unmanned aerial vehicle provided by the invention, the remote starting device is arranged for the small-sized unmanned aerial vehicle, so that the technical effect that the engine is liable to shut down when the small-sized unmanned aerial vehicle flies in a bad environment is overcome; and the wireless signal receiving and sending module arranged in the electrical device is in signal connection with a control base station or a remote controller, so that start and stop of the starting motor are remotely and wirelessly operated, and therefore, powerful technical support is provided for wirelessly starting the internal combustion engine of the unmanned aerial vehicle.

The invention provides a zero backward thrust composite wing aircraft with ducted fan composite ailerons. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons comprises an aircraft body and composite lift wings which are fixedly mounted on the two sides of the aircraft body, wherein the aircraft body is arranged as a deck platform; self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; ducted fan propellers are arranged at the front ends of ducted fan thrust self-energizedcomposite ailerons; the self-sealing ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electricity, liquid and gas ports and the wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wings through thewing hinges. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons has the characteristics that the taking-off and landing distance is short, the flying speed is high, the structural strength of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; and the ailerons adopt compositelift forces to guarantee appropriate power.

The invention provides a foldable composite wing aircraft with twin-propeller thrust composite ailerons. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons comprises an aircraft body and composite lift wings, wherein the composite lift wings are mounted on the two sides of the aircraft body in a foldable manner; the aircraft body is arranged as a deck platform;self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; propellers are arranged at the front ends of propeller thrust self-energized composite ailerons; self-sealing ducted fans are arranged in the propeller thrust self-energized composite ailerons; electricity, liquid and gas ports and wing hinges are arrangedon one side or two sides of the propeller thrust self-energized composite ailerons; and the propeller thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons has the advantages that the take-off and landing distance is short, the flying speed is high,the structural intensity of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; the ailerons adopt composite lifts so that the adaption range of the power is guaranteed.

The present invention relates to a rotation table apparatus for folding a tethered unmanned aerial vehicle arm, and a method for folding an unmanned aerial vehicle arm. The rotation table apparatus comprises: a rotation table base, wherein the rotation table base is not arranged at any parts of a tethered unmanned aerial vehicle body; a rotation table mechanism rotatably arranged on the rotation table base; a clamping mechanism, wherein the bottom portion is arranged at the upper end of the rotation table mechanism; and an unmanned aerial vehicle arm rotation member for fixing and rotating anunmanned aerial vehicle arm, wherein the unmanned aerial vehicle arm rotation member comprises a ratchet-pawl locking mechanism, and is arranged at one side above the clamping mechanism and is connected to the clamping mechanism, and the extending direction intersects with the extending direction of the clamping mechanism.

The invention relates to a ground-powered flight kart and a system. The ground-powered flight kart comprises a flight kart body, wherein a retractable trolley pole, which can transfer among tracks and is used for being connected with ground-powered tracks in order to input electrical energy, is arranged at the bottom of the flight kart body. A ground-powered flight kart system can be formed through the ground-powered flight kart and the ground-powered tracks as well as a ground flight control integrator; the ground-powered flight kart system can be used as a primary flight training apparatus, and no coaches, coach aircrafts or no simulated aircrafts are needed; the ground-powered flight kart system can also be used as flight entertainment equipment of vast masses for experiencing the fun of flight, so that physical and mental pleasures are provided, a flight culture is spread, the safety is guaranteed, and the application scope is very wide; and besides, due to the adoption of a ground-powered scheme, the cost is low, flights can be performed in venues, the industrialization of flight is facilitated, and the flight experience can be closer to the people.

The invention provides a novel flexible-to-operate azimuth control system, which consists of a framework and an integrated circuit board, wherein the framework is provided with an operation and control panel; the integrated circuit board is built in the framework; and a work mode display and a plurality of mode switching press buttons are arranged on the panel. A sensor and a controller of the novel flexible-to-operate azimuth control system are combined into a whole; and the debugging mode of a steering engine can be selected through a work state regulating knob. The novel flexible-to-operate azimuth control system has the advantages that the size is small; the weight is light; the flight energy consumption can be effectively reduced; and the endurance time is prolonged.

The invention provides an azimuth controller applicable to an aircraft. The azimuth controller is composed of a main body and an integrated control chip, wherein a kinetic energy display signal lamp and a plurality of control buttons are arranged on a panel; the control buttons include a mode conversion switch, a positive and negative direction control button, a retarded regulator and a maximum stroke regulator; and the various control buttons are electrically connected to the integrated control chip. According to the azimuth controller applicable to the aircraft, an inductor is integrally combined with the controller and the modes of a steering engine are switched and selected by virtue of the mode conversion switch; therefore, the azimuth controller is not only applicable to a digital steering engine but also suitable for an analog steering engine.

The invention provides a novel azimuthal control system flexible to operate. The azimuthal control system is composed of a skeleton which is provided with an operating panel and an integrated circuit board which is arranged in the skeleton, wherein a working mode display and a plurality of mode switching buttons are arranged on the panel. According to the novel azimuthal control system flexible to operate, a sensor and a control are integrally combined, and the debugging mode of a steering engine is selected by virtue of a working condition regulating knob; and the azimuthal control system disclosed by the invention is small and thin in size and relatively light in weight, and flight energy consumption can be effectively reduced, so that time of endurance is prolonged.

The invention provides a toy aircraft remote control intelligent control system, which consists of a body and an integrated control chip, wherein a function display signal lamp and a plurality of control buttons are arranged on the panel; the control press buttons comprise a mode conversion switch, a positive and reverse control button, a delay regulator and a maximum stroke regulator; and each control button is electrically connected with the integrated control chip. The toy aircraft remote control intelligent control system has the advantages that a sensor and a controller are combined into a whole; and the mode of a steering engine is switched and selected through a mode conversion switch, so that the toy aircraft remote control intelligent control system is applicable to a digital steering engine and is also applicable to a simulated steering engine.

The invention provides a rear single-duct fan type combined wing manned aircraft which is composed of a rear single-duct fan type combined wing aircraft and a manned cabin. The rear single-duct fan type combined wing aircraft comprises an aircraft body, combined lift force wings fixedly installed on the two sides of the aircraft body and a ducted fan propeller. The aircraft body is arranged to bea deck platform. Self-closed ducted fans are arranged in the combined lift force wings, and wing hinges are designed on the outer sides of the combined lift force wings. The manned cabin is installedbelow the aircraft body. The rear single-duct fan type combined wing manned aircraft has the beneficial effects of being short in take-off and landing distance, high in flight speed, high in wing structural strength, capable of storing energy through the wings, low in flight energy consumption, long in hang time, high in safety and the like.

The invention discloses a flying automobile with foldable rotors. The flying automobile comprises an automobile body, rotor mechanisms, a power device and a transmission device, wherein the power device and the transmission device are both installed at the bottom of the automobile body; one set of rotor mechanisms stacked up and down are installed on the front portion of the automobile body, and the other set of rotor mechanisms stacked up and down are installed on the rear portion of the automobile body; and turnover rods are installed on the front portion and the rear portion of the automobile body, and the four rotor mechanisms are hinged to the turnover rods. The flying automobile is stable and safe in flight, the rotor mechanisms are arranged to be foldable, so that the lateral dimension of the flying automobile is reduced, and the flying automobile can travel on land conveniently and has the same high maneuvering performance both in the air and on land.

The invention relates to a rear single ducted fan type composite wing aircraft with double ducted fan composite ailerons. The rear single ducted fan type composite wing aircraft with the double ductedfan composite ailerons comprises a rear single ducted fan type composite wing aircraft and ducted fan thrust self-energized composite ailerons which are assembled on the two sides of the rear singleducted fan type composite wing aircraft, wherein the rear single ducted fan type composite wing aircraft comprises an aircraft body, composite lift wings and a propeller, wherein the composite lift wings are fixedly mounted on the two sides of the aircraft body; the aircraft body is a deck platform; self-sealed ducted fans are placed in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; self-sealed ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electric, liquid and gas interfaces and wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wingsthrough the wing hinges. The rear single ducted fan type composite wing aircraft with the double ducted fan composite ailerons has the advantages of short takeoff and landing distance, high flying speed, high wing structural strength, energy storage ability of the wing, low flying energy consumption, long hang time and so on; and the large-area composite lift wings can have effects of gliders inan emergency case, the safety of the aircraft is greatly enhanced, and safeties of personnel and materials are guaranteed.

The invention discloses a composite lift force aircraft with a development platform. The composite lift force aircraft consist of a rear single-propeller type composite wing aircraft, thrust-free self-powered composite auxiliary wings assembled at the two sides of the rear single-propeller type composite wing aircraft and an manned bin, wherein the rear single-propeller type composite wing aircraft comprises a machine body, composite lift force wings which are mounted at the two sides of the machine body in a foldable mode, and a propeller; the machine body is a deck platform; self-sealing ducted fans are arranged in the composite lift force wings; wing hinges are designed at the outer sides of the composite lift force wings; self-sealing ducted fans are arranged in the thrust-free self-powered composite auxiliary wings; an electric-liquid gas interface and a wing hinge are arranged at one side or the two sides of each propeller thrust self-powered composite auxiliary wing, and are movably connected with the composite lift force wings through the wing hinges; and the manned bin 112 is mounted below the machine body. The composite lift force aircraft has the characteristics of beingshort in takeoff and landing distance, high in flying speed, high in wing structural strength, capable of storing energy by wings, low in flying energy consumption, long in hang time, high in safetyand the like.

The invention relates to a rear single screw foldable composite wing manned craft with an additional wing. The rear single screw foldable composite wing manned craft comprises a craft body, the composite lift force wings mounted at the two sides of the craft body in a foldable manner and a propeller, wherein the craft body is arranged as a deck platform, the self-sealing ducted fans are arranged in the composite lift force wings, and the wing hinges are designed at the outer sides of the composite lift force wings; a manned cabin is arranged below the craft body, a magnetic type automatic interlocking interface male connector and a magnetic type automatic interlocking interface female connector are respectively arranged in front of and behind the composite lift force wings, and the magnetic type automatic interlocking interface male connector and the magnetic type automatic interlocking interface female connector have the same size. A wing hinge and an electric-hydraulic-gas interfaceare arranged on one side, facing the craft body, of the additional wing, and the additional wings are installed at the outer sides of the composite lift force wings in a foldable manner through the wing hinges. The craft has the characteristics of short take-off and landing distances, high flight speed, high structural strength of the wings, energy storage wings, low flight energy consumption, long hang time, high safety and the like.

The invention provides a rear single ducted thrust type composite wing manned aircraft with double ducted thrust composite auxiliary wings and additional wings. A rear single ducted fan type compositewing aircraft comprises an aircraft body, composite lifting power wings which are fixedly installed at the two sides of the aircraft body and propellers, wherein the aircraft body is arranged as a deck platform; self-sealing ducted fans are arranged in the composite lifting power wings, and wing hinges are arranged on the outer sides of the composite lifting power wings; the propellers are ductedfan propellers; the ducted fan propellers are arranged at the front ends of ducted fan thrust self-powering composite auxiliary wings, self-sealing ducted fans are arranged in the ducted fan thrust self-powering composite auxiliary wings, an electro-hydraulic gas interface and a wing hinge / electro-hydraulic gas interfaces and wing hinges are arranged at one side or two sides of the ducted fan thrust self-powering composite auxiliary wings, and the ducted fan thrust self-powering composite auxiliary wings are movably connected with the composite lifting power wings by the wing hinges; the additional wings are installed at the outer sides of non-thrust self-powering auxiliary wings in a foldable mode by wing hinges; fuels or batteries are arranged in the additional wings, and a manned cabin is installed under the aircraft body. According to the rear single ducted thrust type composite wing manned aircraft with the double ducted thrust composite auxiliary wings and the additional wings, the ducted fans can better protect propulsion screw propellers, meanwhile, the safety of personnel on and off the aircraft is ensured, and the efficiency of the propellers is improved.

The invention provides a novel direction control system flexible to manipulate. The system comprises a framework and an integrated circuit board in the framework, and the framework is provided with a control panel. The panel is provided with a work mode displayer and multiple mode switching buttons. A sensor of the novel direction control system flexible to manipulate and a controller are combined, and the debugging mode of a steering engine is selected through a work state adjusting knob. The system is small in size, light and capable of effectively reducing flying energy consumption and prolonging flight duration.

A foldable composite-wing manned aircraft with double-propeller-thrust composite auxiliary wings is provided. A rear-thrust-free type composite-wing aircraft includes a fuselage and composite liftingwings mounted, in a foldable manner, at two sides of the fuselage. The fuselage is a deck platform. Self-sealing ducted fans are disposed in the composite lifting wings. Hinges are arranged at outer sides of the composite lifting wings. Front ends of propeller-thrust self-powered composite auxiliary wings are provided with propellers. Self-sealing ducted fans are disposed in the propeller-thrust self-powered composite auxiliary wings. Electro-hydraulic gas connectors and wing hinges are disposed on one or two sides of the propeller-thrust self-powered composite auxiliary wings. The composite auxiliary wings are movably connected to the composite lifting wings through the wing hinges. A manned bin is mounted at the lower part of the fuselage. The aircraft has characteristics of short take-off and landing distances, a high flight speed, high wing structural strength, a characteristic that the wings can store energy, low flight energy consumption, long flying time, high safety, and the like. Composite lifting force is adopted by the auxiliary wings, thus ensuring the adaptive range of power.