73results about How to "Low energy consumption in flight" patented technology

A torque self-balancing three-ducted-fan bionic aircraft mainly comprises a spherical man-carrying cabin, a flight lift force bottom board, bionic wings, a bionic tail, a transitional aircraft frame,three self-balancing ducted fans / propeller devices, a safety protection system and a power automatic control system. The top and the bottom of the rotatable spherical man-carrying cabin are connectedwith the front end of the transitional aircraft frame, and the front end of the bionic tail is connected with the rear end of the transitional aircraft frame; the bionic wings are fixedly connected tothe top of the transitional aircraft frame, and the flight lift force bottom board is fixedly connected to the bottom of the transitional aircraft frame; and two of the three self-balancing ducted fans / propeller devices are fixed to the bionic wings, the other self-balancing ducted fan / propeller device is fixed to the center line of the head and the tail of the bionic tail, and the three self-balancing ducted fans / propeller devices and the safety protection system are all electrically connected with the power automatic control system. The aircraft is simple in structure, capable of verticallytaking off and landing and using an aircraft body to supply lift force, low in energy loss, good in applicability, low in manufacturing cost and high in safety, and meanwhile the self-balancing problem of the three ducted fans is effectively solved.

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 discloses a hovering toroidal winged saucer aircraft capable of vertical take-off and landing, The aircraft is composed of an elliptical fuselage, a cockpit, passenger cabin, a power cabin, a conical tail rudder, an annular wing, fa light controller and so on. Because the fuselage adopts elliptical dish structure, it is the most ideal configuration to fly in the air flow field, andthe disturbance to the gas flow field is the smallest, and the air drag is the smallest in the flight process. This configuration has the capability of vertical take-off and landing, fixed height hovering and so on, which can be realized by multi-axis helix-powered aircraft. However, compared with multi-axis helix-powered aircraft, its flight attitude is almost unaffected by the side flow of air,and its flight attitude is more stable and reliable. At that same time, the invention can obtain the lift force require by the aircraft, reduce the drag force of the aircraft and improve the flight safety performance, and is easy to popularize and apply. The invention also has the flight speed that the fixed-wing duct aircraft can realize, and the flight energy consumption is far less than the exist fixed-wing duct aircraft, and the take-off and landing do not require runway assistance.

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 novel direction control system flexible to manipulate. The direction control system is composed of a framework provided with a manipulation panel and an integrated circuit board arranged in the framework. The panel is provided with a working mode displayer and multiple mode switching buttons. An inductor and a controller of the novel direction control system flexible to manipulate are combined, and a debugging mode of a steering engine is selected through a working state adjusting knob. The novel direction control system is small in size, low in weight and capable of effectively reducing flight energy consumption and prolonging endurance time.

The invention belongs to the technical field of rotorcrafts and relates to a helicopter type rotorcraft. The helicopter type rotorcraft comprises a body, an engine, a main rotor mechanism, a feed mechanism, a tail vane and an undercarriage, and is characterized in that the main rotor mechanism comprises a rotationally assembled spindle, a main rotor is mounted at the upper end of the spindle through a variable-distance rotor handpiece assembly, and the lower end of the spindle is connected with a main speed reduction box of the engine through a main clutch; the feed mechanism comprises two angle gearboxes which are symmetrically mounted on brackets on the left and right sides of the body, power input ends of the two angle gearboxes are in drive connection with the main speed reduction boxof the engine through correspondingly arranged drive shaft assemblies respectively; variable-distance propeller assemblies are mounted on power output shafts on the backs of the two angle gearboxes respectively. The rotorcraft can realize vertical take-off and landing, the site area required for taking off of the rotorcraft is small, and the use range of the rotorcraft is wide.

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 relates to an integrally molded four-axis unmanned aerial vehicle main body and a manufacturing method thereof. The integrally molded four-axis unmanned aerial vehicle main body is formed by paving and integrally molding a first carbon-fiber prepreg cloth layer, a second carbon-fiber prepreg cloth layer, a first glue film layer, a foamed core, a second glue film layer, a first carbon-fiber one-way cloth layer, a second carbon-fiber one-way cloth layer, a third second carbon-fiber prepreg cloth layer and a fourth second carbon-fiber prepreg cloth layer from bottom to top in sequence. The integrally molded four-axis unmanned aerial vehicle main body and the manufacturing method have the advantages that the weight of the unmanned aerial vehicle can be greatly reduced, the strength of the unmanned aerial vehicle and the levelness of blades of the unmanned aerial vehicle are improved, the looseness of standard parts due to long-time flying is avoided, and the overall performance of the unmanned aerial vehicle is improved.

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 invention relates to an unmanned aerial vehicle flight control system and a method based on Beidou navigation. The flight control system comprises a processor module for controlling the unmanned aerial vehicle to fly according to a corresponding path and a path optimization subsystem connected with the processor module, wherein the path optimization subsystem is used for acquiring real-time data of wind between buildings and establishing an urban inter-building wind tunnel network. After the unmanned aerial vehicle sets a flight destination, the path optimization subsystem is used for selecting the optimal path for enabling the unmanned aerial vehicle to fly to the destination according to the urban inter-building wind tunnel network, the optimal path for enabling the unmanned aerial vehicle to fly to the destination is acquired through the path optimization subsystem, the direction of the wind between the buildings is made full use of, the flying speed is improved, and the flying energy consumption is reduced.

The invention provides a thrust compound auxiliary wing with double ducts and a rear single-propeller type compound wing man carrying aircraft with the auxiliary wings. The rear single-propeller typecompound wing man carrying aircraft is composed of a rear single-propeller type compound wing aircraft and the ducted fan thrust self-energy-supply compound auxiliary wings arranged on the two sides of wings of the rear single-propeller type compound wing aircraft. The rear single-propeller type compound wing aircraft comprises an aircraft body, the compound lift force wings fixedly installed on the two sides of the aircraft body and a thruster. The aircraft body is arranged as a deck platform; self-sealed ducted fans are arranged in the compound lift force wings, and wing hinges are arrangedon the outer sides of the compound lift force wings; and the thruster is a propeller thruster. The rear single-propeller type compound wing man carrying aircraft has the beneficial effects that the take-off and landing distance is short, the flight speed is high, the wing structural strength is high, the wings can store energy, flight energy consumption is low, and the hang time is long, the auxiliary wings adopt compound lift force, the adaption range of power is guaranteed, meanwhile, the large-area compound lift force wings can achieve the effect of a glider under an emergency, the safety of the aircraft is greatly improved, and safety of personnel, goods and materials 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 an unmanned aerial vehicle for spatial geography shooting. The unmanned aerial vehicle includes a shell body; four fixing connecting rods are installed on the top end of the shell body and annularly and uniformly distributed at the periphery of the shell body; a camera is installed in the middle position on the bottom end of the shell body; screw rod motors are respectivelyinstalled at each of the four corners on the bottom end of the shell body; driving motors are fixed on one ends of four fixing connecting rods through covers; the bottom ends of the four screw rod motors are rotatably connected to telescoping rods through screw rods; and cushioning footpads are fixed on the bottom ends of the four telescoping rods. The internal of the covers are provided with sound insulation cotton layers, so that the problems, that the working of the driving motors can easily generate noise which can cause noise pollution on environments, can be solved; and through the arrangement of the telescoping rods, the telescoping of supporting legs of the unmanned aerial vehicle can be realized, the flight resistance of the unmanned aerial vehicle can be decreased, the flight energy consumption of the unmanned aerial vehicle can be reduced, the flight path of the unmanned aerial vehicle can be enhanced, and therefore, the unmanned aerial vehicle can be more energy-saving andefficient.

The invention discloses a rear single-vortex type composite wing manned aircraft. The rear single-vortex type composite wing manned aircraft comprises a rear single-vortex type composite wing aircraftand a manned bin, wherein the rear single-vortex type composite wing aircraft comprises a machine body, composite lifting wings fixedly mounted at the two sides of the machine body, and a propeller;the machine body is a deck platform; vertical tail wings are further arranged above or below the machine body; the vertical tail wings are arranged at the two sides of the wings; the vertical tail wings can realize folding; the rear surfaces of the vertical tail wings are equipped with movable vertical rudder wings; self-sealed duct fans are arranged in the composite lifting wings; wing hinges andelectrical gas interfaces are designed at the outer sides of the composite lifting wings; the propeller is a turbine jet engine; and the manned bin is mounted below the machine body. The rear single-vortex type composite wing manned aircraft integrates characteristics of the turbine jet engine, and has the characteristics of being short in lifting distance, rapid 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 provides a foldable composite-wing cargo aircraft provided with single rear propeller. The foldable composite-wing cargo aircraft comprises a single rear propeller type composite-wing aircraft and a cargo bin, wherein the single rear propeller type composite-wing aircraft comprises an aircraft body, composite lift wings mounted on two sides of the aircraft body in a foldable manner and a thruster; the aircraft body is set as a deck platform; a self-sealing ducted fan is arranged in each composite lift wing, and a wing hinge (1028) is designed on the outer side of the composite lift wing; a magnetic type automatic interlocking port male head and a magnetic type automatic interlocking port female head are arranged on the front and rear sides of each composite lift wing respectively and are of the same size; the thruster is the propeller; the cargo bin is mounted at the lower part of the aircraft body. The foldable composite-wing cargo aircraft has the characteristics of short taking-off and landing distance, high flying speed, high wing structural strength, low flying energy consumption, long hang time and high safety, and the wings can store energy.

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 propeller-thrusted composite wing manned aircraft with additional wings. A composite wing aircraft with a rear single-propeller comprises an airframe, additional wings assembled on two sides of a wing, and a manned cabin; a self-enclosed ducted fan is arranged in the composite lift wing, and wing hinges are designed on the outside of the composite lift wing; the wing hinge and an electro-hydraulic gas interface are arranged on one side, towards the airframe, of each additional wing, and the additional wing is arranged on the outside of the composite lift wing in a folding way through the hinge wing; the electro-hydraulic gas interface is provided with a cover, and battery and fuel are built in the additional wing; and the manned cabin is arranged below the airframe. The composite wing manned aircraft disclosed by the invention is not only short in take off and land distance, fast in flight speed, high in wing structure intensity, low in flight energy consumption, long in hang time and high in security, and the wing can store energy; the electro-hydraulic gas interface is arranged on one side or two sides of the additional wing, the energy intercommunication between the additional wing and the composite lift aircraft airfoil is realized, and the flexibility of the whole aircraft is improved since the action is controlled by the composite lift aircraft.

The invention provides a rear single ducted fan type composite-wing aircraft with zero thrust composite ailerons and additional wings. The rear single ducted fan type composite-wing aircraft with thezero thrust composite ailerons and the additional wings comprises a rear single ducted fan type composite-wing aircraft, zero thrust self-energized ailerons and additional wings, wherein the zero thrust self-energized ailerons and the additional wings are assembled on the two sides of wings; the additional wings are mounted on the external sides of the zero thrust self-energized ailerons through wing hinges in a foldable manner. The rear single ducted fan type composite-wing aircraft with the zero thrust composite ailerons and the additional wings has the advantages 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, large-compositelift wings can have effects of gliders in the case of emergency, 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.

The invention provides a rear single ducted fan type composite wing aircraft with zero thrust composite ailerons. The rear single ducted fan type composite wing aircraft with the zero thrust compositeailerons comprises a rear single ducted fan type composite wing aircraft and zero thrust self-energized composite ailerons which are assembled on the two sides of the rear single ducted 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 aircraft body; the aircraft body is arranged as a deck platform; self-sealed ducted fans are embedded 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 zero thrust self-energized composite ailerons; electricity, liquid and gas ports and wing hinges are arranged on one sides ortwo sides of the zero thrust self-energized composite ailerons; and the zero thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges. Therear single ducted fan type composite wing aircraft with the zero thrust composite ailerons has the advantages that the take-off and landing distance is short, the flying speed is high, the wing structural strength is high, the wing can store energy, the flying energy consumption is low, the aircraft can stay in the air for long time and so on; and the large-area composite lift wings can have effects of a glider in case of emergency so that the safety of the aircraft is greatly enhanced and safeties of personnel and materials are guaranteed.