56results about How to "Increase cruising speed" patented technology

The invention relates to a tilt rotor aircraft adopting parallel coaxial dual rotors, which comprises a fuselage, wings, an empennage, a pitch control scull system, a landing gear, a power and fuel system, a transmission system, a rotor system, a rotor nacelle and a tilt system, wherein the wings are arranged at the center section of the fuselage; the empennage and the pitch control scull system are arranged at the tail of the fuselage; the landing gear is positioned at the belly of the fuselage; the power and fuel system is arranged inside the center section of the fuselage and is connected with the rotor system and the pitch control scull system through the wings and the transmission system in the fuselage; the rotor system is arranged on the rotor nacelle at the tip of the wings; partial wing which is fixedly connected with the rotor nacelle and simultaneously can tilt is arranged at the inner side of the rotor nacelle; and the tilt system is arranged in the wings and is connected with the rotor nacelle and the partial wing which can tilt. The tilt rotor aircraft is mainly characterized by adopting the pitch control scull system, the parallel coaxial dual rotors and the partialwing which can tilt to realize flight status transformation and conventional taxiing and landing, thereby improving the forward speed and the propulsive efficiency.

A tilt rotor aircraft adopting a thrust tail rotor and a slipstream rudder for operation and propelling and a design of two parallel rotary wings and common pneumatic distribution comprises an airframe, wings, an empennage, a system of thrust tail rotor and slipstream rudder, an undercarriage, a power-fuel system, a transmission system, a rotary wing system, a rotary-wing nacelle and a tilt rotor system of the rotary-wing nacelle. The aircraft adopts the system of the thrust tail rotor and slipstream rudder to operate the VTOL and the pitching and drifting of the forward flight; the system comprising the thrust tail rotor, an elevator and a rudder is arranged on the empennage; a tilting wingtip appears as a small-area wing which is arranged on the outside of the rotary-wing nacelle and rotates together with the rotary-wing nacelle; the plane shape of the tilting wingtip appears as a trapezoid of leading edge sweepback and trailing edge sweepforward and the aspect ratio is 1.5 and the area of the tilting wingtip occupies about 15 to 20 percent of the whole wing area and the tilting wingtip is just integrated with the appearance of the rotary-wing nacelle and fixedly connected with a nacelle bevel gear box. The tilt rotor aircraft is a novel aircraft type with the development potential and prosperous prospect.

An aircraft includes a fuselage and a pair of channel wings which may vary incidence with respect to the fuselage and a pair of channel canards which can also vary incidence with respect to the fuselage and that can move independently of each other for the purpose of vertical takeoff and landing as well as forward and reverse flight. The wings may have multiple channels and may be powered by single propeller or contra-rotating propellers. The thrust to the propellers may be provided with an internal combustion engine or electric motors or a turbo prop or hybrid system. The channel wing allows the fuselage to maintain a level pitch with respect to the horizon. The aircraft will also have increased maneuverability in hover because it can independently vary the incidence of the wings and canards and be able to tightly turn about a point.

The invention provides a vertical take-off and landing fixed-wing unmanned aerial vehicle, which belongs to the technical field of aircrafts. The purpose is to solving problems that the take-off and landing condition of a fixed-wing aircraft is harsh, the loitering speed of a rotor craft is low and the endurance of the rotor craft is short in the prior art are solved. The vertical take-off and landing fixed-wing unmanned aerial vehicle comprises a fixed-wing structure system, a fixed-wing power system, a rotor structure and power system, a rotor structure supporting piece as well as a flight control system and an avionic system, wherein the fixed-wing power system comprises a single cylinder two-stroke engine and a propeller A, which are fixed at the tail end of an aerial vehicle body; a power output end of the engine is connected with the propeller A; the rotor structure and power system is arranged on the fixed-wing structure system; the rotor structure and power system comprises a motor, an electronic speed controller and propellers B; the motor is electrically connected with the electronic speed controller; an output end of the motor is connected with the propellers B; four propellers B are respectively arranged on the upper end surfaces of two supporting rods of the fixed-wing structure system; the propeller A is perpendicular to the propellers B; the rotor structure supporting piece is fixed at the upper end of a wing of the fixed-wing structure system and used for mounting a rotor power system; and the flight control system and the avionic system are used for controlling the flight path and posture of the unmanned aerial vehicle.

The invention relates to an inclined rotating wing aircraft with telescopic wing membranes. The inclined rotating wing aircraft comprises an aircraft body, a center shaft, a main transmission mechanism, first to third power units, an outer side rod, a support rod, a main wing membrane, a flight controller, and first to third undercarriages. The inclined rotating wing aircraft disclosed by the invention is improved on the basis of the structure of the traditional four-wing aircraft, and an inclined rotating structure of an inclined rotating four-rotary wing aircraft and a wing membrane structure of a flapping wing aircraft are added. According to the inclined rotating wing aircraft, the structural state of the inclined rotating wing aircraft includes a ground sliding state, a four-rotary wing flying state and a high-altitude cruising state; when the inclined rotating wing aircraft is in a ground movement state, the undercarriages contact with the ground, the main wing membrane is open, and the forward movement, backward movement, left rotation movement, right rotation movement, climbing movement and downgrade movement of the aircraft are realized by regulating the speed of four rotary wings; the movement state of the aircraft on the ground is realized under the action of the undercarriages, and the movement state is impossible to realize by the inclined rotating four-rotary wing aircraft and the flapping wing aircraft; and the climbing movement and the downgrade movement can be realized without changing the state of the aircraft, so that the energy consumption is reduced, and the complexity of a control program is prevented.

The invention discloses a novel tilt-rotor unmanned aerial vehicle attitude control system. The system comprises two parts of a hardware circuit and control software, wherein the hardware circuit comprises a main control chip, a gyroscope, a sensor, a remote controller, a heading attitude control mechanism and a tilt-rotor execution mechanism, the main control chip captures an instruction of the remote controller through wireless transmission, an expected attitude of the remote controlled instruction is compared with a real-time attitude monitored by the gyroscope, a compared result serves as controlled input quantity, and a corresponding control command is output after the input quantity is operated and processed by the main control chip. By means of close integration of software and hardware, an unmanned aerial vehicle can detects real-time attitudes of the vehicle and controls movement of the heading attitude control mechanism and the tilt-rotor execution mechanism according to the remote controller instruction, and the aircraft mode can be freely switched between a fixed wing aircraft and a rotorcraft. According to the novel tilt-rotor unmanned aerial vehicle attitude control system, great practical significance is achieved for development of tilt-rotor unmanned aerial vehicles, and high reference value is achieved for development of manned tilt rotorcrafts.

A rotorcraft having an enhanced configuration in which a simple wing and a propulsive anti-torque system are combined is disclosed. The propulsive anti-torque system includes an anti-torque thruster system in which a variable pitch fan is installed internal to the tail boom of the rotorcraft and an anti-torque thruster nozzle is mounted at the extremity of the tail boom. The fan is driven directly from the main rotor drive. The configuration and location of the fan allows the primary exhaust from the engine to be mixed with the compressed air flow from the fan. The mixed air flow from the fan and the engine passes through the tail boom and out the thruster nozzle.

The invention discloses an offshore wind power intelligent inspection system which comprises a buoy and an unmanned aerial vehicle take-off and landing recovery platform. The side surface of the buoyis fixedly provided with a water jet propulsion device, and the water jet propulsion device is composed of a water jet propeller and a protective cover; the two sides of the upper surface of the buoyare connected with a deck through a front damping device and a rear damping device correspondingly, an underwater inspection device is fixedly installed on the lower surface of the deck, and the unmanned aerial vehicle take-off and landing recovery platform is fixedly installed in the middle of the upper surface of the deck; and an intelligent unmanned aerial vehicle is correspondingly arranged atthe upper end of the unmanned aerial vehicle take-off and landing recovery platform. According to the offshore wind power intelligent inspection system, a novel structural design is adopted so that the device can enable an intelligent unmanned aerial vehicle and an unmanned ship to work cooperatively, the detection range of equipment is expanded, the unmanned ship operates autonomously through awater jet propulsion structure, and the cruising efficiency is improved; and an anti-wave structure is arranged in the device, and the relative stability of the unmanned ship in the cruising process is improved.

The invention discloses a power-operated tail-sitting type mixed layout vertical take-off and landing aircraft. The power-operated tail-sitting type mixed layout vertical take-off and landing aircraft is composed of a fuselage, airfoils, motors, propellers and landing gears; the fuselage axis coincides with the OX axis of a body axial system, the projections of the fuselage axis and the OX axis in an XOY plane of the body axial system are distributed in an X shape; each airfoil on the fuselage is divided into several sections, sweepback angles and dihedral angles of all the sections are different from one another, and excellent pneumatic performance and maneuvering performance are achieved through positively-curved airfoil profiles and negatively-curved airfoil profiles; four sets of propeller-motor power systems are installed on the four airfoils correspondingly, and the distances between the positions where the propeller-motor power systems are located and the OX axis of the body axial system are the same; and four power devices take off in an X-shaped quad-rotor mode in the vertical take-off and landing processes and complete conversion operation to enter a cruising state through different tensile forces of the motors or by being matched with maneuvering surfaces, and required maneuvering is completed through tensile force changing of the motors in the whole process. The power devices of the aircraft are simple, the control mode is reliable, propeller slipstreams can be effectively utilized, and the aircraft is suitable for serving as flying platforms of a tail-sitting type vertical take-off and landing unmanned aerial vehicle.

The invention provides a separable four-propeller double-wing unmanned aerial vehicle. The separable four-propeller double-wing unmanned aerial vehicle comprises a first double-propeller single-wing unmanned aerial vehicle, a second double-propeller single-wing unmanned aerial vehicle, a first arrestment net parachute cabin, a second arrestment net parachute cabin, a first arrestment net pod and a second arrestment net pod, wherein the first double-propeller single-wing unmanned aerial vehicle is connected with the first arrestment net parachute cabin through a first connection mechanism, and the first arrestment net pod is in rigid connection with the first arrestment net parachute cabin; the second double-propeller single-wing unmanned aerial vehicle is connected with the second arrestment net parachute cabin through a second connection mechanism, and the second arrestment net pod is in rigid connection with the second arrestment net parachute cabin; and the first arrestment net pod is connected with the second arrestment net pod through a third connection mechanism. According to the separable four-propeller double-wing unmanned aerial vehicle, arrestment is conducted through cooperation of the two double-propeller single-wing unmanned aerial vehicles, the flexibility is high, secondary arrestment can be carried out, and the recoverability is achieved; and the cost is low, and the separable four-propeller double-wing unmanned aerial vehicle is applied to arrestment of aerial low, slow and small targets.

The invention relates to a gravity-center-adjustable composite propulsion unmanned aerial vehicle and the control method thereof, two power machine arms of the unmanned aerial vehicle are hinged to a comprehensive bearing vehicle body in parallel through four cross beams, and rotary joints rotate to drive the machine arms to move forwards and backwards, so that gravity center adjustment of the unmanned aerial vehicle is achieved; the unmanned aerial vehicle adopts a lift rotor wing and a propulsion rotor wing for composite propulsion; the left propulsion rotor and the right propulsion rotor oppositely rotate to counteract the reverse torsion moment, differential rotation provides course control moment when the unmanned aerial vehicle cruises, the self-adaptive lift rotor flies at a positive attack angle, and the attack angle of the unmanned aerial vehicle is adjusted through gravity center adjustment and lift rotor attitude control, so that the flight attack angle of the lift rotor is adjusted. The unmanned aerial vehicle automatically adjusts the attack angle at different airspeeds.

The invention relates to an express delivery unmanned aerial vehicle, wherein a fixed-wing power assembly is arranged at the front end of a body, two groups of rotors are respectively arranged on thelower surfaces of a left wing and a right wing, an express delivery cabin is suspended below the body through an express delivery cabin suspending frame arranged on the lower surface of the gravity position of the body, the body is in a horizontal state at a vertical take-off and landing stage, and the attack angle is 3.5 DEG when the body is changed into a cruise stage. According to the present invention, when different express delivery cabins are selected, the distance between the pulleys on both sides of the express delivery cabin body is adjusted by adjusting the screw degrees of the screwrods on both ends of the express delivery cabin body, such that the match between the pulleys on both sides and the guide rail can be met; the four landing buffer strips prepared from the hard foam material are uniformly distributed on the bottom surface of the express delivery cabin, and are used for providing the buffer effect during the landing of the unmanned aerial vehicle and providing thesupporting effect during the take-off of the unmanned aerial vehicle; and with the express delivery unmanned aerial vehicle, different express delivery cabins can be selected based on different typesof express delivery parcels so as to delivery the multiple express delivery parcels at one time, and the long-distance rapid delivery can be achieved so as to improve the economy of the express delivery.

A watercraft vessel with at least one planing hull, in the form of a single unitary hull or with two or more interconnected hulls, each hull having at its bottom portion a deadrise angle in the interval 5°-70° and provided with at least one water-deflecting surface which extends rearwardly and outwardly in relation to a keel region and which is oriented and configured so as to create a lifting force, and also a forward thrust on the hull. The forward thrust is caused by a lateral spray water stream, which is redirected rearwardly by the water-deflecting surface. The latter should be located laterally outwardly of but adjacent to an approximately triangular bottom part which is submerged at the planing speed. The hull will also provide a smoother ride than conventional, planing hulls, especially in heavy sea.

The invention discloses a training image building method based on a field outcrop three-dimensional model, and the method comprises the steps: firstly selecting a field outcrop block, obtaining fieldoutcrop model data based on an unmanned plane oblique photography technology, and building a three-dimensional quantitative space model of a field outcrop; establishing a reservoir geological knowledge base, and counting reservoir skeleton model parameters; setting outcrop model virtual well points, generating X, Y and Z virtual well point coordinate information data files, virtual well point lithology distribution data and horizon depth data of different virtual wells, and establishing a three-dimensional grid skeleton model of a field outcrop area by utilizing three-dimensional modeling software based on the generated data; and simulating a field outcrop three-dimensional lithologic model through sequential indication based on a two-point statistical method of a variation function; calculating plane lithology contour line distribution data of different layers by using an arithmetic weighted average method, and establishing a training image three-dimensional space distribution model in combination with a reservoir geological knowledge base, so that the problem that a more accurate training image is difficult to obtain at present is solved.

The invention relates to the technical field of urban air traffic, and discloses an electric vertical take-off and landing aircraft structure and a working method thereof. The electric vertical take-off and landing aircraft structure comprises a fuselage component, wing components (2) connected to the left side and the right side of the middle-upper portion of the fuselage component and flat tail components connected to the left side and the right side of the tail of the fuselage component, wherein tilting propellers are arranged at the end parts of the left and right wing components and the end parts of the left and right flat tail components; and nacelle components are respectively connected to the middle parts of the left and right wing parts, and foldable propellers are arranged on the nacelle components. The tilting power system has higher take-off and cruise performance, and the operation efficiency of the aircraft is obviously improved by increasing the cruise flight speed; a propeller tilting mechanism is designed, so that the vertical take-off and landing function is met, and course thrust can be provided for cruising; and a pitch changing mechanism is designed to change the pitch of the propeller, so that the propeller works in a high-efficiency interval under two working conditions of low-speed incoming flow during vertical take-off and landing and high-speed incoming flow during a cruising stage, and the endurance performance of the whole machine is improved.

The invention discloses a co-rotating vertical take-off and landing membrane-wing aircraft. The aircraft comprises a fuselage, at least two rows of power spars are rotationally connected to the fuselage, and propellers are installed on the power spars. membrane wings rotationally connected with the fuselage are arranged between the adjacent power spars; folding angle adjusting mechanisms are arranged in the middles of the membrane wings; and the fuselage is provided with a linkage operation device which enables the membrane wings and the power spars to synchronously rotate relative to the fuselage. According to the co-rotating vertical take-off and landing membrane wing aircraft, the operation of switching between the lifting state and the flying state is simple, the speed range is large, and energy consumption is low.