49results about How to "Improve cruise efficiency" 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.

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.

The invention relates to a layout scheme of a tilt rotor transport aircraft. According to the layout scheme, the tilt rotor transport aircraft comprises a body, front wings, rear wings, front-rear-wing connecting end plates, a vertical tail wing, rotor wings, front wing auxiliary wings, rear wing auxiliary wings, a rotatable main shaft, engines, engine small-angle rotating mechanisms, a slip-flow rudder, a slip-flow rudder surface and a rudder; the body is connected with the front wings, the rear wings, the rotatable main shaft and the vertical tail wing; the front wings and the rear wings are arranged on the front end and the rear end of the body, and the front wing auxiliary wings and the rear wing auxiliary wings are respectively installed on the front wings and the rear wings; the vertical tail wing is installed on the tail end of the body, the rudder is installed on the vertical tail wing, and the rotatable main shaft is connected with the engine small-angle rotating mechanism in a rotating manner; the rotor wing is installed on an output shaft of the engine; the slip-flow rudder is installed on the rotatable main shaft, and the slip-flow rudder surface is installed on the slip-flow rudder. The invention relates to a control method of the tilt rotor transport aircraft. The control method comprises five steps. By adopting the layout and the control method of the tilt rotor transport aircraft, the pneumatic interference and mode transformation between the rotor wings and the wings of the aircraft can be solved, the transport capacity and the vertical take-off and landing capacity of the connected-wing layout can be reasonably combined, and a novel type of transport aircraft is formed.

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 relates to a distributed intelligent search and rescue system using an unmanned aerial vehicle on sea. The search and rescue system comprises the unmanned aerial vehicles and a search and rescue vessel. The unmanned aerial vehicles are disposed on the search and rescue vessel. Each of the unmanned aerial vehicles comprises the following modules: a positioning navigation module, an infrared sensing module, an infrared camera module, an image signal processing module, a wireless communication module, an information collecting module, a control unit, a flight unit and a power supply. The search and rescue vessel comprises the following modules: a video coding module, a display device, an alarm device, a wireless communication module, a digital-to-analog conversion module, a positioning and cruising module, a controller and a power supply device. The control unit of the unmanned aerial vehicle is a sub-module of the controller of the search and rescue vessel. As a total control center, the controller can control multiple control units, that is, the number of the unmanned aerial vehicles exceeds two, thereby realizing distributed search, and having better search effect. The invention has the advantages of automatic positioning, high cruising efficiency, wide distribution range and timely rescue.

The present invention discloses a high-aspect-ratio wing frame architecture design method and relates to the technical field of aircrafts. The design method comprises a rigid wing optimization step and an elastic wing optimization step. The rigid wing optimization step comprises generating an initial population of the wing architecture, performing lift-drag ratio calculation to obtain a local optimal solution, then carrying out optimizing calculation, performing lift-drag ratio calculation on the local optimal solution and comparing with the local optimal solution obtained after the initial population is subjected to the lift-drag ratio calculation, and finally judging the globally optimal solution; and the elastic wing optimization step comprises calculating the aerodynamic load borne by an elastic wing during an flight, then calculating the elastic deformation of the wing, solving the true form of the wing structure under elastic balance at the flight state through multiple iterative computations to obtain the flight load after the elastic deformation and acquire the twist angle of a wing profile architecture, and thus completing the design of the wing frame architecture. The wings designed through the high-aspect-ratio wing frame architecture design method have good geometrical aerodynamic twist angle distribution, the lift distribution is better, the smaller induced resistance can be produced, the best lift-drag ratio is obtained, and thus the cruising efficiency is improved.

The invention discloses a trapezoid layout tandem tilt wing aircraft and a tilting mechanism thereof. Tandem wing layout, trapezoidal power system arrangement, multiple control surfaces and electric power system differential combination control are adopted, so the aircraft integrates vertical takeoff and landing functions and high-speed hover performance advantages, and also has the long-enduranceand long-range characteristics of a fixed wing aircraft and the hovering and vertical takeoff and landing characteristics of a helicopter. The vertical takeoff and landing and the air fixed wing modecruising are completed through the tilting wing layout, so the requirements for a taking off and landing place are reduced, and the cruising efficiency is improved; the trapezoid dynamic system layout can improve the efficiency of propellers; the roots of wings and a fuselage are fused, and the tilting sections of the wings and the fuselage section fused wing roots are connected and rotate relative to each other, so the mounting and positioning precision of the wings is improved; and the multi-control surface layout of the wings makes the control surfaces on the wings generate the rudder effect by using rotor wake during the vertical takeoff and landing, and attitude control participating in the vertical take-off and landing state reduces the control surfaces of a vertical fin, so the structural efficiency is improved.

The invention belongs to the technical field of flying automobiles, in particular to a flying automobile with folding wings for vertical take-off and landing, which comprises a body, a folding wing, atail wing, a power system, a transmission mechanism and a landing gear. The power system is composed of a rotor duct system, a tail propeller and a pitch mechanism. The rotor duct system comprises four sets of coaxial dual rotor ducts. The invention solves the technical problems of long take-off and landing distance of flying vehicles, high requirements on take-off and landing sites, low liftingefficiency, high fuel consumption and insufficient stability of ducted rotor flying vehicles in the prior art. Higher lift acquisition rate, lower fuel consumption, higher reliability, higher safety,and lower cost.

The invention provides a laminar flow aerofoil profile FNLF1 with maximum relative thickness of 0.17 and with an emphasis on stall characteristic by using a computer fluid dynamics method and an aerofoil profile parameterization method and taking a cruising point, a climbing point and a stalling point into consideration in state design on the basis of the internally public NLF0416 aerofoil profile. The leading edge radius of the laminar flow aerofoil profile FNLF1 is 2.11% of C, the maximum thickness of the laminar flow aerofoil profile FNLF1 is 17% of C, the maximum thickness position of the laminar flow aerofoil profile FNLF1 is 5.37% of C, the maximum camber of the laminar flow aerofoil profile FNLF1 is 1.88% of C, the maximum camber position of the laminar flow aerofoil profile FNLF1 is 76.29% of C and the trailing edge thickness of the laminar flow aerofoil profile FNLF1 is 0.43% of C, wherein C is the chord length of the aerofoil profile. In the case that the climbing and cruising performances of the laminar flow aerofoil profile FNLF1 are kept at or slightly superior to those of the NLF0416, the stalling angle of attack of the laminar flow aerofoil profile FNLF1 is delayed and the stall characteristic of the laminar flow aerofoil profile FNLF1 is slowed; and in case that the cruising state is the laminar flow main control, the length of an upper wing surface laminar flow area reaches 48% and the length of an lower wing surface laminar flow area reaches 53%.

The invention relates to a fire-fighting reconnaissance robot path generating method and device, computer equipment and a storage medium. The method comprises the steps that the front path is detectedthrough an ultrasonic radar on the front side of a chassis, information of a barrier in front of the fire-fighting reconnaissance robot is obtained, if the information of the barrier in front of thefire-fighting reconnaissance robot meets a steering triggering model, the steering state of the fire-fighting reconnaissance robot is triggered, in the steering state, left barrier information detected by an ultrasonic radar on the left side of the chassis and right barrier information detected by an ultrasonic radar on the right side of the chassis are received, the turning direction of the fire-fighting reconnaissance robot is determined according to the left barrier information and the right barrier information, and a turning path of the fire-fighting reconnaissance robot is generated according to the turning direction. By adopting the method, the robot can effectively avoid the barriers on the advancing path, and the cruising efficiency of the fire-fighting reconnaissance robot in thefire scene environment is improved.

The invention provides an illegal emergency lane occupation detection method and system based on an unmanned aerial vehicle; firstly, the unmanned aerial vehicle cruises according to a pre-configured target route, and does not need to be controlled by professionally trained personnel; secondly, when the target vehicle occupies the emergency lane, illegal video images can be sent to the control equipment, and the traffic police do not need to observe at any time, so that the efficiency of the traffic police can be improved, for example, one traffic police can process the video images fed back by multiple unmanned aerial vehicles at the same time and confirm the illegal emergency lane occupation behavior; thirdly, the different camera shooting parameters are adopted during cruising and license plate information recognition, it can be ensured that the unmanned aerial vehicle has a large shooting view during cruising, the cruising efficiency is improved, and when it is found that the target vehicle exists, the information of the target vehicle can be clearer by adjusting the camera parameters, and evidence obtaining is facilitated.

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 belongs to a technology of airplane design and relates to an overall arrangement of a large air freighter. The overall arrangement of the large air freighter comprises a fuselage (1), a cockpit (2), wings (3), a retractable nose-wheel landing gear (4), an upturning cargo bay front door (5), an upturning cargo bay rear door (6), and two propulsion devices which are arranged at the rear part of the wings and at the two sides of the fuselage, wherein each propulsion device consists of an engine mounting plate (7) and a power mechanism, wherein each engine mounting plate (7) is provided with a power mechanism mounting hole, and each power mechanism is arranged in the corresponding power mechanism mounting hole; each power mechanism consists of a pitching guide ring (8), a yaw guide ring (9), a propfan engine (10), a pitching rotating shaft (11), a yaw rotating shaft (12) and a support rod (17). By adoption of the overall arrangement of the large air freighter, the cruise efficiency, the structural efficiency and the loading efficiency of the air freighter can be improved, the oil consumption rate is reduced, the empty weight coefficient is reduced, and the fuel load and the flying range are improved.

The present invention provides a quasi-elliptical airfoil for a high-speed helicopter rotor reflux region. The airfoil is a blunt trailing edge airfoil with symmetrical front and rear. The leading edge radius of the upper surface of the airfoil is 0.0385, the leading edge radius of the lower surface of the airfoil is 0.0230, the trailing edge radius of the upper surface of the airfoil is 0.0385, and the trailing edge radius of the lower surface of the airfoil is 0.0230. The maximum thickness of the airfoil is 26% C, the maximum thickness is 50% C and the curvature is 2.8% C. The lower surfaceof the airfoil has some concavity near the leading edge and the trailing edge, so that the lift of the airfoil is improved. The invention has the advantages that the quasi-elliptical airfoil applied to the rotor reflux region of a high-speed helicopter designed according to the actual flow characteristics of the reflux region has smaller resistance of the reflux region, higher aerodynamic efficiency and can effectively suppress the flow separation phenomenon, thereby improving the cruise efficiency of the helicopter and meeting the requirements of a new generation of high-speed helicopter.

The invention belongs to the technical field of aviation aircraft design, and discloses a flying wing layout wide-speed-range aerodynamic operation stability characteristic structure, a wing body and flying wing layout integrated aircraft body, double wings of the aircraft body adopt double sweepback layout, the wings are divided into inner wing sections and outer wing sections, the inner wing sections are wing sections fused with the aircraft body, and the sweepback angles of the front edges of the inner wing sections are large; the sweepback angle of the front edge of the outer wing section is small; the outer wing section is further divided into an outer wing section fixing section and an outer wing section foldable section, the outer wing section fixing section is fixedly connected with the inner wing section, the outer wing section foldable section is in shaft driving connection with the outer wing section fixing section through an outer wing section rotating shaft, and the outer wing section foldable section rotates relative to the outer wing section rotating shaft so as to be folded upwards. When the structure is applied, different aerodynamic and operation stability performance requirements of low-speed take-off and landing, high subsonic speed cruise and supersonic speed cruise design points can be considered.

The invention discloses a ball-borne suspended launching system based on a combined unmanned aerial vehicle, the ball-borne suspended launching system comprises the combined unmanned aerial vehicle provided with a flight control system; a high-altitude balloon connected with the combined unmanned aerial vehicle through a rope; and a rope cutter fixed to the back of the combined unmanned aerial vehicle, wherein the rope is connected to the rope cutter; the combined unmanned aerial vehicle rises to a preset height through buoyancy of the high-altitude balloon and then enters a cruising state. When the balloon and the combined unmanned aerial vehicle lift off to a preset height, the rope cutter is remotely controlled to cut off the rope to separate the balloon from the unmanned aerial vehicle, so that the throwing of the combined unmanned aerial vehicle is completed, and the energy consumed by the common combined unmanned aerial vehicle during ground skating or catapult-assisted take-offis saved.

The invention discloses a vertical/short-distance take-off and landing aircraft with distributed power coupling lift augmentation airfoils, and belongs to the field of aviation aircrafts. The aircraft comprises lift fans, an aircraft body, wings, high lift airfoils, distributed ducted fans and a motion mechanism, wherein the fuselage and the wings are in a flying wing layout with a fused wing body; the lift fan is embedded in the middle of the nose, is in a coaxial contra-rotating form and is used for generating a vertical upward lifting force; the distributed ducted fans are symmetrically distributed at the tail of the fuselage, and the side walls of the two ends of each distributed ducted fan are hinged to side plates fixed to the fuselage through rotating shafts correspondingly. The high-lift airfoil comprises an upper straight wing and a lower straight wing which are arranged in parallel and located at the upper end and the lower end of the outer side of an outlet of the distributed ducted fan respectively, and the two ends of each straight wing are connected with the side plates through movement mechanisms respectively and can tilt relative to the fuselage along the movement mechanisms. Hovering, vertical/short-distance taking-off and landing and cruising level flight of the aircraft in the air can be achieved, and due to the fact that lift force is provided in a lift augmentation airfoil mode, the aircraft can fly more safely and stably in a transition mode.