280results about How to "Increase the voyage" patented technology

A supersonic aircraft comprises a wing, a fuselage, a plurality of fuel tanks contained within the wing and/or fuselage, and a fuel transfer system communicatively coupled to the plurality of fuel tanks and capable of transferring fuel among the plurality of fuel tanks. The aircraft further comprises at least one sensor capable of indicating a flight parameter and a controller. The controller is coupled to the one or more sensors and to the fuel transfer system. The controller can transfer fuel among the plurality of fuel tanks and adjust the aircraft center of gravity to reduce trim drag and increase aircraft range.

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

The invention relates to a canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area. The canard forward-sweep telescoping wing aerodynamic configuration comprises a fuselage, canards, wings, and a vertical fin; the wings comprise forward-sweep inner wings and forward-sweep telescopic outer wings having internal connections with the forward-sweep inner wings by a telescoping mechanism; and the telescoping mechanism extends to allow the forward-sweep telescopic outer wings to extend to the outside of the forward-sweep inner wings when the mach number (Ma) of an unmanned aerial vehicle is 0.2, and the telescoping mechanism contracts to allow the forward-sweep telescopic outer wings to contract to the inside of the forward-sweep inner wings when the Ma of the unmanned aerial vehicle is 0.4, wherein the area ratio of the forward-sweep telescopic outer wings to the forward-sweep inner wings is 0.25-0.45. The telescoping wing configuration with variable span wing area adopted in the invention allows the unmanned aerial vehicle to have good aerodynamic performances in scopes of different spatial domains and different speeds and the mobility and the flexibility of the unmanned aerial vehicle to be improved. According to the canard forward-sweep telescoping wing aerodynamic configuration of the invention, when Ma is equal to 0.2 or 0.4, the cruise lift-to-drag ratio of the high aspect ratio aerodynamic configuration is over 20% higher than the cruise lift-to-drag ratio of the low aspect ratio aerodynamic configuration when the unmanned aerial vehicle flies at a low speed, and the cruise lift-to-drag ratio of the low aspect ratio aerodynamic configuration is about 15% higher than the cruise lift-to-drag ratio of the high aspect ratio aerodynamic configuration when the unmanned aerial vehicle flies at a high speed, so the capacities of the cruise flight with the Ma of 0.2 and 0.4 are possessed.

The invention provides a buoyancy force and attitude balancing device used for long-voyage AUV and a control method. The buoyancy force and attitude balancing device comprises a buoyancy force balancing device, a buoyancy force balancing controller, a vertical plane motion controller, an attitude sensor and a depth sensor, wherein the attitude sensor is used for detecting an attitude, during underwater navigation, of the AUV; the depth sensor is used for detecting depth, during underwater navigation, of the AUV; the vertical plane motion controller is used for controlling the AUV to move at definite depth on the vertical plane; the buoyancy force balancing controller is used for controlling speed that an oil pump pumps oil into oil bags or sucks oil from the oil bags in the buoyancy force balancing device; the buoyancy force balancing device is used for regulating buoyancy force and a longitudinal inclination attitude, during underwater navigation, of the AUV; the buoyancy force balancing device consists of a pressure-resistant oil tank and two oil bags; the pressure-resistant oil tank is on the gravity center of the AUV; and the two oil bags are separately arranged at the bow and the stern of the AUV. The buoyancy force and attitude balancing device provided by the invention can be used for effectively regulating buoyancy force and gravity force balancing, in water, of the AUV, and eliminating longitudinal inclination angle errors of the AUV, so that resistance when the AUV navigates at definite depth is reduced, and AUV voyage is increased under the condition of carrying same energy sources.

A long-range flotage and the thruster driven under- water robot is used in the sea under-water engineering technical field. The invention contains the main body of the robot, a pair of main limbs, a pair of thrusters and upright empennages. The outer of the robot is the penetrating-water rind which is used in commuting. The main limb and the upright empennage is provided with the limb type of the low liquid resistance. The main limbs set on the back of the penetrating-water rind and symmetrically distribute on the left and right sides of the penetrating-water rind. The upright empennage sets on the tail of the penetrating-water rind and in the upright symmetrical side. The thruster sets in the outer of the main limbs. The invention is provided with two driving fashions which are the drive of the thruster and the drive of the flotage. In the drive of the flotage, it depends on the adjusting of the flotage and the barycenter to produce the thrust and control the motorial direction and provides the high endurance capability.

The invention provides a flying wing layout aircraft which comprises an aircraft body (1), aircraft wings (2), ailerons, an elevator (5) and double vertical fins (4), wherein the aircraft body (1) and the aircraft wings (2) are integrated; the ailerons (3) are positioned on the outer sections of the aircraft wings (2), and are used for rolling control in level flight; the elevator (5) is positioned at the rearmost part of the aircraft body (1), and is used for pitching control in level flight; and the dual vertical fins (4) are positioned at the rear part of the aircraft body (1), and are used for enhancing the flight direction safety in level flight. The flying wing layout aircraft provided by the invention has the advantages that the aircraft body integration technique inherits the excellent pneumatic property of the flying wings, and larger internal space is provided; the weight distribution is more reasonable, and the structure is lighter, so that the load and the voyage are increased; front air screws which are arranged in an engine and tilt and rear air screws which are fixed and can be accommodated in the vertical fins achieve the capability of vertical/short take-off and landing, and the interference to the whole pneumatic appearance of the aircraft is lowered greatly; and the connection shaft design among engines greatly improves the reliability of a dynamic system, avoids the dangerous situation of invalidity after taking off, and guarantees the flight safety in vertical/short take-off and landing.

The invention provides a low span chord ratio aerofoil type designing method considering a three-dimensional effect. The method sequentially comprises the steps of building parameterized initial foil type data; determining a foil type design status and a designed target; adopting a Latin hypercube sampling method, a plurality of sample foil type data is obtained; building an agent model; building an optimization population and adopting a multi-target optimization algorithm for optimizing the optimization population. With the combination of a classic foil-type parameterizing method, the agent model technology and the multi-target optimization algorithm, the efficient and reliable fighter low-span-chord ratio aerofoil type designing method, the low span chord ratio aerofoil type performance is ensured through foil type geometric and aerodynamic pneumatic performance under the two-dimensional environment, the transonic speed and the supersonic speed performance of a aerofoil can be greatly improved through the foil type designed by the model, and the voyage and operation radius are increased while the aero supersonic speed cruising capacity is improved.

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

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

The invention discloses a secondary automatic barrier avoiding system and method of an unmanned boat in a high-speed state, and provides an embedded engineering control machine and a hull control module which are arranged on the unmanned boat of AIS equipment, a microwave radar, a millimeter wave radar, a laser radar and an unmanned boat body. The method comprises the steps that barrier objects inlong and short distance are detected by using the AIS equipment, the microwave radar, the millimeter wave radar and the laser radar, and different barrier avoiding selections are adopted in the method. The method and the system have the advantages that the additional consumption of the unmanned boat brought by barrier avoiding can be reduced under the premise that the safety moving of the unmanned boat is achieved, and therefore the effective speed and range of the unmanned boat are effectively improved, and the effect is significant.

A supersonic aircraft comprises a fuselage extending forward and aft, wings coupled to lateral sides of the fuselage, and canards coupled to lateral sides of the fuselage forward of the wings. The individual canards are configured to generate shocks that wrap around the fuselage and intersect with wing leading edges on opposing sides of the fuselage.

A vehicle power management device managing: a vehicle path information generation device generating a vehicle travel path: a drive assembly consuming power to drive the vehicle; a power generator; an electrical load device group; a high-voltage storage device storing power for driving the vehicle; a low-voltage storage device storing power for operating the electrical load device group; and a DC voltage conversion and output device converting voltage of power stored in the high-voltage storage device to generate DC voltage for operating the electrical load device group, and outputting the DC voltage, and controlling electric energy flow in the vehicle. The vehicle power management device controls output of the DC voltage conversion and output device so that a filling rate of the low-voltage storage device is between lower and upper limits of a range in which a charge and discharge speed is equal to or higher than a predetermined value.

The invention discloses a truss type wing leading edge camber continuous changing structure, and belongs to the field of design of aircraft wing structure. The structure includes that a wing leading edge cavity enclosed by upper flexible skin and lower flexible skin is internally provided with a plurality of trusses, two ends of each truss are slidingly connected with the upper flexible skin and the lower flexible skin, and the plurality of trusses are mutually hinged and can be linked; each memory alloy rod assembly is composed of a first memory alloy rod and a second memory alloy rod, the first memory alloy rod is heated to extend, and the second memory alloy rod is heated to shorten; the memory alloy rod assemblies are arranged between each two adjacent trusses, and are respectively andevenly distributed along the upper flexible skin and the lower flexible skin; the memory alloy rod assemblies are heated to deform to drive the trusses to move, and make the upper flexible skin and the lower flexible skin deformed. The structure has the advantages of simple mechanism principle, direct stress efficacy and high reliability, and the wing leading edge deformation is flexible, controllable, reversible and repeated intelligent deformation which can continuously change the camber of the wing.

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

The invention provides an engine combined of pulse detonation ejection and supersonic combustion ramjet, and the engine is mainly composed of the components of a pulse detonation burner, an ejector and the like. The ejector comprises an ejector inlet valve, a mixing isolation segment, a secondary burning chamber and ejector spray pipes. The engine combined of the pulse detonation ejection and thesupersonic combustion ramjet comprises two working modes of a pulse detonation ejection mode and a supersonic combustion ramjet mode. When the flight mach (Ma) number is equal to 0-5, the engine worksin the pulse detonation ejection mode, under the ejecting action of a combustion ejection flow jetted from the detonation burner, more air is ejected into an air inlet passage, the total air pressurerises, the combustion ejection flow is mixed with the ejected air, fuel is jetted to the mixed air flow, secondary detonation is performed, and at this time, the thrust of the engine is mainly provided by the pulse detonation burner and a secondary pulse detonation system; and when the Ma is larger that 5, the engine is switched from the pulse detonation ejection mode to the supersonic combustionramjet mode, and an aircraft continues to accelerate under the push of the supersonic combustion ramjet engine.

The invention discloses an adaptive continuously-adjustable cavitation device structure. The adaptive continuously-adjustable cavitation device structure comprises a benchmark chassis, a rotatable telescopic assembly and a drive mechanism assembly which are connected with one another, wherein the benchmark chassis and the rotatable telescopic assembly rotate under the power drive action of a servomotor, and the diameter of an outer edge formed by multiple layers of sector part groups in rotating is continuously adjustable along with rotation changes of the servo motor. In the variable speed sailing process of an underwater sailing body, the adaptive continuously-adjustable cavitation device structure provides power through the drive mechanism assembly to drive the multiple layers of sector part groups of the rotatable telescopic assembly to synchronously expand outward or contract inward, and adjusts the drive mechanism assembly according to change situation feedback of hydrokinetic parameters of an external flow field of the sailing body so as to realize adaptive change of the diameter of a cavitation device, thereby completing control for the size and the form of vacuoles, decreasing the wetting area of the underwater sailing body and reducing pressure difference resistance additionally caused to the utmost, greatly reducing frictional resistance and total resistance, and greatly improving the maximum speed and sailing distance of the sailing body.

The invention provides a tethered and autonomous flight dual-purpose solar aerostat. The tethered and autonomous flight dual-purpose solar aerostat comprises a gasbag and an auxiliary gasbag. The gasbag is filled with levitation gas. The auxiliary gasbag located on the lower middle portion of the gasbag is used for being inflated and deflated. A film type solar cell is pasted on the upper surface of the gasbag in a covering mode. An X-shaped empennage with a control plane is arranged on the rear portion of the gasbag. Electric duct steering propellers are arranged on the two sides of the middle of the gasbag correspondingly. An electric propeller is arranged at the tail of the gasbag. An undercarriage is arranged on the lower middle portion of the gasbag. The tethered and autonomous flight dual-purpose solar aerostat mainly combines the advantages of a traditional airship and a tethered balloon, thus the single aerostat can fly autonomously and can also achieve fixed point tethering, and meanwhile the solar cell and an energy storage cell are used for supplying electricity and providing flight power for shipboard equipment. Compared with the traditional airship, the dual-purpose solar aerostat has the advantages of being longer in endurance time, environmentally friendly, capable of saving energy and the like. Compared with a conventional tethered balloon, the dual-purpose solar aerostat has the advantages of being high in maneuverability, good in economic property, large in task execution area and the like.

The embodiment of the invention discloses a composite unmanned helicopter and relates to the technical field of aviation aircrafts. Rotor wings and a tail rotor can be made to work at the optimal rotating speed, and the required power of the unmanned helicopter can be lowered to be the lowest. The composite unmanned helicopter comprises the rotor wings (1), a helicopter body (2), the tail rotor (3) and a landing gear (4), wherein the helicopter body (2) is provided with foldable wings (5) which are symmetrically mounted on the two sides of the helicopter body (2). The unfolding directions of the foldable wings are perpendicular to the axial direction of the helicopter body, and the connecting line between the pneumatic center of each foldable wing and the gravity center of the helicopter body is perpendicular to the axis of the helicopter body. The duration of flight and the air range of the helicopter can be effectively prolonged.

The invention provides a tail-sitter vertical take-off and landing unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage (1), wings (2), tail wings (3), motors (4) and propellers (5), wherein the wings (2) and the tail wings (3) are disposed on the outer surface of the fuselage (1); the wings (2) are disposed in a lower dihedral manner, and the tail wings (3) are disposed in anupper dihedral manner; flight modes of the unmanned aerial vehicle comprise a vertical flight mode, a vertical-to-level transition mode, a level flight mode and a level-to-vertical transition mode, and the unmanned aerial vehicle combines both flight characteristics of a rotary-wing unmanned aerial vehicle and a fixed-wing unmanned aerial vehicle, so that an area for takeoff and landing is reduced. The speed in the level flight mode is high. The unmanned aerial vehicle has the characteristics of vertical take-off and landing, can be deployed in various restricted environments such as mountainous and hilly lands and narrow urban streets, and has a horizontal high-speed cruising function, so that the hang time is increased and the navigation is expanded. The invention also provides a control system and a control method of the tail-sitter vertical take-off and landing unmanned aerial vehicle.

The invention provides a small aircraft, comprising an aircraft body (3), an airfoil (11), a horizontal tail (4), a vertical tail (9), a power system part (1) located at the front part of the aircraft body (3), and a propeller (14) located at the front part of the power system (1); the small aircraft is characterized by further comprising a tilting mechanism (2) located at the upper middle part of the aircraft body, wherein the power system (1) is connected with the aircraft in a tiltable manner by the tilting mechanism (2), so that the propeller (14) of the power system (1) can axially tilt correspondingly. The small aircraft further comprises a pitching posture adjusting system arranged at the tail part of the aircraft body and used for controlling the pitching of the aircraft when the aircraft takes off.