114results about How to "Increase flight speed" patented technology

An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.

A hybrid axial / cross-flow fan aerial vehicle includes both axial and cross-flow fan propulsion for efficient hover and forward flight performance. The axial fans provide primarily vertical thrust, while the cross-flow fan provides horizontal, as well as vertical, thrust. The vehicle takes off vertically, is capable of hover, and can fly forward by vectoring the thrust of the cross-flow fan system. This approach provides large internal cargo capacity and high forward flight speeds.

Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been successfully tested. The second process produces vertical motion and relies only on the aether. It has been successfully tested considering the effect of the earth's gravity. Due to the law of conservation of angular momentum, the first process is considered by some to not be possible, but with the proper use of an external field (for example, gravity) and the phenomenon of precession, it is clearly possible. A clear distinction is made between a simple rotor and a gyroscope which is a far more complex device.

Inertial propulsion is a largely undeveloped field. Inertial propulsion is defined as propelling a vehicle without the use of a propellant such as rocket fuel or ions, or by the application of an external force.Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been successfully tested. The second process produces vertical motion and relies only on the aether. It has been successfully tested considering the effect of the earth's gravity. The two processes referenced above are examples of converting the rotary motion of a spinning rotor into unidirectional linear motion. Due to the law of conservation of angular momentum, the first process is normally considered not possible, but with the proper use of an external field (for example, gravity) and the phenomenon of precession, it becomes possible. A clear distinction is made between a simple rotor and a gyroscope which is a far more complex device.

A helicopter with an H-pattern structure is provided. With an H-pattern transmission mechanism operating in collaboration with two pairs of rotor sets, which are disposed at two sides of a front region and a rear region of an airframe and being rotated in opposite directions, torques generated by the two pairs of rotor sets being rotated in opposite directions are counteracted. Thus, a flight posture and rotation direction during a flight of the helicopter is kept balanced, and at the same time, the helicopter is provided with a simple structure and ensured flight safety.

The invention discloses a bionic aircraft which realizes the conversion of a flapping rotor and a flapping wing flight mode based on a deformable wing, and belongs to the technical field of bionic aircraft design. When it is in vertical take-off, landing and hovering, it is a flapping rotor flight mode, and its structure is characterized by that the flapping wings on both sides are mounted in an axisymmetric manner, that is, the airfoils on both sides are antisymmetrical; When in forward flight or gliding, the flapping wing or fixed wing flight mode is characterized by symmetrical mounting ofthe flapping wing on both sides in a fixed wing symmetrical manner, i.e., symmetrical wing profiles on both sides. At that same time, an elastic bow beam is adopt, In the structural design of deformable wing rib composed of chord and multi-bar mechanism, when the shape of deformable wing is changed, by rotating the tie rod installed at the root of wing and the cable connecting each wing rib, the multi-bar mechanism is pulled to force the connected bow beam to produce the elastic deformation required, that is, the overall structure of the airfoil is kept unchanged, but the leading edge and thetrailing edge of the deformable wing are interchanged. The invention simplifies the driving mechanism and the integral configuration of the aircraft, and remarkably improves the aerodynamic efficiencyand the lift coefficient.

The invention discloses a bionic flapping-wing machine with double-section main wings. The bionic flapping-wing machine comprises a driving mechanism, a main bracket, a tail-wing mechanism, a double-section flapping-wing mechanism and two steering machines, wherein the driving mechanism is connected with the front end of the main bracket; the tail-wing mechanism is connected with the rear end of the main bracket; the double-section flapping-wing mechanism is connected to the driving mechanism; the two steering machines are arranged on the main bracket. The bionic flapping-wing machine disclosed by the invention has the following beneficial effects that the structure is simple and compact, the flapping-wing movement with complete symmetry can be realized, the flapping-wing machine can fly like a bird by adopting the double-section flapping-wing mechanism, due to the foldable wings, the resistance of the wings can be small in upwards flapping and the wingspan area can be the largest in downwards flapping, so that large lifting force is generated, and the flying speed and the hang time are increased. In addition, a spherical pair is adopted for connection with the tail-wing mechanism, the direction control of the flapping-wing machine is sensitive and the flapping-wing machine can imitate the flying of the bird. Furthermore, the bionic flapping-wing machine can be applied to the fields of bird repelling of an airport, monitoring, intelligence gathering, disaster rescuing and searching and the like.

The invention discloses a culvert-type vertical take-off and landing lifting body unmanned aerial vehicle and relates to the technical field of vertical take-off and landing unmanned aerial vehicles.The culvert-type vertical take-off and landing lifting body unmanned aerial vehicle comprises a fuselage (1), lifting force rotor wings (2), a take-off and landing culvert (3), tilting-rotating thrustculverts (7) and tilting-rotating thrust rotor wings (8). The take-off and landing culvert (3) is composed of a through hole penetrating through the upper surface and the lower surface of the fuselage (1), and the lifting force rotor wings (2) are arranged in the take-off and landing culvert (3). The tilting-rotating thrust culverts (7) are hinged to the rear end of the fuselage (1) through tilting-rotating control mechanisms (9), the tilting-rotating control mechanisms (9) are configured to be capable of enabling the included angle between the axis of each tilting-rotating thrust culvert (7)and the axis of the fuselage (1) to be variable, and the tilting-rotating thrust rotor wings (8) are arranged in the tilting-rotating thrust culverts (7). Under the conditions that the vertical take-off and landing capacity of the unmanned aerial vehicle is maintained and the overall weight of the unmanned aerial vehicle is not excessively increased, the flight speed of the unmanned aerial vehicle is increased, the flight stability of the unmanned aerial vehicle is improved, the rotor wing exposed problem is avoided through the culverts, and the flight safety and the take-off and landing hovering efficiency are improved.

An airplane capable of performing fixed wing flight and vertical take-off and landing based on a three-axle flight control panel is characterized in the airplane structure and the airplane control connection manner. In the aspect of structure, the airplane is characterized in that front inclination / rotation power capsules are symmetrically arranged on two sides of each wing of the airplane, a rear inclination / rotation power capsule is arranged at the rear part of an airplane body. In the aspect of airplane control connection manner, the airplane is characterized by adopting an innovative connection manner based on a simple three-axle flight control panel, so that the airplane can complete fixed wing flight and vertical take-off and landing under the control of the three-axle flight control panel. The airplane provided by the invention can complete double flight modes including fixed wing flight and vertical take-off and has good maneuverability and high flight efficiency, which is very important for improving the survival rate of the airplane in a war. In addition, the airplane based on the conventional three-axle control panel is convenient and reliable in the control manner and is suitable for mass production.

An integrated hybrid electric power generation system for producing jet thrust, a superconducting direct drive turbine ring motor for vertical lift, multi-megawatt electric current generation and a pulse-phased high power directed energy weapon (DEW). The system is managed electrically, and may be mated directly to a magnetic aerodynamic generation of rotorhead optimized control as a direct drive electric lift-jet thrust rotorcraft system (DDELJTRS) manifesting an all flight managed controls and weaponized electric system in rotorcraft, vertical lift, aerodynamic flight control, directed energy weapon and jet propulsion for forward flight high speed cruise.

The invention relates to the technical field of an aerocraft, in particular to a screw propeller and the aerocraft. The screw propeller comprises an oar hoop and at least two blades which are connected with the oar hoop, wherein at a position (the proportion of the distance from the position to the center of the oar hoop to the radius of the screw propeller is P), the attack angle of the blades is beta, beta is the continuous function of the radius proportion P and satisfies the following conditions that when P is more than or equal to 0 and less than or equal to 25 percent, beta is more than or equal to 10 degrees and less than or equal to 12 degrees; when P is more than 25 and less than or equal to 90 percent, beta is more than or equal to 8.75 degrees and less than 12 degrees; when P is more than 90 percent and less than or equal to 100 percent, beta is more than or equal to 8 degrees and less than or equal to 9 degrees. Due to the fact that different attack angles are arranged at different positions of the blades of the screw propeller, the air resistance is reduced, the efficiency is improved, and the flying speed and the flying distance of the aerocraft are increased; due to the fact that the attack angle beta of the screw propeller is continuously changed, the stability of the screw propeller is improved, and the flying performance of the aerocraft is improved.

The invention relates to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle with a tailed flying wing configuration, which has a plurality of working modes such as vertical take-off and landing / short-distance take-off and landing / conventional take-off and landing / low-speed forward flight / high-speed forward flight and the like and can realize coast-based / vessel-based multi-based configuration. The unmanned aerial vehicle comprises a lifting body type vehicle body of which the longitudinal section is of an airfoil shape, and main airfoils, upper airfoils and end airfoils which are arranged at both sides of the vehicle body and form smooth integration with the vehicle body, and a duct propeller propulsion device and a vertical fin which are arranged at the tail of the vehicle body, wherein the lower end of the vertical fin is fixedly connected with a duct structure of the duct propeller propulsion device arranged at the tail of the vehicle body. According to the invention, the tailed flying wing configuration integrated with jointed wings is adopted, so that the unmanned aerial vehicle has various advantages such as excellent aerodynamic characteristics and high effective load factor of the conventional flying wing configuration, and also effectively overcomes the inherent defects of the conventional flying wing configuration in aspects of stability and operability.

The invention relates to two regenerative cooling afterburners with sound cavities. In order to overcome the defects of the existing afterburners and enlarge the application ranges, a straight-groove sound cavity for shock absorption is arranged and an integrated groove-milled connection structure employing kerosene or liquid hydrogen fuel or hydrogen peroxide having a medium concentration within the range of 70-79% as a regenerative cooling agent is adopted so that the reliability of the afterburner can be improved, and the working time, the service life, and the flight height and the speed can be increased. A schematic diagram of a related supply system is given in addition to the structures of the afterburners. The afterburners are mounted at the rear portion of an aero-gas turbine engine to form a long-augmentation aero-gas turbine engine and a tandem turbo-rocket combined engine. The afterburners can be provided for a plurality of high-speed airplanes as power devices, and are particularly applicable to novel supersonic airliners and advanced space tourism aircrafts. Besides, the afterburners also can be used as auxiliary winged rocket propulsion and withdrawal engines or low-turbine total temperature gas turbine engines for other purposes.

The invention discloses a fixed wing aircraft provided with multiple rotor wings and capable of realizing vertical take-off and landing. The fixed wing aircraft comprises a fuselage, aircraft wings and a tail wing, as well as power rack units arranged on the aircraft wings and the tail wing, wherein the power rack units comprise front rotor wings, rear rotor wings and tail rotor wings. According to the invention, the switching between the helicopter mode take-off and landing and fixed wing flight mode can be realized, the safety performance of the take-off and landing of the aircraft is improved, and the take-off and landing mode of the traditional fixed wing aircraft is changed.

Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been successfully tested. The second process produces vertical motion and relies only on the aether. It has been successfully tested considering the effect of the earth's gravity. Due to the law of conservation of angular momentum, the first process is considered by some to not be possible, but with the proper use of an external field (for example, gravity) and the phenomenon of precession, it is clearly possible. A clear distinction is made between a simple rotor and a gyroscope which is a far more complex device.

A rotorcraft with a fuselage and at least one main rotor, the at least one main rotor being drivable for controlling an associated pitch attitude of the rotorcraft in operation, and the fuselage being equipped with at least one passive wing-type aerodynamic device that is adapted for generating independently of the associated pitch attitude a lift force acting on the fuselage, the lift force being oriented perpendicular to an air flow that is directed in operation of the rotorcraft against the passive wing-type aerodynamic device.

The present invention discloses a nickel-base high-temperature alloy / titanium alloy composite material for aero-engine. The material comprises the following three layers of metal materials: a nickel-base high-temperature alloy plate (2) on the upper layer, a nickel-base high-temperature alloy plate (5) on the lower layer and a titanium alloy plate (4) in the middle layer, wherein the material trademark of the titanium alloy is Ti-6Al-4V, the chemical components of the titanium alloy comprise 5.5-6.75% of aluminum, 3.5-4.5% of vanadium, and the balance of titanium, the material trademark of the nickel-base alloy is K4169, and the chemical components of the nickel-base alloy comprise 0.5% of aluminum, 0.05% of zirconium, 1.0% of titanium, 3.0% of manganese, 5.2% of niobium, 18.5% of chromium, 52% of nickel, 3.0% of molybdenum, 0.05% of carbon, and the balance of iron. According to the present invention, the bonding rate of the composite material achieves 100% and achieves metallurgical bonding, the nickel-base high-temperature alloy has characteristics of high temperature ablation resistance and high high-temperature strength, and can be used for a long time at a high temperature, the titanium alloy can provide a structure support effect, and the composite material has characteristics of light weight, high temperature resistance and high strength, and is a novel aircraft engine composite material with characteristics of light weight, high strength and high temperature resistance.

The invention provides gun, artillery and rocket jet engines, steam turbines, internal combustion engines and air vehicles with an additional magnetic device. A magnet is included, translational motion, through Lorentz force, rotation and vibration of fluid molecules near the magnet in the direction of being perpendicular to the micro-flow direction of fluid are strongly inhibited, and pressure and temperature of the fluid molecules in the direction of being perpendicular to the micro-flow direction of the fluid are significantly lowered, so that the speed that the fluid molecules diffuse in the needed micro-flow direction is significantly increased. Viscous friction, turbulent shear stress, friction force and heat conduction in a boundary layer and shock waves, resistance generated by the shock waves and negative influences of heating on relative movement between air flow and an object are eliminated fundamentally in the microcosmic level or at least weakened greatly. By equipping the magnet on various gun, artillery and rocket engines, jet engines, turbines, gasoline engines, diesel engines and the like, radial pressure and temperature must be significantly lowered, the initial speed of pills is significantly increased, the power and the speed of the rock engines and the jet engines are increased, the energy utilization rate of the gas turbines, the turbines and the internal combustion engines is increased, and various resistances borne by the air vehicles and heating of the air vehicles are significantly reduced.

The invention relates to the technical field of unmanned aerial vehicles, and particularly discloses a propeller and an aircraft. The propeller comprises a propeller hoop and at least two propeller blades connected with the propeller hoop. The wing type of the propeller blades is ARA-D, and each propeller blade is composed of a root portion, a main body portion and a blade tip portion which are sequentially connected. The length L1 of the root portion accounts for 20% to 30% of the length L of the propeller blades, and the length L of the propeller blades is the length, in the first direction from the center of the propeller hoop to the farthest end of the blade tip portions, of the propeller blades; the installing inclined angle of the root portions ranges from 10 degrees to 15 degrees, and the blade widths of the root portions are gradually increased in the first direction; the length L2 of the main body portions accounts for 60% to 70% of the length of the paddle blades, and the blade widths of the main body portions are gradually decreased in the first direction; the minimum blade width of the main body portions accounts for 55% to 65% of the maximum blade width of the main body portions; and the length L3 of the blade tip portions is equal to L-L1-L2, and the blade widths of the blade tip portions are gradually decreased in the first direction. According to the propeller, the air resistance is reduced, efficiency is improved, and therefore the flying speed and the flying distance of the aircraft are increased.

The invention relates to a telescopic wing of an aircraft, in particular to a telescopic wing on a small aircraft which can lift in complex regions of high mountains, gorges and the like. The telescopic wing comprises a wing body which is vertically arranged. A wing cover is fixed on the rear side of the middle of the gravity center of the wing body, outlets are formed in both the left end and the right end of the wing cover, a worm gear case is arranged at the center of an inner cavity of the wing cover, and telescopic wing bodies are arranged on both the left side and the right side of the worm gear case and in sliding fit with the outlets. Rectangular notches are formed in the lower sides of the outer ends of the two telescopic wings, wing blocks are arranged in both the rectangular notches, and a worm and gear mechanism is arranged in the worm gear case. Through the worm and gear mechanism and the like, the telescopic function of the telescopic wing can be achieved, and the angles of the wing blocks can be adjusted. The aircraft with the telescopic wing is small in oil consumption, high in flight speed, and long in voyages.

The invention discloses a tilting photographic camera with a self-stabilizing system and a control method thereof. The tilting photographic camera is provided with an inertial navigation system and a servo drive system; the inertial navigation system includes an inertial navigation sensor (1), the The servo drive system includes a rolling servo brushless motor (2) and a pitching servo brushless motor (3), and the tilting camera also includes a control circuit system. Because the control rate of the inertial navigation control system is very fast, the present invention can quickly respond to the attitude change of the tilt camera brought about by the attitude change of the UAV itself, so that the real-time control servo system can correct the tilt camera, and then combine the physical Vibration reduction system, tilting the camera will get very good practical effect.

Belonging to the technical field of aircraft design, the invention discloses a deformable lift and buoyancy integrated aircraft aerodynamic configuration. The aerodynamic configuration has a single-fuselage, tandem wing and horizontal tail-free layout, double vertical tails tilt outward certain angle, wings are located at the upper part of the fuselage, front wings and back wings have the same design. The fuselage can produce radial deformation, the fuselage is divided into a front section, a middle section and a back section, and the three sections of the fuselage deform respectively. Because of the introduction of dynamic lift, the aircraft has higher flight height than an airship, greater flight speed, and stronger wind resistant performance and maneuverability; and due to the introduction of static lift, the aircraft has loading capacity far higher than that of conventional high-altitude unmanned aerial vehicles, and has higher structural height and strength. In the process of vertical rising and fall, the fuselage can produce corresponding deformation to change the fuselage volume so as to guarantee the fuselage lift and the aircraft weight balance. With no need for ballonet and ancillary equipment in conventional airships and lift and buoyancy integrated aircrafts, the deformable lift and buoyancy integrated aircraft aerodynamic configuration provided by the invention can reduce the aircraft weight and decrease the ground parking volume of the aircraft.

The invention discloses a platinum channel and a manufacturing method and a coating zirconium oxide dry powder mixture thereof. After the zirconium oxide dry powder mixture is sprayed on the surface of a platinum channel body, oxidization and volatilization of platinum in the platinum channel in a sintering process under high temperature can be effectively prevented. The zirconium oxide dry powdermixture is prepared from the following ingredients of 9.3% to 16% of SiO2, 2.7% to 4.3% of Al2O3, 80% to 87% of ZrO2 and 0.01% to 0.03% of Na2O. According to the platinum channel, the outer surface of the platinum channel is coated by a coating layer of the zirconium oxide dry powder mixture; a zirconium oxide dry powder filling material, a zirconium oxide groove profile brick and a zirconium oxide thermal insulation brick which are in tight contact are sequentially arranged outside the coating layer from inside to outside; the thickness of the coating layer is 0.8 to 1mm.

The invention provides a duct type tilting aircraft with vertical take-off and landing functions. The duct type tilting aircraft comprises an aircraft body, front wings, rear wings, rotary wing plates, tilting rotors and rotor adjusting mechanisms, wherein the rotary wing plates are hinged to openings of the rear wings through wing shafts; the tilting rotors are fixedly arranged on the wing shafts; the rotor adjusting mechanisms drive the wing shafts to rotate, so that the rotary wing plates and the tilting rotors are driven to rotate; a duct and a duct propeller are arranged in the middle of the aircraft body; an upper hatch cover and a lower hatch cover are mounted at upper and lower air inlets of the duct. When propellers at the tips of the wings tilt, lift force supply to the air craft is increased according to the rotating speed of the duct propeller, so as to guarantee the controllability of the attitude of the aircraft; the upper and lower hatch covers are closed under a cruising mode of the aircraft so as to reduce the leveling off resistance and increase the flying speed; in a process that the rotor adjusting mechanisms operate, a motor cannot generate a false position and vibration, so that the overall stability is effectively improved.