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208 results about "Flight velocity" patented technology
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Spiral-based axial flow devices
Axial flow devices using rigid spiral band profiled blade catenaries attached variably along and around an axially elongated profiled hub, of axially oriented profile section sequences 75 mapped relative to truncated cones-of-generation. Upon rotation and lubricity-masked progression through axial planes-of-shear, this time-domain sequence travels in 2-dimensional axial-datum-plane-relative path-excursions and ejects frictional adhesions via anguillar reverse vortex street thrust due to an after-body accelerating wave shape-sequence 48. This guides bound vortex pressures at linear path-velocity substantially parallel to the collective plane-of-shear, conferring higher differential pressures through path-vector-addition, improved force-vector orientation, extended laminar flows, lower form drag and tip vorticity. As a wind turbine, path-vectors are added to inflow, ducting an increased mass flow inward for increased power extraction per diameter. As a propeller, path-vector-subtraction guides the wave front flight-path-transverse, allowing higher flight velocities and improving thrust-per-torque through enhanced force vectors and mass flow rates.
Owner:POLACSEK RONALD R
Rotocraft power-generation, control apparatus and method
InactiveUS20100308174A1Easy to meetMore dragTethered aircraftWind motor supports/mountsGround stationRotary wing
A control system for a power generation apparatus and method may fly a rotorcraft rotary wing at an altitude above the nap of the earth. A tether, suitably strong and flexible, connected to the rotorcraft framing is pulled with a force generated by the rotary wing. The force is transmitted to a ground station that converts the comparatively linear motion of the tether being pulled upward with a lifting force. The linear motion may be transferred to a rotary motion in the ground station to rotate and electrical generator. The tether may be retrieved and re-coiled by controlling the rotorcraft aircraft to basically fly down at a speed and lift force to support recovery of the rotorcraft at a substantially reduced force compared to the larger lifting force in effect during the power-developing payout of the tether. Moreover, the duty cycle of such a system is substantially increased over any terrestrially based or tower-mounted wind turbine mechanisms.
Owner:CALVERLEY GRANT
Arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole pitot probe
InactiveUS6336060B1Digital data processing detailsVolume/mass flow measurementTime responseEquation of the center
An arithmetic processing method and system in a wide velocity range flight velocity vector measurement system using a square truncated pyramid-shape five-hole Pitot probe. Approximation equations that determine attack angle alpha and sideslip angle beta in the form of third-order equations concerning attack angle pressure coefficient Calpha and sideslip angle pressure coefficient Cbeta, which are known numbers, are expressed in the form of a polynomial equation concerning Mach number M, where the coefficients are obtained from a lookup table. Coefficient calculations in the polynomial equation, and attack angle a and sideslip angle beta, calculations may be performed as simple calculations by specifying and applying known numbers into the approximation equation without solving third-order equations, with calibration coefficients that form the basis of coefficient calculation with the polynomial equation first being stored in memory in advance as a table for each wide velocity range on the basis of wind tunnel testing. A Mach number may be calculated instantly from a lookup table by specifying Mach pressure coefficient CM and angle to airflow pressure coefficient Cgamma. Wide velocity range flight velocity vector measurement with a high update rate which is capable of real time response in flight control as demanded by aircraft is obtained.
Owner:JAPAN AEROSPACE EXPLORATION AGENCY
Unmanned plane flight path drawing method, device and system
ActiveCN105589471AIncrease success rateRelieve stressPosition/course control in three dimensionsFlight directionElectronic map
The invention provides an unmanned plane flight path drawing method, device and system. The method comprises the steps of: planning a flight destination and a flight path of an unmanned plane; receiving a position signal returned in the flight process of the unmanned plane every a set time interval, and drawing the flight path of the unmanned plane on an electronic map according to the position signals; and if failing to receive the position signals in the set time interval, then setting the position, corresponding to the last received position signal, on the electronic map as a starting point of a virtual path, starting drawing the virtual path, using the flight speed of the unmanned plane at the time of the last received position signal as an analog flight speed of the unmanned plane, determining the flight direction at the present position of the unmanned plane according to the direction of the destination, determining the next arrived position of the unmanned plane after the set time interval, and drawing the virtual path of the unmanned plane on the electronic map according to the next position. By adopting the unmanned plane flight path drawing method, a user is enabled to estimate the position of the unmanned plane after the unmanned plane is lost, and the user is enabled to be still ready for unmanned plane recovery.
Owner:盯盯拍浙江智能设备有限公司
Method and device for setting the fuse and/or correcting the ignition time of a projectile
To avoid mechanical and thermodynamic wear of a programming system, a microwave transmitter, preferably operating in the GHz range, is integrated in the system, while at the same time the advantages of measurement of the muzzle velocity and of a current compensated fuse setting are preserved. The microwave transmitter transmits the current fuse setting, for example, as determined by a fire control computer, to the ammunition, e.g., a projectile. A direct measurement of the actual muzzle velocity itself can be dispensed with, since the real muzzle velocity is determined by the current flight velocity information of the projectile, i.e., it is extrapolated back from this. On the basis of this current projectile velocity, the ignition time, which was preset with the ignition time of the projectile using a standard muzzle velocity, is corrected and used as the current fuse set time.
Owner:OERLIKON CONTRAVES BESCHRAENKTER HAFTUNG
Multi-unmanned aerial vehicle four-dimensional track collaborative planning method and system
ActiveCN112817330AIncrease profitMeet real-time requirementsInternal combustion piston enginesPosition/course control in three dimensionsSimulationUncrewed vehicle
The invention provides a multi-unmanned aerial vehicle four-dimensional track collaborative planning method and system. The method comprises the following steps: giving unmanned aerial vehicle three-dimensional task space and task time range, take-off sites and destination sites of multiple unmanned aerial vehicles, and flight time constraint information; discretizing the three-dimensional task space into three-dimensional cuboid grids, numbering the three-dimensional cuboid grids, marking the position of the terrain and the position of the threat space in the three-dimensional task space, and abstracting the three-dimensional task space into a directed graph; constructing a single-target multi-unmanned aerial vehicle four-dimensional flight path planning model according to the unmanned aerial vehicle three-dimensional task space and the task time range; and solving the single-target multi-unmanned aerial vehicle four-dimensional route planning model to obtain a planned route, take-off time and flight speed of each unmanned aerial vehicle. Through time optimization, the problem that in a traditional method, only a three-dimensional path is optimized, but time optimization is ignored is solved, the flight path time of the unmanned aerial vehicle is determined better while path planning is carried out, and the utilization rate of space-time resources is increased.
Owner:BEIJING UNION UNIVERSITY
High-altitude capable wide velocity range flight velocity vector measurement probe and measurement system
InactiveUS20060178790A1Erroneous detectionPrevent fallingDigital data processing detailsFluid speed measurement using pressure differenceAnomaly detectionFlight velocity
It is an object of the present invention to solve the problem of a drop in precision in conventional systems using a square pyramid type five-hole probe due to the drop in atmospheric pressure in high altitude ranges, and to provide a wide velocity range flight velocity vector measurement system that can prevent a drop in measurement precision. Furthermore, it is also an object of the present invention to provide a method for eliminating the effects of detection fluctuations caused by adhering water droplets, ice particles or dust in a wide velocity range flight velocity vector measurement system. The flight velocity vector measurement probe of the present invention comprises means in which a static pressure hole is formed in the tube wall surface of the probe, so that a static pressure value is obtained from the pressure detected by this static pressure hole, the Mach number M is calculated on the basis of an equation approximated by a fourth-order polynomial of the static pressure / total pressure signal and the angle of attack, and in cases where an abnormal detection value is detected, this is replaced by the preceding detection value.
Owner:JAPAN AEROSPACE EXPLORATION AGENCY
Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift
ActiveUS9278753B2Improving stall behaviorInfluencers by generating vorticesWingsLeading edgeJet aeroplane
A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.
Owner:AIRBUS OPERATIONS GMBH
Method and device for measuring flying speed and landing coordinate of projectile of double-tube volley weapon
InactiveCN102183183AAccurate measurement of flight speedAccurate measurementAmmunition testingDouble tubeMeasurement device
The invention discloses a method and a device for realizing measurement of a flying speed and a landing coordinate of a projectile of a double-tube volley weapon for outdoor target lanes. The method comprises the following steps that: eight test light curtain arrays are arranged along a trajectory direction; when the projectile flies through the light curtain arrays, a detecting device generates corresponding electric signals so that eight paths of data acquisition devices acquire curtain-passing signals accurately, and transmit the signals to an upper computer through wireless digital transmission equipment; and the upper computer recognizes the flying projectile through a speed and landing coordinate calculation algorithm, stores and displays the flying speed of the projectile and the position coordinate on the surface of the target. The method is simple in theory and easy to realize. The measurement device provided by the invention comprises the detecting device, the data acquisition devices, the wireless digital transmission equipment, the upper computer, a memory and a display; and the detecting device consists of two four-light-curtain detecting devices. The device has a simple structure and low cost, and can realize quick and precise measurement of trajectory parameters of double-tube or single-tube volley weapons under the large-scattering condition of the trajectory at the end point.
Owner:XIAN TECHNOLOGICAL UNIV
Vision calibration method and system, and unmanned aerial vehicle
ActiveCN107194399AHigh precisionEasy to identifyCharacter and pattern recognitionUncrewed vehicleComputer science
The invention discloses a vision calibration method. The method comprises the steps of collecting a vision calibration pattern arranged on the ground through a camera on an unmanned aerial vehicle; identifying a concentric annulus, a concentric square and a direction calibration image in sequence to obtain identification results; according to the identification results, adjusting flight attitude of the unmanned aerial vehicle to enable the direction of the head of the unmanned aerial vehicle to be consistent with that of the direction calibration image; and when the direction of the head of the unmanned aerial vehicle is consistent with that of the direction calibration image, reducing the flight speed of the unmanned aerial vehicle to a preset speed, thereby enabling the unmanned aerial vehicle to land at the preset speed. According to the method, the unmanned aerial vehicle identifies the provided vision calibration pattern richer in geometric characteristic and easier to be subjected to image identification, so that the autonomous landing precision of the unmanned aerial vehicle is improved and the occurrence frequency of autonomous landing exception events is reduced. The invention furthermore discloses a vision calibration system and the unmanned aerial vehicle, which have the abovementioned beneficial effects.
Owner:GUANGDONG UNIV OF TECH
Method and system for monitoring speed of unmanned plane
ActiveCN106199039AEmbody mobilityThe result is accurateImage enhancementImage analysisAngular velocitySimulation
Owner:SHENZHEN HIGHGREAT TECH DEV CO LTD
Speed prediction based segmentation iteration remaining time estimation method
InactiveCN104077469AImprove estimation accuracySpecial data processing applicationsState variableFlight velocity
The invention discloses a speed prediction based segmentation iteration remaining time estimation method. The flight velocity of a missile is a known constant value, starting from a starting point of a first segmented section, the starting point is corresponding to the initial conditions of the relative motion of the missile and a target, and corresponding state variables at the tail ends of the segmentation sections are calculated by a segmentation iteration method according to the initial conditions of the relative motion of the missile and the target. According to the speed prediction based segmentation iteration remaining time estimation method, the problems that the accurate estimation on the remaining time is difficult to achieve due to the time-varying size of the flight velocity of the missile due to the fact that the size of the velocity of the practical missile is not controlled can be effectively solved; compared with the existing segmentation iteration remaining time estimation method, the estimation accuracy of the remaining time is greatly improved; the estimation accuracy is improved and the problem that the existing remaining time estimation method based on the proportional guidance law or the proportional guidance law with angle control is only applicable to the ideal situation that the flight velocity of the missile is the known constant value in case of a large advance angle is well solved.
Owner:NAVAL AERONAUTICAL & ASTRONAUTICAL UNIV PLA
Electric aircraft with a plurality of ducted propellers, telescopic wing and telescopic aircraft body
The invention provides an electric aircraft with a plurality of ducted propellers, telescopic wing and telescopic aircraft body, which belongs to the field of air materials. According to the invention, the wing comprises a plurality of embedded wing sections; during taking off, landing and parking, the tail parts of the wing and the aircraft body can retract; after liftoff, the tail parts of the wing and the aircraft body are unfolded; and the plurality of ducted propellers capable of tilting are symmetrically distributed in front of and behind the wing and on left and right sides of the aircraft body. Through adoption of the layout, the aircraft can vertically take off and land and can also rapidly fly in a flat way; the floor area is reduced during vertical take off and landing and parking; and during flat flight, the plurality of ducted propellers can tilt for 90 degrees so that the flying speed and airborne period are increased. The takeoff and landing process is safe and reliable and the flight attitude is stable. The invention can be made into manned aircrafts and can be also made into unmanned aerial vehicles.
Owner:苏州儒博特科技有限公司
Universal smart fuze for unmanned aerial vehicle or other remote armament systems
An unmanned aerial vehicle is equipped to carry a payload of explosives for remote delivery upon a target. The vehicle includes a small TV camera, global positioning system, and auto pilot homing target software. The modified vehicle is capable of being detonated upon an impact or selectively while still in flight. Vehicle flight is monitored by an operation person at a ground control station. The vehicle includes universal smart fuze circuitry for enabling the multiple functions for the vehicle and for enabling communications / commands from the operator at the ground control station. The fuze continuously communicates aspects of fuze status back to the ground control station; measures flight velocity by sensing air speed of the UAV; arms / disarms an explosives warhead package in the vehicle; in flight fires the explosives or else detonates the explosives warhead package upon impact with a select target. The camera images are communicated back to the operator who can make a decision on completing / aborting a mission. The wind speed indications, also fed back to the operator, can further aid in verifying a successful launch / good flight for decision of completing / aborting a mission.
Owner:UNITED STATES OF AMERICA THE AS REPRESENTED BY THE SEC OF THE ARMY
Combined type tilting rotor-wing helicopter
PendingCN106882373ASimple control methodImprove forwarding speedVertical landing/take-off aircraftsRotocraftFlight vehicleFlight velocity
The invention discloses a combined type tilting rotor-wing helicopter. The aircraft has characteristics of vertical ascending and descending, hovering and high-speed forward flight; compared with a traditional helicopter, the flight speed is high; compared with a tilting rotor-wing aircraft, the control reliability is high. The aircraft comprises a main lifting power rotor wing, a tilting rotor wing, a tilting airfoil, a fixed airfoil, a fuselage body and an undercarriage. The main lifting power rotor wing is a coaxial reversing propeller double-rotor-wing system; the tilting rotor wing and the tilting airfoil can be rotated through an actuating mechanism along a rotary shaft. The aircraft needs to undergo a vertical flight state, a transition flight state and a vertical flight state from takeoff to flat flight. In a whole flight process, the main lifting power rotor wing provides main lifting power to the aircraft all the time, and attitude of the aircraft is mainly controlled through tilting of the tilting rotor wing and the tilting airfoil. The combined type tilting rotor-wing helicopter has advantages of the tilting rotor wing and a coaxial helicopter, and mechanism and control defects of the tilting rotor wing and the coaxial helicopter are overcome; meanwhile, the reliability of the mechanism and a control method is improved.
Owner:北京天宇新超航空科技有限公司
High-altitude capable wide velocity range flight velocity vector measurement probe and measurement system
InactiveUS7480548B2Prevent fallingEliminate the effects ofDigital data processing detailsFluid speed measurement using pressure differenceAnomaly detectionFlight velocity
Owner:JAPAN AEROSPACE EXPLORATION AGENCY
Optimized method of controlling yaw for rotary-wing aircraft, and a system for implementing it
InactiveCN1721274AImprove defectsImproves and/or overcomes deficienciesAttitude controlRotocraftFlight velocityTail rotor
The invention relates to a method of controlling the blade propeller pitch of the tail rotor of a rotorcraft. The method comprises the following steps: a) a main control (18) of a blade propeller pitch of the tail rotor is produced as the function of the control element (4b) to control the blade propeller pitch of the tail rotor and operated by the pilot of the aircraft. b) A collective pitch and yaw decoupling control (16) is produced as the function of the rotor collective pitch. c) A deviation control (17) is produced and then is changed as the function of the flight velocity of the aircraft and the function of the position of the control element (4b). The deviation control is added to the decoupling control and the main control by a summing device (111) to get a collective control (10), thereby controlling the blade propeller pitch of the tail rotor.
Owner:EUROCOPTER
Systems and methods for classifying flying insects
Systems, apparatuses, and methods of classifying flying insects. The methods utilize recording the wingbeat frequency and amplitude spectrum of flying insects and comparing them to known or created insect models to properly classify the flying insect. The error rate of the classification is reduced by utilizing multiple inputs to the classification system, which may include a precise circadian rhythm for the time of year, current environmental conditions, and flight velocity or direction.
Owner:RGT UNIV OF CALIFORNIA +1
Onboard sensor suite for determining projectile velocity
InactiveUS8433460B1Improve performanceAccurate predictionDirection controllersDigital data processing detailsProximity sensorFlight velocity
An onboard sensor suite generally includes two main components: a proximity sensor suite for measuring the projectile muzzle velocity; and a pressure sensor suite for measuring the projectile airspeed. The flight velocity of the projectile can then be estimated with a high degree of accuracy using either the muzzle velocity by itself or the airspeed by itself, or, in a preferred embodiment, by using both the muzzle velocity and the airspeed. The proximity sensor suite includes proximity sensors that are mounted along a projectile body; a wire harness; and an onboard computer or CPU. The pressure sensor suite includes a Pitot pressure transducer and two static pressure transducers that are mounted within the projectile body; a wire harness; and a CPU.
Owner:UNITED STATES OF AMERICA THE AS REPRESENTED BY THE SEC OF THE ARMY
Detection method and device of radical cooling temperature, flying speed, and movement track
ActiveCN105066983ARealize two-dimensional detectionAchieve coincidenceTurn-sensitive devicesGyroscopeLight beam
The invention discloses a detection device of radical cooling temperature, flying speed, and movement track. The detection device comprises a detection light path system and a single acquisition system; the detection light path system comprises an incident optical fiber (11), a beam expanding and collimation system (12), a diaphragm (13), and a reflector (14); the single acquisition system comprises a focusing lens (21), a photodiode PD (22), and a CCD (23); three intersection areas of three flake-like parallel light beams, which are formed via illuminating of the diaphragm (13) by the beam expanding and collimation system (12), with the radical movement track are taken as detection areas. The detection method and device are skillful is design, and simple in structure, can be used for detection of radical cooling temperature, flying speed, and movement track with a single detection device, and improving atom laser gyroscope performance further.
Owner:NO 717 INST CHINA MARINE HEAVY IND GRP
Monitoring method and device for laser phase Doppler powder dust particle
InactiveCN1587984AAvoid Measuring EffectsLarge measuring rangeScattering properties measurementsParticle size analysisBeam splitterPhase difference
A laser phase Doppler dust particle monitoring method and apparatus belongs to particle measuring technique. It includes the steps that two beams of coherent incident light has concourse and irradiate normally to flowing direction of dust particle current; two sensors are installed with symmetry, optical signal of particle scattering received by which has the same frequency but different phase, its frequency is proportional to flight velocity of particle and phase difference is proportional to with diameter of particle, by using processor to extract frequency and phase difference of signal, the diameter, velocity and other information of particle are obtained. The apparatus consists of detecting system containing laser source, polarizer, beam splitter, objective lens and APD sensor and processing system containing signal preprocessor, high speed synchronous A / D converter, wavelet processor, parameter processor and data fractional, synchronous controller. The invention has the advantages including high accuracy and reliability of parameter measurement like velocity and diameter of dust particle, wide measuring range and excellent applicability.
Owner:TIANJIN UNIV
Unmanned aerial vehicle cruising and tracking system and method based on deep learning technology
The invention relates to an unmanned aerial vehicle cruise and tracking system and method based on a deep learning technology. The system comprises a cruise mode and a tracking mode. The cruise mode comprises an image real-time collection module, a dangerous article, dangerous behavior and dangerous personnel detection module, and an warning module which is used for warning a ground command station after discovering dangers. The tracking mode comprises a real-time video acquisition module, a detected dangerous person tracking module, a laser ranging module which is used for detecting the distance between a dangerous person and the unmanned aerial vehicle, a flight control module which adjusts the flight speed and direction of the unmanned aerial vehicle, and a data transmission module which shares the real-time position of the unmanned aerial vehicle with the ground command station and shoots videos in real time. The unmanned aerial vehicle cruise system and the unmanned aerial vehicletracking system provided by the invention are high in operation speed, high in detection precision and flexible in detection area, so that the timeliness of alarm can be guaranteed, the defects of existing monitoring can be overcome, and real-time guarantee is provided for personnel safety in areas such as squares.
Owner:AVIC JINCHENG UNMANNED SYST CO LTD
Rear ventilation cooling device of piston engine
PendingCN110901930AFlexible and controllable openingReduce aerodynamic dragPower plant cooling arrangmentsFlight velocityForced convection
The invention discloses a rear ventilation cooling device of a piston engine, and relates to the technical field of unmanned aerial vehicle piston engines, an engine fairing and a fuselage are coordinated in appearance for aerodynamic design, an air channel door is completely attached to the fairing after being closed, the opening degree is controllable after the air channel door is opened, cooling airflow is introduced into an air channel from an external flow field, and closed-loop control over an engine cylinder body is achieved through adjustment of the air inflow. According to the flightspeed of the unmanned aerial vehicle, the environment temperature and the engine cylinder temperature, the air passage door is controlled to be opened at different opening degrees, the engine cylindertemperature is controlled within the optimal temperature range, the engine cooling air entraining requirement is met, and the flight resistance can be reduced. Forced convection heat dissipation is conducted on the engine cylinder body in the flow guide cover, cooling airflow flows out of a rear opening of the flow guide cover, the section of the rear opening of the flow guide cover is close to the rotating plane of the propeller, auxiliary heat dissipation can be conducted through the suction effect of the propeller during work, the cylinder body cooling response speed is high, the structureis simple, and the cooling efficiency is high.
Owner:XIAN AISHENG TECH GRP +1
Optimized configuration algorithm of independent scenery storage micronet based on improved fish swarm algorithm
The invention discloses an optimized configuration algorithm of an independent scenery storage micronet based on an improved fish swarm algorithm, which utilizes particle flight velocity v and inertiaweight w to improve the foraging behavior, clustering behavior and tail collision behavior of the artificial fish swarm algorithm. The algorithm uses the particle swarm optimization algorithm to update the best fitness of the elite artificial fish swarm; in the artificial fish swarm optimization algorithm, the best fitness of the artificial fish is found, and the particle swarm optimization algorithm is used to update until the required accuracy or iteration times. In this case, the position obtained by iteration is obviously better than the initial point, but it requires multiple times of iteration to obtain the current best solution. Considering the overall efficiency, the termination condition of the improved PSO artificial fish swarm algorithm is constructed by using the precision anditeration times. The invention applies the algorithm to configure the independent wind-solar storage micro-grid, and the independent micro-grid optimized configuration is to meet the requirements ofthe lowest total operation cost and the lowest new energy power generation abandonment rate of the micro-grid by the normal operation of the micro-source and satisfying each constraint condition.
Owner:SHANGHAI DIANJI UNIV
Flight vehicle health state monitoring system based on distributed optical fiber sensing
InactiveCN107255492AAchieve targetedEffective maintenanceMeasurement devicesComputer controlStructural health monitoringEnvironmental indicator
The invention discloses a flight vehicle health state monitoring system based on distributed optical fiber sensing. The flight vehicle health state monitoring system comprises a motion detection unit, an operation detection unit, an atmospheric environmental indicator detection unit, a central processor, an early warning unit, and a wireless communication module. The motion detection unit is used for the real-time detection of the flight velocity and the flight height of the flight vehicle. The operation detection unit is used for the real-time detection of the attitude information, the pressure-bearing information, and the vibration information of the flight vehicle. The atmospheric environmental indicator detection unit is used for real-time detection of air temperature, dust concentration, and illumination intensity. The system is used for the comprehensive monitoring and analysis of the main rotor, the tail rotor, the transmission system, the parts of the engine of the flight vehicle by using external sensors to realize the integral health monitoring of the flight vehicle. The health state fault of the flight vehicle is diagnosed and predicted, and powerful data support is provided for the health monitoring, and therefore the targeted, timely, and effective maintenance of the flight vehicle is realized, and good economic benefits and good military benefits are provided.
Owner:ZHENGZHOU UNIVERSITY OF AERONAUTICS
Hybrid axial/cross-flow fan multi-rotor aerial vehicle
ActiveUS9783291B2Effective capabilityAmple internal cargo capacityAircraft stabilisationUnmanned aerial vehiclesFlight velocityForward flight
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.
Owner:PROPULSIVE WING
Self-adaptive rhombic wing layout of air vehicles
ActiveCN105235889AVersatilityThe overall structure is simple and reliableHeat reducing structuresFlight vehicleFlight velocity
The invention provides a self-adaptive rhombic wing layout of air vehicles. According to the self-adaptive rhombic wing layout of the air vehicles, a nose, a tail, four wings, an engine, a task bin, four connecting arms, hinges and control vanes are involved. The four wings are arranged in a rhombic mode from front to back. The four connecting arms can be telescoped and are transversely or longitudinally arranged in a crisscross mode. The nose and the wings are connected through the hinges, the tail and the wings are connected through the hinges, and the engine and the wings are connected through the hinges. The task bin is connected with the nose, the tail and the engine through the telescopic connecting arms and can be changed according to task requirements. The wings are provided with the control vanes used for controlling flight attitudes. The sweepback angle and the sweep-forward angle of the wings can be changed by telescoping the connecting arms so as to obtain rhombic wing layouts adapting to different flight speeds and improve the aerodynamic performance. The self-adaptive rhombic wing layout of the air vehicles has the advantages of being simple and reliable in structure, low in cost and multiple in function.
Owner:INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift
ActiveUS20130320150A1Avoid temperatureReduce air resistanceInfluencers by generating vorticesWingsFlight vehicleFlight velocity
A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased.
Owner:AIRBUS OPERATIONS GMBH
Automatic planning method for intelligent spraying path of ship outer plate based on unmanned aerial vehicle
ActiveCN112917486AImprove spray qualityImprove resource utilizationProgramme-controlled manipulatorSpraying apparatusUncrewed vehicleFlight velocity
The invention discloses an automatic planning method for an intelligent spraying path of a ship outer plate based on an unmanned aerial vehicle. The method comprises the following steps of: (1) collecting an image of the ship outer plate by using the unmanned aerial vehicle; (2) performing three-dimensional reverse modeling on the ship outer plate, and classifying the ship outer plate model according to the regularity of the shape; (3) respectively planning the flight times and spraying path of the spraying unmanned aerial vehicle for a plane, a regular curved surface and a complex curved surface; and (4) generating the spraying path of the spraying unmanned aerial vehicle and the operation parameters of the unmanned aerial vehicle. According to the automatic planning method disclosed by the invention, the three-dimensional model of the ship outer plate is quickly generated, the flight speed, spraying pressure, spray gun distance and spraying path spacing of the spraying unmanned aerial vehicle for the plane, the regular curved surface and the complex curved surface are respectively optimized by a multi-objective particle swarm algorithm, and the automatic planning method has important significance for improving the spraying quality, resource utilization rate and operation efficiency of the spraying unmanned aerial vehicle.
Owner:JIANGSU UNIV OF SCI & TECH
Airship tail vectored thrust device
The invention discloses an airship tail vectored thrust device which mainly comprises a tail cone, a two-degree-of-freedom rotary table base, a Z-axis rotating body, a Y-axis rotating body and thrust devices. When the airship tail vectored thrust device is operated, deflection of the Z-axis rotating body and the Y-axis rotating body drives the thrust devices to enable the same to rotate tipsily in an airship body plane and a vertical plane within the range of + / -90 degrees, and a certain vectored thrust is generated, so that pitching and yaw attitude adjustment and auxiliary acceleration of an airship are achieved. By the aid of the airship tail vectored thrust device, response speed of airship attitude (pitching and yaw) adjustment is remarkably increased, control torque is increased, flying speed is increased in an assisted manner, and environmental adaptability of the airship is enhanced.
Owner:湖南航天远望科技有限公司
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