740 results about "Cruise" patented technology

The invention discloses a pneumatic layout of a vertical taking-off and landing aircraft with a tilted duct. The pneumatic layout is characterized in that front duct fans are symmetrically arranged at the outer sides of the head parts of all the aircraft bodies; rear duct fans are symmetrically arranged at the inner sides of the middle parts of all the aircraft bodies; and all the duct fans are respectively connected with transmission components in the aircraft bodies by duct rotating shafts in the transmission components. The axial distance between protection points of the axial lines of all the duct rotating shafts on the axial lines of the aircraft bodies and the center of gravity of the whole aircraft along the aircraft bodies is 1.125 times of the chord length of wings. In the pneumatic layout, the duct fans can rotate around the duct rotating shafts; when the aircraft takes off or lands vertically, the duct fans are positioned at the vertical 90-degree position, the thrust vector is upward; in the transition stage, the duct fans rotate forwards around the duct rotating shafts; and in the cruise stage, the duct fans are positioned at a horizontal 0-degree position, and the thrust vector is forward, so that vertical taking off and landing and high-speed cruise flying are realized. The pneumatic layout disclosed by the invention has the advantages of high pneumatic efficiency, compact structure, strong reliability, strong maneuverability, flexible operation, long voyage and low noise and the like.

Embodiments of the present invention relate to a system and method for better conveying information to a pilot and / or other members of a flight crew present on the flight deck of an aircraft. Embodiments of the invention are of particular use in the briefings that precede various phases of the flight operations of an aircraft (such as start-up of the engines, take-off, ascent to cruise altitude, descent from cruise altitude and landing). The system and method provide a briefing output relevant to the particular phases of a flight in both of a visual form and an audio form, with the briefing output including data of most relevance to the particular flight phase.

Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft.

An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up / down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections.

The invention provides a low-altitude remote sensing system based on an automatic cruise unmanned aerial vehicle. The low-altitude remote sensing system comprises a load system, a data acquisition system, a data transmission system and a control system. High-precision constant altitude cruising of the unmanned aerial vehicle along a preset route can be realized, and remote sensing data acquisition is performed. The scheme has remarkable effects of being lightweight, high in time and space resolution and low in cost.

The invention discloses a fan blade autonomous inspection method based on an unmanned aerial vehicle. The method comprises the following steps that S1, determining whether the geometric structure of ato-be-inspected fan is known, if yes, entering the step S2, if not, entering the step S3; S2, carrying out image shooting on a to-be-inspected fan, determining coordinate information of a plurality of inspection points on the fan in combination with the geometric structure of the to-be-inspected fan, and entering the step S4, the inspection points being target points shot during inspection; S3, carrying out image shooting on the to-be-inspected fan, acquiring coordinate information of a plurality of inspection points on the fan through image processing, and entering the step S4; and S4, according to the coordinate information of the inspection point, determining a cruise point coordinate and generating an autonomous cruise trajectory, the cruise point being a place where the unmanned aerial vehicle hovers and shoots, and the unmanned aerial vehicle completing inspection of the fan blade according to the autonomous cruise trajectory. According to the invention, the workload of autonomous inspection route generation can be effectively reduced, the accuracy of the route is improved, and the inspection efficiency of the fan is improved.

The invention discloses a fixed-wing aircraft on which retractable multi-rotor assemblies are mounted and which can perpendicularly take off and land. In the scheme of the fixed-wing aircraft, the fixed-wing aircraft comprises fixed-wing assemblies, retractable multi-rotor assemblies, a multi-rotor extending and retracting control mechanism, a multi-rotor hatch which can be opened and closed and a hatch opening and closing control mechanism. The fixed-wing aircraft is characterized in that when the aircraft is in a take-off stage or a landing stage or when the aircraft needs to hover in the air, the retractable multi-rotor assemblies in the lower part of an aircraft body are unfolded to provide a perpendicular take-off and landing capacity; when the aircraft cruises at a high speed, the multi-rotor assemblies are retracted in the aircraft body, the multi-rotor hatch is closed to keep the aerodynamic performance of the fixed-wing aircraft; and besides, when the fixed-wing aircraft is in perpendicular take-off and landing state, hovering state and cruising state at a high speed, the highest energy service efficiency can be obtained, so that the fixed-wing aircraft disclosed by the invention has a large perpendicular take-off and landing weight and a long range at the same time. According to the fixed-wing aircraft disclosed by the invention, a solution of a perpendicular take-off and landing fixed-wing unmanned aerial vehicle which is low in cost and high in energy efficiency is provided, is wide in application, and is particularly suitable for being applied to trades including point-to-point article transportation, long-distance cruise and the like.

The invention discloses an unmanned operational intelligent ship apparatus which comprises an intelligent ship body. The intelligent ship body is provided with a main control module. The main control module is connected with a navigation system, a water quality detection system and a data transmission module. The water quality detection system comprises a sensor module arranged at the lower part of the intelligent ship body. The navigation system comprises a Beidou and GPS dual-mode positioning module and a compass module. The main control module is further connected with an execution mechanism, a range finding module, and an electricity amount detection system. The data transmission module communicates data with an intelligent terminal. The intelligent terminal is provided therein with a control system APP used to control the intelligent ship. The apparatus and the control system of the invention are able to realize self-cruise, to automatically avoid barriers, to automatically back charge, to communicate data with the intelligent terminal and to control an unmanned operational intelligent ship according to the data acquired on the site. And at the same time, the monitoring and managing of the intelligent ship and the water areas become more convenient by providing checkable intelligent ship's travel trajectory at any time, the ship power amount state, the water quality parameters of a culturing area to control the working of the intelligent ship.

A platform including two winged aircraft are tethered during flight by a single tether near their respective centers of gravity. The tether is windable about a reel, so that a distance between the aircraft can be changed during flight. The aircraft contain avionics configured to enable autonomous flight using natural wind gradients. One aircraft imposes aerodynamic forces on the other, through the tether, while flying at an altitude where wind speed is significantly different than wind speed at an altitude of the other aircraft. The two aircraft cruise back and forth within a maximum distance from a station on the ground. Cruise conditions are established using an iterative computer algorithm which utilizes flight measurements. The aircraft communicate information between each other, and the ground, and contain a payload which performs a useful function at high altitudes.

The invention relates to the technical field of aerospace equipment, in particular to a flight bird repellent and a flight bird repelling system. The flight bird repellent comprises a central body and 2n+2 wings respectively connected to the central body, wherein n is a positive integer, a power mechanism is mounted on each wing, a navigation control module and a repelling device for repelling birds are fixedly mounted on the central body, and the power mechanisms and the repelling device are respectively connected with the navigation control module which is connected with a remote control signal transmitter. The ground station system of the flight bird repelling system is connected with the navigation control module and controls the operation of the flight bird repellent. The flight bird repellent and the flight bird repelling system have the advantages that the flight bird repellent has stable and reliable flying ability, the covering range of the bird repelling is enlarged evidently, and operation flexibility and work efficiency are increased; the flight bird repelling system controls one or more flight bird repellents to perform cruise flight or tracking bird repelling through the ground station system, and spatially three-dimensional and flexible and mobile bird repelling effect can be achieved.

Methods and apparatus are provided controlling aircraft cabin pressure, and more specifically engine bleed air manifold pressure, during aircraft descent. An aircraft engine bleed air manifold control pressure setpoint is to either a descent pressure setpoint or a cruise pressure setpoint by determining a rotational speed of an aircraft engine component, determining a component speed setpoint value, and determining aircraft vertical speed. The engine bleed air manifold control pressure setpoint is set to the descent pressure setpoint if either the determined rotational speed of the aircraft engine component is below the component speed setpoint value or the aircraft vertical speed is less than a predetermined vertical speed value.

The invention discloses an unmanned aerial vehicle inspection method for an unknown fan structure. The method comprises the following steps: S1, multi-angle photographing of a whole fan is carried outat a long distance, and the whole fan should be contained in each picture and be close to the center of each picture; S2, inspection point coordinate information for equally dividing the blade is calculated by utilizing obtained key inspection point coordinate information; S3, required cruise point coordinate information is calculated by utilizing the inspection point coordinate information, anda flight path is generated; S4, an unmanned aerial vehicle takes off and arrives at a cruise point, and the pose of the unmanned aerial vehicle is adjusted by utilizing inspection point coordinate information to enable the unmanned aerial vehicle to face a target point; and S5, target identification is performed on an inspection point once before photographing of a cruise point, and the attitude of a holder is adjusted again to make the inspection point be close to the center of each picture as much as possible. The inspection point can be close to the center of each picture as much as possible, and the reliability of autonomous inspection of the unmanned aerial vehicle is higher while the efficiency is improved.

A supersonic cruise configuration aircraft comprises a fuselage extending on a longitudinal axis from a forward nose to an aft tail, and a wing coupled at an inboard section to the fuselage and extending to an outboard tip, and having a leading edge and a trailing edge. The aircraft further comprises a landing gear that is coupled to the wing and capable of stowing into the wing and fuselage on retraction. The landing gear has a landing gear strut. The wing is gulled with a dihedral at an angle that is increased inboard and aligns with the retracted landing gear. The wing has a minimum thickness sufficient to enclose the landing gear.

The invention discloses a method for planning obstacle avoidance motion of a UAV under a cruise mission. The method comprises steps of performing rasterizing modeling on a global environment, establishing a risk evaluation function, producing global track points by using an improved A star algorithm, introducing UAV speed constraint and maximum yawing rate constraint in the A star algorithm, smoothing discrete points by using a Doberman curve, and for emergent obstacles, avoiding the obstacles in real time by using a geometric position relationship and the Doberman curve. In the method, control policies of the UAV are modelled by using a Markov decision model, so as to determine an optimal manoeuvre for avoiding the obstacle. Through adoption of the method, the UAV can rapidly figure out asafe track according to the position of the known obstacle, can respond to sudden barriers and perform the optimal manoeuvre, so as to avoid colliding with an obstacle.

A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft.

The invention provides a vertical take-off and landing unmanned aerial vehicle and a control method thereof. A vehicle body of the unmanned aerial vehicle adopts aerodynamic layout of high lift-drag ratio class flying wings, and four motors and propellers are installed on the vehicle body in a mode of cross-shaped arrangement. An elevating control torque is formed by the thrust difference generated by the upper propeller and the lower propeller of the vehicle body, a yaw control torque is formed by the thrust difference generated by the left propeller and the right propeller of the vehicle body, and through the roll control torque formed by the different rotating speeds of the four propellers, the attitude control of the vehicle body of the unmanned aerial vehicle is conducted so that vertical take-off and landing in a narrow region and spot hover at any positions in the flying process of the unmanned aerial vehicle can be achieved. After the unmanned aerial vehicle is switched into a flat flying state, the vehicle body of the class flying wing layout can generate a large cruise lift-drag ratio, the effective loading level of the unmanned aerial vehicle is greatly improved, and the flying distance of the unmanned aerial vehicle is greatly prolonged. When the unmanned aerial vehicle horizontally flies, propelling can be conducted for low-speed flying only by using the left propeller and the right propeller, and propelling can be conducted for high-speed flying by simultaneously using the four propellers.

The invention discloses a method for automatic cruise detection of comprehensive information of greenhouses. According to the method, an optimal cruise path can be set according to the needs of different greenhouse soil bin structures and greenhouse comprehensive information acquisition, the precision of cruise is guaranteed through ultrasound position detection, a detection target is located based on laser sensing, and power is timely supplemented to a mobile platform through an automatic charging device during cruise intervals. Thus, continuous-cruise dynamic monitoring on greenhouse environment and crop information is realized, the detection efficiency and accuracy are improved, and an unmanned management mode is realized. The method of the invention can be applied to detection of greenhouse environment and crop growth information.

The invention discloses a tilt-rotor based on combination of four rotor wings and a fixed wing. The tilt-rotor is structurally characterized in that a first rotor wing, a second rotor wing, a third rotor wing and a fourth rotor wing are divided into two groups which are respectively symmetrically mounted on the two sides of a tilt-rotor body by two shafts; (1, 2) is a front motor group; (3, 4) is a rear motor group; a middle wing is horizontally mounted on the tilt-rotor body and is vertical to the tilt-rotor body; backswept wings on the two sides are respectively mounted on the two sides of the middle horizontal wing at a backswept angle of 50 degrees. According to the tilt-rotor disclosed by the invention, the four rotor wings and the fixed wing are enabled to share a set of power system to realize vertical takeoff and landing, hovering and cruise level flying; the front and rear tilting motor groups (1, 2) and (3, 4) share a set of tilting device to realize synchronous tilting by a tilting drive shaft, thereby simplifying a tilting structure and improving the operability and stability of the tilt-rotor.

The invention discloses a drone and a multi-sensor fusion positioning method for bridge three-dimensional cruise detection. The drone comprises a controller and k kinds of positioning sensors, whereineach kind of the positioning sensor is connected to the signal input end of the controller. The controller is configured with a multi-sensor fusion positioning program. The multi-sensor fusion positioning program is configured to perform a coordinate data fusion on the three-dimensional coordinate of the same point according to the m kinds of sensors, when 1<m<=k, outputs the spatial coordinate of the current cruising of the drone. The invention further provides a multi-sensor fusion positioning method for bridge three-dimensional cruise detection, and adopts the drone of the invention for bridge three-dimensional cruise detection to perform real-time positioning during the cruise process. The invention solves the technical problem that the accuracy of the drone relied on GPS positioningis low caused by instability of the satellite signal during the cruise detection process in the prior art.

The invention discloses a method for extracting the cruise section of a flight path from a three dimensional position sequence of an air craft, including: (1) reading atmospheric pressure height data of the air craft and recording the time of the data; (2) calculating the flight level at which the air craft is located currently; (3) cutting off climbing and descending sequence section in level flight section to obtain the level flight sequence section of the cruise section; (4) reading GPS longitude and latitude data and recording the time of the data; (5) intercepting the GPS longitude and latitude sequence into direct flight sequence section and cutting off turning sequence section to obtain the direct flight sequence section of the cruise section of the air craft; (6) solving an intersection of the level flight sequence section and the direct flight sequence section over time; calculating the difference of atmospheric pressure height data with lower sample rate in the sequence duration of which meets the duration requirement to extract the cruise section of the flight path is extracted. The method realizes analysis and processing on the three dimensional position sequence of the air craft, effectively removes climbing, descending and turning sections and extracts the cruise section of the flight path.

Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t / c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t / c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t / c) is the average value of (t / c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.

In the so called internal combustion (reaction type) airbreathing jet engines (including turbojets and turbofans) fast moving discharging combustion exhaust gases from core exhaust stream and air will generate jet propulsion. In other words, the produced thrust thru an exit nozzle in such engines moves the jet aircraft forward in flight.During flight of a jet aircraft the essential steering movements (roll, pitch and yaw type maneuvers) are normally performed via control surfaces on its wings and its tail sections. These controls are activated by pilot from inside the cabin.This invention allows for swiveling of a pivotable jet engine mounted under the wings of a commercial jet aircraft, to direct exhaust gases (combustion gases and bypass airflow in case of turbofan engines and in general the engine core exhaust gases for turbojets) upward or downward or sideways (outboard of the cabin and the fuselage) to some limited extent to achieve more agile air maneuvers compared to the traditional fixed under the wing-mounted jet engines. The restricted hinged swivel angular motion of the engine(s) pivotally mounted under the wings of such a jet aircraft will make it possible for comfortably (and not abruptly) shortening the required air distance needed to perform aircraft's attitude adjustment maneuvers needed such as during descent, takeoff, landing approach or during cruise to control flightpath and / or quickly avoid air traffic potential problems.Therefore, the idea of performing agile maneuvers “which at times can become critical in the flight safety of especially larger passenger jetliners” is realized by swiveling jet engines under the wings of a 2 or 4 engine commercial jet aircraft about a pivot point mounted along the engine nacelle to enable highly efficient pitch and roll motions in flight (with enhanced agility), as well as making efficient and agile yaw type motion in flight by turning the entire / plurality of engine assembly (away from the fuselage / cabin) around a central point underneath the wing assembly.

A user interface that improves the cruise line itinerary research and selection process by integrating an interactive geographical display that is able to display multiple cruise line itineraries thereby reducing the number of page reloads during the user interaction with the user interface. Further, the user interface improves the cruise line cabin selection process by integrating spatial dimension data into cabin search results across cabin types and / or categories.

The invention provides a high-mobility active capture type anti-unmanned aerial vehicle system and method. The system comprises an unmanned aerial vehicle, a capture frame, a terminal guidance device, a flight control and electromagnetic interference system, a sensor device and a capture net, wherein the capture frame is mounted above the unmanned aerial vehicle; the capture net is mounted in the capture frame to achieve a buffering effect when low, small and slow targets and other aerial small flying targets (such as birds) are captured; and the terminal guidance device, the flight control and electromagnetic interference system and the sensor device are mounted in the center position of the unmanned aerial vehicle. According to the invention, a ground station system is used for controlling a novel fuselage tilting type unmanned aerial vehicle with vertical takeoff and landing and high-speed cruise capabilities, and low, slow and small targets and other aerial small flying targets are captured in high precision and high mobility according to multiple guidance modes. The system captures the targets by adopting the novel fuselage tilting type unmanned aerial vehicle with high mobility according to multiple guidance modes, secondary capture can be carried out, and the cost is low.

The invention discloses an UAV (unmanned aerial vehicle)-based river line detection system and method and belongs to the technical field of UAV delivery. The system comprises two modes, that is, a mode of interaction control between an UAV and a ground station, and a mode of output control based on the UAV, and the two modes are parallel technical schemes. In the first mode, the UAV transmits images to the ground station, the ground station carries out image processing and returns the processing result to flight control of the UAV through a data transmission device to finish a function; and inthe second mode, the UAV is provided with an image processing chip (a DSP chip), and the UAV finishes image acquisition, processing and data interaction work. The UAV can realize an autonomous cruisefunction without any manual operation; the method can realize cruise according to actual conditions of a river, and the case of flying away from the river cannot occur; and the method is higher in precision than a GPS navigation mode.

A safe, easy to control, efficient, and compact flying car configuration is enabled through the combination of multiple vertical lift rotors, and a thrust propellers which is placed on the center of lower frame of the vehicle. The vertical lift rotors, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight whereas the propeller help to steer the vehicle in air. This multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The passengers are safe inside the vehicle as the rotors and the propeller are surrounded by a thick frame around them. This rotors provide a controlled thrust for a specific lift range.

The invention belongs to the field of water quality monitoring. The purpose of the invention is to provide a water area water quality abnormal point detecting and pre-warning method which has very high detection accuracy and degree of intelligence. According to the technical scheme, the water area water quality abnormal point detecting and pre-warning method comprises the following steps: (a) intelligent cruise; (b) monitoring data model analysis; (c) suspected abnormal data point check; and (d) abnormal data point on-site water sample collection. According to the method, an intelligent cruise ship is used as a carrier, a water quality abnormality analysis model serves as a software support, and human-computer interaction is performed based on the Internet-of-things technology. Water quality abnormal point detecting and pre-warning is truly realized.

The invention belongs to the field of flight mechanics, and particularly relates to a subsonic cruise voyage optimization design method for a fixed-wing aircraft. The method comprises the steps: obtaining 1, flight parameters of the fixed-wing aircraft, wherein the flight parameters comprise the maximum lift-drag ratio Kmax, the cruise lift coefficient Cy and the cruise Mach number M; 2, determining the engine thrust oil consumption rate Ce0 of a cruise entry point and the engine thrust oil consumption rate Ce1 of a cruise end point according to the flight parameters; 3, calculating the average oil consumption rate according to the engine thrust oil consumption rate Ce0 at the cruise entry point and the engine thrust oil consumption rate Ce1 at the cruise end point, and taking the averageoil consumption rate as the voyage calculation oil consumption rate Ce; and 4, calculating the variable-height cruise voyage L of the fixed-wing aircraft according to the voyage calculation oil consumption rate Ce. According to the optimization design method for the subsonic cruise voyage of the fixed-wing aircraft, a large amount of original data used by professional performance software or simulation software is not needed, calculation is rapid and simple, and the model argumentation precision requirement is met.