206 results about "Flight velocity" patented technology

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.

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.

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.

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.

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.

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.

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.

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.

The invention provides a method and system for monitoring the speed of an unmanned plane, and the method comprises the steps: obtaining the current flight altitude and angular velocity and an image; obtaining feature points of the image, and calculating the optical flow of each feature point; carrying out the counting of the optical flows of all feature points, and selecting the optical flow with the maximum optical flow repetitive rate in the same direction as the optical flow of the image; and calculating the current flight velocity according to the current flight altitude and angular velocity and the optical flow of the image. The invention also relates to a system corresponding to the above method. The method obtains the feature points of the current image through calculation, calculates the optical flows of all feature points, and selects the optical flow with the maximum optical flow repetitive rate in the same direction as the optical flow of the image. Afterwards, the method carries out the calculation of the current flight velocity according to the optical flow of the image and the current flight altitude and angular velocity. The method is simple in calculation, is small in calculation burden, gives consideration to the influence of a plurality of factors, and is precise in calculation result.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

The invention provides a quantitative spray control method in a flying process. The control method is used for controlling spray of an aircraft loading a spray pump and includes the steps: a, determining the unit area spray amount A of the spray pump in unit area B; b, setting the expected opening quantity S of the spray pump based on the unit area B and the unit area spray amount A of the spray pump and the real-time flight velocity V and the spray span L of the aircraft; c, acquiring the real-time opening quantity of the spray pump; d, calibrating the spray pump based on the real-time opening quantity to achieve the expected opening quantity. A uniform and accurate spray mode is realized, and limit of water pump types, working power and the like is avoided.