172 results about "Ground track" patented technology

The invention discloses an intelligent mobile charging automobile system and method. The system comprises a charging automobile, a large-capacity energy storage battery pack, a DC-DC direct-current converter A, a vehicle-mounted charger, a charging connection device, a charging transfer device, a ground track, a mobile phone client terminal, a scheduling center server and a charging room, wherein the scheduling center server comprises a wireless communication unit, a data receiving unit, a data processing unit and a data feedback unit; the charging automobile comprises a driving system, a whole-automobile controller, a wireless communication module, a sound-light alarm module, a tracking detection module and an obstacle avoidance detecting module. According to the intelligent mobile charging automobile system, navigation and landmark tracks are mounted and paved on the ground on the basis of the existing facilities of parking lots; the charging transfer device is mounted on the ground of the preserved charging automobile parking space; the automatic connection charging is implemented; the problem that charging stations and charging piles are inconveniently built in the existing parking lots can be solved; the system is simple and convenient; the building cost and the maintenance cost are greatly reduced; and the charging time is reduced.

The invention relates to a micro coaxial dual-rotor helicopter control device and micro coaxial dual-rotor helicopter control method, which belong to the technical field of helicopter control. The device comprises a ground device and an air device, wherein the ground device comprises a video wireless receiver, a ground wireless transmission module, a ground processor, a displayer and an upper computer; and the air device comprises a three-axis magnetic direction sensor, a three-axis gyroscope, a three-axis acceleration sensor, a GPS, a air pressure gauge, an ultrasonic transducer, an ARM processor, a micro wireless camera, a video decoding module, a video wireless transmission module and an air wireless transmission module. The device and the method have the advantage of improving the utilization rate of resources. In the invention, the network communication of helicopter groups can be realized conveniently. The system can realize aerial photographing and task setting automatic flight and ground tracking automatic flight and realize convenient automatic and manual operation switching.

A forward looking cross-track laser altimeter comprises: a first configuration of optical elements for guiding pulsed laser beams along a first optical path; a mirror element coupled to a scanner and disposed in the first optical path, the scanner operative to oscillate the mirror element to sweep the reflected laser beams back and forth across a line at a predetermined frequency; the scanner and mirror element configurable to reflect the pulsed laser beams along paths forward and downward at a predetermined angle to the flight path of the aircraft, wherein the pulsed laser beam paths are caused to be line swept across a ground track forward the aircraft; the mirror element for receiving returns of the pulsed laser beams from the terrain and objects on the terrain forward the aircraft and reflecting the returns along a second optical path to a light detector which produces a return signal in response thereto; a first circuit governed by the return signals for measuring times-of-flight of the returns and generating time-of-flight signals corresponding thereto; the scanner for generating a line sweep position signal; and a second circuit for generating for each return a data profile comprising range and line sweep position thereof based on the corresponding time-of-flight and position signals.

A new approach for designing satellite constellations whereby each satellite follows a common ground track is being proposed for performing high-precision change detection imagery for long periods of time. By precisely prescribing the orbital parameters, i.e., the relationship between the right ascension of the ascending nodes (RAAN) and the phase angle difference between successive satellites, for example, sharpened change detection images may be taken from successive satellites in the constellation without the need to process out blurring by any special image re-working software. The relationship between the orbital parameters of the satellites is precisely tuned to the earth's rotation rate for the altitude of the satellites. A reduction in the total satellite count is achievable due to tiling the satellite coverage in near optimal arrangements. Such high-precision change detection imaging by successive satellites in orbit around the earth is at least useful in the detection of underground facilities activities and the detection of slow moving objects.

The invention relates to a simulation experiment device of a fire disaster on an external wall face of an urban building. The device comprises a simulation wall body, a burning closet, a weighing mechanism, a slope board, a ground track, a thermoelectric couple frame and a thermal radiation flux measurement frame, wherein the simulation wall body is in a vertical framework shape; the burning closet is a square box the bottom of which is connected with a weighing support; the weighing mechanism comprises an electronic scale and a movable support; the thermoelectric couple frame is a rectangle framework, and more than 10 thermoelectric couples are distributed on the thermoelectric couple frame; the thermal radiation flux measurement frame is in a cross shape, and one end of the cross-bar thereof is provided with a thermal radiation probe, and the thermal radiation probe is correspondingly located in the door of the burning closet. In the invention, a set of simulation experiment device for researching fire disaster features on the external wall face of the building and a mechanism that the fire disaster features are influenced by a slope is firstly established, with a safe, flexible, convenient and fast sloping degree regulating system, and the experiment device is provided with a complete measurement system for temperature and thermal radiation intensity.

A system, and the method of operation and use thereof, for controlling and adjusting the height of a base cutter of a sugar cane harvester, during a harvesting operation, and without the necessity for continuous user intervention and adjustment, to maintain the height of the cut at approximately a desired height, including a control system that has a processor unit which is operable under program control during a harvesting operation, following initiation of program operation by a machine operator, to simultaneously monitor both the detected base cutter height and the detected cutting resistance encountered by the harvester as it traverses a particular ground track, and, based upon such detected conditions, to automatedly control the adjustment of the height of the harvester chassis above the ground surface so that the cutting apparatus of the base cutter unit is continuously adjusted to cut at approximately the desired cutting height, within an acceptable vertical movement range or bandwidth, during the course of the harvesting cut operation.

The invention relates to a satellite orbit maintenance and control method based on two lines of radicals, which comprises the following steps of: calculating two lines of radical data disclosed by a satellite by utilizing a SGP4 orbit determination model, calculating and obtaining a geographical latitude and a geographical longitude of a sub-satellite point of the satellite and comparing with an agreed ground nominal track. Through taking the duration of a first sample opposite to an orbit epoch moment as an independent variable and taking the ground track distance difference as a variable, all samples are subjected to quadratic curve fitting by using an average method; the difference delta at between an actual value of a satellite orbit semi-major axis and a nominal value by a latest sample moment as well as the average attenuation rate of the satellite orbit semi-major axis within the time interval of the sample are calculated and obtained through a fitting polynomial coefficient; and finally, the next orbit control time Tc as well as the control quantity delta af required to be used are predicted and obtained by utilizing a fitted secondary curve and an allowable drift range [-delta Lmax and delta Lmax] to ensure that the position of an actual ground track within the satellite next drift period opposite to a ground nominal track is within the allowrable drift range.

In general, a constellation of spacecraft is used to broadcast to a particular region with high angles of view in order to reduce blockage or shadowing. A constellation of a plurality of spacecraft is placed in 24-hour orbits having inclination of about 550, eccentricity of about 0.32, semi-major axis of about 42,000 km, longitude of the ascending node of about 43° East, argument of perigee of about 270°, and longitude of the ground track at maximum latitude of about 7° East. The preferred number of spacecraft ranges from three to six. In a particular application of Digital Audio Broadcast to Europe in some embodiments, the most populous cities are provided with service from no more than about 10° from vertical, and broadcast takes place when the spacecraft are above at least 35° North latitude. The broadcast power is reduced during those portions of the orbit in which the ground track lies in the Southern hemisphere. (146)

The invention provides a navigation data processing method and system based on cloud computing. The method comprises the steps that ground tracking data of a medium and high earth orbit GNSS satelliteand GNSS satellite observation data of a low earth orbit satellite are acquired; distributed cloud computing is adopted to preprocess the ground tracking data of the medium and high earth orbit GNSSsatellite and the GNSS satellite observation data of the low earth orbit satellite; a first observation model from a ground station to the medium and high earth orbit GNSS satellite and a second observation model from the medium and high earth orbit GNSS satellite to the low earth orbit satellite are constructed according to the preprocessed data; linearization processing is performed on the firstobservation model and the second observation model according to preset parameter initial values; and a least square method is adopted to calculate the first observation model and the second observation model after linearization, and joint orbit determination parameters of the medium and high earth orbit GNSS satellite and the low earth orbit satellite are obtained. Through the navigation data processing method and system, an orbit of the low earth orbit satellite can be determined with high precision, joint orbit determination and time synchronization of the navigation satellite and the low earth orbit satellite are realized, therefore, real-time high-precision service is provided for a user, and system service performance is improved.

The AirScene™ Pavement Management System of the present invention automatically tracks data required to determine various factors in an assessment of current and future pavement maintenance needs and utilizes this data to quantify the pavement damage caused by each individual aircraft movement and thus compute pavement condition based on an initial survey and the calculations of accrued damage over time. This information can be displayed through AirScene™ in the form of tables, graphs, or graphically represented on an airport diagram showing present conditions, rates of accruing damage, and future wear rates and areas. The system draws on the data from the AirScene™ Data Warehouse (ADW), a single repository for all the information acquired from a number of different sources. These data include: Aircraft or vehicle type (wheel layout, weight, vehicle specific parameters, and the like), Aircraft or vehicle location (ground track, position, gate used, and the like), Aircraft or vehicle dynamics (velocity, acceleration, take off, touchdown, and the like), Aircraft or vehicle actual weight (cargo load, fuel load, and the like), as well as Future operational data (flight schedules, increasing flight loads and demand, and the like).

Provided are methods and systems for the disambiguation of an in trail procedure (ITP) vertical display by calculating and rendering symbology on a plan view traffic collision avoidance system (TCAS) display. The symbology represents an intersection point between the ground track of an ITP aircraft and the ground track of a blocking aircraft and further represents an association between the intersection point and the respective ITP blocking aircraft.

The invention discloses a method for determining an absolute orbit and a relative orbit of a formation flight satellite. According to the method, aiming at a formation flight task of equipment for measuring interstellar relative distance, an absolute orbit number and a relative orbit number of two formation satellites are obtained by resolving a relative measure value of the interstellar distance. The measure value of relative distance is only needed in the resolving process and a third-party signal source is avoided, so that a receiving party of the interstellar distance can separately determine the absolute orbit number and the relative orbit number of the formation flight task without support of a ground tracking telemetry and command station, a GPS (Global Position System) and other auxiliary equipment.

A new method of constellation design based on combining repeating ground tracks with common ground tracks and / or sun-synchronous orbits is used for performing high-precision change detection imagery for longer periods of time while minimizing battery usage. By precisely prescribing the orbital parameters, sharpened change detection images may be taken without the need to process out blurring by any special image re-working software. The relationship between the orbital parameters of the satellites is precisely tuned to the earth's rotation rate for the altitude of the satellites. The unique set of earth orbits minimizes satellite battery requirement while optimizing the ability to perform coherent change detection (CCD).

The invention discloses an autonomous orbit determination method for a satellite based on synthetic aperture radar, which belongs to the technical field of autonomous orbit determination of satellites and aims at achieving high-precision and real-time autonomous orbit determination of a low-orbiting satellite without being supported by a ground tracking telemetry and command station. The method comprises the following specific steps of: designing the shape and the material of a manual ground identification point; designing an arrangement mode of the ground identification point, arranging the ground identification point and measuring the position of the ground identification point in an earth-fixed coordinate system; storing information of the ground identification point in a space-borne computer; and after a space-borne synthetic aperture radar remotely senses the ground and identifies a ground identification, deriving the information of the ground identification point from a ground identification library on the satellite, applying an orbit determination equation to obtain the position and the speed of the satellite and further finish the real-time autonomous orbit determination of the satellite. The autonomous orbit determination technology for the satellite provides a novel autonomous orbit determination method for the satellite, which can be used for realizing high-precision real-time autonomous orbit determination of the low-orbiting satellite. The method disclosed by the invention is suitable for real-time autonomous orbit determination of a near earth satellite.

The invention discloses a remote sensing satellite space debris evasion maneuvering method based on ground-track keeping needs. According to an allowable ground track drifting range of remote sensing satellite on-orbit operation, a reference ground track keeping control ring is built, and is divided into different areas, and different maneuvering strategies are determined for a spacecraft according to the different areas, wherein, dangerous intersection possibly happens to the spacecraft, and the track maneuvering evasion space debris collision threat is needed to be carried out, so that the aim of avoiding the collision risk is achieved. According to the method, the ground-track keeping control ring is adopted to serves as the basis for generating the strategy, and the method is simple, efficient, easy to operate and particularly suitable for operation of space debris collision evasion with high timeliness; and the efficiency can be improved, time is saved, the valuable time is earned for space debris collision evasion, and satellite in-orbit operation safety is improved. Meanwhile, the influence of evasion maneuvering on a flying task of the spacecraft is reduced to the greatest extent, and the satellite space debris collision early warning and evasion capacity are improved.

The invention discloses a general multi-mode information processor for aircrafts based on software radio. The multi-mode information processor comprises a main control module, a radio frequency module, and a signal processing module. The main control module sends a relay mode selection instruction and a direct mode switching instruction to the signal processing module and the radio frequency module. The signal processing module and the radio frequency module load different executable programs and perform switching between different radio frequency channels according to the relay mode selection instruction, and support two types of relay satellites of different signal systems in carrying out relay communication. According to the direct mode switching instruction, direct communication between an aircraft and ground tracking telemetry control equipment or communication between an aircraft and a relay satellite is supported. The availability and robustness of the information processor are improved, the generality of the information processor is improved, and the development cycle is shortened.

The invention relates to a system and method used for acquiring and measuring running speed in a ground track field. The system includes a data acquisition device, a data transmission device and a data processing, display, storage and output device; the data acquisition device includes a laser range finder with a rotation angle sensor, a laser reflector arranged on the body of a measured athlete and a system control circuit. According to the system and method of the invention, a time of a movement beginning position point and a time of a movement arrival position point, distances from the movement beginning position point and the movement arrival position point to the rotation center of the laser range finder, and laser range finder rotation angles corresponding to the two positions are obtained through the laser range finder which rotates with the movement of the body of the athlete; a distance of a last movement position to the current movement position is calculated through using a cosine law algorithm; and the distance is divided by movement time, so that the speed of the athlete in the distance can be obtained. With the system and method of the invention adopted, real-time and accurate running speed of the athlete in curve and straight tracks in the ground track field can be obtained conveniently and quickly.

Methods and systems for automatically controlling aircraft takeoff rolls. A method in accordance with one embodiment of the invention includes receiving an indication of a target takeoff roll path for an aircraft, and automatically controlling a direction of an aircraft, while the aircraft is on a takeoff roll, to at least approximately follow the target takeoff roll path. The method can further include providing an input to a rudder of the aircraft and, upon receiving an indication of an engine failure, can transfer the input from the rudder to a rudder trim element. In still further embodiments, the method can include commanding a ground track angle when an airspeed of the aircraft reaches a threshold value, and maintaining the ground track angle as the airspeed of the aircraft exceeds the threshold value.

The invention discloses an optical guiding device and method. The device is composed of a guided device 1, an optical detecting unit 2 and a guiding light source 3; and according to the actual usage situation, an indicating light source or a video display module group can also be added. Therefore, problems of automatic navigation of a storage AGV trolley, walking path navigation of a robot, and navigation of a toy car can be solved. Compared with the conventional RFID wireless navigation, the optical guiding device and method have the following beneficial effects: a magnetic material is laid on the ground and ways like an active laser scanning type navigation way are employed; the guiding light source with the low cost and small size is used for realizing automatic guidance, so that lots of work for designing track lines on the ground is saved; and with the space advantages, the operating track can be changed flexibly based on needs. Compared with other automatic navigation method, the optical guiding device is easy to popularize.

The present invention discloses a stereowork quick slag-discharging method in mine excavation. It mainly adopts the following two modes: one is an operation mode for conveying carriage along the tunnel ground track by means of motor car and another is an operation mode for overhead traveling empty carriage by means of overhead traveling device of carriage in the air under the bow of tunnel.

A satellite system provides geosynchronous satellites in elliptical orbits in respective elliptical orbital planes separated by 120 degrees. The satellites traverse a common figure-eight ground track comprising northern and southern loops. The satellites are controllably switched to operate the satellite currently traversing the northern loop to deliver a selected signal (e.g., a selected frequency signal) to satellite receivers.

Disclosed is a system and method for displaying a Horizontal Situation Indicator (HSI) in which the track is projected along a forward direction, and the heading is displayed in a heading indicator that translates around the periphery of the compass card of the HSI, depending on the heading. The track is displayed at the 12:00 position of the compass card, which refers to the forward direction. The heading indicator includes a numerical display and an arrow, which points toward the center of the compass card. By displaying the HSI so that the track is at the 12:00 position, the pilot may guide the airplane along a ground track without having to mentally convert heading into track, thereby relieving the burden on the pilot.

A nano satellite remote-measuring and remote-controlling method capable of switching communication path relates to a satellite remote-measuring and remote-controlling processing method. Without increasing the cost and the complexity of the satellite, the ground also can remotely measure and control the satellite when a malfunction occurs on an on-board computer. In this method, through detecting whether the updating frequency and the communication of remote-measuring data sent by the on-board computer of a satellite system is normal or not, a ground tracking telemetry control station judges whether a malfunction occurs on the on-board computer or not; when a malfunction occurs, the ground tracking telemetry control station directly communicates with a plurality of sub-systems of the satellite through a measuring and controlling sub-system. The method provided by this invention is applicable to the remote-measuring and remote-controlling data transmission of the nano satellite.

The invention discloses an access authentication and key agreement protocol and a method of a special network for space-aeronautics-vehicle-ground tracks. An authentication system consists of a core network configuration authentication subsystem and a user access authentication subsystem, which completes authentication and key agreement between an airship and a security and operation guarantee center and authentication and key agreement between a user and the airship respectively. In view of the structure and communication characteristics of the special network for space-aeronautics-vehicle-ground tracks, a core network configuration subsystem is constructed. Authentication and key agreement between the airship and the security and operation guarantee center is completed with a public key password to get symmetric keys. Symmetric keys used between the user and the airship are mutually authenticated on the basis of an LTE protocol to get a session key. The problem on secure communication and key updating is solved. There is no need for an authentication center to participate in user access authentication and key agreement. The use of symmetric keys ensures light workload and high efficiency. The method is used in access authentication of airship, high-speed rail and trackside equipment users and key agreement, and ensures secure transmission of a wireless communication link from the user to the airship and to the security and operation guarantee center.

The invention provides a high-precision ground trajectory repetitive orbit optimization method and system. The method comprises steps of building a corresponding satellite orbit dynamics recursion model according to the analysis of a non-spherical perturbation order demand of an earth gravity field; giving a heavy rail interference orbit parameter under a J2 low-order gravity field according to ananalytic formula, and performing iterative calculation to obtain a correction parameter under J4 perturbation as an initial value of a high-precision ground trajectory repetitive orbit parameter adaptive setting algorithm; and according to the repeated track precision requirement, self-adaptive optimization setting of high-precision ground track repeated track parameters being carried out. The method solves problems that a traditional low-order gravity field orbit model is low in ground trajectory repetition precision, a high-order gravity field orbit model is high in nonlinearity, many in iterative correction parameters, incapable of being analyzed and solved and the like, and has more general engineering practicability.

An electronic device carrier (110) adapted for transmitting high-frequency signals, including a circuitized substrate with a plurality of conductive layers (240a to 240g) insulated from each other, the conductive layers being arranged in a sequence from a first one of the conductive layers (240a) wherein a plurality of signal tracks (200) each one ending with a contact area (205) for transmitting a high-frequency signal are formed, and a reference structure (215a, 215b, 230) connectable to a reference voltage or ground for shielding the signal tracks the reference structure includes at least one reference track (230) formed in a second one of the conductive layers (240b) adjacent to the first conductive layer and at least one further reference track formed in one of the conductive layers (240d) different from the first and second conductive layer, a portion of each signal track excluding at least the area corresponding to the orthographic projection of associated contact area being superimposed in plan view to a corresponding reference track and at least a part of the area corresponding to the orthographic projection of the contact area associated to each signal track being superimposed in plan view to a corresponding further reference track with interposition of a floating conductive track, i.e. a track not connected to any signal, reference voltage or ground track.

The invention discloses a self-walking large-width heavy take-up and pay-off machine and a take-up and pay-off method thereof. The self-walking large-width heavy take-up and pay-off machine comprises a ground track, a first movable lifting coiling device and a second movable lifting coiling device. The invention further discloses a take-up and pay-off method of the self-walking large-width heavy take-up and pay-off machine. The self-walking large-width heavy take-up and pay-off machine is reasonable and ingenious in structural design. Two movable lifting coiling devices are adopted and arranged on the ground track to move towards each other or away from each other, and correspondingly a wide wire coil is enabled to be clamped or released. The self-walking large-width heavy take-up and pay-off machine is free of limitation of the width of the wire coil and wide in application range, two bridge cranes are adopted to carry out independent load bearing, load bearing load and lifting load can be designed according to the size of the wire coil, the demand for the load bearing load and the lifting load of the wide wire coil is satisfied, and a tip cone lifting mechanism is capable of achieving automatic lifting motion. The self-walking large-width heavy take-up and pay-off machine is convenient to operate, time-saving and labor-saving, capable of lowering labor intensity, effectively improving work efficiency, simple in process, low in cost, prone to achieve, and capable of achieving motions of take-up and pay-off rapidly, evenly and continuously.

The invention provides a single-side hydraulic drive type stereoscopic frame parking stall and mainly solves problems that existing parking stalls occupy large areas and installation and operation are complicated. The single-side hydraulic drive type stereoscopic frame parking stall is characterized in that the cross section of a garage-shaped frame is in an h shape; traveling wheels are installed on lower portions of side edges and travel on the ground track; a lifting slewing device installed on a stand column frame comprises a slewing stand column, an upper slewing support and a lower slewing support, the slewing stand column is installed between the upper slewing support and the lower slewing support, the upper slewing support and the lower slewing support are fixed on an upper cross beam and a lower cross beam of the stand column frame respectively, and a hydraulic slewing driving device which drives the slewing stand column to slew is installed on one slewing support; and a lifting sliding sleeve driven by a hydraulic cylinder is sleeved on the slewing stand column, and a vehicle carrying table board is fixed at the lower end of the lifting sliding sleeve. The single-side hydraulic drive type stereoscopic frame parking stall has the advantages that by means of a frame type main body and single-side hydraulic drive, the stereoscopic frame parking stall is simple in structure.

A method and apparatus for operating an aircraft. The aircraft is flown at a constant bank angle in which the aircraft crosses an intended ground track for the aircraft. Information is identified about a wind using positions of the aircraft flying at the constant bank angle.