66 results about "Instrument landing system" patented technology

A method for mapping an internal structure of a patient with an elongate body is provided. The method includes detecting, at a plurality of instances, contact between a distal portion of an elongate body and an internal structure of the patient; determining a plurality of geometric configurations of the distal portion, the plurality of geometric configurations corresponding to the plurality of instances of contact between the distal portion and the internal structure; determining a plurality of positions of the distal portion, the plurality of positions corresponding to the plurality of geometric configurations; and generating a map of the internal structure based on the plurality of positions of the distal portion.

A system and method of providing aerial navigation. Techniques are described for receiving global positioning system data, receiving local positioning system data such as instrument landing system data, generating a virtual target flight path using the global positioning system data and the local positioning system data, and presenting a virtual target flight path indicator corresponding to the virtual target flight path. In one implementation, the system includes a user interface, a global positioning component, a local positioning component, and a processing system.

An instrument landing system (ILS) provides signals in space receivable by an aircraft in flight to identify, for example, a point in space at which to start an approach along a glide slope path to a touchdown point on a runway. Atmospheric, ground and other conditions may cause transmission anomalies, so that the ILS signals identify a point in space displaced from its intended position. Systems and methods employed in flight use GPS or other positional data to determine the current displacement of such point, as identified by received ILS signals, from its intended position consistent with ILS specifications. In addition to reception and use of ILS and GPS signals, data on geographic runway location and correct ILS signal in space parameters is used for reference purposes in determining signal in space position discrepancies, glide slope path angular discrepancies, or both. The pilot can be alerted not to rely upon the ILS when discrepancies, which can vary on a short time basis and not be discernable from the ground, are determined to exceed safe limits.

A vision system is provided for confirming continuously updated approach information from a global positioning system or an instrument landing system with that from an inertial navigation system. The approach information from the inertial navigation system is displayed when the global positioning system or the instrument landing system is unavailable or whose approach information is determined to be invalid.

The invention relates to an on-line monitoring system of navigation equipment and a method thereof. The monitoring system comprises a test antenna, a GPS antenna, an antenna control module, a radio frequency acquisition and processing module, a signal analysis module and a central controller module. The test antenna is used for obtaining instrument landing system ILS / VHF Omnidirectional Range VOR spatial signals. The GPS antenna is used for receiving satellite signals. The antenna control module transmits signals received by the test antenna and the GPS antenna to the radio frequency acquisition and processing module. The radio frequency acquisition and processing module carries out filtering, demodulation and calculation on the received signals to obtain relevant parameter data and transmits the relevant parameter data to the signal analysis module. The signal analysis module analyzes the received data and transmits analysis results to the central controller module. According to the invention, accurate position measuring points of navigation channels can be determined, and measuring precision and accuracy of the on-line monitoring system of the navigation equipment are enhanced.

The invention discloses an aviation navigation signal simulation system applied to flight check, which mainly comprises a control computer, a multimode receiver, an aviation signal generator, an ARINC (Aeronautical Radio Incorporated) 429 bus, an emission antenna and a receiving antenna. According to the simulation models of various navigation signals under different flight procedures, the system utilizes a simulation system control program to control the aviation signal generator to generate various navigation signals; the navigation signals are sent out via the emission antenna so as to provide an analog simulation signal for the flight check system; and cost for researching, calibrating and maintaining the flight check system is lowered. The aviation navigation signal simulation system can better simulate navigation signals, such as ILS (Instrument Landing System), VOR (Very High Frequency Omnidirectional Radio Range), DME (Distance Measure Equipment), Marker and the like and has the advantages of low cost, beautiful interface and good stability.

The invention discloses a semi-physical simulation landing guide analog system based on a decimeter-wave instrument landing system. The semi-physical simulation landing guide analog system is characterized by comprising a ground equipment simulator for simulating a localizer, a glide-slope localizer and a ranging response signal of the decimeter-wave instrument landing system according to an instruction of the simulator and providing simulated angle information and distance information for airborne equipment, and an airborne equipment simulator for demodulating and decoding the simulated information sent from the ground equipment simulator and providing the simulated information to a flying control system. The semi-physical simulation landing guide analog system has the beneficial effects that the processes of navigation audio signal generation, angle beacon calculation and calibration, control and detection and the like are all digitalized; the ground equipment simulator adopts a digital pulse amplitude modulation mode for generating a simulated high angular resolution signal, and the airborne equipment simulator adopts a digital filtering mode and the like for effectively improving the calculating precision and the ranging precision of an angle localizer; the circuit multiplexing degree is high, the working process is stable and reliable, and the intelligentization, integration and miniaturization are realized.

An instrument landing system gliding line check system based on an unmanned aerial vehicle comprises an airborne system, ground facilities and the unmanned aerial vehicle. The airborne system comprises a FPGA (field programmable gate array) processing system, an airborne GPS (global positioning system) receiver, a wireless data transmission module, a course signal receiving unit, a gliding signal receiving unit, an A / D converter and a power source system, and the ground facilities include a ground monitoring station and a data transmission base station. Ground measuring equipment is adopted to improve inaccuracy of instrument landing system gliding line check, the gliding process of a real airplane guided by navigation signals is simulated through the fixed-wing unmanned aerial vehicle, and real-time gliding position information of the airplane is positioned through the airborne GPS receiver, so that the process when the real airplane approaches can be simulated, each index of gliding lines of an instrument landing system can be checked, testing programs are simplified, all testing check tasks can be completed by only one person, testing is more convenient and quicker, and a lot of expenditure and personnel consumption can be saved for primary check of equipment.

A method for managing a premature descent envelope during descent of an aircraft is provided. The method receives glideslope deviation data by an instrument landing system (ILS) onboard the aircraft; compares, by the ILS, the glideslope deviation data to an acceptable band of glideslope deviation values; and when the glideslope deviation data is within the acceptable band, expands, by a terrain awareness and warning system (TAWS), the premature descent envelope to produce an increased premature descent envelope for the aircraft.

The invention relates to an aircraft fixed point landing image guide method and a landing image system thereof. In the aircraft flight test process, a standard landing system is a microwave landing system, and simultaneously an instrument landing system and a radar approach control system are used alternately; the command of a ground commander plays a decisive role in success of fixed point landing of an aircraft in landing, and the command formation of the ground commander depends on the display information of a particular image on the ground; the time that the commander tells the display information of the particular image on the ground to a pilot lags, so that the pilot can not timely adjust the flight attitude, and thus each successful fixed-point landing can not be ensured. According to the invention, the information of the particular image on the ground is uploaded to an aircraft cockpit through wireless transmission, so that the pilot timely sees the observed image of the driven aircraft from a landing point, and timely adjusts the flight attitude according to the position of the aircraft in the image so as to ensure the successful fixed point landing each time.

A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.

The invention discloses a synthetic vision system calibration method based on an airborne instrument landing device. The method comprises the following steps: calibrating a synthetic vision system at an approach stage by adopting spatial angle information given by an instrument landing system as a reference system; determining a calibration sampling time, calibrating a single-time sampling number, and calibrating the threshold; acquiring a course surface included angle and a lower slide-way angle obtained by the synthetic vision and instrument landing system in real time in the approach process; calculating calibration statistics by adopting the acquired included angle data; carrying out the availability calibration for the synthetic vision system by utilizing the calculated calibration statistics. By adopting the method, the weakness of the traditional method for calibrating the airport characteristic synthetic vision display availability can be overcome, the capacity for calibrating the altitude or angle information situation of the synthetic vision system can be improved, and the calibration efficiency for the updating of the synthetic vision caused by little change of the altitude of an airplane in the calibration process can be improved; the practicability of the synthetic vision system at the approach stage can be effectively improved, and the security of the low altitude flight can be improved.

Systems and methods for performing localizer capture maneuvers are disclosed. In one embodiment, a method includes determining at least one instrument landing system (ILS) threshold of an aircraft, and establishing at least one final approach course (FAC) deviation threshold for the aircraft. The method further includes receiving at least one ILS localizer error, then calculating at least one FAC deviation. The at least one ILS localizer error is compared to the ILS threshold, and the at least one FAC deviation is compared to the FAC threshold. A standard capture maneuver is performed if the at least one ILS localizer error reaches its corresponding ILS threshold prior to the at least one FAC deviation reaching its FAC threshold. However, if the at least one FAC deviation reaches its corresponding FAC threshold prior to the at least one ILS localizer error reaching its corresponding ILS threshold, a modified capture maneuver is performed.

An unmanned aerial vehicle calibration system and method of an instrument landing system are provided. The calibration system includes a flight calibrating unmanned aerial vehicle and a ground station. The flight calibrating unmanned aerial vehicle includes an unmanned aerial vehicle main body and an unmanned aerial vehicle onboard device. The unmanned aerial vehicle main body is a remote-controlled multi-rotor flight vehicle. The unmanned aerial vehicle onboard device is mounted on the unmanned aerial vehicle main body. The ground station is a ground monitoring device. Beneficial effects of the calibration system and method are that calibration of communication and navigation signals of the instrument landing system in an aircraft approach process can be simulated, thus greatly increasing the calibration efficiency, saving the cost and making examination precision high; and equipment is light and portable, flight calibrating steps are simplified, and two persons can complete all calibration tasks, thus making flight calibration more convenient and rapider. The method can meet various flight calibration index requirements of a civil aviation airport on the instrument landing system, can replace traditional flight calibration manners, and can save a large amount of cost and personal for the airport. The calibration system and method are highly automatic and intelligent, and ensure accuracy of the instrument landing system as landing guides and indicators.

A system and method of monitoring received instrument landing system (ILS) signals onboard an aircraft includes performing a pre-approach sampling of the received ILS signals to thereby generate pre-approach phase ILS data. A statistical approach course of the aircraft is determined based at least in part on the pre-approach phase ILS data. A determination is made as to when the aircraft is below a predetermined activation altitude and, when it is, approach sampling of the received ILS signals is performed to generate approach phase ILS data. The approach phase ILS data is compared to the statistical approach course to determine a course deviation. An alert signal is selectively generated when the course deviation exceeds a predetermined magnitude.

Cockpit display systems and methods are provided for performing Glide Slope (G / S) validation processes during Instrument Landing System (ILS) approaches. In one embodiment, the cockpit display system utilizes validated G / S signals to selectively correct the viewpoint of a Synthetic Vision System (SVS) scene generated on a Synthetic Vision Primary Flight Display (SV-FPD). In such an embodiment, the cockpit display system may include an ILS receiver, a cockpit display device on which the SV-PFD is generated, and a controller operably coupled to the cockpit display device and to the ILS receiver. During an ILS approach, the controller selectively performs a G / S validation algorithm to determine the validity of the G / S signals received during the ILS approach. If determining that the G / S signals are valid, the controller then repeatedly updates the SVS viewpoint during the ILS approach based, at least in part, on the validated G / S signals.

The invention provides an approach section flight technology error estimation method based on multi-source information fusion. According to the method, the measurement information of main navigation sources of an aircraft in a current approach section is acquired, wherein the main navigation sources includes an inertial navigation system, a satellite navigation system and an instrument landing system; time registration and space registration are performed on the acquired measurement information; information fusion is carried out by taking federated filtering as a framework, different filteringmethods are selected according to the characteristics of the different navigation sources, and position information with relatively high accuracy is obtained; sensor fault detection is carried out, isolation processing is carried out on fault signals, and the integrity of signals is guaranteed; and finally, vector calculation is conducted on the due flight path of the aircraft and the position information of the aircraft obtained through filtering according to the position information of the aircraft, so that a flight technology error estimation value is obtained. With the method of the invention adopted, flight technology error real-time estimation can be realized; the precision of an estimation result is higher, and the precise approaching operation of the aircraft can be ensured.

The invention discloses a disturbance simulation method of an instrument landing system. The method comprises the following steps: S100, acquiring an actual simulation region of an airport and the site environment of the actual simulation region so as to construct an electromagnetic environment model of the airport; S200, constructing a parallel implicit local one-dimensional time domain finite difference mathematical model; S300, solving the parallel implicit local one-dimensional time domain finite difference mathematical model through a cloud computing platform to obtain the electric fieldvalue of the electromagnetic environment model; and S400, obtaining the difference in degree of modulation according to the electric field value. The disturbance simulation method of the instrument landing system, disclosed by the invention, lowers the complexity of computation, reduces the data transmission among nodes and reduces the bandwidth pressure, so that the instrument landing system canbe normally used on a cloud platform.

Instrument Landing System (ILS) Localizer and Glideslope Simulator Training Stations using GPS and LASER Position Identification for Active Antenna Feedback and Radiation Pattern Simulation is designed to provide complete training for ILS maintenance technicians using a unique combination of hardware and software. GPS and LASER modules embedded in simulated antennas define the physical position of the antennas and custom software coverts that position along with adjustable transmitter and RF Power, Modulation, and Phase distribution settings into a wireless digital data stream that emulates an actual ILS signal when viewed in the field by a custom designed simulated ILS field receiver. The overall system is monitored and controlled through a central processor. Simulated test equipment is provided to measure field readings and transmitter settings.

The invention provides an instrument landing system equipment flight verification result comparative analysis method. The method comprises the steps of data storage, flight verification parameter comparison, correlation analysis setting, equipment optimization suggestion, data visual presentation and data export. The invention relates to an instrument landing system equipment flight verification result contrastive analysis system. In the invention, historical parameters of a flight verification result of blind landing equipment can be automatically sorted, and a flight verification parameter fluctuation is calculated in a comparison mode to judge the stability of the equipment; flight verification parameters are automatically associated with set values of an equipment transmitter or a monitor; and through calculation and comparison of historical equipment transmitter or monitor set values, direct correlation data of a verification result and the equipment set values are obtained and visually presented in a chart or character form, equipment components causing equipment instability can be associated, equipment optimization suggestions are given, and equipment optimization is carriedout timely and efficiently.

Instrument Landing System ("ILS") localizer captures have historically been prone to performance degradations based upon erroneous estimates of the localizer deviation and deviation rate. The angular nature of the ILS beam and the relatively narrow trusted linear course guidance sector of the beam are the primary causes of many such issues. It is highly desirable to convert the angular guidance data into a rectilinear form when used by an autopilot and / or flight director systems, the latter of which allows for more consistent stability and performance with respect to distance to runway threshold. Systems and methods disclosed herein are for accurately converting angular localizer data into rectilinear localizer data, thus allowing for improved localizer capture performance and stability.

The invention belongs to the field of airplane navigation communication design and relates to an airborne instrument landing system data processing method based on software radio. The method comprises the following steps: 1, an AM demodulation module processing two digital baseband signals of a same-phase component sequence XI(n) and an orthogonal component sequence XQ(n) so as to obtain envelope signals A(n); 2, dividing the A(n) signals into four signals, obtaining 90Hz signals (i.e., A(n) signals) by subjecting one signal to a 90Hz filter, obtaining 150Hz signals (i.e., Z(n) signals) by subjecting one signal to a 150Hz filter, obtaining voice signals by subjecting one signal to a 300-3000Hz filter, and obtaining DC components by subjecting one signal to a DC component estimation module; 3, performing amplitude measurement on the X(n) signals and the Z(n) signals, wherein the amplitude measurement is performed by intercepting last one tenth of sampling points of a signal sequence; 4, respectively multiplying the 90Hz signals and the 150Hz signals by a coefficient square root of 2 so as to obtain corresponding amplitude output X' of X(n) as amplitude of the 90Hz signals and corresponding amplitude output Z' of Z(n) as amplitude of the 150Hz signals; and 5, according to the X', Y and the Z', obtaining a difference of depth of modulation needed for instrument landing through calculation.

A method for managing a premature descent envelope during descent of an aircraft is provided. The method receives glideslope deviation data by an instrument landing system (ILS) onboard the aircraft; compares, by the ILS, the glideslope deviation data to an acceptable band of glideslope deviation values; and when the glideslope deviation data is within the acceptable band, expands, by a terrain awareness and warning system (TAWS), the premature descent envelope to produce an increased premature descent envelope for the aircraft.

The invention, which belongs to the technical field of avionics display controlling, relates to a ground velocity measurement method based on an instrument landing system. According to vertical acceleration outputted by an attitude heading reference system, an aircraft height outputted by an air data computer / radio altimeter, and an airport altitude outputted by an aircraft management system, a vertical speed of the aircraft is calculated by complementary filtering; on the basis of a geometrical relationship, a ground velocity based on an instrument landing system is calculated; and then the ground velocity is filtered by using the acceleration along a runway direction to obtain a smooth available ground velocity. According to the ground velocity measurement method based on an instrument landing system, while the ground velocity that can not be outputted by the attitude heading reference system is calculated by using the vertical acceleration, the aircraft height, the airport height, the glide slope offset, and the reference glide slope angle comprehensively, noises caused by the glide slope offset are suppressed by acceleration complementary filtering, so that the obtained groundvelocity is smooth and has high integrity; and high-safety application like head-up flight guidance is supported.

The invention provides a flight precisely approaching and landing method and system. The flight precisely approaching and landing method comprises the steps that mapping and photographing in airport peripheral areas are carried out, and a three-dimensional virtual reality scene of VR equipment is established; a GNSS difference base station sends differential data to a differential data receiver onan aircraft through a broadcast mode in real time; an airborne GNSS navigation receiver obtains real-time positioning navigation data and differential data real-time summary received by a same differential data receiver, real-time position, elevation, flight speed and posture orientation of the aircraft are calculated and integrated into the established three-dimensional virtual reality scene ofthe VR equipment for scene matching; and in the process of aircraft approaching, the elevation, the flight speed and the posture orientation of the aircraft are observed and adjusted in real time to complete precisely approaching and safely landing of the aircraft. According to the flight precisely approaching and landing method, precisely approaching and landing of the aircraft under any visibility conditions can be realized, accurate measurement and control are achieved, and instrument landing system (ILS) CAT III of a civil aviation organization is completed.

A system for determining a region of interest for an imaging device based on instrument landing system (ILS) is provided herein. The system may include an imaging device attached to an aircraft; an ILS detector; a computer processor configured in to calculate in a line of sight between said aircraft and a planned touch down point, based on the received ILS signals; a touchdown positioning module executed by the computer processor and configured to calculate a position in a field of view (FOV) of said imaging device which represents the planned touchdown point, based on said line of sight; and a region of interest (ROI) module executed by the computer processor and configured to define a region of interest (ROI) of the imaging device based on said position in said FOV, wherein said computer processor is further configured to apply an image processing operation only to data within said ROI.

A remotely controlled simulative tester for the instrument landing system of airplane features that the working motherboard is connected to power supply unit, working unit, working state display unit, remote control signal processing unit, beacon system unit, direction system unit, and glide system unit, the RF signal coupling unit is connected to beacon system unit, course system unit, glide system unit and emitting antenna unit, the remote control signal receiving unit is connected to remote controll beacon processing unit, and the working control unit is connected to power supply unit.