18 results about "Instrument landing system" patented technology

The invention relates to the technical field of radio testing, in particular to a radio comprehensive detector which comprises a main control part, an upper computer part and a radio frequency part. The main control part is composed of an MCU and an FPGA in a cooperative mode, the MCU communicates with an upper computer through a communication interface, and the FPGA is connected with the radio frequency part through a parallel bus and is provided with a PS mode program loading interface; the radio frequency part adopts a zero intermediate frequency software radio architecture and comprises a receiving channel and a transmitting channel; the upper computer part comprises a touch screen and is connected with the main control board through a communication interface, communication navigation signals of an airplane, a ship, a control tower and a satellite can be simulated, and function testing of 17 types of radio airborne equipment such as a short wave / ultra-short wave radio station, a microwave / instrument landing system and a radio altimeter is completed; the outfield maintenance targets of single-person carrying, single-person operation and single-person flying are achieved, and the universality, efficiency and environmental adaptability of maintenance are remarkably improved.

The invention discloses an instrument landing navigation method which comprises the following steps: firstly, constructing an ILS instrument landing system comprising a course beacon LOC and a glide beacon station GS, and accurately calculating a DDM modulation degree difference by adopting a normalization method; then, the system receives an intermediate-frequency 70MHz signal transmitted by the VOR navigation station, and noise and interference components in the signal are effectively removed through digitization and low-pass filtering processing; then, amplitude modulation and frequency modulation demodulation are carried out on the filtered signal, and a key 30Hz navigation signal is successfully extracted; by using the DDM and the 30Hz signal, the system performs zero-cross detection and accurately calculates the phase difference; and finally, according to the calculated phase difference, the system determines the VOR azimuth angle deviation degree of the aircraft relative to the VOR navigation station, and the flight direction of the aircraft is calibrated according to the VOR azimuth angle deviation degree, so that the navigation accuracy and the flight safety are effectively improved.

A system for determining an automatic landing path for an aircraft that can conduct automatic landings in many different scenarios. The system includes an aircraft landing controller, a network of sensing systems comprising a Global Navigation Satellite System (GNSS), an Instrument Landing System (ILS), and a vision sensing system, a processor, a communication device, and computer-readable memory. In operation, the system receives one or more radio signals from the ILS, one or more GNSS signals from the GNSS, and one or more vision sensor signals from the vision sensing system. The system evaluates, via the processor, the received signals to generate an aircraft landing profile indicative of the method of automatically landing the aircraft. The system transmits the aircraft landing profile to the aircraft landing controller. The system can provide automatic landings for any approach type including on runways without published instrument approaches.

The present invention discloses an electromagnetic simulation method and an electronic device for an instrument landing system, including the following steps: Step S100: Obtain the actual simulation area of the airport and the on-site environment of the actual simulation area, and construct an airport electromagnetic environment model; Step S200: Construct a finite-difference time-domain mathematical model according to the terrain within the preset range of the antenna; Step S300: Use the alternating direction implicit waveguide equation to construct an implicit-explicit step mathematical model for the far-source electromagnetic field, forming a tridiagonal equation; Step S400: Solve the finite-difference time-domain mathematical model and the alternating direction waveguide equation through a cloud computing platform to obtain the electric field value of the electromagnetic environment model; Step S500: Obtain the modulation difference through the electric field value. The simulation method of the present invention reduces the computational complexity, reduces the bandwidth pressure by reducing the data transmission between nodes, and enables ultra-large-scale electromagnetic simulation to operate efficiently with extremely high accuracy on the cloud platform.

A virtual synthesis and anomaly monitoring method for a glide slope deviation signal in an instrument landing system (ILS), comprising: generating a Gs glide slope deviation signal by means of the ILS (120); converting longitude / latitude / altitude data outputted by an INS and a satellite positioning system into longitude / latitude / altitude data fused by a Kalman filter (112); on the basis of the position of an aircraft and longitude and latitude coordinates of an airport Gs station and the altitude of the aircraft, calculating distance information between the aircraft and the airport Gs station (114); on the basis of the distance information, using a trigonometric function to calculate a virtually synthesized glide slope deviation signal (116); comparing the virtually synthesized glide slope deviation signal with the Gs glide slope deviation signal to determine whether the difference between the two exceeds a preset threshold (132): if not, determining that the Gs glide slope deviation signal is normal and selecting the Gs glide slope deviation signal for landing guidance (134); and if yes, determining that the Gs glide slope deviation signal is anomalous and selecting the virtually synthesized glide slope deviation signal for landing guidance (136).

The invention discloses a dual-master control device and method for an instrument landing system, and the device comprises a first master control unit, a second master control unit and internal equipment, and the first master control unit and the second master control unit are electrically connected through a first bus, and are electrically connected with the internal equipment through a second bus and a third bus. When the first main control unit is in primary use, the first main control unit acquires operation data of internal equipment through the second bus, interacts data with the second main control unit through the first bus, communicates with external equipment to receive an operation instruction, issue a control instruction and feed back state data, and is switched to be standby when a communication link is abnormal; when the first main control unit is standby, the second main control unit obtains data through the third bus, interacts data with the first main control unit, communicates with external equipment and issues a control instruction; and the internal equipment receives the instruction to output heading channel and glide channel signals. Through the dual-master control and dual-bus redundancy design, the reliability of the system is improved, non-stop maintenance is supported, and the flight safety is guaranteed.

The invention relates to the technical field of avionics, in particular to a real-time digital monitoring data processing method and device for a dual-frequency modulation signal. Processing a monitoring composite signal of the instrument landing system received by the front end of the receiver to obtain an attenuation processing analog signal; according to an ADC analog-to-digital conversion circuit, performing digital signal conversion on the attenuation processing analog signal to obtain a digital domain sampling signal; performing two-stage DDC orthogonal digital down-conversion processing on the digital domain sampling signal to obtain a baseband signal, a 90Hz component and a 150Hz component; extracting and sampling the baseband signal, the 90Hz component and the 150Hz component to obtain a direct current component sequence, a 90Hz component sequence and a 150Hz component sequence after synchronous downsampling; according to the direct current component sequence, the 90Hz component sequence and the 150Hz component sequence, a modulation degree difference DDM and a modulation degree sum SDM are obtained, and updating of real-time digital monitoring data of the dual-frequency modulation signals is achieved. And the accuracy of signal acquisition and the reliability of subsequent processing are improved.

The invention relates to the technical field of air transportation, in particular to an instrument landing system signal processing method and system based on an FPGA, and the method comprises the steps: receiving a course channel signal and a glide channel signal of an instrument landing system, and carrying out the radio frequency processing of the signals, thereby obtaining an intermediate frequency signal; performing analog-to-digital conversion on the intermediate frequency signal to obtain a corresponding digital signal, and performing rectification processing, multi-stage decimation filtering processing, band-pass filtering processing, amplitude detection processing and modulation degree difference calculation on the digital signal in sequence to obtain a modulation degree difference; finally, according to the modulation degree difference value, the deviation state of the airplane relative to the runway center line and the lower slide way center line is judged. According to the invention, the measurement precision of the modulation degree difference value is improved, the circuit complexity is simplified, the navigation error of the aircraft in the approaching and landing stages is effectively reduced, and the flight safety is obviously improved.

A system for harvesting electrical energy from wind currents produced at an airport is disclosed. The system comprises at least one bladeless energy conversion unit positioned within a jet blast catchment zone of an aircraft runway. The bladeless energy conversion unit captures kinetic energy from airflow produced by aircraft engine exhaust during take-off and landing operations, while the energy conversion means converts the captured kinetic energy into electrical energy. The bladeless energy conversion units may include oscillating vertical column turbines, multi-aerofoil oscillating turbines, enclosed blade turbines, and stationary wind energy capture devices, strategically positioned to minimize interference with airport communication systems while maximizing energy capture. The system incorporates a support structure with a frangible base section, and installation points are carefully selected to prevent signal interference with the Instrument Landing System. Comprehensive power management capabilities ensure seamless integration with airport infrastructure, while advanced monitoring systems maintain operational safety and efficiency.

The invention discloses an automatic approach control method based on a helicopter. The method comprises the steps that course signals of an instrument landing system and a magnetic course sensor are acquired, high-frequency jitter components in the signals are extracted, smoothing processing is conducted on the signals through a low-pass filter, and high-frequency interference is removed; according to the interaction model of the runway terrain and the rotor wake flow, dynamic characteristics of eddy current disturbance are analyzed, a mathematical expression of an eddy current disturbance propagation rule is constructed, and the change trend of disturbance intensity and direction is determined; an eddy current angle disturbance observer is introduced into the course control law, the influence of eddy current disturbance on course control is estimated in real time, and if the disturbance intensity exceeds a preset range, a periodic variable pitch compensation mechanism is triggered; and adjusting the amplitude and frequency of periodic variable pitch compensation by adopting a self-adaptive control algorithm, and if the crosswind condition changes remarkably, dynamically updating compensation parameters to offset course deflection torque caused by a ground effect.

1. Name of the design product: interlocking panel. 2. Use of the design product: the design is one of the components of instrument landing system, which ensures the interlocking of equipment under certain conditions, and guarantees the safety of operation and reliability of the system. 3. Design points of the design product: in shape. 4. Picture or photo that best indicates the design points: perspective view.

A virtual synthesis and anomaly monitoring method for a glide slope deviation signal in an instrument landing system (ILS), comprising: generating a Gs glide slope deviation signal by means of the ILS (120); converting longitude / latitude / altitude data outputted by an INS and a satellite positioning system into longitude / latitude / altitude data fused by a Kalman filter (112); on the basis of the position of an aircraft and longitude and latitude coordinates of an airport Gs station and the altitude of the aircraft, calculating distance information between the aircraft and the airport Gs station (114); on the basis of the distance information, using a trigonometric function to calculate a virtually synthesized glide slope deviation signal (116); comparing the virtually synthesized glide slope deviation signal with the Gs glide slope deviation signal to determine whether the difference between the two exceeds a preset threshold (132): if not, determining that the Gs glide slope deviation signal is normal and selecting the Gs glide slope deviation signal for landing guidance (134); and if yes, determining that the Gs glide slope deviation signal is anomalous and selecting the virtually synthesized glide slope deviation signal for landing guidance (136).

The present invention relates to the field of radio testing technology, and particularly relates to a radio integrated detector, comprising a main control part, a host computer part, and a radio frequency part; the main control part is collaboratively constituted by an MCU and a FPGA, the MCU communicates with the host computer via a communication interface, the FPGA is connected to the radio frequency part via a parallel bus, and is configured with a PS mode program loading interface; the radio frequency part adopts a zero intermediate frequency software radio architecture, including a receiving channel and a transmitting channel; the host computer part comprises a touch screen, and is connected to a main control board via a communication interface. The present invention can simulate communication and navigation signals of aircraft, ships, towers, and satellites, and complete functional tests of 17 types of radio airborne equipment, such as shortwave / ultra-shortwave radio stations, microwave / instrument landing systems, and radio altimeters, thereby achieving the field maintenance goals of single-person carrying, single-person operation, and single-person flight, and significantly improving the versatility, efficiency, and environmental adaptability of aircraft maintenance.

The invention discloses an aircraft landing auxiliary system based on a navigation aid lamp, relates to the technical field of aviation, and constructs an auxiliary system independent of a traditional instrument landing system (ILS) by deploying a sensor array to actively sense obstacles and combining aircraft position deviation delta G, thereby solving the problem of strong dependence on ground facilities and improving the aircraft landing accuracy. And the all-weather operation capability and the field adaptability of the aircraft are obviously improved. Meanwhile, the original data fusion and arbitration module of the system effectively solves the risk of'arbitration failure 'of multi-sensor data conflict by dynamically distributing the credibility weight omega, and ensures the high credibility of output information. The mechanism ensures absolute accuracy of a series of subsequent decision-making instructions such as a light flicker frequency index Sjpli generated based on the threat coefficient Wxxsi, a brightness control index Ldkzi and a final guidance alarm index Yjzsi, so that the fatal risk of wrong guidance is eradicated, clear and reliable visual warning is provided for pilots, and the system is suitable for popularization and application. And the security and robustness of the system are greatly enhanced.

This invention relates to the field of civil air traffic control system technology, and discloses a frequency domain measurement method for instrument landing systems based on software radio. The method includes the following steps: The digital baseband signal obtained from AM demodulation is divided into three frequency ranges using the CZT algorithm in the spectrum refinement algorithm for refinement analysis, resulting in three refined spectrum segments centered at 90Hz, 150Hz, and DC. By calculating the maximum value within each frequency range, the amplitude of the desired frequency is obtained, and then the modulation index and modulation difference are calculated. Compared with traditional time-domain demodulation methods and methods using Fourier transform, this method can effectively save hardware resources while better identifying the signal frequency domain amplitude.

The utility model discloses a centralized monitoring alarm device for an instrument landing system, which relates to the field of monitoring alarm, and is characterized in that a signal access circuit is used for accessing and processing alarm signals sent by navigation equipment in the instrument landing system; the power supply control circuit is used for controlling the working state of the alarm trigger circuit according to the output signal of the signal access circuit; the alarm trigger circuit is used for generating a control signal and controlling the alarm to give an alarm through the control signal; according to the utility model, centralized monitoring of each navigation device in the instrument landing system is realized, and when any device fails, an operator can be prompted rapidly through a remarkable sound-light alarm.

The application discloses an IRS / DME / LOC combined navigation method and a combined navigation terminal for a civil aircraft. k The IRS position is calibrated to obtain the aircraft position, and k=k+1 is set to jump to the first step for iteration; the application fuses navigation information output by an inertial reference system (IRS), ranging information output by a distance measuring equipment (DME) and a LOC modulation depth difference (DDM) output by an instrument landing system (ILS), and provides continuous and accurate positioning information for the aircraft in the approach phase of the aircraft.

The invention relates to the technical field of flight verification, and discloses an intelligent auxiliary debugging method and system for instrument landing system parameters, and the method comprises the steps: constructing a multi-dimensional coupling virtual state space and a standard working geometric polyhedron, and positioning a current equipment state vector based on flight verification original data; calculating a multi-dimensional displacement deviation with a target center, generating an initial suggestion adjustment vector in combination with the hybrid model, and performing simulation deduction to obtain a candidate adjustment strategy; after steady-state judgment and filtering in a hysteresis silence zone, packaging into an atomization execution instruction set, performing closed-loop verification after execution, and adaptively updating the hybrid model; according to the method, debugging deadlock is broken through virtual rehearsal and coupling adaptation, and steady-state operation of the system is guaranteed.