8 results about "Instrument landing system" patented technology

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.

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.

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.

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 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.