4 results about "Instrument landing system" patented technology

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 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.