50 results about "Air data computer" patented technology

A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The controller communicating a heating cycle which defines a multiple of electric pulse trains to sequentially provides power to a multiple of heating elements in a designated blade set. Each electric pulse train is defined by an element on-time, a null time between the element on-time for this element and the next element, and an off-time between repetition of the heating cycle for the first heater element. The element on-time is a function of outside air temperature (OAT). The off-time is a function of liquid water content. The tail rotor heating cycle is a more straightforward version of the main rotor heating cycle as each of the tail rotor blade are activated simultaneously and there is only a single heating element on each tail rotor blade.

A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information, or in lieu of the ADC information when the ADC information is unreliable or unavailable.

A system and method are provided for calculating Mach number and true airspeed without reference to data from a pitot static sensor. The true airspeed and Mach number are calculated using the altitude information from GPS, IRS, Radio Altimeter and other onboard sensors other than the air data computer (ADC). The computed true airspeed or Mach number could be used to confirm the ADC information or in lieu of the ADC information when the ADC information is unreliable or unavailable.

An avionics system and process for detecting pneumatic blockages having an air pressure measurement system including a first sensor positioned in association with the air inlet of an air probe component. The air pressure measurement system having a second sensor positioned in association with the air inlet for detecting air pressure in which the second sensor has a frequency response higher than that of the first sensor. An air data computer is coupled to each of the first and second sensors being configured and operable to calculate a first aircraft movement measurement using detected air pressure from the first sensor and is further operative to determine if the first sensor is faulty or if the air inlet is blocked in dependence upon the frequency content and amplitude of the output from the second sensor.

A method of accounting for errors in the altitude reporting of a terrain alert and warning system (TAWS) is disclosed wherein errors due to non-standard atmospheric conditions, incorrect altimeter setting and air data computer (ADC) sensor error are detected and corrected for by compensating ADC altitudes for cold temperatures as well as using global positioning system (GPS) altitude data to confirm the accuracy of the ADC altitude information at all times.

The invention relates to an airborne wind speed measurement laser radar system. The system comprises a narrow-linewidth laser pulse light source module, a radar transceiving optical antenna module and a signal receiving and processing module. The narrow-linewidth laser pulse light source module comprises a narrow-linewidth seed light source, an optical fiber preamplifier, an acousto-optic modulator, a C-waveband boosting semiconductor optical amplifier and an optical fiber main amplifier. The radar transceiving optical antenna module is connected with the narrow-linewidth laser pulse light source module and comprises an optical fiber circulator, an optical switch and an optical antenna. The signal receiving and processing module is connected with the narrow-linewidth laser pulse light source module and the radar transceiving optical antenna module; the signal receiving and processing module comprises an optical fiber adjustable attenuator, an optical fiber beam combiner, a balance photoelectric detector, a signal processing circuit and an embedded computer. The airborne wind speed measurement laser radar system is reasonable in structural design and stable and reliable in use, can provide real-time wind speed data for an airborne atmospheric data computer, improves the performance of an airplane, and guarantees the flight safety.

The invention discloses a comprehensive avionics system for a small-sized general aircraft. The comprehensive avionics system comprises a comprehensive display, a data processing and interface computer and a sensor function module, wherein the comprehensive display is connected with the data processing and interface computer; the data processing and interface computer is respectively provided with the sensor function module, the sensor function modulecomprises an attitude heading unit, an air data computer, a GPS (Global Positioning System) navigation satellite receiver, an ultrashort wave radio, a multi-mode receiver, an air traffic-control responder, a motor parameter acquirer and an audio controller; the comprehensive display is connected with the data processing and interface computerthrough a high-speed data bus; and the data processing and interface computer is connected with the sensor function module through a point-to-point data bus. The comprehensive avionics system disclosed by the invention has the characteristics of high integration level, capability of improving flight experience, flexibility for configuration and extension, high reliability, low cost, and capability of meeting requirements of general aircrafts on comprehensive performances.