English to Russian Tech/Engineering Aerospace / Aviation / Space Прибор контроля датчиков

[0021] The method proceeds to 420 with executing a propagator-estimator configured with an aircraft model for a plurality of aircraft states based on an aircraft attitude state vector, a velocity state vector, a Sink Rate Error state vector, and a wind velocity state vector. In one embodiment, the aircraft model is implemented using the simple aircraft model 200 described above with respect to Figure 2. The time derivative of attitude vector “d/dt Attitude” may be calculated from a function of the aircraft present thrust, rudder positions, angle-of-attack, velocity and attitude. Present thrust, angle-of-attack and rudder setting may be collected from other aircraft systems and sensors. The second state vector time derivative “d/dt Velocity” is also calculated by the aircraft model as a function of the aircraft’s present thrust, rudder positions, angle-of-attack, attitude and velocity. A third state variable, referred to as the “Sink Rate Error” represents the uncertainty in the measured barometric sink rate. It should be appreciated that altimeter measurements produced from the aircraft’s barometric altimeter (air data unit) are not perfectly geometric representations of the aircraft’s altitude, but will also change depending on environmental conditions such as air temperature and local air pressure variations. As such, the derived barometric Sink Rate comprises a rate measurement that roughly represents true geometric changes in the aircraft’s altitude and the error in this measurement is modeled by the state vector Sink Rate Error. The fourth state vector derivative “Wind Velocity” is a wind velocity estimate representing the error in the measured True Air Speed obtained from aircraft sensors (air data unit). The propagator-estimator may be implemented using a Kalman filter or some variant or equivalent thereof. The method proceeds to 430 with generating measurement error residual values using a propagator-estimator, wherein the propagator-estimator is configured to iteratively predict and update the plurality of aircraft states of the aircraft model.

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