초록 ▼

A plurality of two-axis rate gyros are arranged in relation to an aircraft-fixed coordinate system such that they redundantly supply angular rate information. A plurality of accelerometers supply correspondingly redundant acceleration information. First signal processing means comprise means for fai

A plurality of two-axis rate gyros are arranged in relation to an aircraft-fixed coordinate system such that they redundantly supply angular rate information. A plurality of accelerometers supply correspondingly redundant acceleration information. First signal processing means comprise means for failure detection and elimination, such that angular rate and acceleration information subjected to error are eliminated. The angular rate and acceleration information thus cleared from errors supply stabilization signals for the autopilot. Second signal processing means obtain the angular rate and acceleration information cleared from errors and integrated if required, and therefrom supply heading and attitude reference signals.

대표청구항 ▼

An integrated, redundant reference system providing angular rate and heading and attitude information for the flight control of aircraft by means of an autopilot, comprising (a) at least four strap-down, dynamically tuned gyros, each of said gyros having a spin axis and two mutually orthogonal input

An integrated, redundant reference system providing angular rate and heading and attitude information for the flight control of aircraft by means of an autopilot, comprising (a) at least four strap-down, dynamically tuned gyros, each of said gyros having a spin axis and two mutually orthogonal input axes normal to said spin axis, the directions of said axes being defined by respective direction vectors, each of said dynamically tuned gyros providing two angular rate signals indicative of angular rates about said two input axes, (b) said gyros being oriented with the direction vectors of their spin axes extending radially with respect to a common reference axis, the direction vectors of said input axes of all gyros being different and located on a notional cone having a cone angle of 90°, the axis of said cone coinciding with said reference axis, (c) means equally operatively connected to all gyros for detecting deficiencies of said gyros and for eliminating signals from deficient gyros, the angular rate signals from all said gyros being supplied to said deficiency detecting and eliminating means, said deficiency detecting and eliminating means, in normal operation, providing a set of selected angular rate signals from operative gyros, (d) first signal processing means to which said set of selected angular rate signals is applied for providing a set of corrected angular rate signals referenced to a vehicle-fixed coordinate system, said corrected angular rate signals being applied to said autopilot for stabilizing said aircraft, and (e) second signal processing means to which said corrected angular rate signals are applied for providing heading and attitude reference signals.