Gyroscopic navigation system and method

Abstract

A compact, lightweight, cost effective, self-contained standby electronic navigation system with high signal-to-noise ratio and good dynamic stability is provided. The system includes a first sensor module for providing a plurality of rotational rate signals, a second sensor module for providing a plurality of compensation signals, and a microcontroller module for processing the rotational rate signals and the compensation signals and sending the signals to a display for displaying attitude information, directional information, and turn coordinate information on a single screen simultaneously. In one embodiment, the first sensor module includes a plurality of rotational sensors made of piezoelectric elements. The piezoelectric elements are made from a single sheet of piezoelectric material so that the elements possess uniform characteristics, and are arranged to reduce systematic drift and random noise normally present in a rotational rate sensor. The sensors can be configured on a single multi-sensor chip.

1 - 40 . (canceled)  
   
   
       41 . A solid-state gyro for displaying gyroscopic navigational attitude information, direction information, and turn coordinate information simultaneously on a display, comprising: 
 a substrate having a proof-mass;    a membrane, the proof-mass being suspended on the membrane;    a common electrode layer being disposed on the membrane;    a sheet of piezoelectric material in a thin-film format being disposed on the common electrode layer; and    a plurality of electrodes being disposed on the sheet of piezoelectric material, the rotational rate signals being outputted through the electrodes, wherein each of the electrodes, the piezoelectric material, and the common electrode layer form a plurality of piezoelectric elements.    
   
   
       42 . The gyro of  claim 41 , wherein the piezoelectric elements are arranged -and configured in a circular shape with a plurality of pairs of piezoelectric elements, one element in a pair is disposed on an inner ring of the circular shape, and the other element in the pair is disposed on an outer ring of the circular shape.  
   
   
       43 . The gyro of  claim 42 , wherein the two elements of the pair have equal area.  
   
   
       44 . The gyro of  claim 43 , wherein each pair of piezoelectric elements has a mirror image pair of piezoelectric elements disposed on opposite side of an axis passing through a center of the proof-mass.  
   
   
       45 . The gyro of  claim 41 , wherein the piezoelectric elements are arranged and configured in an oval shape with a plurality of pairs of piezoelectric elements, one element in a pair is disposed on an inner ring of the oval shape, and the other element in the pair is disposed on an outer ring of the oval shape.  
   
   
       46 . The gyro of  claim 45 , wherein the two elements of the pair have equal area.  
   
   
       47 . The gyro of  claim 45 , wherein each pair of piezoelectric elements has a mirror image pair of piezoelectric elements disposed on opposite side of an axis passing through a center of the proof-mass.  
   
   
       48 . An aircraft instrument system, comprising: 
 a plurality of aircraft primary instruments including a mechanical attitude gyro, a mechanical directional gyro, a mechanical-electrical turn coordinator/slip-skid indicator;    a standby gyroscopic navigation system connected independently of the primary instruments;    electrical power having a primary power source and a battery power source, the primary power source supplying power to the primary instruments and the standby gyroscopic navigation system, the standby battery power source supplying power to the standby gyroscopic navigation system to provide attitude information, directional information, and turn coordination information when the primary power source fails; and    wherein the standby gyroscopic navigation system includes a solid-state gyro for displaying gyroscopic the attitude information, the directional information, and the turn coordinate information simultaneously on a display.    
   
   
       49 . The system of  claim 48 , wherein the solid-state gyro comprises: 
 a substrate having a proof-mass;    a membrane, the proof-mass being suspended on the membrane;    a common electrode layer being disposed on the membrane;    a sheet of piezoelectric material in a thin-film format being disposed on the common electrode layer; and    a plurality of electrodes being disposed on the sheet of piezoelectric material, the rotational rate signals being outputted through the electrodes, wherein each of the electrodes, the piezoelectric material, and the common electrode layer form a plurality of piezoelectric elements.    
   
   
       50 . The system of  claim 49 , wherein the piezoelectric elements are arranged and configured in a circular shape with a plurality of pairs of piezoelectric elements, one element in a pair is disposed on an inner ring of the circular shape, and the other element in the pair is disposed on an outer ring of the circular shape.  
   
   
       51 . The system of  claim 50 , wherein the two elements of the pair have equal area.  
   
   
       52 . The system of  claim 51 , wherein each pair of piezoelectric elements has a mirror image pair of piezoelectric elements disposed on opposite side of an axis passing through a center of the proof-mass.  
   
   
       53 . The system of  claim 48 , wherein the piezoelectric elements are arranged and configured in an oval shape with a plurality of pairs of piezoelectric elements, one element in a pair is disposed on an inner ring of the oval shape, and the other element in the pair is disposed on an outer ring of the oval shape.  
   
   
       54 . The system of  claim 53 , wherein the two elements of the pair have equal area.  
   
   
       55 . The system of  claim 53 , wherein each pair of piezoelectric elements has a mirror image pair of piezoelectric elements disposed on opposite side of an axis passing through a center of the proof-mass.