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.

Description

CROSS-REFERENCE TO RELATED APPLICATION(S) [0001] This application claims benefit under 35 U.S.C. § 119(e) to U.S. application Ser. No. 10 / 055,186, filed Jan. 23, 2002, entitled “Gyroscopic Navigation System and Method” (Attorney Docket No. 14143), the contents of which are incorporated herein in their entirety for all purposes.FIELD OF THE INVENTION [0002] The present invention relates generally to aircraft instruments, and more particularly, to a gyroscopic navigation system for a small aircraft's primary instruments, such as an attitude indicator (AI), a directional gyro (DG), and a turn coordinator (TC) / slip-skid indicator. BACKGROUND OF THE INVENTION [0003] All aircraft, large and small, production or experimental, depend on gyroscopes for a variety of navigational data. Most aircraft utilize mechanical or spinning-mass gyros to derive information, such as heading and attitude. Often housed in a remote location, an aircraft's gyro (or gyros) feed data back to a cockpit, which ar...

AI Technical Summary

Benefits of technology

"The present invention provides a standalone gyroscopic navigation system that can operate as a backup to the aircraft's primary vacuum and electrical systems in the event of failure. The system includes a high-performance solid-state gyroscope, a microcontroller module, and a display. It can provide key navigational information that is normally provided by the aircraft's primary instruments and can operate as a primary navigation system in the absence of the primary systems. The system is lightweight, compact, and easy to retrofit. It is also designed to withstand shocks of 1000 Gs or more and is battery-powered, making it a reliable and efficient solution for emergency situations."

Problems solved by technology

Loss of vacuum or electrical power, especially during instrument flight, renders these instruments useless and can result in pilot disorientation and, at times, fatal crashes.

However, the cost of having a second set of primary instruments is prohibitively expensive for a small aircraft.

In addition, a small aircraft is extremely sensitive to extra weight.

Further, cockpit size and instrument panel space are very limited in small aircraft.

However, the system is not user-friendly.

This increases pilot's cockpit management load, thereby reducing overall pilot awareness, which is considered dangerous in operating a small aircraft.

In addition, the Goodrich system is generally too heavy and too costly for a small aircraft.

Random noise are typically caused by characteristics of a device, such as the sensitivity of a sensor, etc.

However, due to the instability, gyro instruments can only hold for a certain period of time and then tend to drift back to a level position.

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