# US 10,482,783 B2 · Adaptive assistance for flight simulation

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- Number: US 10,482,783 B2
- Document ID: US10482783B2
- Status: Granted
- Kind: B2
- Application number: 15/339,231
- Filed: 2016-10-31
- Published: 2017-08-24
- Granted: 2019-11-19
- Earliest claimed: 2015-11-06
- Assignees: FRASCA International Inc.
- Applicants: FRASCA International Inc.
- Inventors: Glen Dimock
- Web page: https://patentgrep.com/patent/US10482783B2

## CPC

- G09B 9/46: the aircraft being a helicopter
- G09B 9/12: Motion systems for aircraft simulators
- G09B 9/24: including display or recording of simulated flight path
- G09B: EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS (devices for psychotechnics or for testing reaction times A61B5/16; games, sports, amusements A63; projectors, projector screens G03B)

## Abstract

A simulator assistance method and system adaptively mitigates Pilot Induced Oscillations (PIOs) with respect to axes of rotation about the vehicle's center of mass. The method detects PIOs in a body rate signal by band pass filtering the body rate signal, and provides an adaptive response based on the amplitude of the body rate signal within the frequency band.

## Claims

### Claim 1

A computer program product for use in an aircraft flight simulation training device, the computer program product comprising a computer readable medium having computer readable program code stored thereon, the computer readable program code including program code for
monitoring a simulated aircraft body rate signal with respect to at least one axis of rotation,
frequency decompositing the simulated aircraft body rate signal about at least one axis of rotation by band-pass filtering the body rate signal between a low-pass value and a high pass value to provide a filtered body rate signal in a preselected frequency band, calculating a gain coefficient as a function of the amplitude of the filtered body rate signal in which the gain coefficient is adaptive such that it decreases as the pilot progresses in a flight training maneuver, and
applying an artificial aircraft body rate damping coefficient based on the calculated gain coefficient to reduce the filtered body rate signal.

### Claim 2 (depends on 1)

The invention as in claim 1 wherein the aircraft flight simulation training device simulates movement of a rotary wing aircraft.

### Claim 3 (depends on 1)

The invention as in claim 1 wherein the monitoring step includes monitoring a simulated aircraft body rate with respect to pitch, roll, and yaw axes.

### Claim 4 (depends on 1)

The invention as in claim 1 wherein the monitoring step includes monitoring a simulated aircraft body rate with respect to surge, sway, and heave axes.

### Claim 5 (depends on 1)

The invention as in claim 1 wherein the low and high pass values typically bound the frequency of pilot induced oscillations that are encountered in simulated aircraft.

### Claim 6 (depends on 1)

The invention as in claim 1 wherein the gain coefficient is set as a constant value.

### Claim 7 (depends on 1)

The invention as in claim 1 wherein indication of the gain coefficient is displayed on a flight instrument panel.

### Claim 8 (depends on 1)

The invention as in claim 1 further comprising outputting an audible signal proportional to the gain coefficient.

### Claim 9 (depends on 1)

The invention as in claim 1 further comprising outputting a signal based on the gain coefficient to create a nudging force of appropriate amplitude and phase on the flight controls held by the pilot to emulate a corrective action.

### Claim 10 (depends on 1)

The invention as in claim 1 wherein the gain coefficient is adaptive such that it decreases as the pilot progresses in a flight training maneuver.

### Claim 11

A flight training method to reduce pilot induced oscillations during operation of a flight simulator for a rotary wing aircraft, comprising
monitoring a simulated aircraft body rate signal with respect to at least one axis of rotation,
frequency decompositing the simulated aircraft body rate signal about the at least one axis of rotation,
band-pass filtering the body rate signal between a low-pass value and a high pass value to provide a filtered body rate signal in a preselected frequency band,
calculating a gain coefficient as a function of the amplitude of the filtered body rate signal,
outputting a human discernable indication of the gain coefficient to a user, and
applying an artificial aircraft body rate damping coefficient in proportion to the calculated gain coefficient to reduce the filtered body rate signal.