Concurrent, multi-sensor, multi-inertial navigation system flight emulation

Patent metadata

Field	Value
Publication number	US-11756433-B2
Application number	US-202117235564-A
Country	US
Kind code	B2
Filing date	Apr 20, 2021
Priority date	Apr 20, 2021
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

A flight emulation system receives global positioning system (GPS) data into one or more EGIs (embedded GPS/inertial navigation system (INS)) or GPS receivers from a GPS emulator. The GPS data are based on a pre-defined flight trajectory plan of an aircraft. The system calculates real-time positional, orientational, and inertial emulation data using outputs of the EGIs or GPS receivers and platform-specific, flight dynamics data, and then transmits the real-time positional, orientational, and inertial emulation data to one or more subsystems associated with the aircraft for use by operations of the one or more subsystems.

First claim

The invention claimed is:

1. A process comprising:
receiving global positioning system (GPS) data from a GPS emulator into one or more EGIs (embedded GPS/inertial navigation system (INS)) or GPS receivers, the GPS data based on a pre-defined flight trajectory plan of an aircraft;
calculating real-time positional, orientational, and inertial emulation data using outputs of the EGIs or GPS receivers and platform-specific, flight dynamics data; and
transmitting, based on subsystem destinations and message definitions contained in a configuration file, the real-time positional, orientational, and inertial emulation data to two or more subsystems associated with the aircraft for use by operations of the two or more subsystems.

2. The process of claim 1 , comprising:
dividing the GPS data into a plurality of data sets;
synchronizing time and position of the plurality of data sets; and
providing the synchronized plurality of data sets to the one or more EGIs.

3. The process of claim 1 , wherein the pre-defined flight trajectory plan includes a plurality of destinations comprising latitude, longitude, altitude, and speed that are used to emulate the GPS data for a particular test.

4. The process of claim 1 , wherein the pre-defined flight trajectory plan and the flight dynamics data reside in configuration files.

5. The process of claim 1 , wherein the flight dynamics data comprise equations or data tables that link aircraft orientation and inertial parameters to GPS positional data and GPS rate of change data.

6. The process of claim 1 , wherein the two or more subsystems comprise devices that rely on positional or inertial information for functionality.

7. The process of claim 1 , comprising concurrently transmitting the real-time positional, orientational, and inertial emulation data to the two or more subsystems.

8. The process of claim 7 , wherein the concurrent transmission of the real-time positional, orientational, and inertial emulation data simultaneously emulates the one or more EGIs.

9. The process of claim 1 , wherein the calculation of the real-time positional, orientational, and inertial emulation data using the outputs of the one or more EGIs or GPS receivers and the platform-specific, flight dynamics data comprises combining the real-time positional, orientational, and inertial emulation data with the flight dynamics data to calculate the positional, orientational, and inertial emulation data to transmit to the two or more subsystems.

10. The process of claim 1 , wherein the GPS data comprise radio frequency (rf) GPS data; and wherein the platform-specific, flight dynamics data are provided by a user.

11. A non-transitory computer-readable medium comprising instructions that when executed by a processor execute a process comprising:
receiving global positioning system (GPS) data from a GPS emulator into one or more EGIs (embedded GPS/inertial navigation system (INS)) or GPS receivers, the GPS data based on a pre-defined flight trajectory plan of an aircraft;
calculating real-time positional, orientational, and inertial emulation data using outputs of the EGIs or GPS receivers and platform-specific, flight dynamics data; and
transmitting, based on subsystem destinations and message definitions contained in a configuration file, the real-time positional, orientational, and inertial emulation data to two or more subsystems associated with the aircraft for use by operations of the two or more subsystems.

12. The non-transitory computer-readable medium of claim 11 , comprising instructions for:
dividing the GPS data into a plurality of data sets;
synchronizing time and position of the plurality of data sets; and
providing the synchronized plurality of data sets to the two or more EGIs.

13. The non-transitory computer-readable medium of claim 11 , wherein the pre-defined flight trajectory plan includes a plurality of destinations comprising latitude, longitude, altitude, and speed that are used to emulate the GPS data for a particular test.

14. The non-transitory computer-readable medium of claim 11 , wherein the flight dynamics data comprise equations or data tables that link aircraft orientation and inertial parameters to GPS positional data and GPS rate of change data.

15. The non-transitory computer-readable medium of claim 11 , wherein the two or more subsystems comprise devices that rely on positional or inertial information for functionality.

16. The non-transitory computer-readable medium of claim 11 , comprising instructions for concurrently transmitting the real-time positional, orientational, and inertial emulation data to the two or more subsystems;
wherein the concurrent transmission of the real-time positional, orientational, and inertial emulation data simultaneously emulates the one or more EGIs.

17. The non-transitory computer-readable medium of claim 11 , wherein the calculation of the real-time positional, orientational, and inertial emulation data using the outputs of the one or more EGIs or GPS receivers and the platform-specific, flight dynamics data comprises combining the real-time positional, orientational, and inertial emulation data with the flight dynamics data to calculate the positional, orientational, and inertial emulation data to transmit to the two or more subsystems.

18. The non-transitory computer-readable medium of claim 11 , wherein the GPS data comprise radio frequency (rf) GPS data; and wherein the platform-specific, flight dynamics data are provided by a user.

19. A system comprising:
a computer processor; and
a memory coupled to the computer processor;
wherein the computer processor and computer memory are operable for:
receiving global positioning system (GPS) data from a GPS emulator into one or more EGIs (embedded GPS/inertial navigation system (INS)) or GPS receivers, the GPS data based on a pre-defined flight trajectory plan of an aircraft;
calculating real-time positional, orientational, and inertial emulation data using outputs of the EGIs or GPS receivers and platform-specific, flight dynamics data; and
transmitting, based on subsystem destinations and message definitions contained in a configuration file, the real-time positional, orientational, and inertial emulation data to two or more subsystems associated with the aircraft for use by operations of the two or more subsystems.

Assignees

• Raytheon Co

Inventors

• Williams Brad S
• Taylor Thomas M

Classifications

• G05D1/101

  specially adapted for aircraft · CPC title

• G08G5/32

  for flight plan preparation · CPC title

• G08G5/30 Primary

  Flight plan management · CPC title

• G01C21/20 Primary

  Instruments for performing navigational calculations (G01C21/24, G01C21/26 take precedence) · CPC title

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title