Method for updating strapdown inertial navigation solutions based on launch-centered earth-fixed frame
US11578992B2 · kind B2 · utility
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Key dates
| Filing date | Apr 23, 2020 |
| Grant date | Feb 14, 2023 |
| Priority date | — |
| Expiry date | Mar 10, 2041 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG06F17/16
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
The present invention relates to a method for updating strapdown inertial navigation solutions based on a launch-centered earth-fixed (LCEF) frame (g frame). The present invention uses the g frame as a navigation reference frame of a medium-to-short-range surface-to-surface missile. This is beneficial to establish a relative relationship between the missile and the ground so as to keep the same missile parameters required by a missile control and guidance system. The calculation of a navigation algorithm in the g frame is moderate, which is suitable for an embedded system.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.