Missile navigation method
US8242423B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 2, 2009 |
| Grant date | Aug 14, 2012 |
| Priority date | — |
| Expiry date | May 12, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF42B15/01
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
A missile has a pair of systems to provide acceleration information during flight. The primary system is a microelectromechanical systems (MEMS) inertial measurement unit (IMU) that provides accurate rate sensor output, such as providing pitch and yaw rates, at low cost, over a wide range of conditions. However MEMS IMUs are susceptible to temporary incorrect responses when subjected to shocks, such as acoustic-range shocks, for instance in the range of 10-20 kHz. The missile includes a secondary system to temporarily provide acceleration data during the periods following shocks, when the MEMS IMU does not provide valid (reliable or usable) rate sensor output, for use in estimating pseudo pitch and yaw rates. The secondary system may be an accelerometer that does not provide navigation-quality acceleration data, but does provide a sufficiently accurate response in order to maintain stable flight during the post-shock period.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.