Flight control system and method of using piezoelectric modal sensors to mitigate flexible body dynamics
US7645970B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 15, 2007 |
| Grant date | Jan 12, 2010 |
| Priority date | — |
| Expiry date | Nov 1, 2027 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/107
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
A flight control system is provided with one or more modal sensors that are each configured to measure the rate and possibly acceleration for a flexible body mode of the flight vehicle. The modal sensor's rate and suitably acceleration are subtracted from the rate and acceleration measured by the IMU such that the values provided to the flight controller more closely represent only the rate and acceleration of the flight vehicle's rigid airframe component. A piezoelectric modal sensor is capable of sensing a particular flexible body mode over variations in the modal frequency without inducing additional phase loss in the control loop in order to maintain suitable phase and gain margins. Sensors are suitably provided for at least and possibly only the 1st lateral bending modes in the pitch and yaw channels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.