Multi-dimensional vibration control method for the model of strut tail-supported aircraft
US10969298B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 20, 2019 |
| Grant date | Apr 6, 2021 |
| Priority date | — |
| Expiry date | Sep 20, 2039 |
Classification
- Technology area (CPC H)Electricity
- CPC primaryH10N30/853
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
A multi-dimensional vibration control method based on piezoelectric ceramic actuator applied to wind tunnel test of aircraft model. The pitch and yaw acceleration sensors arranged on the center of mass of the aircraft model are used to measure the two components of the main vibration acceleration of the aircraft model, and the main vibration vector of the aircraft model is obtained and the real-time vibration plane of the strut is determined. Inertia is introduced to solve the dynamic bending moment on the active section of the multi-dimensional vibration damper, and then the stress distribution on the active section is obtained. The multi-dimensional active vibration control system is adopted to improve the stability and reliability of the active vibration control system of wind tunnel model, extend the service life of piezoelectric ceramic actuator, and ensure the quality of wind tunnel test data and the safety of wind tunnel test.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.