Verification method of a flight control system using a transportable wind tunnel
US5756891A · kind A · utility
Assignees
Inventors
Key dates
| Filing date | Nov 18, 1996 |
| Grant date | May 26, 1998 |
| Priority date | — |
| Expiry date | Nov 18, 2016 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01M9/06
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
A transportable three-dimensional calibration wind tunnel system consisting of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. When verifying a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and t…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.