Verification method of a flight control system using a transport

Details Verification method of a flight control system using a transport Verification method of a flight control system using a transport

1996-11-18

1998-05-26

Biegel, Ronald L.

Measuring and testing

Wind tunnel: aerodynamic wing and propeller study

738656, 244194, G01M 902, G05D 108

Patent

active

057568910

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 the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.

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