公开(公告)号：JPH09133605A

公开(公告)日：1997-05-20

申请号：JP31583095

申请日：1995-11-10

Applicant: NAT AEROSPACE LAB

Inventor： MINEGISHI MASAKATSU ,  ANDO YASUYOSHI ,  MATSUZAKI TAKETSUGU

IPC: G01M9/08 ,  G01M9/04

Abstract: PROBLEM TO BE SOLVED: To obtain a supersonic flutter stopping apparatus by which a flutter is stopped immediately so as to respond to the generation of the flutter at high speed and which can prevent an object to be tested from being damaged in the wind tunnel test of the object, to be tested, such as a wing model or the like in a supersonic region. SOLUTION: A flutter stopping plate 6 is installed at the front of an object 5, to be tested, so as to be capable of rising and laying down, and the flutter stopping plate 6 is normally maintained in a lain-down state against a spring 20 by a coupling device 7. Then, when a vibration amplitude sensed by a strain gage 8 reaches a set value set at a control device and the generation of a flutter is sensed, the coupling device 7 is operated, and the coupling of the flutter stopping plate 6 is released. Therefore, the flutter stopping plate is raised at high speed by the complex action of the spring 20 and a high-speed air current, and the flutter is stopped instantaneously.

公开(公告)号：JPH06148024A

公开(公告)日：1994-05-27

申请号：JP31555392

申请日：1992-11-02

Applicant: NAT AEROSPACE LAB

Inventor： ANDO YASUYOSHI ,  MATSUZAKI TAKETSUGU ,  MINEGISHI MASAKATSU ,  EJIRI HIROSHI ,  SAKAKIBARA MORIZO ,  NODA JUNICHI ,  SEKINE HIDEO ,  ISHIDA KIYOMICHI ,  TATE ATSUSHI ,  WATANABE MITSUNORI

IPC: G01M9/08

Abstract: PURPOSE:To prevent a cantilever wing model with a fixed part of 100% or less from being damaged by controlling fixing conditions of a supporter with vibration damper for supporting a free end of a wing base by a detection signal from a response signal detector of the wing. CONSTITUTION:A 50%-fixed delta wing model 5 which is a test piece is attached to a wing model fixing attachment block 4. A controller 11 controls a solenoid valve 9 by a response signal 13 from a distortion gage 8 which detects an output/input control signal 12 of the wing 5 or a response of the wing 5. A support arm 7 of a supporter 6 with vibration damper fixed to the block 4 moves in parallel or opens/closes by 180 degrees by activation of an actuator to support or make a free end of a wing base of the wing 5 free. The controller 11 frees the arm 7 only during experimental data measurement, while otherwise the wing 5 supports the wing 5 from both sides to prevent its damage. If a flutter occurs during data measurement, the arm 7 is actuated by the signal 13 so as to absorb fluctuation energy of the wing 5 by the damper to prevent the wing 5 from being damaged.