公开(公告)号：JPH10332728A

公开(公告)日：1998-12-18

申请号：JP15930097

申请日：1997-06-03

Applicant: NAT AEROSPACE LAB

Inventor： NAKATANI TERUOMI ,  KUWANO NAOAKI ,  NAKAMURA MASATAKE ,  HANZAWA ASAO

IPC: G01P5/175 ,  G01P5/165 ,  G01P13/02

Abstract: PROBLEM TO BE SOLVED: To enable acquisition of flying speed vectors with high accuracy and high speed even for flying in a wide speed range from low speed to supersonic speed and at a high attitude angle. SOLUTION: From five pieces of information detected by a truncated quadrangular pyramid type 5-holed probe 1, an elevation angle pressure coefficient Cα of air flow, an angle of side-slip pressure coefficient Cβ and an angle-to- airflow pressure coefficient Cγ are obtained, an arithmetic processing expression made of polynominal approximate expressions is constituted with these pressure coefficients and each pressure calibration coefficient according to Mach number M, an elevation angle α, and an angle of side-slip β of the above probe 1 per each speed range that a wide speed range stored in an arithmetic processor in advance is divided into a plurality, and the above pressure calibration coefficient in the speed range is called so as to calculate the flying speed vectors (M, α and β) with the above polynominal approximate expression.