公开(公告)号：JPH0862091A

公开(公告)日：1996-03-08

申请号：JP21958194

申请日：1994-08-23

Applicant: NAT AEROSPACE LAB ,  NAT SPACE DEV AGENCY

Inventor： NAKATANI TERUOMI ,  OKAMOTO OSAMU ,  KUWANO NAOAKI ,  SUZUKI SEIZO ,  SASA SHUICHI ,  NAKAYASU HIDEHIKO ,  KOSAKA MASAKAZU

IPC: G09B9/00 ,  B64F5/00 ,  G01M9/02 ,  G01M9/06

Abstract: PURPOSE: To obtain a flight motion simulator for obtaining a compact three- dimensional air flow generator for generating a three-dimensional air flow which is similar to a wind tunnel, verifying and evaluating a flight control system for the change of an aircraft for air on the ground using the generator, and simulating flight motion due to the change for air. CONSTITUTION: A three-dimensional air-flow generator 1 is constituted of a compact wind tunnel part 2 for creating a three-dimensional air flow at an arbitrary wind speed and a two-axis angle deformation mechanism 3 for arbitrarily changing air-flow angle in conical motion with a nozzle blow-up port as a top at the wind tunnel part, the generator l is positioned at the tip of a polygonal truncated pyramid type Point tube type probe 50 provided at an active control aircraft 49 for air, and a three-dimensional air flow is generated to verify the flight control system for the change of the active control aircraft for air. Also, a three-dimensional air-flow generator and an air-flow sensor probe are provided at a flight motion simulator, thus simulating the flight motion based on the change for air.

公开(公告)号：JPH0858697A

公开(公告)日：1996-03-05

申请号：JP21958294

申请日：1994-08-23

Applicant: NAT AEROSPACE LAB ,  NAT SPACE DEV AGENCY

Inventor： NAKATANI TERUOMI ,  OKAMOTO OSAMU ,  KUWANO NAOAKI ,  SUZUKI SEIZO ,  SASA SHUICHI ,  NAKAYASU HIDEHIKO ,  KOSAKA MASAKAZU

IPC: G01P5/16 ,  B64C13/18 ,  G01P5/165 ,  G01P13/02 ,  G05D1/06 ,  G05D1/08 ,  G05D1/10

Abstract: PURPOSE: To quickly control the airspeed for the stabilization thereof by obtaining an airspeed vector for a change relative to the air on a real time basis for the supply thereof to a control system, and predicting a flight motion induced due to the change relative to the air. CONSTITUTION: This device has an air data sensor probe 1 formed out of polygonal truncated pyramid Pitot tube type probe, and an airspeed vector signal processor 2 calculates an airspeed vector on the basis of relative air pressure information detected with the probe 1. In addition, an airspeed vector signal is inputted to an onboard control computer 3 in parallel to a signal from each type of aircraft body movement detection sensor 4 and read into an air control system. Thereafter, a flight motion induced due to a change relative to the air is thereby predicted to generate a flight control rule for stabilizing the control of the airspeed.

公开(公告)号：JP2000275269A

公开(公告)日：2000-10-06

申请号：JP7782999

申请日：1999-03-23

Applicant: NAT SPACE DEV AGENCY ,  NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD ,  TOKYO AIRCRAFT INSTR CO

Inventor： KOSAKA MASAKAZU ,  SHIGEMI HITOSHI ,  INOKUCHI HAMAKI ,  ONO MASAHIRO ,  HATA TAKESHI ,  SAITO TAKASHI ,  ENDO MASARU

IPC: G01P5/16 ,  G01P5/17

Abstract: PROBLEM TO BE SOLVED: To measure stable air data extending over a wide range of angle of attack and angle of sideslip by mixing air data obtained by a plurality of computing parts by the use of prescribed weighting factor, and outputting them as air data. SOLUTION: A first computing part 5A obtains air data from the pressure of the vertex (total pressure) of a polygonal truncated pyramid 1 detected by a pressure detecting means 3 (pressure transducer) and pressure on the respective pyramidal faces (local pressure), based on the Newton-Lapson method. A second computing part 5B obtains air data based on pressure difference of the total pressure and the respective local pressure. A mixer 5C mixes the air data obtained by the first computing part 5A and the air data obtained by the second computing part 5B by the use of a prescribed weighting factor, and outputs them as air data. Namely, in the range of large angle of attack α and angle of sideslip β, the first computing part β A is used, and when the angle of attack αand the angle of sideslip p become in the vicinity of 0 deg., the second computing part 5B is used.