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公开(公告)号：JPH06119962A
公开(公告)日：1994-04-28
申请号：JP28821392
申请日：1992-10-05
Applicant: NAT AEROSPACE LAB
Inventor： OKAMOTO OSAMU , NAKATANI TERUOMI
IPC: H01R39/00
Abstract: PURPOSE:To provide a multi-stage slip ring device which can certainly supply electric energy and give and take electric signals to/from a rotor to be tested having a multiple rotary shaft or a single-axis rotary shaft rotating at a super- high speed and which is applicable to a rotation test device through positive rotating of the rotor tested. CONSTITUTION:Outside rotors 2 of a structure one stage of more are concentrically fitted between a stationary base 1 and an inner rotor 3 rotatably, and multipolar multi-contact slip ring mechanisms 9, 10 are provided between these rotors. A motor 15 rotates the outside rotors 2 relative to the stationary base 1, and the relative revolving speed of the inside rotor with the base is decreased.
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公开(公告)号：JPH0599943A
公开(公告)日：1993-04-23
申请号：JP28543791
申请日：1991-10-07
Applicant: NAT AEROSPACE LAB , TOKYO AIRCRAFT INSTR CO
Inventor： NAKATANI TERUOMI , EBIHARA MASAO , HAYASHI YOSHIO , SUZUKI SEIZO , KUWANO NAOAKI , HANZAWA ASAO , SAITO TAKASHI , USAMI MITSUO , IWATA TORU
Abstract: PURPOSE:To measure a speed accurately even in a low-speed region, wherein the changing rate of dynamic pressure is small, and to obtain aerodynamic data for the speed and the flying attitude accurately even under the conditions of cross wind and downwash. CONSTITUTION:A total-pressure pipe is arranged at the apex part of a multiple- pyramid trapezoid. A pressure hole is arranged in each pyramid surface. A Pitot tube 1 determines the velocity vector of flow and the static pressure based on the pressure received with the total pressure pipe and the pressure received with the pressure hole. A screening duct 10 is provided at the outer surface part of the pitot tube 1 so that a wind path 11 is formed and the tip of the duct is made to extrude slightly from the tip part of the Pitot tube. A suction-flow generating means for generating the suction flow in the axial direction is provided at a part close to the rear part of the screening duct 10. The wind flow is artificially generated in the duct at a low-speed region. Thus, the dynamic pressure is shifted, and the change is made large.
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公开(公告)号：JP2002326174A
公开(公告)日：2002-11-12
申请号：JP2002126392
申请日：2002-04-26
Applicant: NAT AEROSPACE LAB
Inventor： OKAMOTO OSAMU , NAKATANI TERUOMI , KAMIMURA HEIHACHIRO , YAMAGUCHI ISAO
Abstract: PROBLEM TO BE SOLVED: To allow smooth operation with simple route generation and high response speed even in an advanced articulated robot having complicated and accurate movement. SOLUTION: In this method of controlling the advanced articulated robot having complicated and accurate movement by an offset rotating joint, the operating area of an end effecter 3 is divided into a plurality of blocks B, and the operating conditions of the joints required to move to specified blocks are stored as a data base for each block. The teaching of operation points in the specified block area is stored as a data base. Up to the block of a working area, the route is created based on block area data. When the generation reaches the reference point of the block, working point data in the block is called to determine the operations of the joints.
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公开(公告)号：JP2001242190A
公开(公告)日：2001-09-07
申请号：JP2000049666
申请日：2000-02-25
Applicant: NAT AEROSPACE LAB
Inventor： SHIGEMI HITOSHI , NAKATANI TERUOMI , SHINDO SHIGEMI , TAKIZAWA MINORU , ONUKI TAKESHI
Abstract: PROBLEM TO BE SOLVED: To provide an arithmetic processing algorithm for accurately performing arithmetic processing of flight velocity vector for indicating the level of velocity and an air flow angle and a static pressure for indicating altitude with a high update rate, in a wide-speed region from low speed to ultra-high speed in a flight velocity vector measurement system, using Pitot tube of a quadrangular pyramid type five-hole probe. SOLUTION: In the arithmetic processing algorithm, an approximation expression for obtaining an elevation angle α and a side slip angle β is expressed by a third-order polynomial for an elevation angle pressure coefficient Cα having a known number and a sideslip angle pressure coefficient Cβ, and each coefficient is expressed by a polynomial expression up to fifth order, regarding Mach number that can be calculated from a look-up table, the coefficient of the polynomial expression and the elevation angle α and the sideslip angle β can be calculated through simple arithmetic processing, by instantly inputting a known number into the approximation expression for making specific, and the Mach number can be calculated instantly from the lookup table by making specific a Mach pressure coefficient CM and an air flow angle pressure coefficient Cγ, and at the same time a wide-speed-region flight velocity vector measurement can be executed with a high update rate.
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Patent Agency Ranking
公开(公告)号：JP2001138279A
公开(公告)日：2001-05-22
申请号：JP31933499
申请日：1999-11-10
Applicant: NAT AEROSPACE LAB
Inventor： OKAMOTO OSAMU , NAKATANI TERUOMI , KAMIMURA HEIHACHIRO , YAMAGUCHI ISAO
Abstract: PROBLEM TO BE SOLVED: To provide a high-functional articulated robot having an offset rotary joint of small and light construction and bearing a high torque and capable of making complicated and precise motions with a high payload, whereby track preparation can be made simply and smooth operations with quick response be performed even of the required motions are complicated. SOLUTION: A high reduction ratio transmitting and torque increasing mechanism is adopted to a rotation transmitting mechanism provided inside each joint of an offset rotary joint so that adoption of a small-sized motor is made practicable, and motion region of an end effector 3 is divided into a plurality of blocks B and the motion conditions of each joint required to make movement to the specified block are turned in database block while the instruction of working points in the specified block region is turned in database, and track preparation is made in the basis of the block region data till the block of the working region, and when the reference point of the block is attained, the intra-block working point data is called and the motion of each joint is decided.
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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
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.
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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
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.
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公开(公告)号：JPH05288761A
公开(公告)日：1993-11-02
申请号：JP11243492
申请日：1992-04-06
Applicant: NAT AEROSPACE LAB , TOKYO AIRCRAFT INSTR CO
Inventor： NAKATANI TERUOMI , EBIHARA MASAO , HAYASHI YOSHIO , SUZUKI SEIZO , KUWANO NAOAKI , HANZAWA ASAO , SAITO TAKASHI , USAMI MITSUO , IWATA TORU
Abstract: PURPOSE:To obtain a speed vector apparatus which can be actually mounted to an apparatus and which uses a Pitot tube-type probe in the shape of a frus tum of pyramid. CONSTITUTION:The pressure data detected by a Pitot tube-type probe 1 in the shape of a frustum of pyramid is input to a speed vector operator/processor 2 to convert to electric signals. By processing the signals with using a preliminarily obtained pressure coefficient of each hole to the speed vector, the dynamic pressure (q), angle of elevation, and yawing angle beta are calculated. the flying speed vector to the atmosphere is obtained by engaging the probe with a posture/azimuth reference device.
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公开(公告)号：JPH03182898A
公开(公告)日：1991-08-08
申请号：JP32033489
申请日：1989-12-08
Applicant: NAT AEROSPACE LAB
Inventor： NAKATANI TERUOMI , YANAGISAWA MITSUNORI , SUZUKI SEIZO
Abstract: PURPOSE:In a wing structure having steering planes on wing ends of an aircraft or the like, to improve the steering performance of wings by providing fin steering panes on both wing ends so as that steering hinge axes are arranged on or near main wing reference lines and symmetrical to the central axis of the aircraft body with a toe-out angle respectively, and enabling the active control with actuators provided in and out the wings. CONSTITUTION:Fin steering planes 3 are attached to both wing ends of main wings 2 of an aircraft 1 so as that steering hinge axes 4 are arranged on main wing reference lines respectively. And the steering hinge axes are provided on both wings symmetrically to the central axis of the aircraft body with a toe-out angle gamma. And the planes are driven with actuators to swing around the hinge axes 4, and can be controlled to obtain an arbitrary cant angle deltaCANT. Thereby the steering performance can be improved.
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