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公开(公告)号：JPH11344413A
公开(公告)日：1999-12-14
申请号：JP15008198
申请日：1998-05-29
Applicant: NAT AEROSPACE LAB , KAWASAKI HEAVY IND LTD
Inventor： MIWA HITOSHI , HAYASHI YOSHIO , SHIKODA SHIGEKAZU , NAKAJIMA KATSUMI , YAGI EIICHI , YONEMOTO KOICHI , OGAKI MASANOBU
Abstract: PROBLEM TO BE SOLVED: To provide a dynamic stability testing apparatus for an aircraft, by which a dynamic stability differential coefficient regarding a rolling motion can be found precisely. SOLUTION: A driving motor 16 which is used to give a motion to an aircraft model 78 is provided. A conjugate cam unit 22 which is arranged and installed inside the aircraft model 78 is provided. A sting 20 which is used to support the conjugate cam unit 22 is provided. A driving shaft 24 which is supported to be freely rotatable inside the sting 20 is provided. The input shaft 36 of the conjugate cam unit 22 is driven by, and coupled to, the driving motor 16 via the driving shaft 24. The output shaft 38 of the conjugate cam unit 22 is attached to the aircraft model 78. A driving force from the driving motor 16 is transmitted to the aircraft model 78 via the driving shaft 24 and the conjugate cam unit 22. Thereby, a rolling motion is given to the aircraft model 78.
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2.发明专利
公开(公告)号：JPS6392242A
公开(公告)日：1988-04-22
申请号：JP23670186
申请日：1986-10-02
Applicant: NAT AEROSPACE LAB
Inventor： NAKATANI TERUOMI , HAYASHI YOSHIO , SUZUKI SEIZO
IPC: H02K15/16 , B23Q1/54 , B25J9/10 , B25J9/14 , F16C23/10 , G05D3/00 , H01L21/00 , H01L41/09 , H02K7/075
Abstract: PURPOSE:To enable an output shaft to be moved at three degrees of freedom and accomplish the positioning of a translational position and a rotational position at the same time, by combining a complex eccentric shaft rotor and an output shaft rotor with each other. CONSTITUTION:A motor-operated direct driving positioning apparatus is composed of a bearing base cylinder A, an external eccentric shaft rotor B, an internal eccentric shaft rotor C, and an output shaft rotor D. The external eccentric shaft rotor B and the internal eccentric shaft rotor C are independently rotated by a motor rotational-driving mechanism section, and by the combined rotational motion of the eccentric shaft rotors B and C, the translational motion of the output shaft rotor D inserted into the internal wall of the cylinder of the internal eccentric shaft rotor C is performed at two degrees of freedom on a level at the right angle to the shaft.
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Patent Agency Ranking
公开(公告)号：JPS5830673A
公开(公告)日：1983-02-23
申请号：JP12926481
申请日：1981-08-18
Applicant: NAT AEROSPACE LAB
Inventor： NAKATANI TERUOMI , HAYASHI YOSHIO
Abstract: PURPOSE:To measure the flow rate vectors of detection pressure and the static pressure at the same time by arranging a total pressure tube at the tip of a pyramidal trapesoid shaped Pitot tube type probe and also pressure hole on the pyramidal faces. CONSTITUTION:The tip end of a probe is formed by grinding a rod member at 45 deg. with respect to its axis 1 and the tip is provided with a shielding total pressure tube section (a) and each of the pyramidal faces with pressure holes 2a-2c. The total pressure section has a total pressure tube 3 positioned at a length L towards inside of a shielding hole 7 with diameter D, and the rod member is provided with partial flow holes 8a-8c which leak part of the pressure in the shielding hole. By means of the pressure tube 3' connected to the total pressure tube and the pressure tubes 4a-4c conncted to the pressure holes 2a-2c their pressure PH of the total pressure tube and the respective pressures P1-P3 of the pressure holes 2a-2c are measured, and flow rate vectors and static pressure are sought from the pressure PH and pressure differences PH-P1, PH-P2 and PH-P3.
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公开(公告)号：JPH11344414A
公开(公告)日：1999-12-14
申请号：JP15008298
申请日：1998-05-29
Applicant: NAT AEROSPACE LAB , KAWASAKI HEAVY IND LTD
Inventor： MIWA HITOSHI , HAYASHI YOSHIO , SHIKODA SHIGEKAZU , NAKAJIMA KATSUMI , YAGI EIICHI , YONEMOTO KOICHI , OGAKI MASANOBU
Abstract: PROBLEM TO BE SOLVED: To provide a dynamic stability testing apparatus, for an aircraft, by which a dynamic stability differential coefficient regarding a pitching motion or a yawing motion can be found precisely. SOLUTION: A driving motor 16 which is used to give a motion to an aircraft model 96 is provided. A three-dimensional cam unit 22 which is arranged and installed inside the aircraft model 96 is provided. A sting 20 which is used to support the three-dimensional cam unit 22 is provided. A driving shaft 24 which is supported to be freely rotatable inside the sting 20 is provided. The three-dimensional cam 36 of the three-dimensional cam unit 22 is driven by, and coupled to, the driving motor 16 via the driving shaft 24. The rocking member 38 of the three-dimensional cam unit 22 is attached to the aircraft model 96. A driving force from the driving motor 16 is transmitted to the aircraft model 96 via the driving shaft 24 and the three-dimensional cam unit 22. Thereby, a pitching motion or a yawing motion is given to the aircraft model 96.
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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：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：JPS6371629A
公开(公告)日：1988-04-01
申请号：JP21552886
申请日：1986-09-12
Applicant: NAT AEROSPACE LAB
Inventor： NAKATANI TERUOMI , HAYASHI YOSHIO , SUZUKI SEIZO
Abstract: PURPOSE:To reduce the weight of a model, to accurately separate the variation component of air force, and to obtain data on flight performance by disconnecting weight bodies of in-model high-pressure air supply piping, a pusher, a scale, and a model deformation mechanism part from a light airframe main body and providing them at specific positions of a rocking base plate. CONSTITUTION:The dynamic part in an air channel is divided roughly into the model main body A and a rocking device B. The model main body A consists of the airframe main body 1 and the rocking base plate 2 which supports the heavy bodies such as the airframe main body and the pushed, etc., and the rocking base 2 is supported on the rocking device B through a flexible joint, etc. The rocking base plate 2 is provided with a simulated jet turbine engine 3 through the air supply piping 5 and the model deformation mechanism part 4 and scale 6 are further fixed on the base plate 2. An internal frame 11 where the rocking base plate 2 is fitted is recessed in the airframe main body 1 and various small-sized, lightweight active controllers are provided at specific positions. The rocking device B consists of an alpha setting mechanism part 12 and alpha beta setting mechanism 13 for setting an elevation angle alpha and a yawing angle beta, front support piping 14, and rear support 15. Consequently, the variation component of air force regarding flight characteristics is accurately separated.
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