公开(公告)号：JPS63282233A

公开(公告)日：1988-11-18

申请号：JP11419487

申请日：1987-05-11

Applicant: TOSHIBA TUNGALOY CO LTD ,  NAT AEROSPACE LAB

Inventor： TSUYA HIROKO ,  KOBAYASHI MASAKI ,  MATSUMOTO MASAAKI ,  NISHIMURA MITSURU ,  SEKI KATSUMI

IPC: F16C33/38 ,  C22C29/00 ,  C22C32/00 ,  C22C38/00 ,  C22C38/12

Abstract: PURPOSE:To develop a heat-resisting cage for rolling bearing excellent in wear resistance, by mixing a self-lubricative material which is composed principally of WS2 and in which WS2 is substituted, in part, by MoS2 or graphite with an alloy powder for binding phase having a specific composition and by subjecting the resulting powder mixture to press compacting and then to sintering. CONSTITUTION:At the time of manufacturing a heat-resisting cage for rolling bearing, a powder mixture consisting of, by weight, 10-90% binding phase composed of alloy and the balance WS2 as self-lubricative material is press- compacted and sintered at high temp. so as to be formed into the heat-resisting cage for rolling bearing. At this time, as the alloy for binding phase, a metal powder which is composed principally of at least one kind among alloys consisting of 50-95% of at least one element among W, Mo, Ta, Nb, Ni, Co, and Fe and the balance Cu and alloys consisting of 5-95% Mo and the balance Fe and in which the above-mentioned principal components are substituted by

公开(公告)号：JPS63248978A

公开(公告)日：1988-10-17

申请号：JP8179987

申请日：1987-04-02

Applicant: NAT AEROSPACE LAB

Inventor： HAYAKAWA YUKIO

IPC: F03H1/00

Abstract: PURPOSE:To improve the ion generating performance by arranging a magnet having a reduced dimension and weakened magnetism in close to the screen electrode side for attracting the positive ions generated from a positive electrode and weakening the lines of magnetic force in that part. CONSTITUTION:The xenon gas G which passed through a flow rate adjustor 3 is introduced into s neutralizer 6, and the electrons E for neutralization are emitted. The gas G which passed through a flow rate adjustor 4 is discharged as atoms A into an ion generating chamber 10 from a distributor 12 through an insulation device 7, and the gas G which passed through a flow rate adjustor 5 is allowed to emit atoms A, positive ions I and electrons E from a main cathode 9. The atoms A are ionized to generate positive ions I in the ion generating chamber 10, and the positive ions I are attracted by a screen electrode 15, and acceleration-transported by an accelerating electrode 16, and a propulsion force is generated. In this case, a magnet 14F which is closest to the screen electrode 15 among the magnets 14 arranged in the ion generating chamber 10 is used, with the reduced dimension and weakened magnetism in comparison with other magnets.

公开(公告)号：JPS6394130A

公开(公告)日：1988-04-25

申请号：JP23991686

申请日：1986-10-08

Applicant: NAT AEROSPACE LAB

Inventor： KIKUCHI TAKAO ,  KAYABA SHIGEO ,  SUZUKI SEIZO ,  MUROTA KATSUICHI ,  ANDO YASUYOSHI ,  SOTODATE MASATAKA

IPC: G01M9/00 ,  G01M9/04

Abstract: PURPOSE:To stop a test body from fluttering and to prevent the test body from being broken owing to excitation by a panel which has many ventilation holes while stood against an air flow at an upstream position of a test body support position in a wind channel. CONSTITUTION:The panel 1 consisting of the frame 3 and a wire gauge 2 is stood pivotally on the floor 6 of a blade model 7 at the upstream position in the wind channel. The panel 1 is laid face-down on the floor 6 first and the wind velocity in the wind channel is increased gradually. The signal of an accelerometer 8 mounted on the blade model 7 is monitored during this period and when the blade model 7 begins to flutter, a signal is sent out to an unshown panel driving device to raise the panel 1 speedily from the floor 6. An air flow is reduced in speed and rectified by the many ventilation holes of the panel 1 to stop the blade model 7 from fluttering. At this time, the disturbance of the air flow behind the panel 1 is small, so the blade model 7 never flutters owing to excitation after the stop of the fluttering.

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.

公开(公告)号：JPS6377356A

公开(公告)日：1988-04-07

申请号：JP21883086

申请日：1986-09-17

Applicant: NAT AEROSPACE LAB

Inventor： YAMADA HIROSHI

IPC: H02K19/08

Abstract: PURPOSE:To obtain a hysteresis motor having a large ratio of synchronizing torque to the moment of inertia of a rotor by constituting the rotor of a hysteresis ring consisting of a plastic hysteresis material and a universal core. CONSTITUTION:Plate-shaped support members 26, 27 composed of a non- magnetic material are fixed to a shaft 21, and a hysteresis ring 28 is fastened so as to cover the outer circumferential surfaces of the support members 26, 27. The surface of the hysteresis ring 28 and a stator core 11 are faced oppositely through an air gap g1. A 2-17 group rare earth plastic magnet having an axis of easy magnetization in the thickness direction is used as the hysteresis ring 28. A universal core 29 made up of a laminated core is mounted rotatably through an air gap g2 with the hysteresis ring 28 and the shaft 21 by bearings 30, 31 through an air gap g3. According to such constitution, the moment of inertia of a rotor is reduced extremely, thus increasing the ratio of synchronizing torque to the moment of inertia of the rotor.

公开(公告)号：JPS62270823A

公开(公告)日：1987-11-25

申请号：JP11238786

申请日：1986-05-16

Applicant: NAT AEROSPACE LAB

Inventor： MURAKAMI TSUTOMU ,  NAKAJIMA ATSUSHI

IPC: F16C32/04 ,  F16C39/06

Abstract: PURPOSE:To eliminate a non-modulation gap and facilitate design and control with simple construction using less number of electromagnetic coils by furnishing a rotor and a stator each having two yokes forming two sets of gap magnetic paths facing each other. CONSTITUTION:Flux PHI1 is passed from N to S pole of a permanent magnet 9 of a rotor 1. That is, from a gap magnetic path G1 via solenoid yokes 6, 7 of the stator, the flux PHI1 shall flow into a gap magnetic path G1. Then the flux PHI1 shall flow into the yoke 5 from the yoke 7 through a gap magnetic path G2 for returning to the S pole, and thereby magnetic attraction force is applied to said gap magnetic paths G1, G2 between the yokes 4, 6 and 7, 5. Displacement of the rotor 1 is sensed by a location sensor 13 for X axis, and current is allowed to flow in solenoids 12a, 12c to allow a flux PHI2 to flow in such a direction as to set off change of the attraction force of the flux PHI1 caused by the permanent magnet 9. Thereby the whole attraction force is balance, and the rotor 1 is restored to the neutral position as original.

公开(公告)号：JPS62232588A

公开(公告)日：1987-10-13

申请号：JP7638986

申请日：1986-04-02

Applicant: NAT AEROSPACE LAB

Inventor： YAZAWA KENJI

IPC: G01S1/14 ,  B64D45/08

Abstract: PURPOSE:To provide the same information as visual flight landing to a pilot even when an atmospheric condition is bad, by displaying a dummy runway at the same position as an actual runway using a head-up display. CONSTITUTION:The positional information of an airplane is obtained by a positional information measuring apparatus 1 comprising a landing aid apparatus or an altimeter on the ground and precise positional information is calculated from said information and a posture angle and inertia speed information, which obtained from an inertia sensor 2 comprising an inertia navigation device, by a precise position calculating and processing unit 3. A dummy runway is displayed on a dummy runway display device 5 using the half mirror of a head up display on the basis of said precise position information and said posture angle information by an image processing unit 4. By this method, a pilot 6 can see the dummy runway at the same position as an actual runway.

公开(公告)号：JPS6244645A

公开(公告)日：1987-02-26

申请号：JP18456785

申请日：1985-08-22

Applicant: NAT AEROSPACE LAB ,  RETSUKUSU KK

Inventor： HAYASHI SHIGERU ,  WATANABE SHINICHI

IPC: G01N15/02 ,  G01N21/49

Abstract: PURPOSE:To shorten a measurement time and to reduce the size of a measuring instrument by irradiating a group of sprayed particles with a laser beam, converting light scattered by the atomized particle group and photodetecting it by a photoelectric element, and calculating particle size instantaneously on the basis of a current signal obtained by the photoelectric element and displaying it digitally. CONSTITUTION:The laser beam irradiated by a laser beam oscillator 1 is collimated by a collimator lens 2 into parallel laser beam 3, which illuminates the group 3 of sprayed particles to be measured. An optical lens 5 is provided to converge light transmitted or scattered by the particle group 3 and photoelectric converting elements 6 and 7 are arranged concentrically at the focus position of the lens 5. Current signals from the elements 6 and 7 are amplified by logarithmic amplifiers 8 and 9 which have the same characteristics and inputted to a subtracting circuit 10. The output of the circuit 10 is inputted to a computing element 12 through an A/D converter 11 and the arithmetic result is displayed digitally on a display device 13. Thus, the measurement time is shortened and the size of the instrument is reduced.

公开(公告)号：JPS6151308A

公开(公告)日：1986-03-13

申请号：JP17248284

申请日：1984-08-21

Applicant: Nat Aerospace Lab

Inventor： MOTOE SHINJI ,  UEDA TOSHIO ,  KATO KENICHI

IPC: B28D5/02 ,  B28D1/22 ,  B28D5/00 ,  H01L21/304

公开(公告)号：JPS60160465A

公开(公告)日：1985-08-22

申请号：JP1746084

申请日：1984-02-01

Applicant: NAT AEROSPACE LAB

Inventor： WATANABE AKIRA ,  WAKAIRO KAORU

IPC: G06F9/46 ,  G06F9/52 ,  G06F15/16 ,  G06F15/17 ,  G06F15/177

Abstract: PURPOSE:To eliminate overhead loss time and to quickly and easily adjust a timing for interruption by supplying a clock of a clock signal generator as a synchronizing interruption signal through a delay circuit to each computer. CONSTITUTION:A master clockboard 20 is set in a computer to become a master of composite computers, while delay circuit boards 211-21n are set in each of slave computers. A period of the master clock is decided by the master computer and also the master computer works on activation of this clock. While the delay circuits 121-12n set in each slave computer are set by the computer of the optimum delay period needed by the computer.