公开(公告)号：JP2000356567A

公开(公告)日：2000-12-26

申请号：JP16615899

申请日：1999-06-14

Applicant: JAPAN SCIENCE & TECH CORP ,  NAT AEROSPACE LAB

Inventor： KIKUCHI TAKAO

IPC: G01M9/04 ,  G01M7/02

Abstract: PROBLEM TO BE SOLVED: To achieve pseudo sinusoidal wave vibration without using any advanced control rules and at the same time automatically change the average elevation of a wing model, the vibration amplitude, and the frequency by controlling three motors with a personal computer. SOLUTION: After the average elevation and vibration amplitude of a wind model connected to a hollow shaft 1 are initially set, an elevation-setting motor 11 is rotated. Then, a rotary pulley 10 and a rotary base 9 are rotated via a ball screw 14 and a slide plate 13, and an amplitude-setting motor 8 is rotated with the same rotary center as an amplitude-setting pulley 7 and the pulley 10. At this time, when the rotation of a vibration motor 6 and the amplitude- setting motor 8 is locked, a slide rod 3 is locked and a vibration pulley 2 is rotated, and the elevation of the wind model can be set via a hollow shaft 1. Also, when the rotary shaft of a rotary inclined plate 5 is inclined, the vibration motor 6 is rotated, the slide rod 3 is subjected to linear or rotary movement via the movement of a connecting rod 4, linear movement being taken out by connecting fitment 12 is converted into rocking movement via a steel belt, is transmitted from a hollow shaft 1 to a wing mode type, thus drawing a pseudo sinusoidal wave trace.

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.

公开(公告)号：JP2000230882A

公开(公告)日：2000-08-22

申请号：JP3121699

申请日：1999-02-09

Applicant: ISHIKAWAJIMA HARIMA HEAVY IND ,  NAT AEROSPACE LAB

Inventor： KOMI JUNSUKE ,  ITAHARA KANJI ,  YANAGI RYOJI

IPC: G01M9/06 ,  F01D25/00 ,  F02C7/04 ,  F02K9/96 ,  G01M15/00 ,  G01M15/14

Abstract: PROBLEM TO BE SOLVED: To lower the back pressure of a supersonic nozzle and to enhance a starting property without making the capacity and the size of a pump or an exhauster large. SOLUTION: In this semifree-jet testing apparatus, a supersonic diffuser 6 is connected to the exit part 2b of a supersonic nozzle 2 which takes into a supersonic airflow, The extrance part 10a of a subsonic diffuser 10 is made to communicate with the exit part of the supersonic diffuser 6. A turbo-engine 11 is connected to the exit part 10b of the subsonic diffuser 10. A cowl external bypass part 14 is formed on the side of a cowl 7a which becomes the surface of the supersonic diffuser 6. A cowl external bypass part 15 which changes the opening area of the cowl external bypass part 14 is equipped at the part.

公开(公告)号：JPH11177156A

公开(公告)日：1999-07-02

申请号：JP36362597

申请日：1997-12-16

Applicant: NAT AEROSPACE LAB

Inventor： NODA YASUTOSHI ,  KOU YASUO ,  MORIYA SHINICHI ,  SHINNO MASAYUKI

IPC: H01L35/14 ,  H01L35/34

Abstract: PROBLEM TO BE SOLVED: To enhance thermoelectric conversion characteristics by performing pressure deformation or extrusion plastic working of a fused or sintered thermoelectric semiconductor material while heating electrically. SOLUTION: A metal powder material 6 for one electrode of a thermoelectric conversion element, a sintered or fused mass of thermoelectric semiconductor material 5, and a metal powder material 6 for the other electrode are arranged sequentially on a punch 4 in the cavity 1 of a die 2. Punches 3, 4 are then pressed each other or one punch is pressed against the other thus compressing the powdery electrode material 6 and the semiconductor material 5. Under that state, a large current is fed between the conductive punches 3, 4 and hot working is performed. Alternatively, a punch 23 is pressed toward the outlet 24 of a die 22 to extrude the thermoelectric semiconductor material 5 while softening. In this regard, a large current is fed between the conductive punches 23, 22 to generate heat and the material is extruded by applying a pressure while controlling the working temperature.

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.

公开(公告)号：JPH10141662A

公开(公告)日：1998-05-29

申请号：JP30751296

申请日：1996-11-05

Applicant: NAT AEROSPACE LAB

Inventor： TAMARU TAKU ,  SHIMODAIRA KAZUO

IPC: F23R3/42 ,  F02K1/82 ,  F23R3/04

Abstract: PROBLEM TO BE SOLVED: To improve combustion efficiency and reduce emission of unburnt substances by providing a heat insulating material wall where a wall surface enclosing a combustion chamber is formed with a non-metal heat insulating material on an outer cylinder of the combustor, and providing an air passage in the heat insulating material wall, and further allowing desired air to pass through and be distributed into the combustion chamber from the air passage. SOLUTION: Heat insulating material walls 2, 2' are provided at a portion corresponding to an annular passage between outer cylinders 1, 1' of a gas turbine combustor 10, and a wall surface of the combustion chamber 3 is constructed inside therof. A fuel nozzle 5 and an air whirling unit 6 or a burner 7 are disposed at the center of a combustion chamber head part wall 4. Thereupon, the heat insulating material walls 2, 2' are mounted so as to have small gap passages 8, 8' between the outer cylinders 1, 1' whereby the outer cylinders 1, 1' and the heat insulating material walls 2, 2' are prevented from being raised in temperature. Further, there are provided air passages 11, 11' for feeding air into the combustion chamber 3 which are communicated with an air inflow inlet 12'. Hereby, high temperature of the combustion chamber 3 wall surface is endured, and the outer wall on the side of the outer cylinders 1, 1' is prevented from being overheated.

公开(公告)号：JPH10104115A

公开(公告)日：1998-04-24

申请号：JP25613696

申请日：1996-09-27

Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD

Inventor： ITO KATSUHIRO ,  MURAMOTO HAJIME

IPC: G01M9/04

Abstract: PROBLEM TO BE SOLVED: To reduce a sliding distance of a firing plug and a firing pipe, and increase moving velocity of the firing plug to improve acceleration performance of a piston by forming an expanded inner wall equipped with stages on an inner peripheral face of the firing pipe and by providing a flange having an outer diameter approximately similar to that of the expanded inner wall on an outer peripheral face of the firing plug behind a back seal face. SOLUTION: By providing an expanded inner wall 105 with stages 106 on an inner peripheral face of a firing pipe 101, when a firing plug 110 moves backward (leftward), a seal face 112 of the firing plug 110 immediately comes out of a sealed part 102, thereby reducing frictional force due to sliding. In addition, the stages 106 can reduce friction of a sealer. Further, by providing a flange 120 behind (on the left of) the firing plug 110, high pressure air flowing from an air blowout part 4 functions to improve acceleration of the firing plug 110. Therefore opening velocity of the blowout port 4 increases, thereby improving acceleration performance of the piston 5.

公开(公告)号：JPH10100086A

公开(公告)日：1998-04-21

申请号：JP27522096

申请日：1996-09-27

Applicant: NAT AEROSPACE LAB

Inventor： WAKABAYASHI SACHIKO ,  MATSUMOTO KOTARO

IPC: B25J13/00 ,  G05B9/02 ,  G05B23/02

Abstract: PROBLEM TO BE SOLVED: To efficiently incorporate the real time verification system in the remote operation system of highly reliable type by providing a keeping and delay mechanism of the remote operation command on the command side and the remote side. SOLUTION: Re-editing in processing inconveniences is performed referring to a command side keeping and delay mechanism 16, and the operation command in a remote side keeping and delay mechanism 18 which is not realized as a result of the re-editing is replaced by the new succeeding operation command. The operation command reaching the execution stage after elapse of the imaginary time delay on the command side is realized by transmitting the final execution command with the discrimination information of the operation command to the remote side. Thus, the time for collation and confirmation of transmission/reception of the remote operation command can be used as a part of or a whole of the imaginary time delay, and the real time verification and re-editing can be efficiently realized by the remote operation system of highly reliable type.

公开(公告)号：JPH1065222A

公开(公告)日：1998-03-06

申请号：JP23258396

申请日：1996-08-14

Applicant: NAT AEROSPACE LAB

Inventor： NODA YASUTOSHI ,  KOU ENSEI ,  TANJI YASUNORI ,  KUMAGAI TATSUO ,  SHINNO MASAYUKI ,  TADA YASUO

IPC: H01L35/08 ,  H01L35/14 ,  H01L35/16 ,  H01L35/26 ,  H01L35/34

Abstract: PROBLEM TO BE SOLVED: To enable a thermoelectric conversion device to be surely manufactured which is long in service life and high in reliability. SOLUTION: A sintered or a molten thermoelectric semiconductor material 4 is prepared. The material 4 and electrode materials 5 are pressed against each other and plasma-bonded together by applying a large current, whereby a thermoelectric conversion main body 11 formed of the material 4 and electrodes 12 are integrated into one piece for the formation of a thermoelectric conversion device 10.

公开(公告)号：JPH1010300A

公开(公告)日：1998-01-16

申请号：JP17867596

申请日：1996-06-20

Applicant: NAT AEROSPACE LAB

Inventor： HAYAKAWA YUKIO ,  KITAMURA MASAHARU

IPC: G21K1/00 ,  F03H1/00 ,  G21K5/04 ,  H01J27/02 ,  H01J37/08

Abstract: PROBLEM TO BE SOLVED: To prolong life and maintenance-free operation hour by making the shape of electrode hole ion screen electrodes non circuit and improving the circularity of the cross sectional shape of a charged particle beamlet. SOLUTION: A screen electrode 2 is fixed in a plasma generating chamber 1 and an acceleration electrode 3 is fixed by putting a spacer 5 in between. At this moment, the shift of electrode holes 6 and 7 in pairing electrodes 2 and 3, respectively, is not made excessive. The shape of the electrode holes 6(7) is chamfered hexagon and each electrode hole is arranged so that the apex (side) positions closest to adjacent electrode holed 6(7). Thus, the diameter of each electrode becomes maximum(minimum) at the closest point and minimum(maximum) at the mid point. In this manner, by making the electrode holes 36 and 7 be chamfered hexagon and making the apex or side be the closet point to adjacent electrode holes, the degree of circle of the charged particle beamlet is raised. As the results, the degree of wear on accelerating and decelerating electrodes on charged particle beamlet path due to impingement of the charged particles reduces.