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：JPH05338595A

公开(公告)日：1993-12-21

申请号：JP27911592

申请日：1992-09-04

Applicant: NAT AEROSPACE LAB

Inventor： YAZAWA KENJI

IPC: B64D45/08 ,  G01S1/02

Abstract: PURPOSE:To correctly land with little burden to a pilot by providing a setting means to set a landing target marker on the simulated landing strip of HUD, a path angle computing means, an azimuth angle computing means, and a landing target marker moving means to move the display position of the landing target 7 marker based on the computed path angle and azimuth angle. CONSTITUTION:A landing target marker 23 is moved up and down, right and left, by means of marker moving switches 31, 32. At first, + or - of the differential value is selected by the switch 32 for moving a path angle alpha. A slant range D' from an aircraft to a landing strip is computed by an element 25 from the path angle alpha and the altitude Ha, the differential value is obtained by a computing element 26, and it is integrated to move the landing target marker 23 accompanying the aircraft, The difference DELTAPSI between the line connecting the landing strip azimuth PSIr and the landing point and the azimuth PSIa similarly changed to the differential value by the switch 31, integrated to obtain D by a computing element 24, and the differential value of DELTAPSIf is computed by a computing element 28. Hereby, PSIa is similarly moved right or left by the switch 31.

公开(公告)号：JPS60165685A

公开(公告)日：1985-08-28

申请号：JP2259284

申请日：1984-02-08

Applicant: NAT AEROSPACE LAB ,  KAWASAKI HEAVY IND LTD ,  SHIMADZU CORP

Inventor： YAZAWA KENJI ,  INAGAKI TOSHIHARU ,  TANAKA TAKASHI ,  SHIMIZU YUKIO ,  YAHIRO SHIZUMA ,  NAKATANI MITSURU ,  TOKUNAGA MASAHIDE ,  MORII KOUJI

IPC: G09B9/08 ,  B64D45/08 ,  B64F5/00 ,  G09B9/02 ,  G09B9/05 ,  G09B9/06 ,  G09B9/16 ,  G09B9/20 ,  G09B9/24 ,  G09B9/28 ,  G09B9/30 ,  G09B9/32 ,  G09B9/44 ,  G09B9/50