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135 条记录 (耗时 0.027 秒)

    Landing approach aids
    1.
    发明授权
    Landing approach aids 失效
    登陆方法艾滋病

    公开(公告)号：US3555897A

    公开(公告)日：1971-01-19

    申请号：US3555897D

    申请日：1969-06-27

    申请人： ELLIOTT BROTHERS LONDON LTD

    发明人： SLEIGHT GEORGE ROBIN

    IPC分类号： G01C23/00 ,  G01S1/02 ,  G05D1/06 ,  G01C21/06

    CPC分类号： G05D1/0676 ,  G01C23/005 ,  G01S1/02

    摘要： THE INVENTION RELATES TO AN AIRBORNE LANDING APPROACH AID FOR AN AIRCRAFT IN WHICH A SYMBOL PARALLEL TO AND DEPRESSED WITH RESPECT TO THE HORIZON IS PRESENTED ON A HEADUP DISPLAY. WHEN THE AIRCRAFT IS REMOTE FROM THE TOUCHDOWN POINT OF A RUNWAY THE LINE IS DEPRESSED BY THE GLIDE SCOPE ANGLE, NORMALLY 3*, WITH RESPECT TO THE HORIZON. TO ALLOW FOR ERRORS INTRODUCED BY THE DISTANCE BETWEEN THE PILOT AND THE MAIN LANDING GEAR OF THE AIRCRAFT THE ANGLE OF DEPRESSION OF THE SYMBOL VARIES WITH DISTANCE FROM THE TOUCHDOWN POINT OF RUNWAY SO THAT IT IS THE LANDING GEAR, AND NOT THE PILOT''S EYES, WHICH TRACK DOWN THE GLIDE SCOPE.

    Aircraft alignment systems
    2.
    发明授权
    Aircraft alignment systems 失效
    飞机对准系统

    公开(公告)号：US3552687A

    公开(公告)日：1971-01-05

    申请号：US3552687D

    申请日：1967-11-14

    申请人： ELLIOTT BROTHERS LONDON LTD

    发明人： HOWARD RONALD W ,  BISHOP GEOFFREY S

    IPC分类号： G05D1/02 ,  B64C13/18

    CPC分类号： G05D1/0204 ,  G05D1/0676

    摘要： The present invention is directed to providing at the output of a control integrator by the use of a yaw-rate gyro, a course deviation indicator (course deviation being the difference between runway heading and aircraft heading) and a feedback arrangement, a signal at the start of a terminal stage of landing, which accurately represents the course deviation, if any, then existing, and thereafter with the feedback arrangement inoperative, varying the output signal of the control integrator according to the output signal of the yaw rate gyro until a suitable kickoff or decrab altitude is reached. The feedback arrangement may be between the output and the input of the control gyro or between the output and the input of a means for synchronizing the control integrator to eliminate from the output signal thereof any component due to rate-gyro offset. In the first case, the feedback arrangement consists of a circuit providing a differentiator receiving an output signal from the course deviation indicator and the output signal of the control integrator, a feedback integrator receiving the differentiator output signal via a switch by means of which the feedback circuit can be disabled, and feeding its output signal to the control integrator which also receives the output signal of the yaw-rate gyro. When the feedback circuit is operative i.e. up to the start of the terminal stage, the differentiator serves to produce a differential signal if any undue variation occurs between the course deviation signal and the output signal of the control integrator, which differential signal is fed to the input of the control integrator so that the output signal thereof is slaved to the course deviation signal. In the second case, the synchronising means comprises an amplifier receiving the output signal of the yaw-rate gyro and producing a signal which is fed to the input of the control integrator which also receives the output signal of the course deviation indicator. The feedback arrangement comprises a feedback integrator and a switch by means of which the feedback arrangement can be disabled at the start of the terminal stage of the landing phase.