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    AIRBORNE MISSILE LAUNCHER
    1.
    发明授权
    AIRBORNE MISSILE LAUNCHER 失效

    公开(公告)号：KR860000221B1

    公开(公告)日：1986-03-15

    申请号：KR820004172

    申请日：1982-09-15

    Applicant: GEN DYNAMICS CORP

    Inventor： OLDHAM DELBERT J ,  CARISH JOHN A

    IPC: F42B17/00 ,  F41F3/06

    Abstract: The launcher has a central support frame with attachment points that permit attachment to the aircraft or other launching platform. It has a central frame with a launch tube saddle-support assembly at each side of the frame, quick-detachable clamps and an alignment guide for quickly positioning and securing the launch tubes into position, auto connectors for automatically connecting the electronic control system and coolant gas to the launch tube assembly when the assembly is clamped into position. An aerodynamically shaped shell is used to enclose the support structure and the electronic control system.

    MISSILE
    3.
    发明授权
    MISSILE 失效

    公开(公告)号：KR810001576B1

    公开(公告)日：1981-10-27

    申请号：KR770001583

    申请日：1977-07-07

    Applicant: GEN DYNAMICS CORP

    Inventor： INGE MAUDAL

    IPC: F42B15/18

    Abstract: A missile steered by constant burning thrust reaction motors. These motors(24,30,32) are integral with the tail panels(20,26,28) of the missile to enhance the effect patricularly during the boost phase of flight. The motors provide thrust along the chord of the tail panel and are moved about the axis(22) of rotation of the tail panel(20) by the servo motor(34) associated with the tail panel(20). The servo motors(34,36,38) are activated by central missile control circuitry. Rocket steering of the missile at low speed is thus achieved with the minimum of complication and no extra control circuitry.

    ROLLING AIRFRAME AUTOPILOR
    6.
    发明授权
    ROLLING AIRFRAME AUTOPILOR 失效

    公开(公告)号：KR810001575B1

    公开(公告)日：1981-10-27

    申请号：KR770000345

    申请日：1977-02-16

    Applicant: GEN DYNAMICS CORP

    Inventor： COLE D

    IPC: F42B15/04

    Abstract: The autopilot incorporates a single linear accelerometer transducer and a single pitch rate sensor. The outputs are summed with the command signal in the control cct. A servo is controlled by the modified control signal to vary the incidence of a single plane control system, in an intentionally rolling airframe. The pitch angle control system are variable incidence canard surfaces, controlled by the output of the autopilot. Varying the incidence of the control surfaces produces lift on the control surfaces which rotate the body of the airframe in the control plane and causes the airframe to assume an angle of attack relative to the previous flight path.

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