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    DETERMINATION OF GUIDED-MUNITION ROLL ORIENTATION
    1.
    发明申请
    DETERMINATION OF GUIDED-MUNITION ROLL ORIENTATION 审中-公开

    公开(公告)号：WO2018128612A1

    公开(公告)日：2018-07-12

    申请号：PCT/US2017/012290

    申请日：2017-01-05

    Applicant: BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION, INC.

    Inventor： SCHORR, David J. ,  BATCHELDER, Jason H. ,  GIBSON, Jeremy B. ,  STEENSON JR., James H. ,  VASILE, Joseph D.

    IPC: F41G7/00 ,  F41G7/22 ,  F41G7/26 ,  F41G7/30 ,  F41G9/00 ,  F42B15/00 ,  F42B15/01

    Abstract: Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.

    GUIDED MUNITION SYSTEMS FOR DETECTING OFF-AXIS TARGETS
    2.
    发明申请
    GUIDED MUNITION SYSTEMS FOR DETECTING OFF-AXIS TARGETS 审中-公开

    公开(公告)号：WO2018111282A1

    公开(公告)日：2018-06-21

    申请号：PCT/US2016/067014

    申请日：2016-12-15

    Applicant: BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.

    Inventor： VASILE, Joseph D. ,  SCHORR, David J. ,  STEENSON, JR., James H.

    IPC: F42B10/62

    Abstract: Systems are disclosed for navigating a missile to a target using a fixed sensor onboard the missile. In an embodiment, a system includes a launch platform traveling a pre-programmed route to deliver the missile within an area. The missile travels a first flight path through the area in effort to detect targets. If no targets are detected along the first flight path, the missile transitions to a second flight path, different from the first flight path, to locate targets off-axis relative to the first flight path. While the missile travels the second flight path, the sensor receives signal identifying a target located at a position off-axis relative to the first flight path. The missile then adjusts the second flight path to direct the missile to the target. In an example embodiment, the first flight path is straight or arced, while the second flight path is u-shaped, corkscrew-shaped, or spiral-shaped.

    ORDNANCE NOSE CONE
    3.
    发明申请
    ORDNANCE NOSE CONE 审中-公开

    公开(公告)号：WO2021194564A1

    公开(公告)日：2021-09-30

    申请号：PCT/US2020/062847

    申请日：2020-12-02

    Applicant: BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC.

    Inventor： SCHORR, David J. ,  BATCHELDER, Jason H. ,  SPITSBERG, Richie ,  CLEVELAND, Kenneth D.

    IPC: F42B10/46 ,  F42B10/34

    Abstract: An ordnance includes a nose cone configured to be attached to a fuze or a warhead. The nose cone, when attached or coupled to the fuze or warhead, covers the fuze and at least a portion of the warhead to provide the ordnance with an aerodynamic profile. The nose cone has a shape that improves the aerodynamic profile of the ordnance as compared to ordnance that does not include a cover over the fuze. The improved aerodynamic profile enables the ordnance to achieve a greater range (approximately 20% or more) than ordnance that does not have a separate nose cone covering the fuze.

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