公开(公告)号：US10371494B2

公开(公告)日：2019-08-06

申请号：US15357407

申请日：2016-11-21

Applicant: BAE SYSTEMS Information and Electronic Systems Integration Inc.

Inventor： David J. Schorr ,  Matthew F. Damiano ,  James H. Steenson, Jr.

IPC: F42B15/01 ,  F42B35/00 ,  F42B15/08 ,  G06F17/50

Abstract: Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.

公开(公告)号：US20180142997A1

公开(公告)日：2018-05-24

申请号：US15357407

申请日：2016-11-21

Applicant: BAE SYSTEMS Information and Electronic Systems Integration Inc.

Inventor： David J. Schorr ,  Matthew F. Damiano ,  James H. Steenson, JR.

IPC: F42B15/01 ,  G06F17/50 ,  G06F17/13 ,  F42B35/00

CPC classification number: F42B15/01 ,  B64C2201/027 ,  B64C2201/082 ,  F42B15/08 ,  F42B35/00 ,  G06F17/5086 ,  G06F2217/16

Abstract: Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.