THE EFFECT OF THRUST DIRECTION HISTORY ON DOWNRANGE IMPACT ERRORS ARISING FROM INERTIAL INSTRUMENT INACCURACIES.
AIR FORCE MISSILE DEVELOPMENT CENTER HOLLOMAN AFB NM
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Missile position and missile velocity as determined by inertial measuring devices are subject to errors due to imperfect measuring instruments and to initial misalignment. These errors in the indicated position and velocity at engine cutoff are related to range error through a linear equation. As a result, the contribution of a given type instrument error to the range error can be expressed as the sum of two integrals. The integrand of one of the integrals is a function of the direction of the thrust vector. For gyro associated errors, the corresponding range error can be reduced or eliminated by choosing the proper thrust direction history. Similarly, range errors resulting from accelerometer inaccuracies are significantly effected by the choice of thrust direction history. No general statement can be made about the selection of a thrust history to reduce all accelerometer associated errors. Author
- Surface-Launched Guided Missiles