| 摘要 |
<p>PURPOSE:To reduce acceleration carried on an airframe to improve hit precision by selecting an optimum covariance of optimum system noise and observation noise from a Kalman filter covariance table according to measurement noise power with the use of a noise measuring instrument to set in a Kalman filter calculation part to estimate a degree of optimum target addition to add to the output of a proportional navigation calculation part. CONSTITUTION:A noise power measuring instrument 18 measures noise power containing a guide signal which is the output of a FFT circuit 13. A Kalman filter calculation part 15 performs Kalman filter calculation by the use of covariance selected from a covariance table 19 to estimate target acceleration so as to add to the output of a proportional navigation calculation part 14. In a receiver, optimum covariance is selected from a Kalman filter covariance table 19 according to noise power measured with the use of a noise measuring instrument 18 to set in the Kalman filter calculation part 15. Acceleration compensation type proportional navigation is realized by adding an estimation target acceleration to the output of the proportional navigation calculation part 14 to reduce acceleration carried on an airframe so as to improve hit precision.</p> |
