An Approximation Algorithm of Gravity Anomaly along Flight Trajectory

doi:10.3969/j.issn.1000-1093.2018.12.010

Acta Armamentarii ›› 2018, Vol. 39 ›› Issue (12): 2363-2370.doi: 10.3969/j.issn.1000-1093.2018.12.010

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An Approximation Algorithm of Gravity Anomaly along Flight Trajectory

ZHOU Huan¹, DING Zhi-jian², ZHENG Wei³

(1.Institute of System Engineering, China Academy of Engineering Physics, Mianyang 621999，Sichuan, China;2.China Aerodynamics Research and Development Center, Mianyang 621000，Sichuan, China;3.College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073，Hunan, China)

Received:2018-01-09 Revised:2018-01-09 Online:2019-01-31

Abstract

Abstract: An approximation algorithm of gravity anomaly along flight trajectory based on the net function theory is proposed. The factors that affect the approximation precision are analyzed, and the approximated error is deduced. The impact point errors due to approximated errors for trajectories with different ranges, azimuth angles and launching points are calculated. The results show that an average approximated error and a consequent ballistic impact point error are controlled wthin about 10^-2 mgal and 8m, respectively, when memory space is about 1 000 data for a 12 000 km-range trajectory. The modest memory requirement and vastly decreased computational time allow the proposed method to apply to onboard computations of gravity anomaly along any trajectory. Key

Key words: ballisticmissile, gravityanomaly, fastapproximation, netfunction, impactpointerror

CLC Number:

V412.4⁺2

ZHOU Huan, DING Zhi-jian, ZHENG Wei. An Approximation Algorithm of Gravity Anomaly along Flight Trajectory[J]. Acta Armamentarii, 2018, 39(12): 2363-2370.

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第39卷第12期
2018 年12月兵工学报ACTA
ARMAMENTARIIVol.39No.12Dec.2018

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[2]	ZHOU Huan, DING Zhi-jian, ZHENG Wei. Optimization of Reconstruction Model for Gravity Anomaly along Glide Trajectory [J]. Acta Armamentarii, 2018, 39(12): 2371-2379.

An Approximation Algorithm of Gravity Anomaly along Flight Trajectory

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