CLC number:
On-line Access: 2024-08-27
Received: 2023-10-17
Revision Accepted: 2024-05-08
Crosschecked: 0000-00-00
Cited: 0
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Citations: Bibtex RefMan EndNote GB/T7714
Kai CHEN, Cheng-zhi ZENG, Sen-sen PEI, Wen-chao LIANG. Normal gravity model for inertial navigation of a hypersonic boost-glide vehicle[J]. Journal of Zhejiang University Science A, 2022, 23(1): 55-67.
@article{title="Normal gravity model for inertial navigation of a hypersonic boost-glide vehicle",
author="Kai CHEN, Cheng-zhi ZENG, Sen-sen PEI, Wen-chao LIANG",
journal="Journal of Zhejiang University Science A",
volume="23",
number="1",
pages="55-67",
year="2022",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2100133"
}
%0 Journal Article
%T Normal gravity model for inertial navigation of a hypersonic boost-glide vehicle
%A Kai CHEN
%A Cheng-zhi ZENG
%A Sen-sen PEI
%A Wen-chao LIANG
%J Journal of Zhejiang University SCIENCE A
%V 23
%N 1
%P 55-67
%@ 1673-565X
%D 2022
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2100133
TY - JOUR
T1 - Normal gravity model for inertial navigation of a hypersonic boost-glide vehicle
A1 - Kai CHEN
A1 - Cheng-zhi ZENG
A1 - Sen-sen PEI
A1 - Wen-chao LIANG
J0 - Journal of Zhejiang University Science A
VL - 23
IS - 1
SP - 55
EP - 67
%@ 1673-565X
Y1 - 2022
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A2100133
Abstract: The normal gravity model of a hypersonic boost-glide vehicle in near space is studied in this paper with the aim of alleviating the influence of the gravity model error on the precision of the inertial navigation system (INS) during flight. First, a spherical harmonic model of the Earth’s gravitational field is introduced and the normal gravity of the Earth is derived from it. Then, the coordinate transformation needed for the application of the gravity model to the near-space navigation algorithm is formulated. Subsequently, the gravity disturbance in near space and the impact of J2 and J4 gravity truncation errors are analyzed. Finally, different normal gravity models and different precisions of inertial measurement unit (IMU) are exploited to simulate the near-space navigation algorithm. Based on this, the influence of the independent and combined effects caused by the interference factors is analyzed, and the applicable conditions of the normal gravity model are discussed.
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