Verification of Roll Angle Estimation Performance of Slowly Rolling Guided Munition by Flight Experiment

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This paper presents methods and results of both flight test examining roll angle estimation performance of slowly rolling munition forced to spin in the air, and fabricating a replica of guided munition. Guided munition was deployed from multi rotor type UAV mother ship whose altitude and velocity was conveyed to it as initial state. Flight test scenario is composed of a sequence of munition drop(deployment), munition spin, roll angle estimation and stabilization. Munition was deployed from mother ship at around 200m high with horizontal velocity of 15m/s, and was made spun using internal reaction wheel. Performance analysis on roll angle estimation is provided in comparison with commercial aerospace graded GPS/INS. Moreover, several mechanisms that rotates munition using reaction wheel, and actual product that realizes one of them are introduced.
Publisher
KOREAN SOC AERONAUTICAL & SPACE SCIENCES
Issue Date
2020-09
Language
Korean
Article Type
Article
Citation

JOURNAL OF THE KOREAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, v.48, no.9, pp.681 - 689

ISSN
1225-1348
DOI
10.5139/JKSAS.2020.48.9.681
URI
http://hdl.handle.net/10203/281065
Appears in Collection
AE-Journal Papers(저널논문)
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