PROBLEM TO BE SOLVED: To provide an inertia navigation system of missile capable of reducing a margin of error in calculation of a nose direction, caused by sideslip.SOLUTION: An inertia navigation system of missile comprises: an inertia navigation device; an imaging device for imaging an image of ground; and a processing device 13 for calculating flight data based on the inertia data detected by the inertia navigation device and the image of ground imaged by the imaging device. The processing device 13 comprises: a flight data calculation part 21 for calculating flight data before correction, based on the inertia data; and a correction part 22 for correcting the flight data before correction, based on change of the images of ground imaged by the imaging device.
【課題】横すべりに起因する機首方向算出における誤差を低減した飛翔体の慣性航法システムの実現。【解決手段】慣性航法装置と、地上の画像を撮影する撮像装置と、慣性航法装置の検出した慣性データおよび撮像装置が撮影した地上の画像から、飛行データを算出する処理装置13と、を備え、処理装置13は、慣性データから補正前飛行データを算出する飛行データ算出部21と、撮像装置が撮影した地上の画像の変化から、補正前飛行データを補正する補正部22と、を有する飛翔体の慣性航法システム。【選択図】図2
INERTIA NAVIGATION SYSTEM OF MISSILE
飛翔体の慣性航法システム
2015-11-05
Patent
Elektronische Ressource
Japanisch
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