Patent ID: 9242745
Filing Date: 2016-01-26
CPC Classification: B64G,F02K

Claim Text:
1. An orbit attitude control device, comprising: a pressure sensor configured to detect a pressure of a combustion chamber to generate a pressure detection value; a first axis acceleration sensor configured to detect an acceleration in a first axis direction as a first axis acceleration; a second axis acceleration sensor configured to detect an acceleration in a second axis direction as a second axis acceleration; a plurality of nozzles respectively having a plurality of valves and configured to emit combustion gas generated in said combustion chamber through said plurality of valves, whose opening degrees are controlled based on valve opening degree control values, and wherein said plurality of nozzles comprises a first couple of nozzles respectively having a first couple of valves and emitting the combustion gas in opposite directions along a first axis and a second couple of nozzles respectively having a second couple of valves and emitting the combustion gas in opposite directions along a second axis; a storage section configured to store an inertia model of an object whose orbit is controlled by said first couple of nozzles and said second couple of nozzles; and a control section configured to: