36 results about "General plan" patented technology

The invention relates to a flight vehicle pneumatic error model component hierarchical design method based on control demands. The method sequentially includes the steps that 1, parameters are collected in real time; 2, a pitching moment coefficient increment produced by pitching rudder deviation is obtained, and a pitching moment coefficient increment, a yawing moment coefficient increment and a rolling moment coefficient increment, produced by rolling rudder deviation, are obtained; 3, a pitching constant value item deviation, a pitching steerage item deviation, a pitching moment coefficient deviation induced by the rolling rudder deviation, a yawing constant value item deviation, a yawing stable item deviation, a yawing moment coefficient deviation induced by the rolling rudder deviation, a rolling constant value item deviation, a rolling stable item deviation and a rolling steerage item deviation are obtained; 4, a pitching moment coefficient deviation, the yawing moment coefficient deviation and a rolling moment coefficient deviation are established; 5, a three-level pneumatic error model is divided. According to the method, design difficulty of various subsystems can be balanced in overall design, general plan closing is quickened, flight test risk points are fully indicated, and references are provided for pneumatic error quantity value diminishing after a flight test.