FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft guided missiles with differential control of control surfaces and can be used in aircraft ejection devices intended for hitting air and ground targets. Missile autopilot comprises linear acceleration and angular velocity transducers, control signal computing units, filtration units and control signal adders. Note that, additionally, autopilot incorporates units limiting rate of control signal variations in course and pitch channels and shaper of the said rate limiting value. Note here that first input of the unit limiting rate of control signal variations in course and pitch channels is connected to filtration unit output, while its second input is connected with the output of aforesaid shaper. Input of the latter is connected with roll angular velocity transducer, while outputs of the units limiting rate of control signal variations in course and pitch channels are connected to control signal adders.
EFFECT: higher flight stability and stabilisation system reliability.
1 dwg
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