Guidance method of extended-range aircraft

The invention discloses a guidance method of an extended-range aircraft, which is characterized in that the extended-range aircraft needs to take off and launch at a large overload, and the large overload can cause the failure rate of an execution mechanism of the aircraft such as a steering engine to be increased, so that possible steering engine failure factors need to be considered in a guidance method of a terminal guidance section of the aircraft. On the basis of the self-adaptive sliding mode technology, a control rudder instruction is divided into a fault-tolerant guidance law instruction and a self-adaptive guidance law instruction, and then the condition of partial failure of a steering engine is adapted in combination with a self-adaptive parameter estimation value, so that the aircraft can be controlled to name a target according to a preset angle under the condition of partial failure of the steering engine. 本发明公开了一种增程飞行器的制导方法，所述增程飞行器需要大过载起飞发射，而大过载会导致飞行器的执行机构如舵机的故障率提高，为此该飞行器的末制导段制导方法需要考虑可能出现的舵机故障因