Design method of distributed adjustable TBCC air inlet channel flow control device

The invention discloses a design method of a distributed adjustable TBCC air inlet channel flow control device, and relates to aerospace. According to the requirement of a hypersonic aircraft, an adjustable inward rotating TBCC air inlet channel is designed, and an adjusting component of a binary structure is adopted to ensure that the structure is adjustable in rotation. In order to avoid the kick phenomenon of ending shock waves in the channel close to the inlet of the channel, distributed adjustable rotating plates are arranged on the adjustable upper wall face of the turbine channel, and communicated distributed adjustable rotating plates are arranged between the lower wall face of the turbine channel and the upper wall face of the stamping channel. The channels are controlled through pressure signals transmitted by pressure sensors arranged in the channels; opening and closing of the adjustable rotating plate are flexibly controlled through a pressure signal, a distributed sluice channel is formed to res