The invention discloses a BTT guidance control method for a near-space hypersonic flight vehicle. The guidance control method includes the steps that S1, a combined control model of a rolling channel and a yawing channel is established based on the aileron control quantity of the rolling channel, and a control model of a pitching channel is established based on the pitching control quantity; S2, a nonlinear state equation of BTT guidance is established based on the kinetic parameters of the flight vehicle, and the nonlinear state equation is transformed into a state-dependent linear-like structure; S3, by adopting a Riccati equation control method, a guidance law model of the rolling channel, the yawing channel and the pitching channel of the flight vehicle is obtained according to the state-dependent linear-like structure. The guidance control method solves the problem of multichannel cross coupling in BTT control of the near-space hypersonic flight vehicle and can meet the demand for high-precision control of the near-space hypersonic flight vehicle.