This paper proposes an Incremental Nonlinear Dynamic Inverse (INDI) control scheme for the problem of transition mode control of Tilt Rotor Unmanned Aerial Vehicle (TRUAV). Firstly, based on the dynamic characteristics of the quadrotor TRUAV, a longitudinal motion model suitable for control is established. Then, the virtual control command and control allocation methods are studied, and an adaptive tilt scheme for the transition mode of the TRUAV is designed based on these methods. Subsequently, based on the incremental nonlinear dynamic inverse control theory, the inner/outer loop controllers for the altitude, velocity and attitude transition modes are designed, as well as a mixed control method for rotor and rudder deflection control quantities. Finally, simulation experiments validate the effectiveness of the adaptive tilt scheme based on virtual control command allocation, as well as the robustness of the altitude, velocity, and attitude controllers.

Under hypersonic flight conditions, the residence time of fuel in the scramjet combustor is extremely short, while sufficient mixing, ignition, and stable combustion of fuel and oxidants are important issues for hypersonic propulsion. To improve the mixing and combustion performance of fuel in the combustion chamber, domestic and foreign researchers have introduced mixing and combustion stabilization devices such as struts, ramps, cavities, and backward steps into the combustor, and have obtained certain achievements. In previous studies, the recirculating zone formed by the strut and cavity in the flow field can achieve good mixing and combustion stabilization performance, receiving widespread attention and expansion. This paper reviews the recent research progress on strut, cavity, and strut-cavity combination configurations around the world, and explores the future development direction of related research.