Ascent Corridor Design Method for Combined Power Hypersonic Vehicles

Aiming at the characteristics of air-breathing combined power vehicles with many constraints in the ascent stage and high precision requirements of terminal windows, a flight corridor design method based on the velocity-altitude profile is proposed. The velocity-altitude profile is used to describe the flight corridor, the relationship between constraints and velocity and altitude is analyzed, and the constraints contained in the upper and lower boundaries of the corridor are determined. Based on the analysis of the constraints, the angle of attack that satisfies the constraints and maximizes or minimizes the altitude at the current velocity is solved. A sample vehicle is used as an example to design and analyze the flight corridor in the ascent stage, and the calculation result shows that the method can be used for flight corridor design under multiple constraints in the ascent stage of the combined power vehicle.