2 results about "Transition point" patented technology

The application provides a threat area fly-around prediction-correction guidance method and system. The method comprises the following steps: constructing a reentry motion model and determining an initial state of an aircraft; determining a state value of a transition point between an initial descent segment and a glide segment according to a nominal attack angle and a constant roll angle acting on the model based on the initial state of the aircraft; in the longitudinal guidance design, taking the state value of the transition point as the initial state of the glide segment, determining a five-segment resistance acceleration profile according to a reentry range requirement, generating a longitudinal range analytical solution, determining a roll angle amplitude based on the resistance acceleration profile and a controller requirement, and inputting the roll angle amplitude into the lateral guidance; in the lateral guidance design, updating a heading angle corridor according to the state value of the transition point and the roll angle amplitude, determining a roll angle reverse logic for flying around the forbidden flight area, and outputting a roll angle sign. The application can improve the range calculation speed and adapt to different configurations and multiple threat areas.

The application provides a method and a terminal for calculating aerodynamic performance of a fan blade. The method comprises: obtaining a transition point parameter on the fan blade; inputting the transition point parameter as a boundary constraint condition into an aerodynamic simulation model to calculate blade airfoil aerodynamic coefficients in a first angle of attack range; and obtaining blade airfoil aerodynamic performance data through an extrapolation model according to the blade airfoil aerodynamic coefficients in the first angle of attack range. The application uses the transition point as an erosion proxy parameter and combines simulation and extrapolation, so that complete airfoil aerodynamic performance data in a full angle of attack range can be quickly and accurately obtained without constructing a complex erosion geometry.