Abstract: A modeling method for an integrated intake/exhaust/engine aero propulsion system with multiple geometric parameters adjustable includes the following steps: establishing an inlet and nozzle model by quasi one-dimensional aerodynamic thermodynamics and the method for solving the excitation system on the basis of a traditional engine component-level model; adding an inlet and engine flow balance equation and an engine and nozzle flow balance equation to the engine model, and establishing a propulsion system model based on the iteration method; and integrating the design of geometric parameters of an inlet and a nozzle into the model to realize the design of structure sizes of an intake/exhaust system and the simultaneous adjustment of multiple parameters.

Abstract: A connecting mechanism of a detachable chair foot, an assembling method thereof and a chair foot assembly are provided. The connecting mechanism is connected between the central chassis and a detachable chair foot, and includes a one-foot connecting arm connected to the central chassis and extends radially outward, a connecting groove including a transversal groove opening, and a longitudinal groove opening and operatively engaged with the one-foot connecting arm, two inner-convex locking portions respectively arranged on two opposite side groove walls of the connecting groove, two longitudinal locking groove bodies respectively arranged on the one-foot connecting arm; a concave-convex matching structure arranged on the one-foot connecting arm and in the connecting groove of the detachable chair foot. The chair foot assembly with the connecting mechanism not only can save transportation space and improve transportation efficiency, but also reduce the amount of assembly work.

Abstract: The present invention belongs to the technical field of numerical calculation of aero-engines, and provides an iterative algorithm for an aero-engine model based on hybrid adaptive differential evolution, comprising the following steps: establishing a component-level model of an aero-engine; solving the engine model by a hybrid adaptive differential evolution algorithm; and establishing a dynamic calculation model of the aero-engine. The aero-engine model established by the algorithm of the present invention is widely suitable for traditional turbojet engines and turbofan engines, advanced integrated engine propulsion systems and variable cycle engines, can maintain the dynamic model calculation without dead engine or interruption, and satisfies real-time requirements under most operating conditions.