Integrated aerodynamic layout method for hypersonic aircraft forebody, air inlet duct and supporting plate

Abstract

The invention discloses an integrated aerodynamic layout method for a hypersonic aircraft forebody, an air inlet duct and a supporting plate. A combined standard flow field combining an inner core flow field, an isentropic flow field and a truncation Busemann flow field is adopted, a streamline tracer technology is used, based on a free incoming flow capture size and a downstream combustion chamber inlet size given by the overall configuration of an aircraft, a forebody compression face, an air inlet duct compression face and a supporting plate lateral compression face are constructed with traced streamline clusters starting from an outlet of the downstream air inlet duct, and the forebody, the air inlet duct and the supporting plate are smoothly connected to achieve integrated aerodynamic layout configuration. The three-dimensional space structure of the aircraft forebody and the air inlet duct is improved, the disturbing influence of the supporting plate is eliminated in a side face compression mode, adverse factors are converted into favorable compensation, the forebody, the air inlet duct and the supporting plate are reasonably laid out from the space three-dimension perspective, and flowing is kept to be isentropic flowing to the maximum extent, which is beneficial for reducing flowing loss and improving overall performance of the aircraft.

Description

technical field [0001] The invention belongs to the technical field of integrated aerodynamic layout of a hypersonic vehicle precursor, an air inlet and a support plate, and particularly refers to an air-breathing hypersonic vehicle precursor, an air intake and a support plate integrated with a parallel multi-module engine Aerodynamic layout method. Background technique [0002] High-speed near-space aircraft is a strategically important aircraft that countries around the world are vigorously developing to make full use of space, including a new generation of space-to-ground shuttle vehicles, hypersonic cruise vehicles, hypersonic long-range passenger aircraft, etc. Various combined propulsion cycle systems of combustion ramjet engines, such as rocket-based and turbine-based combined cycle systems. [0003] One of the key technologies to achieve hypersonic flight in near space is the integrated design of the aircraft precursor and the propulsion system inlet. The airway, i...

AI Technical Summary

Problems solved by technology

[0004] Aiming at the deficiencies of the above-mentioned prior art, the object of the present invention is to provide an integrated aerodynamic layout method of the hypersonic vehicle precursor, the air inlet and the support plate, so as to solve the problems of the hypersonic vehicle precursor, the air inlet and the support plate in the prior art. The design of the support plate affects the overall performance of the propulsion system, eliminating the adverse interference caused by the support plate and turning it into a favorable integrated airflow compression to improve the overall performance of the three

Images