Hypersonic aircraft aero-propulsive integrated layout method based on combined power

Abstract

The invention discloses a hypersonic aircraft aero-propulsive integrated layout method based on combined power. According to the hypersonic aircraft aero-propulsive integrated layout method, a hypersonic air inlet channel of a dual-mode ramjet passage and a tailpipe nozzle are integrally designed with the front body and the rear body of an aircraft respectively; the dual-mode ramjet passage is taken as a basis; a turbine engine passage, a rocket ejector ramjet passage and the dual-mode ramjet passage are parallelly arranged, so that the three passages can coordinate with one another to work according to the own working conditions under the flight Mach number; the dual-mode ramjet passage and the rocket ejector ramjet passage are parallelly connected in an up-down manner; the turbine engine passage is parallelly connected with the dual-mode ramjet passage and the rocket ejector ramjet passage in a left-right manner; and a dual-engine mode under the left-right side-by-side layout is designed. By adoption of the hypersonic aircraft aero-propulsive integrated layout method disclosed by the invention, the middle-altitude and low-altitude working performance advantages of a turbine engine can be remained; through a rocket ejector ramjet, relatively high residual thrust can be provided in a transonic and supersonic climbing acceleration process of the aircraft; and the climbing acceleration of the aircraft to a cruising altitude within a short time can be achieved.

Description

technical field [0001] The present invention relates to the technical field of aerodynamic / propulsion integrated layout design of hypersonic vehicles, and in particular refers to a hypersonic vehicle aerodynamic layout method using a TRBCC combined cycle propulsion system (Turbine and Rocket Based Combined Cycle, turbine rocket based combined cycle propulsion system) . Background technique [0002] Hypersonic aircraft is one of the important research directions of future aircraft. This type of aircraft can realize hypersonic (Ma>5) maneuvering flight in dense atmosphere, near space and across the atmosphere, and has broad application prospects in intelligence collection, surveillance, reconnaissance, transportation, combat strikes, etc. has great significance. [0003] In order to realize the wide Mach number flight from low speed to hypersonic speed and capable of taking off and landing aircraft, this type of aircraft usually uses turbine-based or rocket-based combined...

AI Technical Summary

Problems solved by technology

Relatively speaking, the specific impulse of RBCC engine is relatively low. Compared with TBCC engine, when completing the same task, the fuel consumption rate is higher and the take-off weight of the aircraft is larger. The economy is poor when it is repeatedly used. It also transitions from the sub-combustion mode to the scram stamping die. Thrust discontinuity also exists in the state; but it has the advantages of simple adjustment law, relatively large thrust weight, and suitable for short-term accelerated flight within the range of working Mach number

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