Hypersonic flight vehicle aerodynamic configuration based on pre-cooling type combined powder and working method

Abstract

The invention discloses a hypersonic flight vehicle aerodynamic configuration based on pre-cooling type combined powder and a working method. The hypersonic flight vehicle aerodynamic configuration based on pre-cooling type combined powder comprises a flight vehicle aerodynamic configuration and a pre-cooling type air turbine rocket engine, wherein the pre-cooling type air turbine rocket engine comprises air inlet channels, a pre-cooling system, an air compressor, an annular combustion chamber, a turbine, an afterburner and exhaust nozzles which are successively connected; the air inlet channels and the lower surface of the front body of the flight vehicle aerodynamic configuration are designed integrally; an adjustable hemicone is arranged at an air inlet end of each air inlet channel; the exhaust nozzles and the lower surface of the rear body of the flight vehicle aerodynamic configuration are designed integrally; and an adjustable cone is arranged in each exhaust nozzle. Medium-altitude and low-altitude working performance advantages of turbine engines are retained, by application of a pre-cooler, it can be ensured that large residual thrust can be provided for a flight vehiclein a transonic / supersonic climbing acceleration process, and therefore, the flight vehicle can climb to a cruise altitude in an accelerated manner within a short time.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic / propulsion layout design of a hypersonic vehicle, and specifically refers to an aerodynamic layout of a hypersonic vehicle using a precooling type air turbine rocket combined cycle propulsion system and a working method thereof. Background technique [0002] Hypersonic aircraft is one of the important research directions of future aircraft. The aerodynamic layout method provided in this paper can be used to design air-breathing hypersonic aircraft for horizontal take-off and landing; Space hypersonic cruise and other aspects have broad application prospects, and are of great significance to future military and civilian uses. [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 adopts combined cycle engines, and the main types of engines included are: turbine, ramjet and rocket e...

AI Technical Summary

Problems solved by technology

[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 adopts combined cycle engines, and the main types of engines included are: turbine, ramjet and rocket engines. There are big differences and have their own advantages and disadvantages: the turbine engine has good performance at medium and low altitudes, but when it is installed on an aircraft, it will remain in the stages of transonic, supersonic climb acceleration and Mach number greater than 2.5. The thrust is relatively small, which will lead to thrust discontinuity in the transition from the turbine mode to the sub-combustion mode; the ramjet has good specific impulse and fuel consumption performance in the hypersonic stage, but it cannot be started independently at the low speed stage, and must be used other propulsion systems transition at low speeds, which imposes certain constraints on their use on aircraft

The use of rocket engines is relatively low in specific impulse. When completing the same task, the fuel consumption rate is higher than that of turbo and ramjet engines, and the take-off weight of the aircraft is large. When it is used repeatedly, it is economical. However, it has simple adjustment rules and relatively thrust-to-weight The advantage of being large and suitable for short-term accelerated flight

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