A Rocket-Based Combined Cyclic Ejection Modal Performance Experimental Engine

Abstract

The invention discloses a rocket-based combined cycle ejector mode performance test engine. A main rocket combustor is fixed in the front of a secondary combustor; intake ducts are mounted above and below the main rocket combustor respectively; intake ends of the intake ducts are fixed in the rear of the main rocket combustor through support lugs; the rear ends of the intake ducts are connected with the secondary combustor through an intake duct flange and a second combustor flange; the secondary combustor is in a divergent straight structure; the main rocket combustor is fitly connected with the secondary combustor; a flue of a nozzle divergent segment gradually changes from round to square. The main rocket combustor is charged through the combination of seven-pointed star shape and inner holes by close-to-wall pouring; after ignition, the flow of gas in a main rocket is kept basically unchanged; variation pattern of the rocket-based combined cycle ejector mode performance along with flight Mach number and height is verified; the basis is provided for passage design. The rocket-based combined cycle ejector mode performance test engine is simple in structure and convenient to maintain, and the influence of gas composition upon engine performance and trajectory climb can be extensively researched.

Description

technical field [0001] The invention belongs to the field of rocket ramjet engines, in particular to a rocket-based combined cycle ejection modal performance experimental engine. Background technique [0002] The rocket-based combined-cycle (Rocket-Based-Combined-Cycle, RBCC) propulsion system organically combines the rocket engine and the ramjet engine in the same flow channel, so that it can enable the optimal working mode at different flight altitudes and Mach numbers. State, give full play to the respective characteristics of the rocket engine and the ramjet engine, so that the rocket-based combined cycle propulsion system has the advantages of zero-speed start and reusability while having high specific impulse and high thrust-to-weight ratio. And all flight tests are the only way to turn from ground research to practical application. For the rocket-based combined cycle propulsion system, the application of ejection rocket mode, that is, Mach number Ma=0~2.5, is the key...

AI Technical Summary

Problems solved by technology

In the GTX test project, three solid boosters evenly distributed outside the aircraft are bound to accelerate the aircraft to Mach 2.4, and then the RBCC engine starts to work from the sub-combustion ramjet mode, and its zero-speed take-off and automatic acceleration capabilities cannot be verified, and The system is huge and complex, the test period is long, and the investment is large; in the CAMUI subsonic flight test, in view of the fact that the program uses the CAMUI-90P engine, the thrust is 900N, and the increase in the additional mass of the ejector pipe results in a maximum flight altitude of only 500m. The Mach number is only 0.3, which cannot verify the ejection performance of the RBCC engine in transonic and low supersonic flight conditions

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