The characteristics and shortcomings of gas turbine, rocket, and ramjet engines are outlined and the combustion and regression mechanism of solid fuel ramjets is described. The advantages in propulsion system mass and volume reduction of hybrid engines over separated powerplants to cover wide flight envelopes are discussed, and a variety of air breathing hybrid engines are examined to consider the suitability as means of propulsion for future guided weapons. The powered range of the ramjet-propelled missiles evaluated is estimated to be some 5 1/2 times greater than that obtained by rocket propulsion. A metallized solid ramjet fuel enabled the required thrust to be developed for the most economical fuel mass consumption rate, although variations in propulsion system efficiencies could easily erode the apparent advantage. Nonetheless, the greater density of the metallized fuel offered a clear advantage for volume-limited applications. Solid fuels and propellants offer significant benefits in reducing servicing and preparation activities; and the integral rocket solid fuel ramjet provides the best prospect for the propulsion of future air-lanched tactical missiles. The gas generator ramrocket's potential to provide a more compact, but heavier, engine makes it more attractive for land and ship launched applications. The ejector ramjet and air turbo ramjet/ramjet-rocket concepts are unsuitable for guided weapons use, and their greater flexibility and complexity make them more appropriate for multi-mission atmospheric and trans-atmospheric vehicle propulsion.


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    RAMJET PROPULSION METHOD

    BOVANKOVICH MARK | Europäisches Patentamt | 2024

    Freier Zugriff

    Ramjet propulsion method

    BOVANKOVICH MARK | Europäisches Patentamt | 2024

    Freier Zugriff


    Application ranges of ramjet propulsion

    Saenger-Bredt, I. | Engineering Index Backfile | 1961